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
2001050200060	20010502	00060	CE  	2001	5	2	00114            	1	20010318	G	7110	45A350271	COWLING         	BEECH       		BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					LT ENGINE	BENT            	E			DJFA	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	23	456CW	4448 				RK56				COWLING ON LEFT HAND ENGINE BOTTOM INBOARD SIDE WAS BENT BACK DURING FLIGHT. THE CAUSE IS UNKNOWN, THESE COWLINGS ARE KN	OWN TO HAVE THIS TYPE OF PROBLEM.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2001080200248	20010802	00248	CE  	2001	8	2	010204           	1	20010723	G	7713	C4820020108	RELIEF VALVE    			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	INDUCTION SYSTEM	FAILED          	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6506G					21064406	294271R	001099		A TCM REBUILT ENGINE WAS INSTALLED INTO THIS AIRCRAFT WITH ALL THE ASSOIATED NEW PARTS.  THE AIRCRAFT COULD NOT ACHIVE 3	6.5 IN. AT 2700 RPM FOR TAKEOFF POWER. ALL INDICATING INSTRUMENTS WERE VERIFIED FOR CALIBRATION.  WE INSTALLED THE OLD A	BSOLUTE PRESSURE RELIEF VALVE AND OBTAINED 36.5 IN. EASILY.				1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001080200250	20010802	00250	CE  	2001	8	2	010726           	1	20010726	G	7713	C4820020108	RELIEF VALVE    			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	INDUCTION SYSTEM	MALFUNCTIONED   	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6506G					21064406	294271R	001099		AFTER A REBUILT TCM ENGINE WAS INSTALLED INTO THIS AIRFRAME A SECOND REBUILT ABSOLUTE PRESSURE RELIEF VALVE FROM CONSOLI	DATED FUEL SYSTEMS, INC. WAS INSTALLED AND THE ENGINE WOULD NOT PRODUCE 36.5 IN OF MANIFOLD PRESSURE REQUIRED FOR TAKEOF	F. REINSTALLED THE ORIGINAL RELIEF VALVE AND THE ENGINE PRODUCED 36.5 IN OF MANIFOLD PRESSURE.				1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001100200006	20011002	00006	WP  	2001	10	2	0109             	1	20010906	G	5552		STOP            			DOUG  	DC8   	DC862       	3021970	WP  										RT ELEVATOR TAB	LOOSE           	H				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SW	99	VP-BH					46111				AUTO PILOT PORPOSING IN LEVEL FLIGHT.   DURING RT ELEVATOR CABLE ADJUSTMENT CHECKED TRAVEL TAB IN BOTH DIRECTION. WITH S	TICK FULL FORWARD THE LEFT ELEVATOR TAB ONLY GOES UP. THE RIGHT ELEVATOR TAB STAYS AT THE SAME POSITION. AFTER TROUBLE S	HOOTING WE FOUND THE STOP SCREW (THE UPPER ONE ) COMPLETELY LOOSE ON RIGHT SYSTEM, CAUSING THE RESTRICTING TRAVEL OF TAB	 IN TRAILING EDGE UP.  AFTER CORRECTING ACTION, THE TRAVEL CHECK IS NORMAL			2	L	7	4 	4F			 	4A25    					 
2001112600003	20011126	00003	NE  	2001	11	26	0115             	2	20011115	G	7200		ENGINE          			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE73131C   	01518	NE  					NR 1	FLAMED OUT      	H				K				NONE                    				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SW	99	BSA					196				APPROX 30 MINUTES INTO FLIGHT AT FL 390 COCKPIT HEAT CONTROL WAS MOVED FROM MANUAL TO AUTO.  SHORTLY AFTER NR 1 ENG FLAM	ED OUT.  NO WARNING LIGHTS, NO VIBRATION.  AN IMMEDIATE RELIGHT WAS PERFORMED AND SUCCESSFUL.  ALL ENGINE PARAMETERS WER	E NORMAL, FLIGHT CONTINUED TO DESTINATION.				2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2002012400095	20020124	00095	SO  	2002	1	24	0116             	1	20011116	G	7830		LOCK            			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     	 	EU  					THRUST REVERSER	FAULTY          	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	VPBSF					1058	16171			WHILE PASSING THROUGH 2,500 FT MASTER WARNING RT THRUST REVERSER UNLOCKED. IMMEDIATELY REDUCED THROTTLES MESSAGE CLEARED	. CONTINUED ON. WHEN PASSING THROUGH 4000 FT SAME WARNING AGAIN. RETURN TO BLOCKS. NORMAL APPROACH AND LANDING MADE.   M	AINTENANCE INSPECTION REVEILED FAULTY THRUST REVERSER INTERNAL LOCK . BOTH ACTUATORS REPLACED				2	L	7	2 	4F	4	F	RT	A12EA   	E25NE				 
2001042400277	20010424	00277	WP  	2001	4	24	01FDEA00289      	1	20010419	G	3260		TARGET          			DOUG  	DC10  	DC1010      	3022110	WP  										RT MLG DOOR	INOPERATIVE     	A			FDEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	25	389FE					46623				01-124  RT MLG RED LIGHT ILLUMINATED ON BOTH PANELS AFTER TAKE OFF.  RECYCLED PER RED TABS, REMAIN ILLUMINATED.  R/R TAR	GET PER EO 8-3260-7-3304-B.  AC OK FOR SERVICE.					2	L	7	3 	4F			 	A22WE   					 
2001070200036	20010702	00036	WP  	2001	7	2	01FDEA00398      	1	20010605	G	3260		WARNING LIGHT   			DOUG  	DC10  	DC1010      	3022110	WP  										COCKPIT	ILLUMINATED     	A			FDEA	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			SO	25	389FE					46623				ON DESCENT RT MLG RED LIGHT ILLUM ON BOTH PANELS.  ACCOMP RED TAB PROC.  FERRIED A/C TO IND.						2	L	7	3 	4F			 	A22WE   					 
2002012400096	20020124	00096	CE  	2002	1	24	040521239        	1	20011204	G	3211	501202015	SUPPORT         			BEECH 	200   	A200        	1152921	CE  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	1546	11996				BC58				LEFT HAND AND RIGHT HAND MAIN LANDING GEAR DRAG LEG SUPPORTS FOUND TO BE CRACKED DURING FLUORESCENT PENETRANT INSPECTION	. INSPECTION ORDERED BY U.S. CUSTOMS SERVICE BASED ON REPORTS FROM U.S. ARMY OPERATORS.					1	L	7	2 	4T			 	A24CE   					 
2002012400097	20020124	00097	CE  	2002	1	24	040521239A       	1	20011204	G	3211	501202015	SUPPORT         			BEECH 	200   	A200        	1152921	CE  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	72470	12534				BC04				LEFT HAND MAIN LANDING GEAR DRAG LEG SUPPORT FOUND TO BE CRACKED DURING FLUORESCENT PENETRANT INSPECTION. INSPECTION ORD	ERED BY U.S. CUSTOMS SERVICE BASED ON REPORTS BY U.S. ARMY OPERATORS.					1	L	7	2 	4T			 	A24CE   					 
2001080200253	20010802	00253	NE  	2001	8	2	1                	2	20010712	G	7261	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					OIL PRESSURE	INOPERATIVE     	B			S88R	E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			SO	21	5202Y					3085	9564			NO ENGINE OIL PRESSURE INDICATION DURIN ENGINE START SEQUENCE.THE OIO PRESSURE TRANSMITTER WAS REPLACED ON MORE THAN ONE	 TIME, BUT THE NEW TRANSMITTER WERE BAD FROM OVERHAULED FACILITY.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001080200256	20010802	00256	SO  	2001	8	2	100000           	2	20010801	G	7414		WIRE            			PIPER 	J3    	J3F65       	7100536	SO  	CONT  	A65   	A658        	17003	SO  					MAGNETO	CHAFED          	G				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		TO	TAKEOFF        	1			GL	07	40782					7496				DURING TAKE-OFF THE ENGINE QUIT. THE AIRCRAFT WAS DESTROYED.  INVESTIGATION BY THE FAA INSPECTOR PROVED THAT THE PROBABL	E CAUSE OF THE ENGINE FAILURE WAS ATTRIBUTED TO BOTH MAGNETO P-LEAD WIRES BEING GROUNDED OUT AGAINST A SCREW THAT SECURE	D THE LEFT-HAND INNER AND OUTER WINDOW TRIM PIECES.      				1	H	7	1 	3O	3	O	 	A692    	E205				 
2001102600009	20011026	00009	CE  	2001	10	26	1024016          	1	20011022	G	3040	265318202071	WINDSHIELD      			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					COCKPIT	ARCED           	B			RE3R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			NM	01	6NR	1834 				46529				PILOTS NOTICED INTERNAL ARCING IN WINDSHIELD AT UPPER EDGE ALONG HEAT ELEMENT BUS STRIP.  ARCING CONTINUED FROM ONE SIDE	 AND PROGRESSED TO OPPOSITE SIDE AND BURNED BUS STRIP PARTIALLY THROUGH.  WINDSHIELD CONTINUED TO HEAT UNTIL BUS STRIP B	URNED COMPLETELY THROUGH WIDTH AT ONE LOCATION.  WINDSHIELD WAS REPLACED PRIOR TO NEXT FLIGHT.  REASON FOR ARCING IS MOS	T LIKELY DELAMINATION IN UPPER EDGE OF WINDSHIELD IN BUS STRIP AREA.  RECOMMEND PRE-FLIGHT VISUAL INSPECTION OF THIS ARE	A FOR DELAMINATION AND EVIDENCE OF INTERNAL ARCING STARTING TO HAPPEN IN ANY AREA.  IF REPLACEMENT IS REQUIRED, REPLACE 	WITH PPG BRAND WINDSHIELD.	2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2002071900081	20020719	00081	CE  	2002	7	19	102401868        	1	20010923	G	3340	S13605L	CIRCUIT BREAKER 			CESSNA	172   	172R        	2072401	CE  										EXTERIOR LIGHTS	FAILED          	D			S1XB	A				UNSCHED LANDING         				A			FLAME/FIRE                			CL	CLIMB          	1			SO	17	2458G					17280893				THE TAIL LIGHT POSITIVE LEAD SHORTED TO GROUND BY CONTACT WITH A TINNERMAN NUT IN THE RUDDER.  THERE WAS NO EVIDENCE OF 	TRAUMA TO THE WIRE.  ONLY A PINPOINT OF CONTACT WAS EVIDENT  THE NAV LIGHT BREAKER DID NOT TRIP AND THE WIRING BURNED FR	OM THE TAIL TO THE CIRCUIT BREAKER PANEL, TAKING OUT HALF THE BUS WITH IT.  THE FIRST WIRE BURNING STARTED A CASCADE OF 	SHORT CIRCUITS.  THIS DOMINO EFFECT SEQUENTIALLY TOOK OUT ADDITIONAL CIRCUITS UNTIL THE MAIN BUSS BREAKER OPENED.  			1	H	7	1 	3O			NT	3A12    					 
2001080200259	20010802	00259	CE  	2001	8	2	2                	1	20010727	G	3232	99810057652	ACTUATOR        			BEECH 	200   	C12C        	       	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	DAMAGED         	B			S88R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	1547		1091 			BC50				DURING A LANDING GEAR RETRACTION CHECK THE L/H LANDING GEAR WHENT FROM THE UP POSITION TO THE DOWN AND LOCK POSITION BY 	OT SELF. AFTER FURTHER INVESTIGATION FOUND THA THE L/H ACTUATOR SHAFT NUT HAD FAILED AND COMPLETLY CAME OF THE SHAFT, CA	USING THE LANDING GEAR TO DROP TO THE DOWN AND LOCK POSITION.				1	L	7	2 	4T	3	T	 	A24CE   	E2NE	6	C	P15EA	 
2001040900164	20010409	00164	CE  	2001	4	9	20010124CW003    	1	20010103	G	7120	10191012253	MOUNT           			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	309M					FL48				COWL ATTACH LUGS CRACKED ON ENGINE MOUNT.  ALSO,  CORROSION FOUND  AT MOUNT TO FUSELAGE ATTACH POINT  BOLTS  AND SPACING	 WASHERS.					2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2001041000002	20010410	00002	CE  	2001	4	10	20010124CW006    	2	20010124	G	7420	M750272	IGNITION LEAD   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360RB   	17025	CE  					RT ENGINE	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4166R					3449185	322077			NR2 AND NR6 CYLINDER IGNITION LEADS ON BOTTOM PLUGS SHORTED OUT, BEHIND IGNITION LEAD SPRING ASSEMBLY.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001041700097	20010417	00097	SO  	2001	4	17	20010124CW007    	2	20010124	G	8520		BEARING         			CESSNA	180   	180B        	2072606	CE  	CONT  	O520  	IO520D      	17032	SO  					CRANKCASE	FAILED          	D				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	99	9283R					18802211	22145373D			BEARING FAILURE ON NR2 MAIN BEARING.  CAUSED DAMAGE TO CRANKCASE, OIL PRESSURE DROPPED 20 PSI IN FLIGHT WITH NO OTHER IN	DICATION.					1	H	7	1 	3O	3	O	 	5A6     	E5CE				 
2001050200001	20010502	00001	EU  	2001	5	2	20010124CW008    	1	20010109	G	6520	365A33600501	BEARING         			AEROSP	SA365 	SA365N1     	8680668	EU  										TAIL ROTOR GRBX	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	89SM					6282				MANUFACTURER TEARDOWN OF GEARBOX, FOUND PITCH CHANGE SHAFT DUPLEX BEARING FAILURE AND SHAFT SHEAR T/R BLADES IN-NEG-PITC	H WITH NO CONTROL OF TAIL ROTOR.NOTE: NO T/R GEARBOXES INSTALLED ON ANY 365 IN OUR FLEET HAVE ELECTRONIC CHIP DETECTOR.					1	G	7	2 	3U			 	H10EU   					 
2001050200002	20010502	00002	CE  	2001	5	2	20010124CW009    	1	20010124	G	2720		RUDDER          			CESSNA	182   	182S        	2072701	CE  										TAIL	INTERFERENCE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	162TC					80164				WHEN CHECKING RUDDER TRAVEL,  ELEVATOR WAS IN NEUTRAL POSITION.  WHILE THE RUDDER WAS DEFLECTED FULL IN EITHER DIRECTION	, THE ELEVATOR WOULD HIT THE RUDDER WHEN THE ELEVATOR WAS RAISED.  THE RUDDER TRAVEL WAS RIGGED CORRECTLY PER MAINTENANC	E MANUAL.  THIS COULD CAUSE THE RUDDER AND ELEVATOR TO JAM IN FLIGHT.				1	H	7	1 	3O			NT	3A13    					 
2001030100079	20010301	00079	EU  	2001	3	1	20010124CW010    	1	20010109	G	6520	3655A33600501	GEARBOX         			AEROSP	AS365 	AS365N2     	8680815	EU  										TAIL ROTOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	365DU	955  	955  			6425				GEARBOX REMOVED DUE TO FAILING  SOAP/OIL ANALYSIS/ OF IRON-18.0 AND MAGNESIUM/ 73.2/SAMPLE TAKEN 12-18-00.  PREVIOUS SAM	PLE TAKEN 12-5-00 HAD IRON AT /3.8/ AND MAGNESIUM AT /10.9/  ALL VALVES ARE IN PARTS PER MILLION.					1	G	7	2 	3U			RT	H10EU   					 
2001050200005	20010502	00005	SO  	2001	5	2	20010125CW002    	1	20010102	G	2140	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FWD HEATER	LEAKING         	G			WVBA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	59764					317652037				PILOT REPORTED HEATER INOPERATIVE.  UPON INSPECTION, FOUND FUEL PRESSURE REGULATOR LEAKING.  UNIT WAS REPLACED, OPS GOOD	.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001050200006	20010502	00006	SO  	2001	5	2	20010125CW003    	1	20010102	G	2140	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					FWD HEATER	LEAKING         	G			WVBA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	27755					317852148				PILOT REPORTED HEATER OUTPUT DECREASES AFTER ABOUT 20 MIN.  UPON INSPECTION,  FOUND FUEL PRESSURE REGULATOR LEAKING.  UN	IT WAS REPLACED.  OPS CHECK GOOD					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001050200007	20010502	00007	SO  	2001	5	2	20010125CW004    	1	20010102	G	2140	44008	VALVE           	ELECTROSYS  		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	HEATER COMP	LEAKING         	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	3527U	2346 	2346 		A98030019	317952141				DURING ROUTINE INSPECTION, FUEL WAS OBSERVED LEAKING FROM FUEL SOLENOID SHUT OFF VALVE.  PART WAS REMOVED FROM SERVICE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	 	 
2001050200008	20010502	00008	SO  	2001	5	2	20010125CW006    	1	20010109	G	2823	35640023564001	SELECTOR VALVE  			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	17WE	3615 				277854118				AC WAS PUT IN UNHEATED HANGER WITH FULL FUEL TANKS, FOUND FUEL ON FLOOR UNDER BOTH WINGS, WAS FOUND TO BE LEAKING FROM O	VERFLOW TUBES OF BOTH INBOARD FUEL TANKS WHICH WERE FULL. OUTBOARD TANKS WERE DOWN, ONLY CONNECTION BETWEEN IB AND OB TA	NKS IS THROUGH FUEL SELECTOR VALVES.  FUEL SELECTOR VALVES WERE FOUND, WHEN IN OFF POSITION, FUEL FLOW WAS NOT COMPLETEL	Y SHUT OFF TO ENG SIDE OF VLV.  AC HAD RECENT ANNUAL INSP. ALL OPS CHECKED GOOD. VALVE LOCATION  IN IB AFT OF FIREWALLS.	 VALVES REMOVED AND SENT TO DUKES, VALVE MFG. SUSPECT ENVIRONMENTAL CHANGE OF AC TO FIND DEFECT OF VALVES.		1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2001050200011	20010502	00011	CE  	2001	5	2	20010125CW009    	1	20010125	G	2701	35524656	CLIP            			BEECH 	35    	S35         	1151532	CE  										CONTROL YOKE	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	354D					D7659				DURING ANNUAL INSPECTION OF AC A VISUAL INSPECTION WAS PERFORMED ON CHAIN INSIDE THE DUAL CONTROL YOKE.  CHAIN MASTER LI	NK PLATE AND CLIP WERE MISSING FROM LOWER LEFT CHAIN ATTACH POINT TO FITTING.  RECOMMEND MORE ATTENTION IN THIS AREA UPO	N ANNUAL INSPECTION/ 100 HOUR INSPECTION				1	L	7	1 	3O			 	3A15    					 
2001041800282	20010418	00282	NM  	2001	4	18	20010125CW010    	1	20010105	G	2910	65447821	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										HYDRAULIC MODULE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1110					HOUSING WAS NOTED TO BE CRACKED AT BOTH THE   A   AND  B   PORTS,  DURING NON-DESTRUCTIVE INSPECTION.						2	L	7	2 	4F			RT	A16WE   					 
2001041700109	20010417	00109	NM  	2001	4	17	20010125CW011    	1	20010104	G	2782	69358521	SLEEVE          	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SLAT ACTUATOR	FRACTURED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					7649K					SLEEVE /145/ OF BLOCKING VALVE ASSEMBLY IS FRACTURED.  PROBABLE CAUSE/ FATIGUE						2	L	7	2 	4F			RT	A16WE   					 
2001041700110	20010417	00110	NM  	2001	4	17	20010125CW012    	1	20010104	G	2910	65447821	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										HYDRAULIC MODULE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01		43127	43127		1134					UNIT NOTED TO HAVE A PIN HOLE LEAK ADJACENT TO OUTLET PORT NR4 AS PRESSURE WAS APPLIED DURING PROOF TEST.						2	L	7	2 	4F			RT	A16WE   					 
2001050200015	20010502	00015	EA  	2001	5	2	20010129CW004    	2	20010104	G	8550	06B26072	GASKET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					OIL FILTER	CUT             	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	35805	61   				318052090	L663461A			GASKET FOUND CUT UPON REMOVAL.  POSSIBLY DUE TO INSTALLATION PROCEDURE.  RECOMMEND MORE CARE IN INSTALLING ADAPTER PLATE	 TO PREVIENT COCKING ON INSTALLATION.  MAKE SURE GASKET IS CENTERED ON PLATE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001041800348	20010418	00348	EA  	2001	4	18	20010129CW008    	1	20010129	G	5330		SKIN            			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF34*       	 	NE  					FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	604WB					5125				AFTER REMOVAL OF SATCOMM ANTENNAS FROM FUSELAGE STATION  349, CORROSION WAS DISCOVERED UNDER ANTENNAS ON AIRCRAFT FUSELA	GE SKIN SURFACE.  AFTER REMOVAL OF CORROSION DAMAGE WAS BEYOND LIMITS, RESULTING IN SKIN REPLACEMENT ON BOTH SIDES.  					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050200021	20010502	00021	CE  	2001	5	2	20010129CW013    	1	20010105	G	5210		DOOR            			CESSNA	182   	182P        	2075816	CE  										RT DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7220H					18263011				FORWARD DOOR POST, INSPECT AND MOD. FOUND CRACK ON RT SIDE.  THE SEB CALLS FOR INITIAL INSPECTION AT 4000 HOURS.  I HAVE	 FOUND THIS CONDITION ON 3 AC.  2 OF THE 3 HAD LESS THAN 2000 HRS T/S.  HISTORY ON BOTH IS NORMAL SERVICE AND NO PASST D	AMAGE OR ABUSIVE USE. SUSPECT CRACKS ARE DUE TO STRESS RELIEVE FROM STRAINS APPLIED DURING ASSEMBLY MORE THAT TYPE OF US	E.			1	H	7	1 	3O			NT	TA13    					 
2001050200022	20010502	00022	CE  	2001	5	2	20010129CW014    	1	20010108	G	5210	504300431273	DOOR FRAME      			BEECH 	200   	200BEECH    	1152920	CE  										AFT DOOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	383JP	8204 				BB615				REMOVED AND REPLACED AFT CABIN DOOR FRAME PRESSURATION PROBLEM.						1	L	7	2 	4T			 	A24CE   					 
2001030700581	20010307	00581	CE  	2001	3	7	20010129CW016    	1	20010108	G	2710		TORQUE TUBE     			CESSNA	560   	560XL       	       	CE  	PWA   	545   	PW545A      	 	NE  					AILERON	CORRODED        	B			DXTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	690QS	564  				5605090				AFT AILERON SECTOR TORQUE TUBE CORRODED THE LENGTH OF THE TUBE BETWEEN THE UPPER AND LOWER BELLCRANKS.						2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2001041800370	20010418	00370	SO  	2001	4	18	20010129CW018    	1	20010109	G	3242	1331317	STATOR          	BFGOODRICH  		EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05					0814A					BRAKE ASSEMBLY PN 21661 FAILED PREMATURELY.  NR2 STATOR CRACKED AT RELIEF HOLES.  25 PERCENT OF STATOR MISSING.  HEAT ST	ACK WARPED AND UNEVEN WEAR.NOTE  OEM PARTS INSTALLED IN BRAKE ASSEMBLY             AND THE MOST RECENT BRAKE            	 CONFIGURATION PN 21661.				2	L	7	2 	4T			RT	A31SO   					 
2001041800372	20010418	00372		2001	4	18	20010129CW020    	4	20010102	G	2565		SLIDE RAFT      	BFGOODRICH  		DOUG  	DC10  	DC10        	N/A-SDR	NM  										CABIN	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					DD041					FOUND 8 FT LONG BY 2 INCHES WIDE, RED WEBBING STRAP TIED AROUND THE FOLDED INFLATABLE SLIDE/RAFT.  IF THE UNIT WERE TO B	E USED IN AN EMERGENCY, THE SLIDE WOULD NOT HAVE DEPLOYED PROPERLY.					2	L	7	3 	4F			RT	A22WE   					 
2001050200029	20010502	00029	GL  	2001	5	2	20010129CW025    	3	20010106	G	6114	HCE2YR2RBSF	HUB             	HARTZL      		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	11JD	7841 	860  		BP6961	277405395	RL1279248A	BP6961		PROPELLER WAS RECEIVED FOR NON-SCHEDULE REPAIR, OIL LEAK.  DURING PRELIMINARY PROPELLER INSPECTION, PROPELLER WAS NOTED 	LEAKING BETWEEN HUB/PN D24772R/ AND CYLINDER/PN B24231.  CYLINDER LIFTED OFFTHE HUB.  PROPELLER ASSEMBLY WAS DISASSEMBLE	D, VISUALLY INSPECTED, HUB AND CYLINDER REPLACED, REASSEMBLED AND BALANCED. PROPELLER GOVERNOR WAS REQUESTED FOR INSP.  	WOODWARD GOVERNOR MODEL NR A210721 WITH SERIAL NR 2455904 WAS RECEIVED FOR INSP.GOVERNOR PRESSURE RELIEF VALVE WAS INSP.	 AND GOVERNOR ASSY WAS BENCH CKD W/NO DEFECTS.REPAIRED PROPELLER AND GOVERNOR WAS REINSTALLED. PROPELLER AND GOV OPS CK 	GOOD.	1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2001030700590	20010307	00590	EU  	2001	3	7	20010130CW004    	1	20010115	G	6321	L635M1025229	BRAKE           			UROCOP	EC135 	EC135P1     	8680990	EU  										TRANSMISSION	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	511ME	138  				0143				ROTOR BRAKE CHATTERING FOUND CRACKED ROTOR BRAKE DISC./ THIS IS SECOND EVENT.						1	G	7	2 	3U			O	H88EU   					 
2001030700592	20010307	00592	SW  	2001	3	7	20010130CW005    	1	20010116	G	6220	430010101101	YOKE            			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	CRACKED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99	430TX					49005				H.A.S.  REPLACED WITH NEW YOKE FROM BELL HELICOPTER.  A 1.5 LONG CRACK WAS FOUND ON TOP OF THE YOKE AT STATION 31.						1	G	7	2 	3U			RT	H9SW    					 
2001030700618	20010307	00618	SW  	2001	3	7	20010130CW006    	1	20010108	G	6510	407340339103	BEARING         	BELL        		BELL  	407   	407         	       	SW  										T/R DRIVE SHAFT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99	407JR					53245				T/ROTOR,  D/SHAFT BEARING PN 407340339101 FAILED.  RESULTING IN THE LOSS OF BALL BEARINGS, SEALS AND GREASE.  DAMAGE TO 	THE FOLLOWING ITEMS WAS CAUSED BY BEARING FAILURE.  BEARING WAS INSTALLED IN NR1 POSITION OF TAIL ROTOR HANGER BEARINGS.	  DAMAGED ITEMS TO FOLLOW:  IMPELLER ASSY, FER OIL COOLER BLOWER, HOUSING, COVER , HANGER SUPPORT, BOTH BEARINGS, BOTH A	DAPTERS ON FWD AND AFT END OF SHAFT.IMPROVEMENTS NEED TO BE MADE IN BEARING DURABILITY AND ABILITY TO RETAIN GREASE FROM	 BEING FORCED OUT BY SUCTION CAUSED FROM IMPELLER ROTATION.		1	G	7	1 	3U			O	H2SW    					 
2001030700620	20010307	00620	GL  	2001	3	7	20010130CW008    	1	20010116	G	5310		TUBE            			ENSTRM	F28   	280F        	3300550	GL  										GEARBOX MOUNTS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	199TV	5503 				1510				4130 TUBING WAS FOUND CRACKED BETWEEN LEFT FORWARD GEARBOX MOUNT AND LEFT REAR GEARBOX MOUNT.  PROBABLE CAUSE, METAL FAT	IGUE.  AC IS 20 YR OLD WITH 5503 HRS. AC DID HAVE HARD LANDING YEARS AGO AT LESS THAN 1000 HRS ON AIRFRAME.  POSSIBLE FR	AME WAS SUBJECTED TO ADDITIONAL STRESS FROM THE HARD LANDING.  RECOMMEND OPERATORS TO INSPECT AIRFRAME TUBING IN THIS AR	EA FOR POSSIBLE CRACKS.			1	G	7	1 	3O			 	H1CE    					 
2001030700622	20010307	00622	EU  	2001	3	7	20010130CW009    	1	20010105	G	6520	365A33600501	GEARBOX         			AEROSP	SA365 	SA365N1     	8680668	EU  	TMECA 	ARRIEL	ARRIEL1C    	60030	NE  					TAIL ROTOR	FAILED          	B				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	911UF				M539	6338	5065			INITIAL GRND RUN-UP, AFTER  MJR INSP, A T/R GBX FAILURE WAS EXPERIENCED AFTER APPROX 15-20 MINUTES.  AC JERKED SEVERAL T	IMES ALONG THE YAW AXIS, WITH NR1 ENG RUNNING AT 68%NG AND NR2 AT 65%NG  AN UNUSUAL NOISE WAS HEARD FRM TAIL ROTOR, SHUT	 DOWN WAS INITIATED, NOISE WORSENED.  ROTOR BREAK WAS APPLIED WITHIN 10 REV OF COMING TO  COMPLETE STOP FRM COAST DWN WI	TH ROTOR BREAK APPLIED, LOUD SQUEALING AND GRINDING NOISE WAS EMITTING FROM THE TAIL ROTOR AND COAST DWN CAME TO A RAPID	 BUT NOT SUDDEN STOP.  INITIAL INSP REVEALED METAL PARTICLES ON TAIL ROTOR CHIP PLUG, OIL AND SPREAD FLEX COUPLING AT TH	E TAIL ROTOR OUTPUT FLNG FROM MAIN GBX.  AFTER TR DWN & INSP, OUTER BRG OF INPUT HSG WAS DRY, GBX OIL LEVEL WAS FULL.	1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2001040900111	20010409	00111		2001	4	9	20010202CW002    	4	20010112	G	3100	4059013	PANEL           			DOUG  	MD11  	MD11        	3023602	NM  										COCKPIT	INOPERATIVE     	D				J	A			DUMP FUEL               	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	03	105EV					48544				PILOT REPORTED ELECTRICAL BURNING ODOR DURING CLIMB, A IL 300, SMOKE APPEARED IN THE COCKPIT CAUSED FUEL DUMPED AND AIR 	RETURNED TO LAX.  MAINTENANCE AND INSPECTION COCKPIT INDICATORS ALL C/B ARE CLOSED OPEN OVHD PANEL, MAINT PANEL AND AVIO	NICS PANEL, EXAMINED ALL COMPARTMENT, IND ALL CONDITIONS ARE NORMAL, NO BURN SIGN WAS FOUND.  REVIEW LAST FLIGHT FAULT, 	REPLACED SYSTEM CONTROL PANEL FOR SAFETY AND MAINTENANCE PREVENTION.			2	L	7	3 	4F			RT	A22WE   					 
2001050200033	20010502	00033	CE  	2001	5	2	20010205CW004    	1	20010105	G	5740	50110231	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	WING SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	401TJ	3000 				402C0109				AFT SPAR REAR TOP WING ATTACH FITTING CORRODED.  INSTALLED NEW FITTING.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001050200034	20010502	00034	SO  	2001	5	2	20010205CW005    	2	20010205	G	8530	637837	VALVE SPRING    			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					NR 4 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	305AT		1354 			402C0030	519128			DURNING DETAILED INSPECTION OF LEFT ENGINE, COMPRESSION CHECK OF NR4 CYLINDER REVEALED LOW COMPRESSION.  APPROX 80/20, U	PON FURTHER INSPECTION THE OUTER SPRING OF THE INTAKE VALVE WAS FOUND TO BE BROKEN.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001050200035	20010502	00035	CE  	2001	5	2	20010205CW006    	1	20010205	G	7714	C6680160107	TACHOMETER      			CESSNA	402   	402C        	207590R	CE  										INSTRUMENT PANEL	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	2711X		94   			402C0116				LEFT ENGINE TACH NEEDLE WOULD NOT PROCEED BEYOND 2300 RPM WHEN ENGINE WAS ACTUALLY AT 2700 RPM.						1	L	7	2 	3O			 	A7CE    					 
2001050200036	20010502	00036	CE  	2001	5	2	20010205CW007    	1	20010116	G	2434	OHC315E	ALTERNATOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	AEIO320E1B  	41508	EA  					ENGINE	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	9627Q	400  				17265711				OHC ALTERNATOR, BOLTS HOLDING HOUSING TOGETHER,  2 BACKED OUT, LEFT HANGING BY INTACT SAFETY TO 3RD BOLT.						1	H	7	1 	3O	3	O	NT	3A12    	1E12				 
2001050200037	20010502	00037	SO  	2001	5	2	20010205CW008    	2	20010115	G	7414		ROTOR           	SLICK       		CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	93111	637  	637  		99061927	21060266	295010R			ROTOR BROKE AT CAM AND GEAR LOCATION/DRIVE GEAR.						1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001050200039	20010502	00039	SO  	2001	5	2	20010205CW010    	1	20010110	G	7160	87327002	VALVE           			PIPER 	PA28  	PA28161     	7102803	SO  										CARB AIR BOX	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	514MS					288316099				AIR VALVE IN CARB AIR BOX HAS BEEN REPLACED 3 TIMES WITH T/S : 1/327.3, 2/622.7, 3/186.4  ALL 3 REPLACEMENTS DUE TO WORN	 OR BROKEN ACTUATOR LEVER.  THIS LEVER WAS ORIGINALLY A STEEL PART THAT SEEMED TO LAST FOREVER.  THE AL APPEARS TO BE TO	O SOFT.  SUSPECT WHEN IT IS WELDED TO THE FHAFT ANY HEAT TREATMENT PRESENT, IS LOST.				1	L	7	1 	3O			 	2A13    					 
2001030700690	20010307	00690		2001	3	7	20010205CW011    	4	20010104	G	2210	761039	TRIM SWITCH     	CENTURY     		PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					PILOT YOLK	SHORTED         	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CE	01	9007Y					3111	RL55061			AFTER TAKEOFF AUTOPILOT TRIM PITCHED UP.  PILOT RETURNED TO AIRPORT AND HAD SAFE LANDING.  FOUND TRIM SWITCH IN PILOTS Y	OLK SHORTED OUT.  FOUND TWO WIRES TOUCHING, CAUSING PITCH UP.  RESOLDERED CONNECTOR AND INSULATED FROM OTHER TERMINALS.					1	L	7	1 	3O	3	O	RT	A20SO   	E14EA				 
2001030700571	20010307	00571	SW  	2001	3	7	20010205CW012    	1	20010117	G	5302	206033004143	MOUNT           			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	64PJ	6177 				51100				CRACK FOUND UNDER TAIL ROTOR GEARBOX AT AFT, RIGHT, MOUNT HOLE.  CRACK WAS NOT SEEN UNTIL GEARBOX WAS REMOVED TO PERFORM	 ASBCRACK WAS ONE INCH LONG, GOING FOR AND AFT THRU HOLE.					1	G	7	1 	3U			 	H2SW    					 
2001030600071	20010306	00071	CE  	2001	3	6	20010205CW013    	1	20010109	G	2910	2407003487	HYDRAULIC LINE  			LEAR  	25    	25D         	5170514	CE  	GE    	CJ610 	CJ6108      	30006	NE  					TAILCONE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	25HF					295				PILOT LOST HYDRAULIC PRESSURE IN FLIGHT.  INSPECTION REVEALED HYDRAULIC PRESSURE LINE FROM LEFT ENGINE TO AUXILLARY HYDR	ALUIC PUMP MANIFOLD LINE, CHAFFED AT CLAMP, RECOMMENDED REMOVING CLAMPS ON THIS SPECIFIC HYDRAULIC LINE ON AIRCRAFT WITH	 THE SAME HYDRAULIC SYSTEM SETUP.				2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2001032200117	20010322	00117		2001	3	22	20010205CW014    	4	20010115	G	2561	KS9P0101105	LIFE VEST       																	CELLS	WORN            	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED TO MEET MFG RECOMMENDED TWO SDI CELL TEST.  LIFE VEST DATE OF MFG JUNE 1983.  FAIR WEAR AND TEAR																			 
2001032200118	20010322	00118		2001	3	22	20010205CW015    	4	20010105	G	2561	KS9P0101	LIFE VEST       																	CELLS	WORN            	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIVE VEST FAILED  MFG RECOMMENDED PSI TEST.NOVEMBER 1982/  FAIR WEAR AND TEAR.																			 
2001030700573	20010307	00573	CE  	2001	3	7	20010205CW016    	1	20010104	G	5531	2707	RIB             			BBAVIA	8     	8KCAB       	2110612	CE  										VERTICAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	68ND	2760 	2760 			66892				DURNING ANNUAL INSPECTION , TAIL FIN FABRIC WAS FOUND BUCKLING APPROX 1 INCH AFT OF TOP LEADING EDGE.  UPON FABRIC REMOV	AL FOR HIDDEN DAMAGE INSPECTION THE FIN RIB WAS FOUND TO BE CRACKED AND BUCKLED AT FWD ATTACHING WELD.  FURTHER INSPECTI	ON REVEALED AFT ATTACHING WELD TO BE CRACKED ALSO, SUSPECTED CAUSE TO BE EXCESSIVELY TIGHTENED DRAG WIRES.				1	H	7	1 	3O			 	A21CE   					 
2001030700576	20010307	00576	SO  	2001	3	7	20010205CW019    	1	20010116	G	5753		BEARING         			GULSTM	G1159 	G1159B      	3953535	SO  										LT FLAP TRACK	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4NR	185  				255				NOTICED INBOARD ROLLER BEARING ON LEFT FLAP TRACK, B, WAS MISSING THE OUTER CASING AND BEARING...ONLY STUD REMAINED, CAU	SE IS UNKNOWN. RECOMMEND THAT ROLLER BEARINGS ARE VISUALLY INSP AT EACH PRE-FLIGHT INSPECTION AND MOVED WITH FINGERS TO 	CHECK FOR BINDING. NEW ROLLER/PN 1159SCC22821 WHICH SUPERCEEDS THE 1159CC2289   PURGED STOCK OF   -9 BEARINGS.				2	L	7	2 	4F			RT	A12EA   					 
2001030700582	20010307	00582	CE  	2001	3	7	20010206CW003    	1	20010108	G	3720	C6685090101	INDICATOR       			CESSNA	182   	182R        	2072731	CE  										INSTRUMENT PANEL	READS LOW       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	4776T	4169 				R18201762				WHILE COMPLYING WITH AD, 3.5 MINIMUM VACUUM COULD NOT BE OBTAINED, EVEN AT SEA LEVEL.  TROUBLESHOOTING REVEALED VACUUM I	NDICATOR WAS 2-2 1/2 IN HG LOW AND REGULATOR HAD BEEN MIS-ADJUSTED.  INSTALLED NEW GAGE, WHICH WAS CALIBRATED,  AND RESE	T REGULATOR DOWN. STANDBY SYSTEM RETESTED, OK.				1	L	7	1 	3O			NT	3A13    					 
2001030700678	20010307	00678	CE  	2001	3	7	20010206CW005    	1	20010112	G	5330	101120108601	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  										LT WING	DEBONDED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	25KA					BB783				LEFT WING UPPER INBOARD SKIN, ABOVE AUX. FUEL TANK, DEBONDING.  INSTALLED DOUBLER.						1	L	7	2 	4T			 	A24CE   					 
2001030700585	20010307	00585	EA  	2001	3	7	20010206CW006    	2	20010111	G	8530	LW16740	EXHAUST VALVE   	LYC         		BEECH 	80    	65A80       	1152808	CE  	LYC   	O720  	IO720A1B    	41546	EA  					CYLINDER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	134BA		216  			LD202	147554A			EXHAUST VALVE BROKEN IN HALF.						1	L	7	2 	3O	3	O	 	3A20    	1E15				 
2001030700587	20010307	00587	WP  	2001	3	7	20010206CW007    	2	20010115	G	7320	254911842	FUEL CONTROL    	GARRTT      		GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE33110    	01514	WP  					RT ENG	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	81448		337  			11327	P79656			WHILE DOING OVERSPEED GOVERNOR CHECK, ENGINE RPM STAYS ABOVE TAKEOFF, PROP GOVERNOR HIGH, AND WILL NOT REDUCE WHEN POWER	 LEVER AND CONDITION LEVER ARE RETARDED.  THIS CONDITION ALSO PREVENTS THE PROP FROM COMING OFF THE LOCKS.  TROUBLE SHOO	TING HAS DETERMINED THAT THE INLET SENSOR AND THE PROP GOVERNOR ARE NOT THE CAUSE OF THIS MALFUNCTION ANDTHE FUEL CONTRO	L IS, INDEED THE PROBLEM.  REPLACED FUEL CONTROL, RAN AND ADJUSTED AS REQUIRED.			1	H	7	2 	3T	4	T	 	2A4     	E4WE				 
2001030700591	20010307	00591	SO  	2001	3	7	20010206CW008    	1	20010111	G	3242	1331317	STATOR          			EMB   	120   	EMB120      	3260201	SO  										BRAKE ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05			2579 							BRAKE ASSEMBLY PN2-1661 FAILED PREMATURELY. NR 2 STATOR CRACKED THROUGH AT 1 RELIEF HOLE, BINDING ON TORQUE TUBE.NOTE: O	EM PARTS INSTALLED IN BRAKE ASSEMBLY            AND THE MOST RECENT BRAKE             CONFIGURATION PN 2-1661.					2	L	7	2 	4T			RT	A31SO   					 
2001032200119	20010322	00119		2001	3	22	20010206CW010    	4	20010113	G	2564		LIFE RAFT       	HOOVERIND   																	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					L301					LIFE RAFT RECEIVED IN PACKAGED CONDITION.  THE PACKAGE WAS OPENED AND FOUND THAT THE MOORING LINE WAS NOT CONNECTED TO T	HE INFLATION VALVES PULL CABLE. WITHOUT MOORING LINE BEING CONNECTED TO THE INFLATION VALVES PULL CABLES,  INFLATION OF 	THE LIFE RAFT WOULD NOT BE POSSIBLE,  IF THE MOORING LINE WAS PULLED DURING A DEPLOYMENT.  MAINTENANCE MANUALS SHOULD HA	VE ATTENTION OF WORKING PERSONNEL.																 
2001041000005	20010410	00005	EU  	2001	4	10	20010206CW012    	1	20010115	G	6730	AC67244	SERVO           	DUNLOP      		AEROSP	AS355 	AS355F1     	8680810	EU  										TAIL ROTOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					658					CRACKED DETECTED ON LOWER END OF SERVO BODY ABOVE END.   CAP EDDY CURRENT TESTING.						1	G	7	2 	3U			 	H11EU   					 
2001030700572	20010307	00572	EA  	2001	3	7	20010206CW014    	1	20010108	G	2752		BEARING         	EATON       		CNDAIR	CL600 	CL6002B19   	       	EA  										FLAP ACTUATOR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09					1385					THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRE-LOAD CONDITION.						2	L	7	2 	4F			RT	A21EA   					 
2001030700597	20010307	00597	SW  	2001	3	7	20010207CW001    	1	20010119	G	5320	206033110189	STIFFENER       			BELL  	206   	206L4       	1182110	SW  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	2036F	1169 				52123				CRACK IN TOP OF RIGHT AFT VERTICAL TUNNEL FWD OF BOX BEAM.  CRACK WAS FOUND IN THE RADIUS OF THE  206033110189 STIFFENER	.  MAY BE PRELOAD PROBLEM.					1	G	7	1 	3U			NC	H2SW    					 
2001030700598	20010307	00598	EA  	2001	3	7	20010207CW002    	2	20010122	G	7414	BL68291013	SHAFT           		D6LN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	59905		364  		J199901GR	317652135				THE GEAR AND SHAFT WERE FOUND LOOSE AND RETAINER WASHER WAS LOOSE AND RUBBING ON COIL FINGER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001030700626	20010307	00626	CE  	2001	3	7	20010209CW007    	1	20010111	G	5412	05530311	FIREWALL        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9421Z	882  				17280267				FOUND 1.8 IN LONG CRACK IN FIREWALL.  CRACK IS LOCATED BEHIND COWL SHOCKMOUNT BRACKET AT RIGHT FIREWALL STEP.  REPAIRED 	CRACK IN ACCORDANCE WITH SB.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001040900497	20010409	00497	CE  	2001	4	9	20010209CW009    	1	20010209	G	5410	505403042	BEAM            			CESSNA	421   	421C        	2076016	CE  										NACELLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	26603					0862				AC TOTAL TIME 4800 HRS , CRACK NOTED ON BOTH BEAMS RIGHT AND LEFT OUTBOARD SIDE OF EACH ENGINE.  BOTH CRACKS APPROX 1.5 	IN LONG.  CRACKS IN RADIUS OF BEND OF TOP STRAP OF BEAM ASSEMBLY NEAR JUNCTION OF FORE AND AFT RUNNING ENGINE MOUNT BEAM	S.				1	L	7	2 	3O			 	A7CE    					 
2001032200121	20010322	00121	EU  	2001	3	22	20010212CW002    	1	20010102	G	5600	F10AZ60200AZ	WINDSHIELD      			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					RT FWD WINDSHLD	CRACKED         	G				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	19	87TH	5660 				178				AIRCRAFT DEPARTED CMI IN VFR CONDITIONS AND DURING CLIMB OUT THROUGH 15,000 FT, THE CO-PILOT''S FWD WINDSHIELD OUTER PAN	E CRACKED.  PILOT  ELECTED TO RETURN TO CMI. AIRCRAFT LANDED WITHOUT INCIDENT.					2	L	7	2 	4F	4	F	 	A33EU   	E6WE				 
2001040900447	20010409	00447		2001	4	9	20010212CW003    	4	20010108	G	3423		WIRE            			BEECH 	36    	A36         	1151604	CE  										COMPASS	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	128JG					E3332				AC FROM FACTORY WITH 18.4 HRS, DURING AN AVIONICS INSTALLATION, DISCOVERED WIRES FOR THE MAGNETIC COMPASS THAT PASS BETW	EEN THE GLARESHIELD AND TOP OF INSTRUMENT PANEL ROUTED SO THEY WERE SANDWICHED AND CHAFING BETWEEN THE TWO.  RELIEF SPOT	 IN TOP OF INSTRUMENT PANEL TO ROUTE OTHER WIRING THAT GOES TO GLARESHIELD, BELIEVE TO BE NEEDED ROUTING FOR COMPASS. DU	E TO LENGTH OF THE WIRES BEING SHORT, COMPASS WIRES WILL NOT MAKE IT THROUGH THE RELIEFAND BE ABLE TO BE CONNECTED.  WE 	FEEL THESE WIRES WERE MISROUTED DUE TO A MANUFACTURING ERROR.  SUSPECT THE WIRE LOOM TO BE TOO SHORT.		1	L	7	1 	3O			 	3A15    					 
2001030600078	20010306	00078	EA  	2001	3	6	20010213CW005    	1	20010105	G	2752	601RR9310318	ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  										TE FLAPS	LACK OF LUBE    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09										THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRE-LOAD CONDITION.						2	L	7	2 	4F			RT	A21EA   					 
2001032200126	20010322	00126	CE  	2001	3	22	20010214CW001    	1	20010118	G	2140	FR81D943ELB4500	HEATER          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520*      	17032	SO  						ERODED          	B			DFZR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	09	922DN	11500				TH922				PILOT SMELLED CABIN HEATER GASES IN AIRCRAFT.  INSPECTED FOUND CABIN HEATER(B4500) CERMA KOTE, COMBUSTION CAN WITH HOLE 	IN AFT AREA OF CAN BY REAR DRAIN.  INSTALLED REBUILT HEATER.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001032700196	20010327	00196	GL  	2001	3	27	20010214CW002    	3	20010122	G	6114	A24182	ROD             	HARTZL      												HARTZL	HCC2Y	HCC2YK1     	GL  	PITCH ROD	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					AW696			AW696		OBSERVED CRACK-LINE INDICATION DURING MAG PARTICLE TESTING.  INDICATION APPEARS TO BE A LAMINATION IN MATERIAL DUE TO ST	RAIGHTNESS OR INDICATION.															5	C	P920	 
2001032700197	20010327	00197		2001	3	27	20010215CW002    	4	20010109	G	3421	5546257001	CONNECTOR       	COLLINS     																OUTER SHELL	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13					2193					EXCESSIVE CORROSION BUILDS UP ON PINS OF CONNECTOR, SPECIFICALLY PINS N AND P, WHICH RESULTS IN FLAGGING.																			 
2001032600328	20010326	00328	EA  	2001	3	26	20010215CW003    	2	20010116	G	8530	AEL6510212	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					HEAD	UNSERVICEABLE   	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4350G	1081 				288490058	L2749236A			A CRACK RUNS FROM TOP SPARKPLUG HOLE AROUND OUTSIDE EXHAUST SEAT TO TOP SPARKPLUG AND CYLINDER WILL SPLIT IN TWO PIECES.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001030700639	20010307	00639	SW  	2001	3	7	20010215CW004    	1	20010123	G	5320	206040338009	HANGER ASSY     	BELL        		BELL  	206   	206B3       	1181506	SW  										TAILBOOM BEARING	MISALIGNED      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	67330				BP36	5138				MOUNTING HOLES MISALIGNED.  PART MUST BE JIG DRILLED AND INSTALLED.  THE JIG WAS MISALIGNED AT INSTALLATION.						1	G	7	1 	3U			 	H2SW    					 
2001032100095	20010321	00095	CE  	2001	3	21	20010215CW005    	1	20010119	G	5210	1144002369	DOOR            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6*        	52043	EA  					BOTTOM AT HING	CRACKED         	B			S1FR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	500PR	5682 				UC139				BOTTOM OF DOOR .5 INCH FROM HINGE ATTACH POINT 3.5IN CRACK.						2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2001032600154	20010326	00154	SO  	2001	3	26	20010215CW007    	1	20010122	G	2910	166	SNAP RING       	ELECTROL    	166         	GULSTM	G44   	G44         	3951502	SO  	FCD   	6440  	6440*       	26003	EA  					CYL PISTON	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	10	69058				105	1291				SNAP RINGS RETAINING PISTONS IN PLACE SNAPED OFF.  ONE RING SHOWS SIGNS OF RUST DAMAGE.  PARTS LODGED IN CYLINDER-STOPPI	NG PROPER OPERATION.  RESULTING IN TOTAL FAILURE OF HYDRAULIC SYSTEM AND EMERGENCY SYSTEMS.CYLINDERS WERE MODIFIED TO AC	CEPT ORINGS INSTEAD OF CHEVRON TYPE SEALS.  SUSPECT ORING FAILURE, RESULTING IN OVER PSI AGAINST ORING ON RETURN PISTON,	 FORCING SNAP RING TO FAIL.			1	H	7	2 	3I	3	I	O	A734    	E216				 
2001032600311	20010326	00311	WP  	2001	3	26	20010220CW001    	1	20010107	G	6100	54H6077	PROPELLER       			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  	HAMSTD	54H	54H60       	NE  	VLV 2 HOUSING	BLOWN           	G				O				OTHER                   				K			FLUID LOSS                			TO	TAKEOFF        	1			GL	23	391FL	841  				278	550640	239764		AIRCRAFT WAS COLD SOAKED, OUTSIDE TEMPERATURE BEFORE DEPARTURE WAS 15 DEGREES.  SUBMITTER FEELS THIS WAS A CONTRIBUTING 	FACTOR TO THIS SEAL BEING DEFECTIVE.  COMPANY INITIATED PROCEDURES NOT TO CHANGE PROP BLADE ANGLE UNTIL MINIMUM OF 40 DE	GREE OIL TEMPERATURE IS OBTAINED, DEFECTIVE SEAL REPLACED.  AC RETURNED TO SERVICE.				2	L	7	2 	4R	4	T	 	6A6     	E282	6	C	P906	 
2001032600327	20010326	00327	CE  	2001	3	26	20010222CW001    	1	20010125	G	7602	S12345	LEVER           			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360*       	41514	EA  					PANEL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	16021	3292 				17702479				MIXTURE CONTROL BROKE ON GROUND RUN UP.   BREAK APPEARS TO BE DEFECT IN MATERIAL.						1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2001041000007	20010410	00007	SO  	2001	4	10	20010222CW002    	1	20010123	G	2410	635796	COUPLER         	CONT        		PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					RT ENGINE	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SW	99	304CW	170  			306527H	347870153	306527H			RT ALTERNATOR FAILED IN FLIGHT AT NIGHT.  ALTERNATOR FAILURE CAUSED BY DRIVE COUPLER FAILURE.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001032600329	20010326	00329	EU  	2001	3	26	20010222CW003    	1	20010118	G	7920	3033356	FUEL FILTER     			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A66      	52043	NE  					DISCHG FUEL FLTR	UNBONDED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	302PB					302				UPON 100 HOUR INSPECTION, REPLACEMENT OF ENGINE DISCHARGE FUEL FILTER.  NEW FILTER FROM 100 HR KIT WAS NOT GLUED TOGETHE	R.  THE TOP AND BOTTOM OF FILTER WERE LOOSE AND COULD BE PULLED OFF.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE				 
2001041000008	20010410	00008	EA  	2001	4	10	20010222CW005    	2	20010109	G	7414	103571651	COIL            		56LSC200    	GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540*      	41532	EA  					MAGNETO	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	411JF		387  		H279909ER	101435	269118			MAGNETO REMOVED FROM UNSERVICEABLE ENGINE.  DURING INSPECTION TO DETERMINE SERVICEABILITY,  FOUND COIL WIRE BROKEN AT PO	INTS END JUST BEFORE SPADE CONNECTOR.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001032200129	20010322	00129	GL  	2001	3	22	20010222CW006    	1	20010110	G	2750	F659	TUBE            			AMTR  	VANS  	VANSRV6     	05605AZ	GL  	LYC   	O320  	IO320*      	41508	EA  					BELOW FLAP	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3891P	117  				23736	L1220627			FLAP ROD BROKE JUST BELOW UPPER BALL JOINT CAUSING FLAP TO RETRACT ON LANDING.  THIS PART IS .3125 X .058 6061 T6 ALUMIN	UM TUBING AND APPEARS TO BE WEAK AFTER THREADS ARE CUT IN ENDS.					1	L	7	1 	3O	3	O	 	EXPA1L71	1E12				 
2001032200130	20010322	00130	CE  	2001	3	22	20010222CW009    	1	20010108	G	8011	PM2401	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	949SP	773  	773  			172S8145	L2812051A			PILOT ATTEMPTED ENGINE START, STARTER WOULD NOT ROTATE.  MAINTENANCE FOUND STARTER HAD TWO TERMINALS MELTED WHERE THAT A	TTACH TO  COMMUTATOR BRUSHES.  REPLACED STARTER,  OPERATIONAL CHECKED SAT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001032200131	20010322	00131		2001	3	22	20010222CW010    	4	20010119	G	2310	551202621	STRINGER        			CESSNA	500   	550         	2076604	CE  										AFT BAG COMPT	CRACKED         	C			U1CM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	26496	5215 				5500607				DURING SCHEDULED INSPECTION, IT WAS FOUND THAT SUPPORT PN1455078519 HAD CAUSED THE STRINGER AT/FS428.5/ TO CRACK AND PUL	L ATTACHING RIVETS LOOSE.  THE AC,  AT FACTORY, HAD ADDITIONAL EQUIPMENT RACKS INSTALLED.  IT SHOULD BE NOTED THAT CLOSE	R ATTENTION SHOULD BE PLACED ON INSPECTING THESE ATTACHMENT POINTS AS THEY MAY OR MAY NOT BE INCLUDED IN AREAS TO LOOK A	T DURING SCHEDULED TIMES.			1	L	7	2 	4F			 	A22CE   					 
2001032200133	20010322	00133	SW  	2001	3	22	20010223CW001    	1	20010117	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	C90   	C9012F      	17009	SO  	MCAULY	1B90	1B90*       	GL  	7TH RIB IB END	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	1205E	4262 				7AC4762	45450712	CM7343		DURING INSPECTION, CRACK FOUND ORIGINATING FROM RIB NAIL RUNNING HORIZONTAL.      SPAR INSTALLED 5/17/59						1	H	7	1 	3O	3	O	 	A759    	E252	5	N	P842	 
2001032200134	20010322	00134	EA  	2001	3	22	20010223CW002    	2	20010105	G	7322	25765362	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL SERVO	VAPOR LOCK      	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	03	567JW	163  			70217008	172S8187	L2822651A			ENGINE START, RUN UP AND TAKEOFF NORMAL, WHEN THROTTLE WAS RETARDED,  ENGINE BEGAN TO RUN ROUGH WITH POPPING OUT EXHAUST	.  MIXTURE WAS READJUSTED WITH NO CHANGE.  ADVANCED THROTTLE AND RETURNED TO HOME STATION.  LANDING UNEVENTFUL.  ENGINE 	RUN UP AFTER ENGINE HAD COOLED COMPLETELY INDICATED NO DEFECTS, ALL OPERATION NORMAL. MAINTENANCE INSPECTION OF ENGINE F	OUND NO DEFECTS.  CONCLUDED THAT FUEL VAPORIZATION CAUSED ROUGHNESS AT IDLE IN FLIGHT WITH INCREASED TEMPS, RETARDED THR	OTTLE AND REDUCED AIRFLOW THRU ENG AS THIS HAS BEEN CONTINUING PROBLEM.  COOLING MODIFICATIONS HAVE BEEN ACCOMPLISHED ON	 AC ENGINE TO INCLUDE INVERTING FUEL FLOW DIVIDER.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001032200143	20010322	00143	SO  	2001	3	22	20010223CW003    	1	20010131	G	3221	89137041	MOUNT           			PIPER 	PA46  	PA46350P    	       	SO  										DRAGLNK FT AREA	BROKEN          	B			HE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11										DRAGLINK FITTING AT ENGINE MOUNT BROKEN LOOSE DUE TO HARD LANDING. NEEDS VISUAL INSPECTION OFTEN, POSSIBLE REINFORCEMENT	 FROM MFG.					1	L	7	1 	3O			RT	A25SO   					 
2001032200197	20010322	00197	CE  	2001	3	22	20010223CW005    	1	20010123	G	7722	2870	PROBE           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520LB   	17040	SO  					NR1 CYL	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	4269S	650  				TJ96	237296R			CUSTOMER REPORTED NR1 EGT ON HIS GEM 1200, INOPERATIVE.  UPON REMOVAL OF EGT PROBE, ABOUT HALF OF THE PROBE TIP WAS BROK	EN OFF AND MISSING.  THE ONLY PATH OF EXIT IS THROUGH THE TURBO CHARGER.  FURTHER INSPECTION OF THE TURBO CHARGER REVEAL	ED FOD DAMAGE TO THE VANES OF THE EXHAUST TURBINE.  THE PROBE WAS REPLACED WITH NEW.  THE TURBO WAS  REPLACED WITH AN O/	H UNIT.NOTE: THESE TURBOS NOT ONLY SUPPLY BOOST TO ENGINE, BUT  ALSO PRESSURIZE CABIN AT ALTITUDE.  RECOMMEND AN INSPECT	ION INTERVAL OR TIME/LIFE LIMIT.		1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001032200202	20010322	00202	SO  	2001	3	22	20010227CW005    	1	20010124	G	2913	HYC5005	POWERPACK       			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C    	41514	EA  					MOTOR	INOPERATIVE     	B			PAID	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	13	6320C	6861 				28R7837157				WHEN LANDING GEAR WAS SELECTED DOWN, GEAR DID NOT EXTEND.  EXTENDED LANDING GEAR USING EMERGENCY PROCEDURES.  GEAR EXTEN	DED AND LOCKED.  LANDING MADE WITHOUT INCIDENT.  FOUND HYDRAULIC POWER PAK MOTOR INOPERATIVE.  INSTALLED OVERHAULED HYDR	AULIC POWER PAK.  GEAR RETRACTION TEST COMPLETED SATISFACTORY.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001032200205	20010322	00205	CE  	2001	3	22	20010227CW007    	1	20010202	G	8010	S1577	SOLENOID        			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	TSIO520*    	17040	SO  					STARTER	SHORTED         	B			BOE2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	7235F					21063038				AIRCRAFT CAME IN WITH DEAD BATTERY, FOUND BATTERY OVERHEATED.  PUT TEST BATTERY IN AND IMMEDIATELY WENT HIGH DISCHARGE. 	 WHEN STARTER WIRE REMOVED DISCHARGED STOPPED.  STARTER WAS SHORTED OUT.  UPON FURTHER INVESTIGATION, FOUND STARTER SOLE	NOID CONTACTS WERE WELDED TOGETHER, CAUSING STARTER TO ALWAYS BE ON THUS SHORTING IT OUT.  INSTALLED NEW STARTER RELAY, 	OVERHAULED STARTER AND INSTALLED NEW BATTERY.  AIRCRAFT RUNUP AND ALTERNATOR CHECK OK.			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001032000104	20010320	00104	SO  	2001	3	20	20010227SG001    	2	20010129	G	7414	BL3492606	MAGNETO         			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	FAILED          	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	99	931E		256  			TC1009	1553646L			PILOT REPORTED THAT THE MAGNETO WOULD FAIL ON RUN UP. TROUBLESHOT THE SYSTEM AND FOUND THE MAGNETO INTERIOR  COATED  IN 	BRONZE LIKE METAL FLAKES.  DETERMINED THAT THE BLOCK BEARING HAD FAILED AND THE ROTOR HAD CHAFED THE POINTS DOWN. THE MA	GNETOS HAD BEEN OVERHAULED BY TCM UNDER THEIR WO NO P53955. DISTRIBUTOR BLOCK PN 10-391586				1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2001050200030	20010502	00030	SO  	2001	5	2	20010227SG002    	2	20010131	G	7314	6467681A1R	PUMP            		TSIO520M    	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	7PAAL	451  			818076R	U20604718	818076R			ENGINE DRIVEN FUEL PUMP BEGAN LEAKING FROM SHAFT SEAL.						1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001050200032	20010502	00032	SO  	2001	5	2	20010227SG004    	2	20010115	G	7314	6467681A1	PUMP            		TSIO520M    	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	HCBXK	15   				U20604404				FUEL LEAK FROM PUMP DRAIN						1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001040900135	20010409	00135	NE  	2001	4	9	20010227SG005    	2	20010201	G	7314	31042681	PUMP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2GG	1848 			PC	5500286	PCE70020			ENGINE OIL PUMP PN: 3104268-1 SN; A1178 WITH 1848.2 HOURS SINCE INSTALLATION FAILED. THE PUMP SEIZED AND CAUSED SHAFT TO	 SHEAR. PUMP WAS REPALCED WITH OVERHAULED UNIT.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001032200209	20010322	00209	CE  	2001	3	22	20010228CW001    	1	20010206	G	2840	535942	RESISTOR        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1C    	41514	EA  					RT  SENDER	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	434ER	244  				17280655				DURING PHASE 1 INSPECTION, RT FUEL QUANTITY READING WAS ERRATIC.  THE SHAFT BEARING OR SEAL WAS FOUND TO BE DEFECTIVE ON	 THE RT SENDER.  THIS APPARENTLY ALLOWED GASOLINE INTO THE SENDER.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001040900229	20010409	00229	EA  	2001	4	9	20010228CW002    	2	20010201	G	8520	LW11026	CRANKCASE       			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					ENGINE	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	87CW	5168 				301639	L349755A			DURING ANNUAL INSPECTION, OIL LEAK NOTED AT CRANKCASE AREA FORWARD OF NR2 CYLINDER.  AFTER CLEANING AN OBVIOUS 1.5 IN CR	ACK WAS NOTED.  ENGINE WAS REMOVED FOR REPAIRS.  LT ENGINE TSMOH 1098.41, 1992 FIREWALL FORWARD, INC.					1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2001032200210	20010322	00210	SO  	2001	3	22	20010228CW003    	2	20010201	G	8520	629288	CRANKCASE       			BEECH 	35    	M35         	1151526	CE  	CONT  	O470  	IO470C      	17026	SO  					LT TOP CTR CRKCS	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	06	9748R	5874 				D6229				DURING ANNUAL INSP, OIL LEAK NOTED AT TOP OF CRANKCASE, CLEANING AND RERUN, OIL LEAK RETURNED.  FOUND 1.25 IN CRACK EXTE	NDING FROM TOP CENTER CASE BOLT HOLE AT AREA WHERE FUEL FLOW DIVIDER BRACKET ATTACHES.  CRACK IN NON-CRITICAL AREA AND W	ITHIN CRACK LIMITATIONS EXCEPT OIL LEAK IN EXCESS.  ENGINE REMOVED FOR REPAIRS/ CRANKCASE RECONDITIONED.				1	L	7	1 	3O	3	O	 	3A15    	E273				 
2001030700623	20010307	00623	SW  	2001	3	7	20010228CW005    	1	20010124	G	6420		YOKE            			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	OUT OF POSITION 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	407LR	1854 				53279				INBOARD BEARINGS 2EA WERE FOUND TO HAVE SHIFTED IN YOKE APPROXIMATELY .050 IN OFF CENTER.  ONE YOKE BORE WAS WORN BEYOND	 LIMITS.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001040900453	20010409	00453	SO  	2001	4	9	20010228CW008    	1	20010124	G	2140	A23D047	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HEATER	LEAKING         	B			FFSA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4501B					318052168				THIS FUEL REGULATOR WAS INSTALLED NEW,  AND WHILE PRESSURE TESTING STATIC ON GROUND, IT WAS FOUND TO BE LEAKING FROM SCR	EW ON TOP OF UNIT.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032100132	20010321	00132	SO  	2001	3	21	20010228CW010    	1	20010116	G	3260	67411002	SWITCH          			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					LT LANDING GEAR	INOPERATIVE     	B			EASR	O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			EA	23	6320C	563  				28R783757				UPON EXTENSION OF LANDING GEAR, NO DOWN & LOCKED INDICATION NOTED ON LEFT LANDING GEAR.  AIRCRAFT LANDED WITHOUT INCIDEN	T.  FOUND LEFT LANDING GEAR DOWN LIMIT SWITCH INTERMITTENT.  INSTALLED NEW SWITCH.  RETRACTION TEST COMPLETED SATISFACTO	RY				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001040900174	20010409	00174		2001	4	9	20010228CW011    	4	20010201	G	2562	MN1300LR20	BATTERY         	ACK         		CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	IO540*      	41532	EA  					ELT	CORRODED        	B			AMVR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	05	4135C				022105	R18200326				UPON INSPECTION OF ELT AND BATTERIES, WERE FOUND TO BE CORRODED AND SWELLING, THE BATTERY COMPARTMENT IS WET WITH A LIQU	ID.  COMPOSITION OF LIQUID UNKNOWN.  ELT IS INSIDE TAIL SECTION OF AC AND NOT SUBJECT TO WATER EXPOSURE.					1	H	7	1 	3O	3	O	RT	3A13    	1E4				 
2001040900228	20010409	00228	EA  	2001	4	9	20010301CW001    	2	20010126	G	8520	SL13790A	SHAFT           			CESSNA	177   	177A        	2073706	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE ROCKERS	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	70847	123  				17701356	L1992336A			ROUGH GRIND FINISH CAUSED ALMOST ALL 8 ROCKER ARM BUSHINGS TO WEAR AND CONTAMINATE OIL WITH BRASS, METAL PARTICLES. BUSH	INGS AND ROCKER SHAFTS WERE DEFECTIVE FROM WEAR AND WERE REPLACED.					1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2001030700569	20010307	00569		2001	3	7	20010301CW004    	4	20010301	G	2562	E01	ELT             			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20      	03013	GL  					CABIN	CRACKED         	E			AWTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	67PJ	300  				3966				INSPECTING ELT, FOUND CASE TO BE IN MANY PIECES WITH CRACKS THROUGHOUT ENTIRE UNIT.  PLASTIC SEEMS TO BE VERY SOFT AND B	RITTLE.  THIS IS SECOND ELT OF THIS MAKE AND MODEL THAT HAS BEEN FOUND IN THIS CONDITION DURING TESTING FOR NON OPERATIO	N.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001032100135	20010321	00135	CE  	2001	3	21	20010301CW006    	1	20010130	G	3250	HM6	ROD END         			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6*        	52043	EA  					NOSE GEAR STRNG	DISCONNECTED    	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	17	11FL	12250				LJ301				NOSE GEAR STEERING ARM BECAME DISCONNECTED DURING TAXI,  SENDING AC INTO HARD RIGHT TURN.  ROD END BALL AND BUSHING SEPA	RATED FROM ROD END EYELET.  NO ABNORMAL WEAR WAS NOTED.  RECOMMEND INSTALLING LARGE DIAMETER WASHER UNDER HEAD OF BOLT F	OR RETAINING ROD END EYELET IN CASE OF FAILURE.  ROD END IS NOT PART OF NOSE GEAR OVERHAUL,  SHOULD BE INSPECTED.				1	L	7	2 	3T	3	T	 	3A20    	E2NE				 
2001041000010	20010410	00010	CE  	2001	4	10	20010301CW008    	1	20010301	G	7920	CH48108	OIL FILTER      			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					OIL SUMP	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2170S					21061131				PIECES OF SEALANT USED TO SEAL THE INLET AND OUTLET OF THE FILTER, INSIDE THE FILTER FLAKING OFF AND GOING DOWNSTREAM IN	 THE OIL SYSTEM.  PIECES COULD GET INTO THE PRESSURE SYSTEM AND STARVE A BEARING FOR OIL.					1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001032700231	20010327	00231	SO  	2001	3	27	20010301CW009    	1	20010301	G	7920	CH48110	OIL FILTER      			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O320  	O320*       	41508	EA  					OIL SUMP	FLAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2602B					3879A0146				FOUND SEALANT MATERIAL IN OIL SUMP DURING NORMAL 50 HR OIL CHANGE.  FOUND ON SUCTION SCREEN.  SEALANT CAME FROM THE OIL 	FILTER.  AREA THAT SEALS THE INLET TO THE OUTLET AREA OF THE FILTER IS FLAKING OFF AND GETTING STUCK IN THE FILTER AND O	N THE OIL SUCTION SCREEN.				1	L	7	1 	3O	3	O	 	A18SO   	E274				 
2001032700232	20010327	00232	SO  	2001	3	27	20010301CW010    	1	20010301	G	7920	CH48110	OIL FILTER      			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235*       	41505	EA  					OIL SUMP	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2596E					3878A0483				SEALANT USED IN MANUFACTURE OF FILTER TO SEAL THE INLET AND OUTLET TO THE FILTER APPEARS TO BE FLAKING OFF.  PIECES ARE 	BEING FOUND INSIDE THE FILTER ON THE PLEATS AND ON THE OIL SUMP SUCTION SCREEN.  THESE PIECES COULD GET INTO THE PRESSUR	E SYSTEM AND STARVE A BEARING FOR OIL.				1	L	7	1 	3O	3	O	 	A18SO   	E223				 
2001032700233	20010327	00233	CE  	2001	3	27	20010301CW011    	1	20010301	G	7920	CH48108	OIL FILTER      			CESSNA	210   	T210N       	2073456	CE  										OIL SUMP	FLAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5201A					21063305				PIECES OF THE SEALANT USED TO SEPARATE INLET AND OUTLET CHAMBERS INSIDE THE OIL FILTER ARE BREAKING OFF AND ARE BEING FO	UND IN THE FILTER PLEATS AND IN THE SUMP ON THE SUCTION SCREEN.  THESE PIECES COULD BLOCK AN OIL PASSAGE IN THE PRESSURE	 SYSTEM AND STARVE A BEARING FOR OIL.				1	H	7	1 	3O			 	3A21    					 
2001030500003	20010305	00003	CE  	2001	3	5	20010302AP001    	1	20010103	G	5712	12210624	BULKHEAD        			CESSNA	210   	T210M       	2073451	CE  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99		6193 								FOUND RIGHT WING INBOARD FLAP BELLCRANK BULKHEAD STA.54.75 CRACKED. CRACK WAS LOCATED LEFT LOWER CORNER OF BULKHEAD (LOO	KING FWD) AND APPROX. 1.5 INCHES LONG. AIRCRAFT HAS  ROBERTSON STOL KIT INSTALLED. SUSPECT HIGHER CABLE TENSIONS BECAUSE	 OF STOL KIT CONTRIBUTED TO THE CRACKING. THIS IS THE THIRD AIRCRAFT FOUND WITH THIS PROBLEM, ALL WITH SIMILAR AIRFRAME 	TOTAL TIME.			1	H	7	1 	3O			 	3A21    					 
2001030200059	20010302	00059		2001	3	2	20010302AP003    	4	20010104	G	2215	275	MOUNT           			BEECH 	36    	36BEECH     	1151602	CE  										SERVO	MISINSTALLED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	111LJ					E1822				SERVO MOUNT (KM-275) WAS FOUND INSTALLED INCORRECTLY NOT ALLOWING FULL ENGAGMENT WITH THE SERVO (KS-270).  SERVO MOUNT W	AS FOUND INSTALLED ON TOP OF SERVO MOUNTING SHELF AND SERVO WAS INSTALLED UNDERNEATH SERVO MOUNTING BRACKET.  THE SERVO 	MOUNTING BRACKET (SHELF) WAS FOUND BETWEEN THE SERVO AND SERVO MOUNT.  INSTALLATION INSTRUCTIONS CALLS FOR SERVO (KS-270	) AND SERVO MOUNT (KS-270) BE INSTALLED UNDERNEATH SHELF.  RESEARCH OF AIRCRAFT RECORDS DID NOT SHOW ANY MAINTENANCE THA	T WOULD HAVE RESULTED IN THIS IMPROPER CONFIGURATION.  SUSPECT INCORRECT INSTALLATION WAS DONE AT INITIAL INSTALLATION O	F THE AUTOPILOT SYSTEM.	1	L	7	1 	3O			 	3A15    					 
2001030200060	20010302	00060	CE  	2001	3	2	20010302AP007    	1	20010109	G	8120	98510441	CHECK VALVE     	ALIDSG      		CESSNA	206   	206CESSNA   	2073302	CE  										TURBO INLET	LEAKING         	D				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			SW	99	PKMPP	704  	704  		BLO26610	U20603719				TURBO CHARGER OIL INLET DRAINS OIL INTO TURBOCHARGER AT SHUTDOWN.  UPON REMOVAL AND INSPECTION, THE CHECH VALVE WAS FOUN	D TO TAKE ONLY LIGHT AIR PRESSURE TO UNSEAT THE CHECK VALVE AND BLOW BOTH DIRECTIONS THROUGH THE CHECK VALVE.					1	H	7	1 	3O			 	A4CE    					 
2001040900249	20010409	00249	CE  	2001	4	9	20010302CW001    	1	20010302	G	3210	3450A	LANDING GEAR    			CESSNA	206   	T206H       	       	CE  										MAINS	COLLAPSED       	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7255T	4    				T20608065				MAIN GEARS COLLAPSED ON FLOAT POND ENTRY / EXIT RAMP.  INSPECTION FOUND RT AND LT MAIN GEAR ACTUATING CONTROL SHAFTS BRO	KEN. REPLACED RT AND LT ACTUATING CONTROL SHAFTS ON MAIN GEAR ASSEMBLY.  GEAR RETRACTION TESTS COMPLETED SATISFACTORY.					1	H	7	1 	3O			 	A4CE    					 
2001040900254	20010409	00254	SO  	2001	4	9	20010302CW003    	2	20010108	G	7414		DRIVE GEAR      			CESSNA	150   	150A        	2071804	CE  	CONT  	O200  	O200A       	17020	SO  					MAGENTO	BROKEN          	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17	7141X	600  				15059241	51063AR			MAGNETO DRIVE GEAR BROKEN.  BROKEN PIECE LODGED BETWEEN CAM GEAR AND GENERATOR GEAR, BREAKING GENERATOR SHAFT, DESTROYIN	G GENERATOR, CAM GEAR AND OIL PUMP COVER.  BOTH MAGNETO DRIVE GEARS WERE UNAPPROVED PARTS.  PARTS INSTALLED.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900077	20010409	00077	CE  	2001	4	9	20010305CW004    	1	20010212	G	3110		POTENTIOMETER   			CESSNA	172   	172S        	2072439	CE  										INSTRUMENT PANEL	MISINSTALLED    	B			ESMR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	563SP					172S8416				REPORT THAT RADIO INDICATOR BACKLIGHTING AND RADIO CONTROL BACKLIGHTING HAD NOT WORKED SINCE DELIVERY OF AC.  TROUBLESHO	OTING, FOUND THAT PIN 1 OF JC005 WAS AT GROUND POTENTIAL, PREVENTING DIMMER POTENTIOMETER FROM FUNCTIONING PROPERLY.  RE	MOVED WIRE FROM CIRCUIT, WIRE THAT HOOKS INTO WARNING / CAUTION ANNUNCIATOR.  RADIO LIGHTING WORKED CORRECTLY.  THE WAY 	SWITCH WAS INTERGRATED INTO SYSTEM WAS CAUSING HARD GROUND CONDITION.			1	H	7	1 	3O			NT	3A12    					 
2001032200215	20010322	00215	SO  	2001	3	22	20010305CW011    	1	20010123	G	7714	640925	ADAPTER         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					90 TACH DR ADPT	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2240D	88   				347970032	807536L			90 DEGREE TACH DRIVE ADAPTER PUT ON AIRCRAFT.  WHEN ADAPTER FAILS, THERE IS NO RPM INDICATION TO TACH.  PROBLEM APPARENT	LY VIBRATION INDUCED.  SOME PROVISION SHOULD BE MADE TO REINFORCE UNIT OR RELOCATE IT TO AN AREA NOT AS PRONE TO VIBRATI	ONS.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001032200216	20010322	00216	SO  	2001	3	22	20010305CW012    	1	20010125	G	7714	640925	ADAPTER         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					90 TACH ADAPTER	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	2240D	121  				347970032	807536R			90 DEGREE TACH DRIVE ADAPTER PUT ON AIRCRAFT.  WHEN ADAPTER FAILS,  THERE IS NO RPM INDICATION TO TACH.  PROBLEM, APPARE	NTLY VIBRATION INDUCED.  SOME PROVISIONS SHOULD BE MADE TO REINFORCE UNIT , OR RELOCATE IT TO AN AREA NOT AS PRONE TO VI	BRATIONS.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001040900019	20010409	00019	SO  	2001	4	9	20010305CW013    	1	20010123	G	7714	640925	ADAPTER         			PIPER 	PA34  	PA34200T    	7103406	SO  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TACH GENERATOR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2240D	274  				347970032	807536R			90 DEGREE TACH ADAPTER PUT ON AIRCRAFT.  WHEN ADAPTER FAILS, THERE IS NO RPM INDICATION TO TACH.  PROBLEMS APPARENTLY VI	BRATION INDUCED.  SOME PROVISION SHOULD BE MADE TO REINFORCE UNIT, OR RELOCATE IT TO AN AREA NOT AS PRONE TO VIBRATION.					1	L	7	2 	3O	3	U	 	A7SO    	E19EU				 
2001040900052	20010409	00052	EA  	2001	4	9	20010305CW014    	2	20010305	G	8550	CH48110	OIL FILTER      			CESSNA	172   	172         	2072402	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	FLAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	737MP					17269524				UPON INSPECTION OF OIL FILTER AFTER 50 HRS USAGE,  FILTER HOUSING DISASSEMBLED FOR INSPECTION AND GASKET / GLUE TYPE MAT	ERIAL NOTED AT MATING FLANGES INSIDE.  THIS MATERIAL NOTED IN FILTER ASSEMBLIES  NUMBEROF TIMES AND ALSO DRAINED FROM OI	L SUMPS, RECOMMEND MFG CHECK AMOUNT OF SEALANT USED AND DESIGN CRUSH TYPE SEAL USED INSTEAD OF MATERIAL THAT CAN FLAKE A	WAY AND GO THROUGH OIL SYSTEM.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001030600022	20010306	00022	SO  	2001	3	6	20010306AP001    	1	20010112	G	2820	67700322	FUEL LINE       			PIPER 	PA32  	PA32301T    	7103209	SO  										BAGGAGE AREA	LEAKING         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	99	81573					328024004				PILOT REPORTED STRONG FUEL ODOR IN CABIN. INVESTIGATION REVEALED FUEL LEAKING FROM FLARELESS FITTING SLEEVE AT BULKHEAD 	FITTING AFT OF FIREWALL BELOW THE NOSE BAGGAGE AREA FLOOR. FUEL WAS CARRIED BACK INTO THE CABIN AREA INSIDE THE PLASTIC 	CHAFF SLEEVE COVERING THE LINE. THE PLASTIC CHAFF COVER WAS SPLIT IN THE CABIN AREA AND FUEL DRIPPED BEHIND THE SIDE PAN	EL. REPLACED LINE ASSEMBLY. SUSPECT FLARELESS FITTING SLEEVE BECAME LOOSE DUE TO VIBRATION AND AGE.   			1	L	7	1 	3O			 	A3SO    					 
2001030600023	20010306	00023	CE  	2001	3	6	20010306AP002    	1	20010112	G	7160	BA4106	AIR FILTER      			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	18033					15073748	669917A			DURING ANNUAL INSPECTION THE AIR FILTER ASSEMBLY WAS REMOVED TO FACILITATE INSPECTION OF CARB AIRBOX AND HEAT VALVE.  UP	ON REMOVAL, IT WAS NOTED THAT THE AIR FILTER FRAME DID NOT HAVE THE GASKET RETAINER LIPS AS REQUIRED BY AD 96-09-06.  TH	E FILTER FRAME WAS MARKED WITH A MANUFACTURERS DATA LABEL IDENTIFYING IT AS A BA-4106 REVISION D.  REVISION D IS TERMINA	TING ACTION FOR THIS AD AND INDICATES THE PRESENCE OF THE GASKET RETAINING LIPS ON THE FRAME.  THE MANUFACTURER, WHEN CO	NTACTED, STATED THAT ALL REV. D FRAME ASSEMBLIES HAD A LETTER L METAL STAMPED IN THE LOWER FLANGE BEFORE ANODIZEING.  TH	IS IDENTIFICATION WAS MISSING.THE SUBMITTER SPECULATES THAT AN UNSCRUPULOUS MISCREANT OBTAINED A REVISION D LABEL IN O	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900138	20010409	00138	CE  	2001	4	9	20010306CW001    	1	20010101	G	2720	071230916AGW	BELLCRANK       			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520*      	17032	SO  					RUDDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4877Q	7758 				18802613T				RUDDER BELLCRANK PN 0712309-16AGW HAD EXTREME WEAR SEVERAL PLACES, BOTH SIDES.  WHERE THEY ARE LOCATED THEY ARE DIFFICUL	T TO INSPECT AND LUBERCATE.  MADE INSPECTION PANEL TO BE ABLE TO GAIN ACCESS TO THIS VITAL AREA.  FAILURE OF THIS PART W	OULD POTENTIALLY CAUSE GROUND LOOP.				1	L	7	1 	3O	3	O	 	A9CE    	E5CE				 
2001040900216	20010409	00216		2001	4	9	20010312CW001    	4	20010212	G	2562	ELT910	ELT             			LKHEED	P3A   	P3A         	5260103	NM  										CABIN	UNSTABLE        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	927AU					151369				ELT SELF ACTIVATED.  THIS UNIT WAS SENT TO THE FACTORY FOR WARRANTY REPAIR FOR THE SAME DEFECT 2 MOS EARLIER.  AIRCRAFT 	WAS SITTING ON RAMP WITH NO POWER. ELT WENT OFF AT 2AM.  UNITS HAVE A POOR SELF ACTIVATION RATE.					2	L	7	4 	4T			RT	A32NM   					 
2001040900222	20010409	00222	SO  	2001	4	9	20010312CW002    	1	20010213	G	3244	217K221	TIRE            			GULSTM	GV    	GV          	       	SO  										NLG	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11										NOSEWHEEL TIRE HAS SEPARATION OF TREAD FROM CARCUS.  BONDING BETWEEN TREAD AND CARCUS DEBONDED.						2	L	7	2 	4F			RT	A12EA   					 
2001040900227	20010409	00227	NE  	2001	4	9	20010312CW003    	2	20010205	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FROM REPAIR STATION FOR PENETRANT INSPECTION.  PART REJECTED 2ND TIME AT PENETRANT INSPECTION FOR INDICATI	ONS AS MARKED IN RADIUS ADJACENT TO MACHINED FACES OF OIL PASSAGES.										4	F			E311NE				 
2001040900225	20010409	00225	NE  	2001	4	9	20010312CW004    	2	20010130	G	7250	2A0847	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR4 BEARING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR PENETRANT INSPECTION.  PART REJECTED AT PENETRANT INSPECTION FOR TWO INDICATIONS AT BOTTOM OF COUNTERB	ORES ON ID OF PART.										4	F			E311NE				 
2001040900226	20010409	00226	NE  	2001	4	9	20010312CW005    	2	20010130	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR4 BEARING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART RECEIVED FOR PENETRANT INSPECTION.  PART REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED IN RADIUS ADJAC	ENT TO MACHINED FACES OF OIL PASSAGES.										4	F			E311NE				 
2001040900102	20010409	00102	EU  	2001	4	9	20010312CW009    	1	20010129	G	5540		BRACKET         			EIRVON	20    	PIK20D      	5760206	EU  										RUDDER HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	7820D					20602				VIBRATION OF A HARD RUBBER TAIL DOLLY TIRE ASSISTS IN THE FORMATION OF THESE CRACKS.  THIS STATEMENT MAY GIVE FALSE SENS	E OF SECURITY TO OWNERS WHO ONLY USE PNEUMATIC TIRES, AS WAS THE CASE WITH THIS AIRCRAFT.  THREE OF THE FOUR FLANGES WER	E CRACKED AND WERE VERY HARD TO SEE, EVEN WITH A 5X MAGNIFICATION.  CRACKS WERE HIDDEN UNDER EPOXI RESIN THAT HAD BEEN I	N PLACE SINCE NEW. ANY RESIN AND USE  OF DYE PENETRANT INSPECTION.			1	K	0	0 	  			 	G31EU   					 
2001040500111	20010405	00111	EU  	2001	4	5	20010314CW001    	1	20010218	G	2612	B332M	FIRE DETECTOR   			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	SHORTED         	E			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5416F					794	836063			DURING PRESTART CHECK.  AFT PROBE SHORTED TO ELBOW ON ENGINE AIR SYSTEM.						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2001040500112	20010405	00112	SW  	2001	4	5	20010314CW002    	1	20010217	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					BLOWER	CRACKED         	E			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL					53247	CAE847167			FOUND DURING ROUTINE MAINTENANCE.   BLOWER HOUSING HAD CRACKED.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001040500113	20010405	00113	SW  	2001	4	5	20010314CW003    	1	20010201	G	5320	NAS6606D70	BOLT            			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT71        	30030	NE  					FUSELAGE	BROKEN          	E			ALGA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	392AL					28114				DURING DAILY INSPECTION, FOUND UPPER RETAINER BOLT, PN NAS6606D70, ON THE FWD NODAL BEAM ASSY HELPER SPRING BROKE, CRACK	ING THE HELPER SPRING SIDE PLATE AND CAUSING CONTACT DAMAGE TO THE RIGHT TORSION ARM ASSEMBLY.  NEED SCHEDULED INSPECTIO	N OR RETIREMENT OF BOTH UPPER AND LOWER BOLTS DUE TO THE HIGH STRESS LOAD ON THESE PARTS.				2	G	7	2 	4U	4	U	 	H10SW   	E8NE				 
2001040500114	20010405	00114	EU  	2001	4	5	20010314CW004    	1	20010126	G	6520	365A33619721	FLANGE          			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL ROTOR G/B	WORN            	E			EGRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	272NE				M538	6435				DURING T INSPECTION, FOUND BOLTS ATTACHING SLIDING FLANGE TO FLEXIBLE COUPLING HAVE LOW TORQUE.  COTTER KEYS WERE INSTAL	LED.  SLIDING FLANGE AND FLEXIBLE COUPLING HAVE GROOVES WORN ON ATTACHING SURFACE.  REPLACED SLIDING FLANGE, FLEXIBLE CO	UPLING, AND ATTACH HARDWARE WITH NEW.				1	G	7	2 	3U	3	U	RT	H10EU   	E19EU				 
2001032200221	20010322	00221	EU  	2001	3	22	20010319CW005    	1	20010222	G	2720		BRACKET         			PDP   	503   	SZD503      	8821647	EU  										ATTACH BOLT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	191CM					B2198				RUDDER PULLEY CONTROL BRACKET CRACKED AT ATTACH BOLT LOCATIONS.  THIS WAS DUE TO LACK OF VARNISH OF THE BRACKETS AND POS	SIBLE SHRINKAGE OF MATERIAL.  PRIOR TO INSPECTION OF AREA, PILOT REPORTED RUDDER FLUTTER AND STICKING.  RECOMMEND INSPEC	TION OF ALL AIRCRAFT FOR SIMILAR CONDITION.				1	K	0	0 	  			RC	G02CE   					 
2001040500137	20010405	00137	SW  	2001	4	5	20010319CW006    	1	20010216	G	6310	47620669S	CLUTCH          	BELL        		BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					M/R TRANSMISSION	DAMAGED         	H			ARUA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	11	48020		369  		B123119	2812	67452C			AIRCRAFT IN CRUISE AT 300 FT AGL CLUTCH SLIPPED AUTOROTATION PERFORMED DISASSEMBLED FOUND PARTIAL CONTACT OF CLUTCH/DRUM	 FACE.  DRUM AT MAX LIMITS.  MORE CAUTIOUS MEASUREMENT DURING OVERHAUL AND REQUIRED INSPECTION.					1	G	7	1 	3O	3	O	 	2H3     	1E13				 
2001032000001	20010320	00001	SO  	2001	3	20	20010320AP001    	1	20010119	G	2140	A23D047	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	C				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99						318152176				THE PROBLEM THAT WE ARE HAVING IS WITH THE HEATER FUEL PRESSURE REGULATORS P/N A23D04-7.5 THEY START LEAKING FUEL AROUND	 THE HOUSEING. THE FIRST ONE STARTED LEAKING AFTER 180.9 HOURS OF HEATER OPERATION. INSTALLED NEW IN STOCK UNIT, AND IT 	LEAKED ON FIRST TEST FIRING. WE ALSO JUST HAD ANOTHER UNIT START LEAKING ON ONE OF OUR OTHER PIPER NAVIJO HEATER. THIS U	NIT HAD 834.1 HEATER HOURS ON IT WHEN IT STARTED LEAKING.			1	L	7	2 	3O			 	A20SO   					 
2001032000187	20010320	00187		2001	3	20	20010320AP002    	4	20010215	G	6113	055032110	BULKHEAD        			CESSNA	172   	172I        	2072426	CE  										SPINNER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	46230					17257123				SPINNER BULKHEAD WAS FOUND BROKEN AT END NEAR BLADE, WHERE LAST NUTPLATE IS LOCATED. THE BULKHEAD WAS REMOVED AND A NEW 	ONE ORDERED THROUGH API. THIS PART HAD BEEN REPLACED LESS THAN ONE YEAR EARLIER, APPROX 300 HOURS WERE ON THE PART. WHEN	 WE RECIEVED THE FACTORY NEW PART WE FOUND A CRACK/DEFECT IN THE EXACT SAME AREA AS WHERE THE BULKHEAD WE WERE REPLACING	 HAD BROKE. CESSNA PRODUCT SUPPORT WAS NOTIFIED BY US OF THIS PROBLEM, BUT THEY DID NOT SEE THAT IT WAS OF ANY CONCERN. 	WE STRONGLY FEEL DIFFERENTLY, AND WE BELIEVE THAT THE MACHINARY USED TO MAKE THIS PRODUCT COULD BE INDUCING DAMAGE THAT 	WILL CAUSE THE PART TO FAIL IN THE FUTURE.	1	H	7	1 	3O			NT	3A12    					 
2001040900253	20010409	00253	GL  	2001	4	9	20010321CW005    	3	20010213	G	6114	C50462	PLATE           	MCAULY      		CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	PROPELLER HUB	MISSING         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2280T				776894	R18200016	L1928840A	776894		WHILE IN FLIGHT, THE C50462 SPINNER MOUNTING PLATES FAILED, RELEASING THE SPINNER FROM THE AIRCRAFT.  THE PROPELLER BECA	ME LOOSE ON THE CRANKSHAFT DUE TO THE MISSING PLATES.  WAS DAMAGED BEYOND REPAIR DUE TO SEVERE FRETTING.  A NUMBER OF TH	E ATTACHING STUDS WERE SKIPPED AS WERE THE CRANKSHAFT BUSHINGS FROM THE SEVERE ABNORMAL LOADS IMPOSED UPON THEM.  COMMON	 TO FIND THE C50462 PLATES CRACKED DURING OVERHAUL OR MINOR REPAIRS.  HOWEVER, THIS IS FIRST OF IN-FLIGHT FAILURE KNOWN.			1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2001040900257	20010409	00257	GL  	2001	4	9	20010321CW006    	3	20010212	G	6111	A2202B	RETAINER        	HARTZL      		PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YK2     	GL  	PROP BLADE	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					C23534			1537		MT INSPECTION REVIELD A CRACK APPROX .1250 INCH LONG ON BOTH SIDES OF RACE MATERIAL.  PROPELLER WAS PURCHASED AS A OVERH	AULED PROPELLER WITHOUT RECORDS.  REPORTED LOST.  PURCHASER SUBMITTED PROPELLER FOR OVERHAUL.  IN ADDITION TO THIS CRACK	ED PART, THE BLADES WERE FOUND TO BE 2 INCHES UNDER  MINIMUM DIAMETER FOR THE INTENDED APPLICATION.				1	L	7	2 	3O			 	1A10    		5	C	P9EA	 
2001040900466	20010409	00466	GL  	2001	4	9	20010322CW012    	1	20010219	G	2730	10680009	CARTRIDGE       			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	ELEV CONTROL	JAMMED          	B			YDSR	O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			GL	15	109CD	1195 				1009	357116	JC13A		ON RUN UP & PREPARING FOR FLIGHT, ELEVATOR DOWN AUTHORITY COULD NOT BE ACHIEVED UNDER NORMAL CONTROL PRESSURE.  PILOT RE	TURNED AND GROUNDED THE AIRCRAFT FOR MAINTENANCE.  INVESTIGATION IDENTIFIED BINDING TO BE LOCATED WITHIN THE PITCH TRIM 	CARTRIDGE ASSEMBLY PN 10681004.  DUE TO FOREIGN OBJECT INTRUSION INTO THE PITCH TRIM CARTRIDGE CUTOUT OPENING IN THE FOR	M OF A SINGLE DISCARDED COTTER PIN TAILING.  WHILE THE PRE-TAKEOFF PITCH TRIM TEST WAS BEING PERFORMED, AND THE ELEVATOR	 PLACED IN THE NOSE UP ATTITUDE, THE COTTER PIN LODGED.  THE AFT SPRING RETAINER IN THE PLACE NOT ALLOWING IT TO RETURN 	WHEN TRIM WAS COMMANDED DOWN.	1	H	7	1 	3O	3	O	NC	A00009CH	E1CE	5	C	P36EA	 
2001040900467	20010409	00467	SW  	2001	4	9	20010322CW013    	1	20010202	G	3340	2061531	CONNECTOR       			MOONEY	M20   	M20R        	5870225	SW  										TAIL STROBE	SHORTED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	91678	650  				290129				DURING ANNUAL INSPECTION TAIL STROBE LIGHT WAS INOPERATIVE,  ELECTRICAL ARCING ACROSS PINS IN CONNECTOR.  CONNECTOR WAS 	LOCATED AT THE PIVOT POINT OF THE TAIL. (TAIL TO FUS MOUNTING AREA), REPLACED BURNT CONNECTOR.  SYSTEM NO LONGER AS STRO	BE SNAP SOUND AT THIS LOCATION.				1	L	7	1 	3O			RT	2A3     					 
2001040900476	20010409	00476	EA  	2001	4	9	20010322CW014    	2	20010206	G	7414	M3548	ROTOR           	SLICK       	4370        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					MAGNETO	SHEARED         	B			UC2R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			GL	19	41487				98030708	2843179	L3628536A			PILOT REPORTED RT MAGNETO TO BE INOPERATIVE DURING GROUND RUNUP.  THE ASSIGNED TECHNICAN REMOVED THE RIGHT MAGNETO AND F	OUND THE CAM SLOT ON THE ROTOR SHAFT COMPLETELY SHEARED OFF.  CAUSE UNKNOWN POSSIBLE PART DEFECT.  THIS MAGNETO WAS INSP	ECTED EVERY 500 HOURS.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001040900477	20010409	00477	EU  	2001	4	9	20010322CW015    	1	20010216	G	6510	E230397911	SPLINE ADAPTER  			AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					GEARBOX	CRACKED         	B			Y3AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911NW	555  	555  			5082	CAEC20F			REMOVED ENGINE ASSEMBLY FOR OIL LEAKS.  REMOVED COMPRESSOR AND TURBINE FROM GEAR BOX TO REPLACE SEALS AND ORINGS.  INSPE	CTION OF SPLINE ADAPTOR FOUND CRACK RUNNING APPROX 340 DEGREES AROUND ADAPTOR.  TOTAL TIME ON PART IS 555.3 SINCE LAST O	VERHAUL AT WHICH TIME THE ADAPTOR WAS REPLACED.  CAUSE OF CRACK UNKNOWN AT THIS TIME.				1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001040900492	20010409	00492	EA  	2001	4	9	20010323CW001    	2	20010219	G	8530	AEL651024	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17		778  	778  			287916130	L1017539A			CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001040900078	20010409	00078	EA  	2001	4	9	20010323CW002    	2	20010126	G	7414	56LSC200	MAGNETO         			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	667CA		721  			1468166	L328148			ENGINE WAS REMOVED FOR TBO DUE WHEN INSPECTED MAGS FOR SERVICEABLILITY.  CAN HEAR CLICK INTERNALLY.  DETERMIND MAG TO BE	 UNSERVICEABLE.  PREVIOUS EXPERIENCE, SUSPECT LOOSE COIL DUE TO COIL WEAR AT POLAR SHOES.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001040900082	20010409	00082	CE  	2001	4	9	20010323CW004    	1	20010227	G	3252	1693800297	SHIMMY DAMPENER 			BEECH 	23    	B19         	1151215	CE  	LYC   	O320  	O320*       	41508	EA  					MLG	DEFECTIVE       	D				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			NM	02	2048A		106  			MB904				FOUND MULITUDE OF (AIR) POCKETS AND AIRCRAFT SHIMMIED EXCESSIVELY ON LANDING AND TAXI.   						1	L	7	1 	3O	3	O	 	A1CE    	E274				 
2001040900200	20010409	00200	CE  	2001	4	9	20010323CW005    	1	20010214	G	2820	63B22623	VALVE           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL DISTRIBUTIO	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	74GW	665  	665  			172S8143	62813751A			SERVO WAS CLEANED AND RECERTIFIED, WHICH PARTIALLY IMPROVED ENGINE PERFORMANCE.  ENGINE STILL BACKFIRED AT 1300-1500 RPM	.  CLEANED INJECTORS, WITH NO CHANGE.   REMOVED AND INSPECTED FUEL DISTRIBUTION VALVE.  FOUND SMALL AMOUNT OF LINT PARTI	ALLY  BLOCKING PASSAGES AT NR3 CYLINDER PORT.  CLEANED AND REASSEMBLED VALVE.  RUNUP AND OPS CHECKS NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001040900224	20010409	00224	CE  	2001	4	9	20010323CW011    	1	20010228	G	2510	C1650310101	CYLINDER        			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					PILOT SEAT	BROKEN          	H			VPFG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	63CE	1450 				18280357				SEAT LOCK CYLINDER PN C1650310101 ON PILOTS SEAT.  THE SHAFT ON CYLINDER BROKE WHERE IT GOES INTO THE FORK THAT ATTACHES	 TO SEAT BACK.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001040900505	20010409	00505	EU  	2001	4	9	20010323CW014    	1	20010215	G	5521	1090200059	RIB             			AGUSTA	A109  	A109A       	0260109	EU  	ALLSN 	250C  	250C28      	03013	GL  					LT ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	25RX	2526 	2526 			7220				DURING A WIRING REPAIR TO THE LEFT NAVIGATION LIGHT, A CRACK WAS FOUND UNDER THE VIBRATION DAMPER WEIGHT.  NO UNUSUAL VI	BRATION HAD BEEN REPORTED PRIOR TO THE CRACK BEING DETECTED.  A DAILY INSPECTION OF THE SYNCH ELEVATOR WOULD NOT HAVE RE	VEALED THIS CRACK, UNTIL THE VIBRATION WEIGHT SEPERATES FROM THE ATTACHING RIB.  RECOMMENDED AN INSPECTION BE INCLUDED I	N THE MFG INSP PROGRAM TO REMOVE THE SYNCH ELEVATOR TIP CAP AND VISUALLY INSPECT THIS AREA.			1	G	7	2 	3U	3	U	 	H7EU    	E1GL				 
2001040900282	20010409	00282	CE  	2001	4	9	20010323CW015    	1	20010215	G	5347	161102105	LOCK            			CESSNA	172   	172S        	2072439	CE  										PILOTS SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	949SP	431  				172S8145				PILOT REPORTED HIS SEAT LOCK PINS WOULD NOT RELEASE.  MAINTENANCE FOUND THE PILOTS SEAT LOCK CONTROL WAS BROKEN.  THIS S	AME CONTROL WAS REPLACED 431.0 HOURS PRIOR FOR THE SAME PROBLEM. BOTH CONTROL ASSEMBLYS HAVE PN 1611020-05 REPLACE CONTR	OL ASSEMBLY, OPERATIONAL CHECK SATISFACTORY.				1	H	7	1 	3O			NT	3A12    					 
2001040900283	20010409	00283	CE  	2001	4	9	20010323CW016    	1	20010124	G	2510	161102105	CONTROL UNIT    			CESSNA	172   	172S        	2072439	CE  										COPILOT SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	494SP	981  	981  			172S8035				CO-PILOTS SEAT LOCK CONTROL ASSEMBLY WOULD NOT RELEASE SEAT LOCK PIN.  MAINTENANCE FOUND THE RIGHT LOCK PIN CABLE BROKEN	.  REPLACED CONTROL ASSEMBLY PN161102105.  THIS HAS BEEN A REOCCURRING PROBLEM ON NEW SEATS.					1	H	7	1 	3O			NT	3A12    					 
2001040900293	20010409	00293	CE  	2001	4	9	20010323CW017    	1	20010108	G	8011	85009614	STARTER         			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	INOPERATIVE     	D				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SW	99	949SP	773  	773  			172S8145	L2812051A			PILOT ATTEMPTED ENGINE START.  FIRST FLIGHT OF THE DAY, STARTER WOULD NOT ROTATE.  MAINTENANCE FOUND STARTER HAD TWO TER	MINALS MELTED WHERE THEY ATTACH TO COMMUTATOR BRUSHES.  REPLACED STARTER, OPERATIONAL CHECKED SAT.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001040900306	20010409	00306	SO  	2001	4	9	20010323CW019    	2	20010223	G	8520	653129	CRANKSHAFT      								CONT  	O360  	IO360DB     	17025	SO  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		1863 					808785R			SUBJECT CRANKSHAFT HAS A 1.5 INCH CRACK IN NR6 ROD JOURNAL AT A 45 DEGREE ANGLE. ENGINE WAS REBUILT PRIOR TO MSB005C APP	LICABILITY.  CRANKSHAFT NOT APPLICABLE PER SN.										3	O			E1CE				 
2001032700425	20010327	00425	CE  	2001	3	27	20010326AP001    	1	20010323	G	7602	5038901223	CONTROL UNIT    			BEECH 	58    	58          	1152740	CE  										RIGHT	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	7MG	60   				TH513				PILOT REPORTED THAT THE CONTROL WAS HARD TO MOVE. FOUND IN THE LOGS THAT THE INSTALLER HAD LUBED THE CONTROL.  LUBRICATI	ON WILL GUM UP THE DRY LUBE AND MAKE IT HARD TO MOVE.					1	L	7	2 	3O			 	3A16    					 
2001040900055	20010409	00055	EU  	2001	4	9	20010326CW003    	1	20010130	G	5711	D21200380	SPAR CAP        			WSK   	M18A  	M18A        	       	EU  	WSK   	ASZ62 	ASZ62IRM18  	 	NE  					WING CENTER BOX	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	51809	4229 				1Z00915				DURING REPAIRS OF THE WING CENTER SECTION FOR CORROSION DAMAGE TO THE TRAILING EDGE SECTION OF THE WING AND DURING HIDDE	N DAMAGE INSPECTION, FOUND .1250 INCH DEEP CRACK IN THE FORWARD LOWER SPAR CAP.  THE CRACK RAN APPROX 24 INCHES INBOARD 	IN A SPANWISE DIRECTION FROM THE LEFT LOWER WING ATTACH FITTING.  CRACK PASSED THROUGH 2 BOLT HOLES IN THE SPAR THAT ATT	ACH THE LOWER WING ATTACH FITTING.  CRACK IN SPAR CAP WAS CONFIRMED BY NDI INSP USING EDDIE CURRENT, AND DYE PENETRANT M	ETHODS.  LOWER SPAR CAP WAS REPLACED WITH NEW PZL PART AND WING CENTER SECTION WAS RETURNED TO SERVICE.  RECOMMEDN A CLO	SE INSPECTIONOF ALL WING ATTACH FITTINGS AND SPAR CAPS DURING ANY INSPECTION ON THIS AC.	1	L	7	1 	3O	3	R	NC	A47EU   	E10NE				 
2001040900059	20010409	00059	SW  	2001	4	9	20010326CW005    	1	20010326	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	03	70824					7EC337				DURING ANNUAL INSPECTION, FOUND COMPRESSION CRACKS ON THE RIGHT WING REAR SPAR AT TOP LOCATION ON TOP SIDE OF SPAR.  THI	S COMPRESSION CRACK WAS HIDDEN UNDER OLD SPAR VARNISH AND WOULD HAVE BEEN MISSED IF TOP INSPECTION HOLES WERE NOT INSTAL	LED.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2001040900395	20010409	00395	CE  	2001	4	9	20010327CW009    	1	20010108	G	2842		TRANSMITTER     			CESSNA	150   	150A        	2071804	CE  	CONT  	O200  	O200A       	17020	SO  					LT FUEL TANK	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	8067F	4757 				15064167	661557A			AC LANDED SHORT OF RUNWAY AFTER ENGINE QUIT.  AC HAD SUBSTANTIAL DAMAGE NO INJURIES.  DETERMINED AC RAN OUT OF FUEL DUE 	TO FAULTY FUEL GUAGE.  REMVD FUEL QUANTITY TRANSMITTER TO FUNCTION TEST.  FOUND TWO RUB SPOTS ON FLOAT, REASON FOR CONTA	CT BETWEEN FLOAT AND TANK APPEARS TO BE MISALIGNMENT OF FLOAT ARM.  FOUND CONTACTOR DIMPLE HAD WORN THROUGH.  CAUSE OF F	UEL GUAGE TO STICK AT HALF TANK INDICATED COMBINATION OF FLOAT CONTACTING INSIDE OF FUEL TANK AND CONTACTOR BEING WORN T	HROUGH.  RESEARCHING LOG FOUND SENDING UNIT HAD BEEN REMOVED 1 YEAR PRIOR & NEW GASKET INSTALLED.   RECOMMEND FOR RECURR	ENCE PREVENTION:  KNOWING SERVICE LIFE OF TRANSMITTERS & VERIFICATION OF NO INTERFERENCE OF FLOAT & INSIDE OF FUEL TANK.	1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900407	20010409	00407	CE  	2001	4	9	20010327CW010    	1	20010129	G	7910	047051	ENGINE          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	NACELLE	DEFECTIVE       	H				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	11	96118					18263409	464601	744427		FACTORY NEW ENGINE GROUND TESTED ONLY.  PROPELLER WILL NOT CYCLE.  HAVE RECHECKED PROPELLER AND GOVERNOR.  PROBLEM APPEA	RS TO BE ENGINE OIL PRESSURE,  INSUFFICIENT TO CYCLE PROPELLER.  WARRANTY RETURN.					1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2001040900482	20010409	00482	SO  	2001	4	9	20010327CW011    	1	20010208	G	8011		BRACKET         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					STARTER	UNSECURE        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	962PA					2844022	L2858251A			THE FORWARD  1 FT STARTER ATTACH BOLT WHICH HOLDS THE ALTERNATOR BRACELET IS STRIPPING THE CASE OUT DUE TO VIBRATION.  H	ELICOILS ARE BEING INSTLLED BUT ARE NOT HOLDING.  A SHELF NEEDS TO BE CUT INTO THE CASE TO SEAT A BOLT HEAD SO A NUT AND	 LOCK WASHER CAN BE INSTALLED.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001040900537	20010409	00537	NE  	2001	4	9	20010328CW001    	2	20010130	G	7322	5704931	CARBURETOR      								PWA   	R985  	R985*       	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	05						489				ENGINE FLOODED WITH FUEL AND DIED.  FUEL LEAKING FROM CARBURETOR WHEN FUEL SELECTOR VALVE TURNED TO  ON.											3	R			5E1	5	C	P28EA	 
2001040900542	20010409	00542	EU  	2001	4	9	20010328CW002    	1	20010125	G	3213	AIR131368	PISTON          			JETAIR	JETSTM	JETSTM4101  	1500501	EU  										MLG STRUT	DAMAGED         	D			FW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										MLG STRUT RECEIVED WITH INTERNAL DAMAGE.  UNIT RECEIVED W/O 5606 OIL BUT NO APPARENT DISASSEMBLY OF THE GEAR HAD OCCURED	.  (GLAND NUT AND FILL PLUGS INTACT).  INTERNAL PARTS WERE DRY.  THE FLUTTER VALVE WAS FOUND LOOSE IN THE TOP OF THE CYL	INDER WITH THE UPPER CARRIER BEARING HELD IN PLACE BY THE CYLINDER LINER.  THE CYLINDER LINER HAD TO BE MACHINED TO BE R	EMOVED FROM THE CYLINDER.  THE UNIT WAS SHIPPED FOR OVERHAUL AFTER THE AXLE WAS OVERHEATED WITH A WHEEL BEARING FAILURE.			2	L	7	2 	4T			RT	A41NM   					 
2001040900496	20010409	00496	CE  	2001	4	9	20010328CW006    	1	20010222	G	5620	10243016215	WINDOW          			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					CABIN	FAILED          	B			MQ3R	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			WP	11	40PG	2666 				TJ309				AIRCRAFT HAD BEEN CRUISING AT FL240 FOR 1 HOUR PLUS TEMP-40 DEGREE.  ON DESCENT OUT OF FL200 THE LEFT MID CABIN WINDOW B	LEW OUT OF AIRCRAFT, CABIN DEPRESSURIZATION.  PILOT CONTINUED DESCENT TO LOWER ALTITUDE AND LANDED WITHOUT FURTHER INCID	ENT.  WINDOWS WEW INSPECTED IN NOVEMBER, 2000 AT 2636.9 HRS. AND WERE FOUND TO BE IN GOOD CONDITION.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001040900375	20010409	00375	EU  	2001	4	9	20010328CW012    	1	20010308	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					HYD SYSTEM	SEPARATED       	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	19	57717	237  				1334	L43402CE			HYDRAULIC BELT FAILED AT BOND LINE DURING FLIGHT WHICH LEAD TO PRECAUTIONARY LANDING.  BELT CONDITION AND TENSION APPEAR	ED NORMAL DURING PREFLIGHT.					1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2001040900302	20010409	00302	NE  	2001	4	9	20010328CW013    	1	20010228	G	6510	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					TAIL ROTOR	DELAMINATED     	D			MV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	38	2436 				760087				ON PRE-FLIGHT INSPECTION FOUND AN AREA OF DELAMINATION AT TAIL ROTOR BLADE STATION 27.00, 4.5 INCHES FROM LEADING EDGE O	F TAIL ROTOR BLADE.  ITS SIZE ABOUT .7500 INCH.  BLADE REMOVED AND SENT FOR REPAIR.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001040900245	20010409	00245	EA  	2001	4	9	20010402CW001    	2	20010205	G	7414	S6LN1258	MAGNETO         			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	IO540*      	41532	EA  					RT ENGINE	BROKEN          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	01	858CH	124  				608265006				RT ENGINE, LT MAGNETO POINT CAM FOLLOWER ARM  BROKE AFTER 124.9 HOURS USE. MAGNETO OVERHAULED. INSTALLED 6-2-99 AT 2180.	1 HOURS. FAILED AND REMOVED AT 2305.0 HOURS.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2001040900334	20010409	00334	CE  	2001	4	9	20010403CW004    	1	20010308	G	2435	23080005	STARTER GEN     			RAYTHN	DH125 	HAWKER800XP 	       	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					LT ENGINE	DESTROYED       	H				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	01	9292X	1081 	563  			258315				AT FLIGHT LEVAL 390, CREW FELT A VIBRATION IN THE AIRCRAFT, AIRCRAFT DIVERTED.  MAINTENANCE FOUND LEFT ENGINE STARTER GE	NERATOR DESTROYED.  GENERATOR WAS REPLACED, GROUND CHECK NORMAL.  THE GENERATOR CARRIES A TBO OF 1000 HOURS.  THIS TIME 	IS RARELY ACHIEVED.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001040900336	20010409	00336	SO  	2001	4	9	20010403CW006    	1	20010131	G	2432	455211	CONTACTOR       			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360*    	17025	SO  					BATTERY	DAMAGED         	B			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	292CA	543  				3449017				BATTERY MASTER CONTACTOR INTERMITTANT. REMOVED AND INSPECTED CONTACTOR.  FOUND BOTTOM COVER FULL OF WATER AND CONTACTS R	USTED.  INSTALLED NEW CONTACTOR, OPERATIONAL CHECK SATISFACTORY.  INSPECTED AFT BAGGAGE DOOR SEAL AND SURROUNDING SKIN S	EAMS FOR SOURCE OF WATER LEAK ONTO RELAY SHELF LOCATED BENEATH BAGGAGE FLOOR.  NO LEAKS NOTED, CARPET AND INTERIOR DRY. 	 SUSPECT GPU PLUG DOOR JUST FORWARD OF RELAY SHELF TO BE PROBABLE CAUSE FOR WATER INFILTERATION.			1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001040900338	20010409	00338	SO  	2001	4	9	20010403CW008    	1	20010315	G	3230	492303	VALVE           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1D     	41514	EA  					MLG	MALFUNCTIONED   	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	15	243AT	100  	100  			4496042				PILOTS REPORTED THAT LANDING GEAR WOULD NOT EXTEND, THEY THEN PULLED THE EMERGENCY EXTENSION VALVE AND THE GEAR LOWERED 	WITH THREE GREEN.  UPON INSPECTION FOUND THE EMERGENCY GEAR EXTENSION VALVE TO BE,  SPRAYING HYDRAULIC FLUID IN NOSE BEL	OW HEATER.  THIS IN TURN DEPLENISHED ALL FLUID IN RESERVOIR AND BURNED UP HYDRAULIC POWERPAK.  SUSPECT INCORRECT ORING I	N VALVE.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001040900343	20010409	00343	SO  	2001	4	9	20010403CW012    	2	20010224	G	8520		ROD             			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	TSIO520H    	17040	SO  					RT ENGINE	DEPARTED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	5988M					421B0231				AIRCRAFT ARRIVED WITH RIGHT ENGINE OIL LEAK.  FOUND OIL LINE TO BE LEAKING.  REPAIRED OIL LINE AND SERVICED BACK UP WITH	 OIL.  ENGINE WAS RERUN AND A ROD CAME LOOSE AND PENETRATED THE CRANKCASE.  NO OTHER INFORMATION WAS RECEIVED, EXCEPT TH	AT THE ENGINE RAN OUT OF OIL DURING FLIGHT, WHICH PROBABLY CAUSED THE ROD TO SEPERATE.  AN OVERHAULED ENGINE  WAS RECEIV	ED AND INSTALLED.			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001040900344	20010409	00344	SO  	2001	4	9	20010403CW013    	1	20010222	G	3246	16105800	WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	63954	3180 				277854085				PILOT NOTICED RIGHT BRAKE GRABING WHILE TAXIING OUT FOR DEPARTURE.  AFTER STOPPING TO INVESTIGATE, NOTICED A BULGE ON TH	E INSIDE RIGHT WHEEL HALF.  WHILE TAXIING BACK TO THE HANGER, THE BEAD AREA LET GO AND THE TIRE DEFLATED.  AN 8 INCH PIE	CE BROKE OFF AT THE BEAD.  THE PILOT STATED THAT A RATHER HARD LANDING HAD OCCURED JUST BEFOR THIS FLIGHT BUT DID NOT CA	USE ANY OTHER DAMAGE.			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001040900345	20010409	00345	CE  	2001	4	9	20010403CW014    	1	20010220	G	5330	10704	SKIN            			RKWELL	NA265 	NA26565     	7630107	CE  										FUSELAGE	CRACKED         	B			UVVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	74VC	1500 				46517				UPON REMOVAL OF INOPERABLE GPS ANTENNA FROM AIRCRAFT, THE UPPER COVER SEPARATED FROM THE BASE OF ANTENNA, EXPOSING THE I	NSIDE.  THE INSIDE OF THE ANTENNA WAS FULL OF RUST FROM BASE.  THE MOUNTING SURFACE OF THE ANTENNA WAS ALSO RUSTED, CAUS	ING THE AIRCRAFT UPPER SOCK SKIN TO CORRODE.  SUSPECT OVER TORQUE OF MOUNTING SCREWS CAUSED THE COVER TO CRACK, ALLOWING	 MOISTURE TO ENTER AND RUST ANTENNA FROM INSIDE OUT.  RECOMMEND INSPECTING OF THESE TYPE ANTENNAS UPON INSTALLATION, TO 	ASSURE THAT SCREWS ARE NOT OVER TORQUED AND HAD CRACKS.		2	L	7	2 	4J			 	A2WE    					 
2001040900348	20010409	00348	CE  	2001	4	9	20010403CW016    	1	20010226	G	5711		SPAR CAP        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3232X	10054				15064632				CORROSION FOUND EXFOLIATING SPAR CAP OR RIGHT WING HEAVY CORROSION ON UPPER CABIN CARRY THRU STRUCTURE.  VERTICAL STABIL	IZER SKIN PILLOWED AND RIVETS POPPED.  FOUND 15 RIVET HEADS PULLED THRU SKIN ON CANTED BULKHEAD AT FUSLAGE STATION 20.5 	BOTTOM FUSELAGE. AIRCRAFT IS BEYOND ECONOMICAL REPAIR.  A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18 YEARS IN FLORIDA	 AND REMAINDER ON EAST COAST.  CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORRROSION BY THE SELLER	.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900349	20010409	00349	CE  	2001	4	9	20010403CW017    	1	20010226	G	5711		SPAR            			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					RT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3232X	10054				15064632				CORROSION FOUND EXFOLIATING (1) SPAR CUP ON RIGHT WING HEAVY CORROSION ON UPPER CABIN (2) CARRY THRU STRUCTURE.  (3) VER	TICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED.  FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSELA	GE STATION 20.5 BOTTOM FUSELAGE.  AIRCRAFT IS BEYOND ECONOMICAL REPAIR.  A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18	 YEARS IN FLORIDA AND REMAINDER ON EAST COAST.  CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD ON CORROSI	ON, BY THE SELLERS.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900350	20010409	00350	CE  	2001	4	9	20010403CW018    	1	20010226	G	5532		SKIN            			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					VERTICAL STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3232X	10054				15064632				CORROSION FOUND EXFOLIATING (1) SPAR CAP ON RIGHT WING HEAVY CORROSION ON (2) UPPER CABIN CARRY THRU STRUCTURE.  (3) VER	TICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED.  FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSELA	GE STATION 20.5 BOTTOM FUSELAGE.  AIRCRAFT IS BEYOND ECONOMICAL REPAIR.  A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18	 YEARS IN FLORIDA AND REMAINDER ON EAST COAST.  CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORROSI	ON BY THE SELLERS.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900203	20010409	00203	CE  	2001	4	9	20010403CW019    	1	20010226	G	5312		BULKHEAD        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					FUSELAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3232X	10054				15064632				CORROSION FOUND EXFOLIATING (1) SPAR CAP ON RIGHT WING HEAVY CORROSION ON  (2) UPPER CABIN CARRY THRU STRUCTURE.  (3) VE	RTICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED.  FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSEL	AGE STATION 20.5 BOTTOM FUSELAGE.  AIRCRAFT IS BEYOND ECONOMICAL REPAIR.  A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 1	8 YEARS IN FLORIDA AND REMAINDER ON EAST COAST.  CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORROS	ION BY THE SELLERS.		1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040900358	20010409	00358	CE  	2001	4	9	20010404CW001    	1	20010206	G	2720	6565007188	CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  										COCKPIT	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	829CB	1108 				5500829				DURING PHASE 5 INSPECTION, PILOTS RIGHT FORWARD RUDDER CABLE FOUND INCORRECTLY ROUTED THROUGH ACCESS HOLE IN WEB INSTEAD	 OF CABLE GUIDE BELOW HOLE.  CABLE HAD CHAFED INTO LOWER EDGE OF HOLE IN WEB AND DOUBLER.  DOUBLER REPLACED AND WEB REPA	IRED, CABLE REPLACED.				1	L	7	2 	4F			 	A22CE   					 
2001040900359	20010409	00359	SO  	2001	4	9	20010404CW002    	1	20010228	G	5521	5423224	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	350MN	3073 				318152042				INSPECTION FOUND BOTH ELEVATOR SPARS CRACKED.  INITIAL INSPECTION ADVISED AT 2500 HOURS TT. THIS WAS FIRST INSPECTION NO	TE: TOTAL TIME 3073.					1	L	7	2 	3O			 	A20SO   					 
2001040900328	20010409	00328	EA  	2001	4	9	20010404CW003    	2	20010219	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4381L	834  				288516016	L1341139A			CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS, FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001040900329	20010409	00329	EA  	2001	4	9	20010404CW004    	2	20010301	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	800KA	1013 				288416019	L810539A			CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001040900577	20010409	00577	SO  	2001	4	9	20010405CW001    	2	20010405	G	8530	646778	ROD CAP         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					CYLINDER 2	FAILED          	B			CGHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	827TS	2206 	895  			TH836	267167R			DURING CRUISE FLT RT ENG NR 2 CYL PISTON CONN ROD BROKE LOOSE FROM CRANKSHAFT, PENETRATED UPPER CRANKCASE.  NR2 CYL SEP 	FROM ENGINE,  RESTED IN COWLING.  THE FORCE OF CONNECTING ROD COMING THROUGH THE CASE BROKE LEFT MAGNETO OFF ITS BASE AN	D PUNCHED A HOLE IN THE UPPER COWL.  PILOT SECURED ENGINE AND FLEW TO A MAINTENANCE BASE.  UPON REMOVING PIECES AND LAYI	NG THEM OUT ON  TABLE IT WAS NOTICED  ONE OF THE CONNECTING ROD CAP BOLTS DID NOT HAVE THE REMAINS OF A COTTER PIN IN EI	THER OF THE SAFETING HOLES.  BOLT HEAD HAD BEEN BROKEN OFF(SUSPECTED FROM THE HAMMERING WHEN THE NUT WAS LOOSE).  IT WAS	 ALSO NOTED THAT THREADS OF SAME BOLT, NOT AS DAMAGED AS BOLT ON OTHER SIDE , INDICATING  IT UNSCREWED ITSELF.	1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001040900451	20010409	00451	NM  	2001	4	9	20010406AP001    	1	20010328	G	2510	600N6525501	SEAT BELT       			DOUG  	600N  	600N        	3027377	NM  										COCKPIT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	957SD					RN011				THE SEAT RESTRAINT SYSTEM ROTARY BUCKLE ASSEMBLY FAILED WHEN THE SCREWS PULLED THROUGH THE BACK PLATE.  OTHER SAME TYPE 	ASSEMBLIES INSPECTED FOUND CRACKED BACK PLATES IN 5 OF THE 6 INSPECTED.					1	G	7	1 	3U			NC	H3WE    					 
2001040900170	20010409	00170	NE  	2001	4	9	20010406CW001    	2	20010201	G	7314	3031632B	PUMP            			CESSNA	500   	550         	2076604	CE  	PWA   	JT8   	JT8D15      	52051	NE  					RT ENGINE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	15	2GG	1848 				5500286	PCE70020			METAL FOUND IN FUEL PUMP FILTER.  UPON DISASSEMBLY OF FUEL CONTROL / FUEL PUMP FOR REPLACEMENT OF FUEL PUMP FOUND BLUE D	YE BETWEEN FUEL PUMP AND FUEL CONTROL INDICATING FUEL CONTROL BEARING WASHOUT DUE TO FUEL PUMP SHAFT SEAL LEAKAGE. THIS 	REQUIRED SENDING FUEL CONTROL OUT FOR REPAIR.				1	L	7	2 	4F	4	F	 	A22CE   	E2EA				 
2001040900092	20010409	00092	NE  	2001	4	9	20010409AP001    	1	20010205	G	2820	26700115	ADAPTER         			CONAER	LA4   	LA4200      	5110310	NE  										FUEL SYSTEM	CRACKED         	D				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			SO	15	9WA	1455 	0    			520				FUEL SMELL IN CABIN, FUEL STAIN LEFT SIDE OF INTERNAL FUSELAGE AT AND BELOW ADAPTER.  VISUALLY INSPECTED PART AND FOUND 	CRACK AT SUMP DRAIN VALVE FITTING.  FUEL LEAKED INTO AND WAS STANDING IN THE HULL.  LEAK DETECTED DURING REPAIR OF STRUC	TURE IN THAT AREA.				1	H	7	1 	3O			 	1A13    					 
2001040900386	20010409	00386	GL  	2001	4	9	20010409AP003    	3	20010131	G	6114	HCC2YR2CLEUF	HUB             	HARTZL      		PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER ASSY	CRACKED         	B				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99		3592 	579  		AU6092			AU6092		DURING PREFIGHT PILOT NOTICED GREASE ON BLADE.  MECHANIC REMOVED SPINNER AND FOUND CRACK ON RADIUS OF THE HUB.						1	L	7	2 	3O			 	A19S0   		5	C	P920	 
2001040900387	20010409	00387	GL  	2001	4	9	20010409AP004    	3	20010131	G	6114	HCC2YR2	HUB             	HARTZL      		PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER ASSY	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		3592 	579  		AU6092			AU6092		DURING PREFIGHT PILOT NOTICED GREASE ON BLADE.  MECHANIC REMOVED SPINNER AND FOUND CRACK ON RADIUS OF THE  HUB.						1	L	7	2 	3O			 	A19S0   		5	C	P920	 
2001040900168	20010409	00168	CE  	2001	4	9	20010409CW001    	1	20010226	G	5320	05132826	WEB             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	733JC					17268322				CORROSION WAS FOUND ON RIGHT WEB AND STRINGER.  REPLACED THESE PARTS LAST YEAR FOR SAME REASON.  THE REPLACED HAD BEEN P	AINTED WITH EXPOXY PRIMER PRIOR TO INSTALLATION.  IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIME HAD BEEN IN 	DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO.  SUSPECT FABRIC WAS SPRAYED WITH SOME FORM OF FIRE RETA	RDENT THAT IS CORROSIVE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040900169	20010409	00169	CE  	2001	4	9	20010409CW002    	1	20010226	G	5313	05120376	STRINGER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	733JC					17268322				CORROSION WAS FOUND ON RIGHT WEB AND STRINGERS.  REPLACED THESE PARTS LAST YEAR FOR SAME REASON.  THE REPLACED PARTS HAD	 BEEN PAINTED WITH EPOXY PRIMER PRIOR TO INSTALLATION.  IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIMES HAD B	EEN IN DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO.  SUSPECTS FABRIC WAS SPRAYED WITH SOME FORM OF F	IRE RETARDENT THAT IS CORROSIVE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040900171	20010409	00171	CE  	2001	4	9	20010409CW003    	1	20010226	G	5313	05120374	STRINGER        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	733JC					17268322				CORROSION WAS FOUND ON RIGHT WEB AND STRINGERS.  REPLACED THESE PARTS LAST YEAR FOR SAME REASON.  THE REPLACED PARTS HAD	 BEEN PAINTED WITH EPOXY PRIMER PRIOR TO INSTALLATION.  IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIMES HAD B	EEN IN DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO.   SUSPECT FABRIC WAS SPRAYED WITH SOME FORM OF F	IRE RETARDANT THAT IS CORROSIVE.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040900324	20010409	00324	WP  	2001	4	9	20010409CW010    	2	20010228	G	7250	30606901	BLADE           								GARRTT	TFE731	TFE7315R    	01518	WP  					LP TURBINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		6823 	4994 				91174			3RD LPT BLADE SEPARATED AT MIDSPAN CAUSING DAMAGE BEYOND LIMITS TO ALL 3RD LPT BLADES. ALSO DAMAGED THE EXHAUST NOZZLE A	ND 3RD LPT NOZZLE BEYOND LIMITS.										4	F			E6WE				 
2001040900330	20010409	00330	SO  	2001	4	9	20010409CW011    	2	20010409	G	8530	A20TK99	VALVE GUIDE     								CONT  	O520  	IO520F      	17032	SO  					CYLINDER	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		500  								RECEIVED 2 EA CYLINDERS FOR OVERHAUL UPON DISMANTLING WE FOUND BOTH EXHAUST VALVES STUCK .  WE HAD TO DRIVE THEM OUT WIT	H A DRIFT.   SN NR 15130 EXHAUST GUIDE SIZE   BOTTOM .433  TOP  .4365    SN NR  15131 EXHAUST GUIDE SIZE  BOTTOM  .433  	  TOP   .437									3	O			E5CE				 
2001040900494	20010409	00494	SO  	2001	4	9	20010409CW012    	2	20010409	G	8530	A22EK99	VALVE GUIDE     								CONT  	O520  	IO520F      	17032	SO  					CYLINDER	STUCK           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		500  								RECEIVED 2 EA CYLINDERS FOR OVERHAUL.  UPON DISMANTLING, WE FOUND BOTH EXHAUST VALVES STUCK.  WE HAD TO DRIVE THEM OUT W	ITH A DRIFT.  SN 15130  EXHAUST GUIDE SIZE  BOTTOM   .433   TOP   .4365        SN 15131   EXHAUST GUIDE SIZE        BOTT	OM   . 433   TOP  .437									3	O			E5CE				 
2001041000275	20010410	00275	EA  	2001	4	10	20010409CW016    	2	20010306	G	8530	L2744051A	CYLINDER        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	CRACKED         	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	07	441CA	2010 				17280441	L2744051			AIRCRAFT WAS 4 MILES FROM AIRPORT WHEN A LOUD BANG WAS HEARD AND THE ENGINE STARTED VIBRATING AND MISSING.  PILOT PULLED	 POWER BACK TO IDLE AND LANDED SAFELY AT AIRPORT.  INSPECTED ENGINE AND FOUND NR 3 ENGINE CYLINDER WITH A CRACK, HALF AR	OUND CYLINDER.  THIS CRACK STARTED AT THE 4TH FIN BACK FROM THE TOP SPARK PLUG HOLE AND PARRELLED THE FIN.  DUE TO FREQU	ENT USE ENGINE TBO IS 2200 HOURS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001050200040	20010502	00040	CE  	2001	5	2	20010410AP001    	1	20010216	G	2820	43362	NEEDLE VALVE    	PREAIR      	MA45        	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  					CARBURETOR	SEPARATED       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	99	3087Q	52   	52   		7509409	18258087	815939R			OWNER REPORTED ROUGH IDLE AFTER LANDING, ASSUMED THE PROBLEM WAS RELATED TO CARB ICE ON THE GROUND.  AIRCRAFT WAS BROUGH	T IN FOR ANNUAL INSPECTION AND DURING PRE INSPECTION RUN UP CONFIRMED ROUGH IDLE,  BUT SMOOTHED OUT WHEN CARB HEAT WAS A	PPLIED.  DURING INSPECTION FOUND THE CARBURATOR IDLE MIXTURE SCREW, SPRING, AND WASHER HAD FALLEN OUT.  THE AIRCRAFT IS 	BASED AT A HIGH ALTITUDE (5883 FT) AIRPORT AND TO OBTAIN CORRECT IDLE MIXTURE SETTING THE IDLE MIXTURE SCREW HAS LIGHT C	ONTACT WITH SETTING SPRING. CARBURETOR WAS SUPPLIED WITH FACTORY REMANUFACTURED ENGINE 52.04 HOURS AGO.		1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001050200042	20010502	00042	CE  	2001	5	2	20010410AP002    	1	20010221	G	5315	12134083	FLOORBEAM       			CESSNA	210   	2105        	2073404	CE  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1825Z	3783 				2050025				DURING ANNUAL INSPECTION DISCOVERED SEVERE INTERGRANULAR CORROSION ON LEFT 4 INCHES OF ANGLE.  CORROSION OCCURED PRIMARI	LY WHERE  .25 IN. HI-SHEAR RIVITS ATTACH ANGLE TO BULKHEAD AND WING LIFT STRUT ATTACH FITTING.  ANGLE WAS LESS THAN HALF	 ORIGINAL THICKNESS WHEN REMOVED.  LIGHT SURFACE CORROSION NOTED IN ENTIRE AREA.  THIS AREA IS VERY CRITICAL AND SHOULD 	BE INSPECTED VERY THOROUGHLY DURING ALL INPECTIONS.FLOORBOARDS REMOVED AND NEW PART INSTALLED.			1	H	7	1 	3O			 	3A21    					 
2001050200043	20010502	00043	CE  	2001	5	2	20010410AP003    	1	20010222	G	3010		BOOT            			CESSNA	441   	441         	2076020	CE  										RT WING	LEAKING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	835MA					4410343				NOTED FUEL LEAK FROM BEHIND RT WING DE-ICE BOOT.  AFTER PEELING BOOT BACK TO RESEARCH LEAK, NOTED NUMEROUS AREAS OF HEAV	Y CORROSION.  AIRCRAFT WAS FERRIED TO FACILITY FOR REPLACEMENT OF LEADING EDGE ASSEMBLY.					1	L	7	2 	3T			RT	A28CE   					 
2001041700148	20010417	00148	CE  	2001	4	17	20010410AP004    	1	20010222	G	5511	073261110	RIB             			CESSNA	182   	R182        	2072734	CE  										HORIZONTAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3621C	2249 				0280				DURING AN ANNUAL INSPECTION FOUND THE RT HORIZONTAL STABILIZER INBOARD LEADING EDGE RIB CRACKED.  DETECTED CRACK DUE TO 	EXCESSIVE SKIN PLAY AT RIB AND A WORKING FASTNER.  CONFIRMED CRACK USING A BORESCOPE. DISASSEMBLED THE EMPENNAGE ENOUGH 	TO FACILITATE RIB REPLACEMENT.				1	H	7	1 	3O			RT	3A13    					 
2001050200044	20010502	00044	CE  	2001	5	2	20010410AP005    	1	20010222	G	5730		SKIN            			CESSNA	441   	441         	2076020	CE  										RT WING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	835MA	3320 	3320 			4410343				FOUND FUEL LEAK COMING FROM BEHIND THE RT WING DE-ICE BOOT.  AFTER PEELING BACK BOOT TO LOCATE LEAK, NOTED SEVERAL AREAS	 OF HEAVY CORROSION ON LEADING EDGE.  FERRIED AIRCRAFT TO FACILITY FOR LEADING EDGE REPLACEMENT.  SUSPECT DE-ICE BOOT WA	S INSTALLED USING IMPROPER PRACTICES ALLOWING MOISTURE TO GET IN BEHIND BOOT AND BECOME TRAPPED.				1	L	7	2 	3T			RT	A28CE   					 
2001050200045	20010502	00045	GL  	2001	5	2	20010410AP006    	1	20010223	G	5720		CUFF            			HOWARD	DGA15 	DGA15P      	4690506	GL  										RT WING STRUT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	36259					1770				THE STAINLESS STEEL CUFFS ARE ONLY ON THE RT WING STUTS AND THEY PROVIDE PROTECTION FOR THE STRUT WHEN OPENING/CLOSING T	HE CABIN DOOR. THESE CUFFS ARE NOT BONDED TO THE WING STRUT BUT ARE WRAPPED AROUND THE STRUT AND CRIMPED IN PLACE. WHEN 	THE CUFFS WERE REMOVED FOR NON-ROUTINE INSPECTION IT WAS FOUND THAT THE WING STRUT WAS SEVERLY RUSTED AND PITTED IN THE 	AREA UNDER THE CUFFS.			1	H	7	1 	3R				A717    					 
2001041900001	20010419	00001	NE  	2001	4	19	20010410AP007    	1	20010221	G	3246	5003929	WHEEL           			SKRSKY	S70   	S70         	8143001	NE  										MLG	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			sw	99										WHEEL ASSY SENT TO A CERTIFICATED REPAIR STATION FOR EDDY CURRENT INSPECTION.  AFTER BUILD-UP,  WHEEL AND TIRE ASSY WAS 	INFLATED TO 140 PSI AND LEFT FOR 12-24 HOUR LEAK CHECK.  AFTER 36 HOURS TIRE PRESSURE WAS FOUND TO BE 30-40 PSI,  AND A 	DAMAGED O-RING WAS SUSPECTED.  UPON APPLYING 125 PSI,  NITROGEN WAS HEARD ESCAPING.  APPLYING LEAK DETECTOR REVEALED A C	RACK AT LOWER PORTION OF INBOARD WHEEL HALF RETAINING BOLT HOLE.			2	G	7	2 	4U			 	H2NE    					 
2001050200046	20010502	00046	EA  	2001	5	2	20010410AP008    	2	20010302	G	8530		STUD            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 3 CYLINDER	BROKEN          	D				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			SW	99	1558E		1349 			17271046	L109476			PILOT REPORTED BAD VIBRATION ON FINAL APPROACH. UPON INSPECTION IT WAS DISCOVERED THAT THREE OF FOUR  OF THE TOP CYLINDE	R HOLD DOWN STUDS ON THE NR 3 CYLINDER HAD BROKEN OFF AT THE ENGINE CASE. NO INTERNAL DAMAGE WAS FOUND. CAUSE UNKNOWN.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001050200047	20010502	00047	CE  	2001	5	2	20010410AP009    	1	20010305	G	2750	45A620911	BELLCRANK       			BEECH 	MU300 	400BEECH    	       	CE  										TE FLAPS	CORRODED        	F				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	406TS	3661 				RJ6				DURING ''A'' & ''B'' INSPECTION FOUND THAT BOTH INBOARD AND OUTBOARD FLAP BELL CRANKS ON BOTH WINGS HAD EXCCESSIVE PLAY.	 THIS CONDITION COULD BE OBSERVED WITH FULL CABLE TENSION WITH FLAPS IN FULL DOWN POSITION. WHEN EACH BELLCRANK WAS  DIS	SASSEMBLED FOUND BOTH BEARINGS, BOLT, STEEL INSERT AND ALUMINUM BELL CRANK TO HAVE HEAVY CORROSION. BOTH OUTBOARD BELL C	RANKS HAD TO BE REPLACED.			2	H	7	2 	4F			RT	A16SW   					 
2001050200048	20010502	00048	SO  	2001	5	2	20010410AP010    	2	20010308	G	8530		PISTON          								CONT  	O550  	TSIOL550B   	 	SO  					NR 4 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	972	544  	544  				8020350			ON A FLIGHT FROM EL PASO TO 5T6 THE OIL PRESSURE STARTED TO FLUCTUATE , ON INSPECTION THE OIL FILTER WAS FULL OF ALUM. W	HEN THE ENGINE WAS REMOVED & DISMANTLED NR 4 CYLINDER PISTON SKIRT WAS BROKEN OFF THERE WERE NO SIGHS OF ANY PARTS OUT O	F ALLIGIMENT OR STUCK PISTON PIN THE CON. ROD NOT BENT THE CYL NO SIGNS OF OVER HEAT OR SUPPER COOLED THE RINGS NORMAL W	EAR.								3	O			E4SO				 
2001050200049	20010502	00049	CE  	2001	5	2	20010410AP011    	1	20010309	G	3233	20152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5169V	7298 				172RG0458				DURING ACCOMPLISHMENT OF CESSNA SEB 01-2, THE RT MAIN GEAR ACTUATOR WAS FOUND TO BE CRACKED IN THE SADDLE AREA AS OUTLIN	ED IN THE SEB.  REMOVED THE ACTUATOR FROM SERVICE AND INSTALLED A NEW ASSEMBLY.					1	H	7	1 	3O			 	3A17    					 
2001050200056	20010502	00056	CE  	2001	5	2	20010410AP012    	1	20010316	G	2510	051421515	SEAT BACK       			CESSNA	172   	172S        	2072439	CE  										COPILOTS SEAT	BENT            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	789EP	1007 				172S8135				DURING PHASE 1 MAINTENANCE INSPECTION, CO-PILOTS SEAT BACK WAS RECLINED APPROXIMATELY 4 INCHES FROM FULL UPRIGHT POSITIO	N.  FOUND SEAT BACK FRAME P/N 0514215-15 WAS BENT AT THE TOP OF THE RIGHT ATTACH FORGING.					1	H	7	1 	3O			NT	3A12    					 
2001050200057	20010502	00057	EA  	2001	5	2	20010410AP013    	2	20010316	G	7322		SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL FLOW	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	949SP					172S8145	L2812051A			ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS.  FUEL FLOW BELOW 1700 RPM IS TOO HIGH. IDLE SPEED AND MIXTURE C	AN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION.  FUEL SERVO REMOVED, SENT FOR REPAIRS.  MAJOR RE	PAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00.  REINSTALLED FUEL SERVO, ADJUSTED	 IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001050200058	20010502	00058	EA  	2001	5	2	20010410AP014    	2	20010316	G	7322	25765362	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	567JW	610  				172S8187	L2822651A			ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS.  FUEL FLOW BELOW 1700 RPM IS TOO HIGH.  IDLE SPEED AND MIXTURE 	CAN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION.  FUEL SERVO REMOVED, SENT FOR REPAIRS.  MAJOR R	EPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00.  REINSTALLED FUEL SERVO, ADJUSTE	D IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001050200059	20010502	00059	EA  	2001	5	2	20010410AP015    	2	20010316	G	7322	25765361	FUEL CONTROL    			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	494SP	841  				172S8035	L2790951A			ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS.  FUEL FLOW BELOW 1700 RPM IS TOO HIGH.  IDLE SPEED AND MIXTURE 	CAN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION.  FUEL SERVO REMOVED, SENT FOR REPAIRS.  MAJOR R	EPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00.  REINSTALLED FUEL SERVO, ADJUSTE	D IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY.  RECOMMEND ALL RSA-5AD1 FUEL SERVO''S BE REFLOWED	 TO PRECISION FLOW SHEET 30075-02 IMMEDATELY.		1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001050200065	20010502	00065	CE  	2001	5	2	20010410AP016    	1	20010326	G	2510	161102105	CONTROL HOUSING 			CESSNA	172   	172S        	2072439	CE  										COCKPIT SEAT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	948SP	1008 				172S8144				DURING PHASE 3 INSPECTION FOUND PILOTS SEAT LOCK CONTROL ASSEMBLY P/N 1611021-05 BROKEN.  ONE SEAT LOCK PIN WAS ENGAGED 	AND WOULD NOT RELEASE DUE TO THE ACTUATOR CABLE BROKEN.  THIS IS THE 5TH SEAT CONTROL ASSEMBLY THAT HAS FAILED WITH A BR	OKEN CABLE FOR THIS ORGANIZATION.  REPLACED CONTROL ASSEMBLY.				1	H	7	1 	3O			NT	3A12    					 
2001050200066	20010502	00066	EA  	2001	5	2	20010410AP017    	2	20010328	G	8530	CCST041CA	CYLINDER        								LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	F				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	99		1310 								CRACK IN CYLIDER EXTENDED FROM BOTH SPARK PLUG BOSSES TO THE EXHAUST SEAT.											3	O			E274				 
2001050200068	20010502	00068	SO  	2001	5	2	20010410AP019    	1	20010315	G	7921	AE7010201K0240	HOSE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					LT ENGINE	CRACKED         	C				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	410CA	112  				31T8166005				DURING CRUSE FLIGHT THE LT ENGINE LOW OIL PRESSURE WARNING SOUNDED ALERTING THE PILOT TO DROPPING OIL PRESURE. PILOT PER	FORMED A PRECAUTIONARY ENGINE SHUTDOWN AND MADE A UNEVENTFUL LANDING. TECHNICICAN INSTALLED A NEW REPLACEMENT INLET OIL 	COOLER HOSE AND RETURNED AIRCRAFT TO SERVICE.				1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2001050200069	20010502	00069	SO  	2001	5	2	20010410AP021    	2	20010403	G	8520	655004	CONNECTING ROD  								CONT  	O520  	IO520D      	17032	SO  					ENGINE	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		0    					575948			FACTORY NEW ENGINE WITH 0 HRS TTIS WAS BEING DISASSEMBLED FOR CRANKSHAFT REPLACEMENT UNDER MSB 00-5.  THE MAJORITY OF CO	NNECTING ROD BOLTS COULD NOT BE REMOVED WITH REASONABLE PRESSURE AND HAD TO BE DRIVEN OUT OF THE CAP.  INSPECTION REVEAL	ED THAT THE ROD BOLTS EXHIBITED A BURR AND EVIDENCE OF GALLING ON THE SHANK AT THE POINT WHERE THE ROD AND CAP PARTING S	URFACE WOULD BE.  INSPECTION OF THE CAPS SHOWED DAMAGE EVIDENCED BY SIGNIFICANT GOUGING WHERE THE BOLTS HAD BEEN REMOVED	, RENDERING THEM UNSERVICEABLE.							3	O			E5CE				 
2001050200070	20010502	00070	EA  	2001	5	2	20010410AP022    	2	20010326	G	7321		DRIVE SHAFT     	BENDIX      	DPF2        	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					FUEL CONTROL	SHEARED         	G				E				ENGINE SHUTDOWN         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			GL	11	484SC				A59060	31T7820022	PCE51554			ON CLIMBOUT FROM EANSVILLE, IN AT 12,500 THE PILOT NOTICED HE COULD NOT CONTROL THE RIGHT ENGINE WITH THE POWER LEVER.  	THE ENGINE WAS SHUT DOWN IN FLIGHT.  THE TORQUE WAS REPORTED TO BE 1600 FT LBS AND THE PROPELLER SPEED WAS REPORTED TO B	E 2200 RPM.  NO OTHER ENGINE INDICATIONS WERE REPORTED. THE OUTSIDE AIR TEMPERATURE WAS -12 DEGREES C AND THE BAROMETRIC	 PRESSURE WAS 30.27. SHEARED FUEL CONTROL DRIVE SHAFT.			1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2001050200071	20010502	00071	SO  	2001	5	2	20010410AP023    	1	20010327	G	3222	6528000	STRUT           			PIPER 	PA28  	PA28140     	7102802	SO  										NOSE GEAR	CRACKED         	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			GL	11	7373J	5518 				2824728				THE STUDENT WAS ON HIS FINAL CROSS COUNTRY FLIGHT TO BLOOMINGTON, IN.  THE TRAFFIC PATTERN AND FINAL APPROACH WAS NORMAL	.  THE PILOT FLARED AND TOUCHED THE MAIN GEAR FIRST ON RUNWAY 35 AT BMG.  THE NOSE GEAR SETTLED ONTO THE RUNWAY, THE PIL	OT REACHED FOR THE BRAKE HANDLE WHEN THE NOSE SETTLED LOWER THAN NORMAL AND THE PROPELLER STRUCK THE GROUND.  THE PILOT 	STATED ALL FLIGHT CONTROLS, AND ENGINE CONTROLS WERE NORMAL.  THE APPROACH AND LANDING, AS DESCRIBED BY THE PILOT WAS CO	NFIRMED BY THE TOWER CONTROLLER ON DUTY AT THE TIME OF THE INCIDENT.  THE NOSE GEAR INNER LOWER TUBE BROKE.  INVESTIGATI	ON REVEALED A POSSIBLE  PRE-EXISTING CRACK RESULTING IN NOSE GEAR COLLAPSE.	1	L	7	1 	3O			 	2A13    					 
2001050200072	20010502	00072	CE  	2001	5	2	20010410AP024    	1	20010405	G	2810	1009200673	FLOAT VALVE     			BEECH 	200   	B200        	1152922	CE  										RT NACELLE TANK	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	773TP	295  				BB1722				THE FUEL VENT FLOAT VALVE IN THE TOP OF THE RT NACELLE TANK WAS IMPROPERLY INSTALLED.  THE FLOAT PIVOT BRACKET WAS BENT.	  THIS WOULD PREVENT THE VALVE FROM SEATING PROPERLY.  THIS WAS ALLOWING FUEL TO TRANSFER INTO THE AUX TANK WHEN EVER TH	E MAIN TANK WAS FULL.				1	L	7	2 	4T			 	A24CE   					 
2001041700096	20010417	00096	SO  	2001	4	17	20010411CW001    	2	20010319	G	8530	530851	LIFTER          			CESSNA	170   	170A        	2072304	CE  	CONT  	C145  	C145*       	17012	SO  					NR 5 CYLINDER	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1228D					19782				AIRCRAFT SUFFERED A LOSS OF OIL PRESSURE.  TEARDOWN OF THE ENGINE REVEALED THE HYDRAULIC LIFTER BODY ON THE NR 5 CYLINDE	R HAD BROKEN.					1	H	7	1 	3O	3	O	 	A799    	E253				 
2001041700013	20010417	00013	SO  	2001	4	17	20010411CW012    	2	20010206	G	7322	25765405	SERVO           			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360RB  	 	SO  					ENGINE CARB	INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	4175D	69   				3449191	322088			COULD NOT ADJUST OVERLY RIGHT MIXTURE.  SENT FOR FACTORY SERVICE.  INSTALLED ON AIRCRAFT STILL COULD NOT ADJUST.  SENT B	ACK TO FACTORY FOR REPAIRS.  NOTE  THESE UNITS ARE INSTALLED ON NEW AIRCRAFT, THIS IS 3RD SET OF SERVOS ON THIS AIRCRAFT	.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001041700014	20010417	00014	SW  	2001	4	17	20010411CW013    	1	20010227	G	2450	727425	CIRCUIT BREAKER 			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	ELECTRICAL	INOPERATIVE     	D				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	09	3758H					240930	L2556551A	993197		AIRCRAFT LANDING GEAR FAILED TO EXTEND AND AIRCRAFT LANDED GEAR UP.  DURING REMOVAL OF AIRCRAFT FROM RUNWAY, IT WAS NOTE	D, LANDING GEAR CONTROL CIRCUIT BREAKER WAS OUT.  DURING OPERATION OF LANDING GEAR ON JACKS, SYSTEM OPERATED NORMALLY.  	NOT KNOWN IF CIRCUIT BREAKER WAS PULLED OR TRIPPED.  NEW CIRCUIT BREAKER WAS INSTALLED AS PRECAUTIONARY MEASURE.				1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2001041700070	20010417	00070	EA  	2001	4	17	20010412CW002    	2	20010307	G	7322	105009	CARBURETOR      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	DEFECTIVE       	B			AMYR	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CE	05	12182	159  				17261866	L3457327A			DURING FLIGHT, AIRCRAFT WAS DOING TOUCH AND GO LANDINGS.  PILOT PULLED BACK ON THROTTLE FOR MORE POWER BUT COULD NOT MOV	E THROTTLE.  LANDED SHORT OF RUNWAY, IN A FIELD.  INVESTIGATION OF THROTTLE , FOUND CARBURETOR STUCK IN IDLE POSITION.  	REMOVED CARBURETOR AND FOUND COPPER BUTTERFLY RUBBING UP AGAINST INTERIOR OF THROTTLE ASSEMBLY.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001041700075	20010417	00075	SO  	2001	4	17	20010412CW005    	1	20010111	G	5711	66762	SPAR            			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540*       	41532	EA  					WING CENTER BOX	CORRODED        	B			MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	32138					287510014				INSPECTION REVEALED MISSING RIVET HEADS,  RUST.   CORROSSION ON REAR SPAR AT CENTER SECTION JUNCTION.						1	L	7	1 	3O	3	O	 	2A13    	E295				 
2001041700077	20010417	00077	SO  	2001	4	17	20010412CW007    	1	20010111	G	5310		SPAR            			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540*       	41532	EA  					FUSELAGE	CORRODED        	B			MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	32138					287510014				AFT CARRY THROUGH SPAR AND BAGGAGE DOOR FRAME AND OPPOSITE SIDE ARE RUSTING AND CORRODING AND STEEL FITTINGS UNDER BAGGA	GE COMPARTMENT  FLOOR.  PN 62448-00 PN 62448-01  PN 62618-00  PN 62619-00  PN 62529-00 65383-00 .					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2001041700078	20010417	00078	SO  	2001	4	17	20010412CW008    	1	20010111	G	5310		DOOR FRAME      			PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540*       	41532	EA  					FUSELAGE	CORRODED        	B			MI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	32138					287510014				AFT CARRY THROUGH SPAR AND BAGGAGE DOOR FRAME AND OPPOSITE SIDE ARE RUSTING AND CORRODING AND STEEL FITTINGS UNDER BAGGA	GE COMPARTMENT FLOOR.   PN 62488-00  PN  62448-01  PN  62618-00  PN 62619-00  PN 62529-00  PN  65383-00.					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2001041700080	20010417	00080	SO  	2001	4	17	20010412CW009    	2	20010301	G	8530		CYLINDER        			CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	IO470U      	17026	SO  					LT ENGINE	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	515HW					310J0102				AIRCRAFT LANDED.  OIL LEAKING FROM LEFT ENGINE.  INSPECTION REVEALED NR 4 CYLINDER VALVE COVER BROKEN DUE TO VALVE ROCKE	R ASSEMBLY BROKEN FROM CYLINDER BOSS.  PROBABLE CAUSE STUCK VALVE OR METAL FATIGUE AT BOSS.					1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2001041700081	20010417	00081	EA  	2001	4	17	20010412CW010    	2	20010301	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	IO540*      	41532	EA  					RIGHT	MAKING METAL    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	283GT					317952139				AIRCRAFT LANDED.  RIGHT ENGINE SHUTDOWN IN FLIGHT,  DUE TO LOSS OF OIL PRESSURE.  INSPECTION REVEALED METAL CONTAMINATIO	N.					1	L	7	2 	3O	3	O	 	A20SO   	1E4				 
2001041700084	20010417	00084	EA  	2001	4	17	20010413CW002    	1	20010302	G	2752	SC14000062	BEARING         	EATON       		CNDAIR	CL600 	CL6002B19   	       	EA  										FLAP ACTUATOR	FAILED          	B			VK6R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09					1102					THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRELOAD CONDITION.						2	L	7	2 	4F			RT	A21EA   					 
2001041700085	20010417	00085	CE  	2001	4	17	20010413CW003    	1	20010220	G	3232	0842102	BELLCRANK       			CESSNA	320   	320F        	2074516	CE  	CONT  	O520  	IO520*      	17032	SO  					NLG	BROKEN          	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	3452Q	3643 				0052				LEFT NOSE GEAR DOOR ROD ATTACH CLEVIS PIN FELL OUT.  UPON RETRACTION OF GEAR,  LEFT NOSE DOOR FOULED THE RETRACTORY NOSE	 GEAR AND JAMMED.  GEARBOX CONTINUED PULLING UNTIL 0842102 BELLCRANK BROKE.  WHEN GEAR WAS EXTENDED NOSE GEAR WOULD NOT 	EXTEND.  DOOR CLEVIS PINS WERE INSTALLED WITH AN 416 PINS INSTEAD OF COTTER PINS AS CALLED OUT BY IFC.				1	L	7	2 	3O	3	O	 	3A25    	E5CE				 
2001041700086	20010417	00086	EA  	2001	4	17	20010413CW004    	2	20010305	G	8520	69796	DOWEL PIN       								LYC   	IO360 	IO360L2A    	 	EA  					NR 1 BEARING	MISINSTALLED    	B			NX42	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15		2173 					L2776751A			DURING ENGINE INSPECTION, IT WAS NOTED THAT THE NUMBER ONE MAIN BEARING DOWEL WAS INSTALLED BACKWARDS WITH IN THE CRANKC	ASE BEARING DOWEL BORE.  THE IMPROPERLY INSTALLED DOWEL PREVENTED THE NEW BEARING FROM FULLY SEATING WITHIN THE CRANKCAS	E BORE.									3	O			1E10				 
2001041700087	20010417	00087	CE  	2001	4	17	20010413CW005    	1	20010321	G	5312	08130005	BULKHEAD        			CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470*      	17026	SO  					FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	101JB	5921 				310K0110				DURING REPLACEMENT OF AIRCRAFT HEATER DUCTING, MECHANIC NOTICED THE RIGHT BULKHEAD AT STA 29.93 UNDER HEATER WAS CRACKED	.  ALSO CHECKED LEFT SIDE BULKHEAD AT STA 29.93 AND FOUND THAT BULKHEAD CRACKED IN THE SAME LOCATION.  NOTE  THAT SUPPOR	T FOR NOSE WHEEL STEERING PULLEY IS ATTACHED TO BULKHEAD NEAR CRACK.  MOVEMENT OF PULLEY AND CABLE TENSION MAY CAUSE BUL	KHEAD TO FLEX.  RECOMMEND CHECKING CABLE TENSION DURING INSPECTION OF NOSE WHEEL STEERING SYSTEM.			1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2001041700088	20010417	00088	CE  	2001	4	17	20010413CW006    	1	20010321	G	5312	08130004	BULKHEAD        			CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470*      	17026	SO  					FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	101JB	5921 				310K0110				DURING REPLACEMENT OF AIRCRAFT HEATER, DUCTING MECHANIC NOTICED THE RIGHT BULKHEAD AT STA 29.93 UNDER HEATER WAS CRACKED	.  REMOVED HEATER TO GAIN ACCESS TO BULKHEAD.  NOTE  THAT SUPPORT FOR NOSE WHEEL STEERING PULLEY IS ATTACHED TO BULKHEAD	 NEAR CRACK.  MOVEMENT OF PULLEY AND CABLE TENSION MAY CAUSE BULKHEAD TO FLEX.  RECOMMEND CHECKING CABLE TENSION DURING 	INSPECTION OF NOSE WHEEL STEERING SYSTEM.			1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2001041700089	20010417	00089	SW  	2001	4	17	20010413CW007    	1	20010319	G	6730	41001554	HOUSING         	TEXTRON     		BELL  	214   	214B        	1182100	SW  										SERVO ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					1109B					CRACKS DETECTED ON FLANGE MOUNTS.  REPLACED SERVO UNIT FROM SURPLUS.						2	G	7	1 	4U			 	H6SW    					 
2001041700102	20010417	00102	EU  	2001	4	17	20010413CW010    	1	20010129	G	2432	20VR4D	BATTERY         			AMD   	FALC50	FALCON900   	2700160	EU  										CELL BLOCK	UNAPPROVED PART 	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09						131				TWO UNAUTHORIZED CELLS INSTALLED IN BATTERY BLOCK.  UNAUTHORIZED CELLS REPLACEMENTS PERFORMED USING UNACCEPTABLE PRACTIC	ES.  RECOMMEND REPLACEMENT OF ENTIRE CELL BLOCK.					2	L	7	3 	4F			RT	A46EU   					 
2001041700103	20010417	00103	EA  	2001	4	17	20010413CW011    	2	20010327	G	7414	10682016	GEAR            								LYC   	O540  	O540*       	41532	EA  					MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23										HAVE FOUND 3 GEARS WITH 1 TOOTH BROKEN.  WERE FOUND A 500 HOUR MAG INSPECTION AFTER ENGINE QUIT ON LANDING.  FOUND 2 MOR	E GEARS WITH SEVERAL TEETH MISSING.  MAGNETO JUMPED INTERNAL TIME.										3	O			E295				 
2001041700104	20010417	00104	CE  	2001	4	17	20010413CW013    	1	20010308	G	3233		ACTUATOR        			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	MLG	DISTORTED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6189R	8567 				172RG0109	L2760936A	951813		FOUND CRACKS ON BOTH SIDES OF SADDLE SHAPED HOLE OF ACTUATOR BODY .						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P7EA	 
2001041700112	20010417	00112	CE  	2001	4	17	20010416CW002    	1	20010416	G	5540		STRUCTURE       			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RUDDER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	12TL					U20606464				THE 206 SEAPLANE RUDDER ASSEMBLY IS PRONE TO DAMAGE AFT OF PN 12310661,  DOUBLER AT THE BOTTOM OF THE RUDDER.  DAMAGE OF	 THIS NATURE IS EVIDENT BY A KINK AT THE BOTTOM OF THE RUDDER ON BOTH SIDES.  THIS DAMAGE IS CAUSED BY THE WIND WHEN A R	UDDER LOCK IS NOT USED.  IF RUDDER IS INSTALLED, A RUDDER LOCK SHOULD BE USED WHENEVER AIRCRAFT IS STORED OUTSIDE.  ALSO	, THIS AREA SHOULD BE CHECKED DURING PREFLIGHT.			1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001041700114	20010417	00114	SO  	2001	4	17	20010416CW006    	1	20010108	G	5740		ATTACH FITTING  			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	O540  	IO540*      	41532	EA  					LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6873C	2451 				32R7885034				INSPECTED AIRFRAME, FOUND THREE SEPARATE CRACKS IN THE LEFT WING FORWARD ATTACH FITTING AREA.						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001041700115	20010417	00115	CE  	2001	4	17	20010416CW007    	1	20010119	G	5540	07126161	BULKHEAD        			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470*       	17026	SO  					RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	9298X	4103 				18253698				WHILE PERFORMING A PRE PURCHASE LOOKOVER,  FOUND A STOP DRILLED CRACK IN THE UPPER RADIUS ABOVE THE LEFT RUDDER STOP BOL	T.  FURTHER INSPECTION FOUND ANOTHER CRACK RADIATING OUTWARD FROM THE UPPER OUTBOARD EDGE OF THE UPPER RIGHT LIGHTENING 	HOLE.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001041700116	20010417	00116	NE  	2001	4	17	20010416CW009    	2	20010110	G	7321	324476810	FUEL CONTROL    			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT ENGINE	INOPERATIVE     	D				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	09	63791		1769 			BB1100	93649			DURING TRAINING FLIGHT IN AN EMERGENCY DECENT SIMILATION, THE LEFT ENGINE FLAMED OUT AND COULD NOT BE RESTARTED.  REPLAC	ED THE FUEL CONTROL AND OPERATION IS NORMAL.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001041700117	20010417	00117	CE  	2001	4	17	20010416CW010    	1	20010313	G	2750	500000863	CONTROL CABLE   			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TE FLAPS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	414JK	6160 				414A0626				CABLE SNAPPED BY FIRST PULLEY OUTBOARD OF FLAP MOTOR,  RIGHT SIDE.  NO EVIDENCE OF WEAR OR CORROSION.  PULLEY WAS TURNIN	G FREE.  FAILURE CAUSED SPLIT FLAPS ON LANDING.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001041700118	20010417	00118	EA  	2001	4	17	20010416CW011    	2	20010223	G	7421	RHB37E	SPARK PLUG      			CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	929MA	211  				T20608107	L1031161A			UPON ANNUAL INSPECTION, FOUND 2 SPARK PLUGS NOT WORKING.  CERAMIC ON TERMINAL END WAS LOOSE INSIDE THE PLUG.  REMOVED AN	D REPLACED.					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2001041700119	20010417	00119	GL  	2001	4	17	20010416CW012    	2	20010325	G	7323	23057869	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	5187S					C10968DV				GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700120	20010417	00120	GL  	2001	4	17	20010416CW013    	2	20010325	G	7323	23057869	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	9106Z					800776D				GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700121	20010417	00121	GL  	2001	4	17	20010416CW014    	2	20010325	G	7323	23057869	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	5200Y					1198D				GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700222	20010417	00222	GL  	2001	4	17	20010416CW015    	2	20010325	G	7323	23057869	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	4575Z					370094D				GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700226	20010417	00226	GL  	2001	4	17	20010416CW016    	2	20010325	G	7323	230578	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	5108E					811075D				GOVERNOR FAILURE RANGES FROM 72 HOURS TO 1750 HOURS.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700227	20010417	00227	CE  	2001	4	17	20010416CW017    	1	20010305	G	2450	VR515GA	VOLT REGULATOR  			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470*       	17026	SO  					ELECTRICAL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	4603N	36   				18267280				VOLTAGE REGULATOR WAS INSTALLED, AIRCREW SQUAWKED LOW VOLTAGE WARNNG LIGHT REMAINED ON AT ALL POWER SETTINGS.  TROUBLESH	OOTING DETERMINED OUTPUT VOLTAGE WAS BELOW MINIMUM OUTPUT AND ERRATIC.  VISUAL INSPECTION OF THE REGULATOR INDICATED NO 	SIGNS OF EXTERIOR DEFECTOR DAMANAGE.  NO DISASSEMBLY WAS ATTEMPTED.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001041700235	20010417	00235	EA  	2001	4	17	20010416CW018    	2	20010315	G	7322	MA3PA	FLOAT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	CRACKED         	D			VCTA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	89061	442  	442  			15282616	1082315			DURING A 50 HOUR INSPECTION,  PM CHECK ON AIRCRAFT RUN UP FOUND AIRCRAFT NOT SMOOTH RUN.  AFTER CHECKING THE CARB, FOUND	 CRACKED FLOAT.  MADE AIRCRAFT RUN RICH.  THIS COULD TURN INTO A DANGER IN THE AIR.  THIS REPLACEMENT OF THE OLDER, BETT	ER BRASS FLOAT WAS NOT GOOD.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001041700093	20010417	00093	CE  	2001	4	17	20010417AP002    	1	20010125	G	5711		SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  										WINGS	DAMAGED         	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6369N	2881 				44				WOOD SPARS; NAILS OUT OF LEADING EDGE RIBS; WOODEN SPACERS WERE LEFTOUT OF FIRST FOUR IN-BOARD LEADINGEDGE RIBS; LEADING	 EDGE LOOSE; NAILSLOOSE; SOMEBODY HAD PATCHED UP BEFORE AND PUT SCREWS INSTEAD OF NAILS ON LEADING  EDGE SPARS AND RIBS;	 SOME RIBS CRACKED; INNER RIB LACING CORDS BROKE; HAVE JUNKED WINGS AND REPLACING WITH NEW METAL SPAR WINGS LATER THIS Y	EAR.			1	H	7	1 	3O			 	A759    					 
2001041700146	20010417	00146	GL  	2001	4	17	20010417AP003    	1	20010411	G	5610		CANOPY          			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  	LYC   	O540  	IO540*      	41532	EA  					CANOPY LATCH	FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	5439N	240  	240  							CANOPY SHATTERED IN FLIGHT, DEPARTED AIRCRAFT AND HIT PROP, DESTROYING PROP. PILOT MADE EMERGENCY LANDING. IT APPEARS TH	E LONG-EZ CANOPY FRAME LATCH PASSED THROUGH THE FRAME AND RESTED ON THE GLASS. THE GLASS SHATTERED.  					1	M	7	1 	3O	3	O	RT	EXPA1M71	1E4				 
2001050200077	20010502	00077	CE  	2001	5	2	20010417AP004    	1	20010412	G	5210		ROD             			BEECH 	MU300 	400A        	1155402	CE  										PAX DOOR	MISSING         	B				O				OTHER                   				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			GL	15	695TA					RK310				CABIN DOOR WILL NOT OPEN FROM INSIDE OR OURSIDE. AFT PINS DO NOT RELEASE WHEN HANDLE IS MOVED. FOUND THE ACTUATING ROD M	ISSING THE ROD END COTTER PIN. REINSTALLED THE PIN AND COTTER PINNED. OPERATION CHECK NORMAL.					2	H	7	2 	4F			RT	A16SW   					 
2001041700113	20010417	00113	SO  	2001	4	17	20010417AP005    	1	20010416	G	3213	7873804	STRUT           			PIPER 	PA32  	PA32301     	7103207	SO  										LT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4291Y	3639 				328306016				DURING ANNUAL INSPECTION FOUND LEFT LOWER MAIN GEAR STRUT CRACKED AT THE ATTACHMENT OF THE STRUT TO THE AXLE SHAFT. THE 	STRUT CASTING WAS CRACKED IN TWO DIFFERENT PLACES WITH ONE CRACK MEASURING OVER 1 INCH IN LENGTH. EXAMINATION OF THE RIG	HT STRUT FOUND NO DAMAGE. REVIEW OF THE AIRCRAFT MAINTENANCE RECORDS REVEALED A LANDING ACCIDENT SEVERAL YEARS AGO. TECH	NICIAN RECOMMENDS DURING INSPECTIONS TO PLAY CLOSE ATTENTION TO MAIN GEAR CASTING.			1	L	7	1 	3O			 	A3SO    					 
2001042300337	20010423	00337		2001	4	23	20010418CW001    	4	20010418	G	3422		GYRO            			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470*       	17026	SO  					COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6312A					33112				DURING ROUTINE ANNUAL INSPECTION THE ELEVATOR WAS FOUND TO TRAVEL ONLY 19 DEGREE UP.  THE TYPE CERTIFICATE CALLS FOR 25 	DEGREE.  INVESTIGATION FOUND THE D. G. MOUNTED DIRECTLY ABOVE THE CONTROL WHEEL TUBE.  AS THE WHEEL WAS PULLED AFT THE A	N3-10A BOLT CONTACTED THE D.G. STOPPING THE TRAVEL.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001042400233	20010424	00233	CE  	2001	4	24	20010418CW002    	1	20010418	G	5412		FASTENER        			CESSNA	182   	182         	2072702	CE  										FIREWALL	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5590B					33590				OWNER REPORTED 2 LOOSE RIVETS AT THE FIREWALL ATTACH POINT  STA. 5.  INVESTIGATION REVEALED 2 MISSING RIVET HEADS AN426A	D4 AND A FURTHER 25 RIVET HEADS HELD ON BY PAINT ALONE.  1 OTHER RIVET HEAD HAD A STRANGE APPEARANCE, SCRAPING THE PAINT	 OFF REVEALED A  BONDO  MATERIAL FILLING THE HOLE.   THE AIRPLANE HAD BEEN REPAINTED IN ABOUT 1988 BY PERSONS UNKNOWN.				1	H	7	1 	3O			NT	3A13    					 
2001042400234	20010424	00234	CE  	2001	4	24	20010418CW003    	1	20010418	G	7120		HEAT SHIELD     			CESSNA	182   	182         	2072702	CE  										ENGINE MOUNT	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5590B					33590				THE ENGINE MOUNT HEAT SHIELDS HAD BEEN REMOVED AT SOME POINT ALLOWING HEAT DAMAGE REQUIRING 3 WELD REPAIRS.						1	H	7	1 	3O			NT	3A13    					 
2001042400235	20010424	00235	CE  	2001	4	24	20010418CW004    	1	20010418	G	2432		WIRE            			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470*       	17026	SO  					BATTERY	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	5590B					33590				THE BATTERY CABLE WAS BARE IN MANY PLACES INCLUDING THE PENETRATION OF THE FIREWALL.  IT HAD ALSO BEEN PENETRATED BY A S	CREW THROUGH THE BELLY OF AIRCRAFT, JUST FORWARD OF THE BATTERY BOX.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001042400257	20010424	00257		2001	4	24	20010418CW005    	4	20010418	G	3422		GYRO            			CESSNA	182   	182         	2072702	CE  										COCKPIT	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	5590B					33590				THE DIRECTIONAL GYRO WAS POWERED BY A WIRE OF THREE SIZES NR 12,  NR 16 AND NR 18, SPLICED TOGETHER OVER A LENGTH OF 20 	INCHES,  THE LARGE END WAS BENT INTO A HOOK, TINNED WITH SOLDER AND CONNECTED TO THE AMMETER.					1	H	7	1 	3O			NT	3A13    					 
2001042400259	20010424	00259	CE  	2001	4	24	20010418CW007    	1	20010402	G	2720	12606421	SPROCKET        	CESSNA      		CESSNA	206   	206H        	2073301	CE  	LYC   	O540  	IO540*      	41532	EA  					IDLER	MALADJUSTMENT   	B			YFRS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	2446X					08097				EXCESSIVE LEFT RUDDER PETAL PRESSURE REQUIRED TO MAINTAIN STRAIGHT AND LEVEL FLIGHT.  FOUND TRIM CHAIN TENSION ADJUSTMEN	T IDLER SPROCKET SLIPPED IN ADJUSTMENT SLOT.  TRIM CHAIN JUMPED POSITION ON STEERING BUNGEE GEAR, CAMPING LIMITED LEFT R	UDDER TRIM.  RUDDER TRIM RIGGING RESET, AIRCRAFT FLIGHT CHECKED, RUDDER CONTROL SYSTEM AND RUDDER TRIM OPERATION NORMAL.				1	H	7	1 	3O	3	O	RT	A4CE    	1E4				 
2001042400260	20010424	00260	CE  	2001	4	24	20010418CW008    	1	20010307	G	2497		WIRE            			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200*       	17020	SO  					INSTRUMENT PANEL	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	5427Q					15073327				WIRE SHIELDING CHAFED OTHER WIRES IN SAME BUNDLE CAUSING MULTIPLE SHORTS.  OCCURRED IN FORMAL OPERATION.  PROBABLE CAUSE	 WAS SHIELDING ON PB 10 TOUGHER THAN INSOLATION IN OTHER WIRES CAUSING SEVERE WEAR.  TO PREVENT RECURRENCE PB 10 NEEDS A	 SLEEVE OR COVER OVER SHIELDING OR ISOLATE PB 10 FROM THE REST OF THE WIRE BUNDLE.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001042400261	20010424	00261	CE  	2001	4	24	20010418CW009    	1	20010308	G	2432	S337711	SWITCH          			CESSNA	172   	172S        	2072439	CE  										COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	1003 	1003 			172S8135				PILOT REPORTED AVIONICS MASTER SWITCH INOPERATIVE,  WHEN BATTERY SWITCH IS TURNED ON, ALL AVIONICS LEFT IN ON POSITION P	OWER UP REGARDLESS OF AVIONICS MASTER SWITCH POSITION.  MAINTENANCE FOUND ONE SIDE OF AVIONICS MASTER SWITCH INOPERATIVE	.  REPLACED AVIONICS MASTER SWITCH.  OPERATIONAL CHECKED SATISFACTORY.				1	H	7	1 	3O			NT	3A12    					 
2001042400262	20010424	00262	CE  	2001	4	24	20010418CW010    	1	20010312	G	2510	051421224	SEAT BACK       			CESSNA	172   	172S        	2072439	CE  										COCKPIT	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	789EP	1003 	1003 			172S8135				MAINTENANCE FOUND RIGHT FROMT SEAT BACK RECLINED APPROXIMATELY 4 INCHES FROM NORMAL UPRIGHT POSITION.  THE SEAT WAS REMO	VED AND INSPECTED, FINDING THE SEAT BACK FRAME BENT.  THE FRAME WAS BENT ON THE LEFT SIDE JUST ABOVE THE ATTACH FORGING 	PN 05142158.  REPLACED SEAT BACK FRAME.				1	H	7	1 	3O			NT	3A12    					 
2001042400263	20010424	00263	CE  	2001	4	24	20010419CW001    	1	20010314	G	2701	05600145	YOKE            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CONTROL COLUMN	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	97662	12525				17276219				MAINTENANCE TECH FOUND AREA BELOW PIVET BOLT EXCESSIVELY COVERED TO THE POINT OF EXFOLIATION.  WHEN DRILLING THE INSPECT	ION HOLE CALLED FOR, THE DRILL BIT ACTUALLY FELL THROUGH AFTER APPROXIMATELY 2 TURNS OF THE BIT.  CENTRAL YOKE WAS REPLA	CED AT THIS TIME.  TECH STRONGLY RECOMMENDS THIS PROCEDURE SHOULD BECOME AN AIRWORTHINESS DIRECTIVE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001042400264	20010424	00264	SW  	2001	4	24	20010419CW005    	1	20010220	G	3210	110538	NUT             			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					MLG AXLE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	613PC					125598				FOUND NEW AXLE NUTS TO HAVE CHAMFER CUT ON INSIDE DIAMETER, WHERE NUT CONTACTS BEARING.  CONTACTED MFG., CONFIRMED THAT 	NO CHAMFER SHOULD BE PRESENT ON INSIDE DIAMETER.					1	H	7	1 	3O	3	O	NC	A759    	E274				 
2001042000076	20010420	00076	EA  	2001	4	20	20010419CW006    	2	20010319	G	7414	10157120Y	PINION GEAR     	BENDIX      		ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENG LT MAGNETO	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	71330				C049605	0542				ENGINE QUIT WHEN LEFT MAG WAS SELECTED DURING MAG CHECK AFTER START.  RESTART WAS UNEVENTFUL.  WITH MAG SWITCH IN BOTH, 	ENG WOULD NOT  DEVELOP POWER,  BEGAN BACKFIRING AND AFTERFIRING.  ATTEMPT TO CHECK MAG TIMING, FOUND THE ENG LT MAG WOUL	D ONLY TURN INTERMITTENT WITH ENG.  MAG AND ALL SPARK PLUGS WERE REPLACED DUE TO HEAVY LEAD AND CARBON FOULING. LOWER PL	UGS HAD LEAD BRIDGING  GAP.  ENG OPS CHECKED GOOD.  PILOT REPORTED HISTORY OF DIFFICULT STARTING.  LEFT MAG CONTAINS RET	ARD POINTS.  TEARDOWN FOUND WOODRUFF KEY SLOT IN PINION GEAR WORN TO A WIDTH OF 90 DEGREES ROTATION WITH OVER HALF OF MA	TERIAL BETWEEN THE GEAR ID AND TEETH GROOVES WORN AWAY.  TIMING GEAR TEETH WERE MISSING AND MAG CASE FILLED WITH DEBRIS.	1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001042400265	20010424	00265	EU  	2001	4	24	20010419CW007    	1	20010306	G	2420	P610151	ROTOR           	AUXILEC     		AEROSP	ATR72 	ATR72202    	8680940	EU  										GENERATOR	SHORTED         	B			XC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					1227					MAIN STATOR WINDINGS ON ROTOR ASSEMBLY SHORTED OUT AFTER 41.8 FLIGHT HOURS, SINCE OVERHAUL.  THIS WAS A NEWLY MODIFIED R	OTOR.  THIS IS A POORLY DESIGNED ROTOR, PREVIOUS PN WAS P603744A, WHICH ALSO HAD A PROBLEM AND CAME APART WHILE IN OPERA	TION.				2	H	7	2 	4T			RT	A53EU   					 
2001042000229	20010420	00229	SW  	2001	4	20	20010419CW008    	1	20010319	G	6730	41002437	LEVER           	TEXTRON     		BELL  	214   	214B        	1182100	SW  										SERVO ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					1228B					CRACKING DETECTED ON TANG EDGE OF LEVER ASSEMBLY.						2	G	7	1 	4U			 	H6SW    					 
2001042400273	20010424	00273	SW  	2001	4	24	20010419CW012    	1	20010402	G	5711		SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6309N					233				A LONGITUDINAL CRACK IN THE RIGHT FORWARD WOODEN WING SPAR, APPROXIMATELY 30 INCHES LONG.						1	H	7	1 	3O	3	O	 	A759    	E223				 
2001042000282	20010420	00282	WP  	2001	4	20	20010419CW013    	1	20010316	G	6322	369A56553	BEARING         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BLOWER ASSY	DAMAGED         	D				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			NM	02	622PB					880318D	831268			DURING SHUTDOWN, A LOUD GRINDING AND POPPING WAS HEARD COMING FROM THE TRANSMISSION AREA.  OIL COOLER BLOWER ASSY PN 369	025630-101 WAS REMOVED AND DISSASSEMBLED FOR INSPECTION.  THE LOWER BLOWER BEARING PN 369A5655-3  HAD FAILED.  IT IS SUS	PECTED THAT THE BEARING CAGE FAILED AS NUMEROUS PIECES OF CAGE MATERIAL WAS RECOVERED.  THIS BEARING HAS A RL OF 1200 HO	URS.  PART TT AT FAILURE WAS 515.4 BEARING RETAINED FOR 90 DAYS AS EXHIBIT.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001042400278	20010424	00278	NE  	2001	4	24	20010420CW001    	2	20010221	G	7230		COMPRESSOR      								PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		48961					P667085			ENGINE WAS RECEIVED AT ENGINE SHOP FOR REPAIR  DUE TO SUSPECTED OIL LEAK AS REPORTED BY THE CUSTOMER.  DURING THE DISASS	EMBLY OF THE HIGH COMPRESSOR MODULE, IT WAS DISCOVERED THAT THE COMPRESSOR DISKS STAGES NUMBER 8 AND 9 EXHIBITED A MELTI	NG CONDITION DUE TO AN EXTREMELY HIGH HEAT EXPOSURE.  THE C9 STAGE DISK BORE WAS MELTED COMPLETELY AND ROLLED OUT OF POS	ITION.								4	F			E2EA				 
2001042400280	20010424	00280	SO  	2001	4	24	20010420CW003    	1	20010315	G	3340	6446	FLUX DETECTOR   	STEC        		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A1D     	41514	EA  					LT WING TIP	MALFUNCTIONED   	B			PIQR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	21	181LS	354  			FV5842	2843227				FOUND LONGLIGHT AND STROBES PULLING HSI OFF HEADING IN EXCESS OF 10 DEGREES.  NO PLACARDS INSTALLED OR REQUIRED TO NOTIF	Y PILOT OF THIS CONDITION.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001042400285	20010424	00285	CE  	2001	4	24	20010420CW007    	1	20010402	G	7170	AV171C47	O-RING          			CESSNA	182   	182         	2072702	CE  										QUICKDRAIN	LEAKING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07		200  								THE QUICK DRAIN ORING THAT CAME WITH THE NEW QUICK DRAIN,  SWELLED UP SO THAT IT IS PUSHED OUT OF THE GROOVE.  OIL LEAKS	 PASSED IT EASILY.					1	H	7	1 	3O			NT	3A13    					 
2001042400286	20010424	00286	GL  	2001	4	24	20010420CW008    	1	20010402	G	5210		LATCH           			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  	LYC   	O540  	IO540*      	41532	EA  					CANOPY	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5439N					98110139				CANOPY DEPARTED THE AIRCRAFT WHILE IN FLIGHT.  CANOPY LATCH FAILED.						1	M	7	1 	3O	3	O	RT	EXPA1M71	1E4				 
2001042300346	20010423	00346	EA  	2001	4	23	20010420CW009    	2	20010316	G	8520	LW11021	BEARING         			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 2	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	7430F	187  	150  			1150452	RL2096751A			AT 25 HOUR OIL CHANGE, FOUND METAL PARTICLES IN SUCTION SCREEN AND FILTER.  ON INSPECTION, FOUND NR 2 MAIN BEARING HAD S	PUN NEARLY CAUSING ENGINE FAILURE. CHECK SCREENS.					1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001042400289	20010424	00289	CE  	2001	4	24	20010420CW011    	1	20010309	G	2910	S217840105	HYDRAULIC LINE  			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	IO360A1A    	41514	EA  					NOSE ACTUATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	9864B				34151	172RG1060				NOSE GEAR UP HOSE PNS217840105 CAME OUT OF SWEDGE FITTING.						1	H	7	1 	3O	3	O	 	3A17    	1E10				 
2001042400308	20010424	00308	CE  	2001	4	24	20010423CW004    	1	20010330	G	7110	J744436	MOUNT           			CESSNA	172   	172R        	2072401	CE  										ENGINE COWLING	TORN            	D			CMXS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	453CM	350  				17280845				RUBBER TORN FROM MOUNTING PLATE.						1	H	7	1 	3O			NT	3A12    					 
2001042400309	20010424	00309	CE  	2001	4	24	20010423CW005    	1	20010402	G	2701	0411257	UNIVERSAL JOINT 			CESSNA	172   	172R        	2072401	CE  										CONTROL WHEEL	CORRODED        	D			CMXS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	455CM	399  				17280847				PIVOTS RUSTY, WOULD NOT SWIVAL,  U JOINT COVERED BY RUBBER BOOT.  PILOT REPORTED AILERONS HARD TO MOVE.						1	H	7	1 	3O			NT	3A12    					 
2001042400310	20010424	00310	EA  	2001	4	24	20010423CW006    	2	20010330	G	8520	LN18840	CAMSHAFT        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					LOBES	WORN            	D			CMXS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	467CM	590  				17280859	LZ871551A			CAMSHAFT WORN ON  NR 5 LOBE.    CYLINDERS  NR 3 AND NR 4 INTAKE VALVE NOT OPENING FULLY. PILOT REPORTED ENGINE RUNNING R	OUGH.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001042400317	20010424	00317	EA  	2001	4	24	20010423CW013    	2	20010326	G	7414	M3548	ROTOR           	SLICK       		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					MAGNETO	BROKEN          	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4148V	1653 			98040879	2843178	L3625536A			PILOT REPORTED EXCESSIVE MAG DROP.  FOUND RIGHT MAGNETO ROTOR ASSEMBLY CAM SLOT TO BE BROKEN.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001042400318	20010424	00318	SO  	2001	4	24	20010423CW014    	1	20010403	G	2421	ALE1003K	PLATE           	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ALTERNATOR	BROKEN          	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146T	1709 			8053286	2843168	L3620536A			DURING ROUTINE MAINTENANCE THE ALTERNATOR END PLATE WAS FOUND WITH THE FORWARD ATTACH EAR BROKEN OFF.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001050200280	20010502	00280	CE  	2001	5	2	20010424CW001    	1	20010131	G	2750	169524074	CONTROL CABLE   			BEECH 	23    	B24R        	1151253	CE  										TE FLAPS	FRAYED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	9321S					MC341				DURING ANNUAL INSPECTION, CABLE WAS INSPECTED AND FOUND TO HAVE SEVERAL BROKEN STRANDS.  AFTER FURTHER INSPECTION, FOUND	 THAT FLAP CABLE 169-524074 WAS CONTACTING A SCREW HEAD WHEN THE FLAPS ARE IN THE UP POSITION.  RECOMMEND THAT PROTECTIV	E TAPE BE PUT OVER THE SCREW AND TO MONITER FLAP CABLE EVERY 1000 HOURS.				1	L	7	1 	3O			 	A1CE    					 
2001050300107	20010503	00107	WP  	2001	5	3	20010424CW008    	2	20010406	G	7200	30756392	SEAL            								GARRTT	TFE731	TFE7315R    	01518	WP  					NR 4	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19		6972 					P91222			NR 4 RUNNER FAILED CAUSING DAMAGE TO NEARBY COMPONENTS.											4	F			E6WE				 
2001050200294	20010502	00294	CE  	2001	5	2	20010425CW007    	1	20010323	G	2710	1260141	TUBE            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					AILERON CONTROL	LOOSE           	B			GSZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6161S	6001 				R18201633				DURING ANNUAL INSPECTION THE TWO ALUMINUM RIVETS SECURING THE FORWARD END OF SHAFT WERE FOUND LOOSE AND THE BUCK TAILS M	ISSING .  THE SQUARK TUBE PORTION OF ASSEMBLY APPEARS TO BE ALUMINUM.  THE FORWARD THREADED END IS STEEL.  THE FIT OF TH	E TWO PARTS IS NOT VERY CLOSE.  FOUND SHAFT ON FORWARD END OF TUBE WORN WERE IT IS INSTALLED IN BEARING BLOCK.  IF THE T	WO RIVETS HAD FALLEN OUT,  IT COULD HAVE RESULTED IN TOTAL LOSS OF AILERON CONTROL.(PHOTOS)			1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001050300396	20010503	00396	CE  	2001	5	3	20010425CW009    	1	20010402	G	2910	24411003	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					MLG	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6623Z					172RG0240				BOTH PIVOTS WERE FOUND CRACKED.  THE RIGHT PIVOT WAS NOT ONLY CRACKED BUT SHOWED SIGNS THAT THE SPLINNED END WAS STARTIN	G TO TWIST OFF.  BOTH PIVOTS CRACKS WERE VISABLE WITH THE NAKED EYE, AND NEITHER LEAKED BRAKE FLUID THROUGH THE CRACKS A	ND INTO THE ACTUATOR.  BOTH PIVOTS WERE ALSO THE OLDER ORIGINAL STYLE.				1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001050300158	20010503	00158	SO  	2001	5	3	20010426CW010    	2	20010123	G	8530		CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1697 					286416R			CYLINDERS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE.    CYLINDER SERIAL NUMBERS:  (52L962936),  52L96293	7,  52L962938,  52L962799.										3	O			E5CE				 
2001050300159	20010503	00159	SO  	2001	5	3	20010426CW011    	2	20010123	G	8530		CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1697 					286416R			CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE.  CYLINDER HEAD SERIAL NUMBERS:  52L962936,  (5	2L962937),  52L962938,   52L962799.										3	O			E5CE				 
2001050300160	20010503	00160	SO  	2001	5	3	20010426CW012    	2	20010123	G	8530		CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	C			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1697 					286416R			CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE.  CYLINDER HEAD SERIAL NUMBERS:   52L962936,   	52L962937,   (52L962938),   52L962799.										3	O			E5CE				 
2001050300161	20010503	00161	SO  	2001	5	3	20010426CW013    	2	20010123	G	8530		CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1697 					286416R			CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE.  CYLINDER HEAD SERIAL NUMBERS:  52L962936,   5	2L962937,   52L962938,  (52L962799).										3	O			E5CE				 
2001050300229	20010503	00229	SO  	2001	5	3	20010426CW015    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDERS HAVE CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20.  CYLINDER SERIAL NUMBERS:  (52J9	76779),  52J976780,  52J976781,  52J976782,  52J976787,  52J976788.										3	O			E5CE				 
2001050900003	20010509	00003	SO  	2001	5	9	20010426CW016    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEAT BETWEEN FINS 14 AND 20.   CYLINDER SERIAL NUMBERS:  52J976779, 	 (52J976780),  52J976781,  52J976782,  52J976787,  52J976788.										3	O			E5CE				 
2001050300329	20010503	00329	SO  	2001	5	3	20010426CW017    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20.  CYLINDER SERIAL NUMBERS:  352J976779,	  52J976780,  (52J976781),  52J976782,  52J976787,  52J976788.										3	O			E5CE				 
2001050300330	20010503	00330	SO  	2001	5	3	20010426CW018    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20.   CYLINDER SERIAL NUMBERS:  52J976779,	  52J976780,  52J976781,  (52J976782),  52J976787,  52J976788.										3	O			E5CE				 
2001050300331	20010503	00331	SO  	2001	5	3	20010426CW019    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20.  CYLINDER SERIAL NUMBERS:  52J976779, 	 52J976780,  52J976781,  52J976782,  (52J976787),  52J976788.										3	O			E5CE				 
2001050900004	20010509	00004	SO  	2001	5	9	20010426CW020    	2	20010213	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1342 								CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20.  CYLINDER SERIAL NUMBERS:  52J976779, 	 52J976780,  52J976781,  52J976782,  52J976787,  (52J976788).										3	O			E5CE				 
2001050300332	20010503	00332	SO  	2001	5	3	20010426CW021    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 							CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT  TO INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDE	RS THESE WERE ALSO CRACKED ON THE EXHAUST SIDE , VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.   SERIAL NUMBERS:  (52L9769	47),  52L976948,  52L976949,  52L976950,  52L976957,  52L976958.									3	O			E5CE				 
2001050300333	20010503	00333	SO  	2001	5	3	20010426CW022    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 							CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER	S THSES WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.  SERIAL NUMBERS:  52L976947,  	(52L976948),  52L976949,  52L976950,  52L976957,  52L976958.									3	O			E5CE				 
2001050300339	20010503	00339	SO  	2001	5	3	20010426CW023    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 				240934R			CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR OR ADJACENT INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER	S THESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.  SERIAL NUMBERS:  52L976947,  	52L976948,  (52L976949),  52L976950,  52L976957,  52L976958.									3	O			E5CE				 
2001050300340	20010503	00340	SO  	2001	5	3	20010426CW024    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 				240934R			CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER	, THESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.  CYLINDER SERIAL NUMBERS:  52L	976947,  52L976948,  52L976949,  (52L976950),   52L976957,   52L976958.									3	O			E5CE				 
2001050300335	20010503	00335	SO  	2001	5	3	20010426CW025    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 				240934R			CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDERS T	HESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.										3	O			E5CE				 
2001050300336	20010503	00336	SO  	2001	5	3	20010426CW026    	2	20010205	G	8530	SA52000A20P	CYLINDER HEAD   								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	90193	1801 	1801 				240934R			CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT.  UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER	S THESE WERE ALSO CRACKED ON THE EXHAUST SIDE, VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20.  SERIAL NUMBERS:  52L976947, 	 52L976948,  52L976949,  52L976950,  52L976957,  (52L976958).									3	O			E5CE				 
2001050300141	20010503	00141	CE  	2001	5	3	20010430CW001    	1	20010327	G	2710	0400107159	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					AILERONS	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	93088	10573				15285398				DURING 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THE LEFT AILERON CROSSOVER CABLE HAD A BROKEN STRAND AT A POINT 63.5 	INCHES FROM THE TURNBUCKLE END.  BROKEN STRAND WAS WHERE CABLE PARTED OVER A RUB BLOCK ATTACHED TO RIB AT WING STA. 56.8	75.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001050300143	20010503	00143	CE  	2001	5	3	20010430CW002    	1	20010307	G	3230		LANDING GEAR    			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MAINS	MALFUNCTIONED   	D			BSYA	O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			GL	07	21ES					TH1123				AIRCRAFT COMING INTO AIRPORT, COULD NOT GET (3) GEAR DOWN AND LOCK LIGHTS.  FOUND GEAR INDICATOR LIGHT SWITCH IN DIM POS	ITION.  PILOT COULD NOT SEE LIGHTS IN DAY FLIGHT.  REPOSITIONED,  CYCLED GEAR OPS CHECKS GOOD.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001050300144	20010503	00144	CE  	2001	5	3	20010430CW003    	1	20010307	G	3230	08421043	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										NOSE GEAR	BROKEN          	D			BSYA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	6160X					310R1305				PILOT HEARD POPPING NOISE OUT OF GEAR,  WHEN GEAR WAS RETRACTED.  SELECTED GEAR DOWN AND DID A FLYBY.  TOWER SAID NOSE G	EAR HALF WAY DOWN, FLEW TO AIRPORT AND LANDED, NOSE GEAR COLLAPSED.  LIFTED AIRCRAFT ON TO RUNWAY.  NOSE GEAR SWUNG DOWN	 AND LOCKED,  ZERO RESISTANCE, FOUND BELLCRANK BROKEN WHERE FORK BOLT GOES THROUGH.				1	L	7	2 	3O			 	3A10    					 
2001050300148	20010503	00148	SO  	2001	5	3	20010430CW004    	2	20010430	G	8550		ENGINE          			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					NACELLE	LACK OF LUBE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	732UH					21061781				OWNER DISCOVERED A GREAT LOSS OF ENGINE OIL, FOLLOWING A COLD WEATHER FLIGHT.  TEMPERATURE WAS 40 DEGREES C/F.  AIR/OIL 	SEPARATOR INSTALLED PRIOR TO RECENT CYLINDER REPLACEMENT.					1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001050300001	20010503	00001	CE  	2001	5	3	20010430CW005    	1	20010329	G	8011	6462751	STARTER         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	90FC		396  			310R1838				THIS STARTER WAS SUPPLIED WITH A ZERO TIME OVERHAULED ENGINE.  THE ENGINE WAS INSTALLED JULY 20, 2000.  STARTER FAILED M	ARCH 23, 2001 AFTER ACCUMULATING ONLY 396.7 HOURS.  DID NOT DISASSEMBLE STARTER DUE TO WARRANTY.					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2001050300328	20010503	00328	CE  	2001	5	3	20010430CW008    	1	20010402	G	2910	244110010	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360A1D     	41514	EA  					RT MLG	BROKEN          	D			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9516B	2800 				172RG0847				WHILE ON CHECK RIDE, THE RIGHT MAIN LANDING GEAR FAILED TO EXTEND.  THE PILOT SUCCESSFULLY MANAGED TO LOCK THE GEAR IN P	LACE BY LAYING ON THE FLOOR BEHIND THE PILOTS SEATS, USING HIS HEAD TO HOLD DOOR OPEN, REACHING OUT AND PULLED GEAR INTO	 POSITION.  LANDED SAFELY.  FOUND THE SPLINED PART OF THE PIVOT HAD COMPLETELY TWISTED OFF FROM THE REST OF THE PIVOT.  	NO HISTORY OF ANY BRAKE PROBLEMS, NOR REPORTS OF HARD LANDINGS WERE MADE.  NO LEAKS WERE DETECTED WHILE PERFORMING THE A	NNUAL INSPECTION.		1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001050300265	20010503	00265	CE  	2001	5	3	20010430CW012    	1	20010402	G	7603		HOUSING         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320D2G     	41508	EA  					THROTTLE CABLE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	70323	3857 				17267200	L937739A			THROTTLE CABLE OUTER HOUSING DETERIORATED AND SEPARATED FROM SWEDGED FITTING AT CLAMP LOCATION AFT OF ENGINE.  THIS ALLO	WED THE OUTER HOUSING TO MOVE INSTEAD OF THE CARBURETOR CONTROL ARM AS THE THROTTLE CONTROL WAS MOVED.  RECOMMEND CABLE 	REPLACEMENT WHEN ANY INDICATION OF CRACKING IN THE OUTER HOUSING BECOMES VISIBLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001050100363	20010501	00363	CE  	2001	5	1	20010501AP004    	1	20010424	G	7830	23220258511	LEVER           	ARONCA      		RKWELL	NA265 	NA26580     	7630108	CE  										THRUST REVERSER	MISMANUFACTURED 	B			JV2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	316EC	369  	369  		144	38038				ON 8/9/99 1EA. P/N232-20258-511 WAS INSTALLED ON L/H T/R. 2EA. P/N 232-20258-513 AND 2EA. 232-20258-514 LEVERS WERE INST	ALLED ON R/H T/R DURING REPAIR OF THESE T/RS.  IN JAN. 2001 THE CUSTOMER REPORTED PROBLEMS WITH THE LT T/R. INSPECTION O	F BOTH T/RS REVEALED BROKEN DRIVE CABLES AND BENT LEVERS.  IT WAS BELIEVED AT THIS TIME THAT THE LEVERS WERE NOT PER DRA	WING AND REMAINING STOCK WAS RETURNED TO LEAR.  LEAR RETURNED THE LEVERS AS BEING MANUFACTURED PER DRAWING.  FURTHER INS	PECTION AND DISCUSSION WITH LEAR ON 4/23/01 REVEALED THE PREVIOUSLY MENTIONED LEVERS INSTALLED NEW 8-20-99 WERE NOT MANU	FACTURED IAW LEAR DRAWINGS.	2	L	7	2 	4F			 	A2WE    					 
2001050300046	20010503	00046	CE  	2001	5	3	20010501CW001    	1	20010207	G	2140		FUEL CAP        			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520F   	17032	SO  					HEATER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	12RJ	5280 				421C0306				FUEL LEAK AT HEATER FUEL FILTER ASSEMBLY IN RIGHT WING.  CAP ON TOP OF ASSEMBLY WAS FOUND TO HAVE CRACK IN THREADS.  CAP	 IS MADE OF ALUMINUM.  PART IS PRESUMED TO BE ORIGINAL EQUIPMENT.  NO KNOW DISASSEMBLY IN SERVICE HISTORY.  CAP WAS LOOS	E IN SPITE OF LOCK TAB STILL BEING INTACT.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001050300112	20010503	00112	NE  	2001	5	3	20010501CW006    	2	20010313	G	8530	212359	CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 2 ENGINE	CRACKED         	G			ZMIG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07	5076					1111	11091			NO RECORDS ON  CYLINDERS.  AIRCRAFT LOST POWER AFTER TAKE OFF AND LANDED LONG, RAN INTO WOODS (DESTROYED AIRCRAFT)  PILO	T UNHURT.  INVESTIGATION REVEALED NR 2 ENGINE CYLINDER VAS CRACKED FROM THE INTAKE VALVE HOLE TO SPARK PLUG HOLE,  ALMOS	T COMPLETELY AROUND THE CYLINDER.				1	Q	7	1 	3R	3	R	 	1A16    	5E2				 
2001050300116	20010503	00116	SO  	2001	5	3	20010501CW007    	1	20010406	G	5210		LATCH           			PIPER 	PA23  	PA23160     	7102304	SO  	LYC   	O320  	O320*       	41508	EA  					PAX DOOR	INOPERATIVE     	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	333PE					232007				DOOR CAME OPEN IN FLIGHT CAUSING AIRCRAFT TO LOOSE DIRECTIONAL CONTROL.  GROUND INVESTIGATION REVEALED THAT LATCH MECHAN	ISM WAS NOT LOCKING PROPERLY AT THE JAMS.					1	L	7	2 	3O	3	O	 	1A10    	E274				 
2001050300201	20010503	00201	CE  	2001	5	3	20010501CW014    	1	20010413	G	3000		SWITCH          	ASC         		BEECH 	35    	B35         	1151506	CE  										LT BRAKE	INOPERATIVE     	B			LX5R	O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			GL	19	171CP				0854A	FL244				LEFT BRAKE DEICE VALVE, SHOWING ITT RISE,  LIGHT NOT ILLUMINATING.  LIGHT SYSTEM CHECKS GOOD.  BAD SWITCH ON VALVE.						1	L	7	1 	3O			 	A777    					 
2001050300202	20010503	00202	CE  	2001	5	3	20010501CW015    	1	20010412	G	3000		SWITCH          	ASC         		BEECH 	B300  	B300        	1159232	CE  										LT BRAKE	INOPERATIVE     	B			LX5R	O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			GL	19	971LL				0831A	FL267				LEFT BRAKE DEICE VALVE INDICATING LIGHT CIRCUIT OPEN IN VALVE.						2	L	7	2 	4T			RT	A24CE   					 
2001050300203	20010503	00203	CE  	2001	5	3	20010501CW016    	1	20010406	G	7160	075014433	AIR BOX         			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	1408M	113  				18264319	226296R			DURING ANNUAL INSPECTION, IT WAS NOTED THAT THE RIVETS THAT SECURE THE CARB HEAT VALVE PLATE TO THE CONTROL CROSS SHAFT 	WER COMING LOOSE.  THIS APPEARS TO HAVE BEEN CAUSE BY SEALING MATERIAL ON THE VALVE PLATE WHICH WAS NOT CORRECTLY TRIMME	D.  AS A RESULT, THE MATERIAL WOULD BIND IN A CARB HEAT NEEDED POSITION, MAKING IT DIFFICULT TO RETURN THE VALVE TO A NO	 CARB HEAT POSITION.			1	H	7	1 	3O	3	O	NT	TA13    	E273				 
2001050300204	20010503	00204	CE  	2001	5	3	20010501CW017    	1	20010501	G	2720	12604567	RUDDER BAR      			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520*      	17032	SO  					RUDDER PEDALS	DAMAGED         	B			CL4R	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AL	03	9497R	3102 				U20606876				PILOT SIDE LEFT RUDDER PEDAL COLLAPSED IN FLIGHT.  SAFECOM FILED.  APPEARS THAT TORQUE TUBE MAY HAVE BEEN DAMAGED BY MAI	NTENANCE WHEN BUSHING WAS INSTALLED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001050300206	20010503	00206	SO  	2001	5	3	20010501CW019    	2	20010303	G	8530	SA52000A1	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					NR 3	DESTROYED       	B			O3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		96   	96   				563729			NR 3 CYLINDER AND PISTON ASSEMBLY.  REMOVED DUE TO LOW COMPRESSION AND COMPLAINT FROM PILOT OF RUNNING ROUGH.  PISTON AP	PEARS TO HAVE SEVERE PREIGNITION OR DETONATION.										3	O			E5CE				 
2001050300207	20010503	00207	CE  	2001	5	3	20010501CW020    	1	20010412	G	2421	635796	COUPLING        	ELECTROSYS  		CESSNA	172   	R172E       	2072413	CE  	CONT  	IO360 	IO360*      	17025	CE  					ALTERNATOR DRIVE	SLIPPED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	7907N				B022733	R1720298	239770R			AT ENGINE CHANGE, FRESH OVERHAUL ALT INSTALLED AFTER 9.0 HOURS OF OPERATION NOTED ERATIC ALTERNATOR  OUTPUT.  INSPECTED 	ALTERNATOR AND DETERMINED ALTERNATOR DRIVE COUPLING SLIPPING.  REPLACED ALTERNATOR DRIVE COUPLING WITH OVERHAULED LIKE I	TEM AND REINSTALLED ALTERNATOR ON AIRCRAFT.				1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2001050300209	20010503	00209	CE  	2001	5	3	20010501CW022    	1	20010412	G	3710	632617D	BEVEL GEAR      	CONT        		CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360GB     	17025	SO  					VACUUM PUMP	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	726AS	725  			7509	33701661	813014R			A DETAILED INVESTIGATION OF THE STARTER DEIVE REVEALED THAT ALL TO THE GEAR TEETH WERE WORN EXCESSIVELY ON ONE OF THE BE	VEL GEARS WHICH DRIVES THE VACUUM PUMP.  THIS IS THE FIFTH FAILURE OF THIS GEAR THAT WE HAVE DETECTED.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001050300210	20010503	00210	SW  	2001	5	3	20010501CW023    	1	20010128	G	3213	530021000	DISK            			MOONEY	M20   	M20D        	5870210	SW  	LYC   	O360  	O360*       	41514	EA  					MLG STRUT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	1923Y					218				MAIN LANDING GEAR SHOCK DISCS WERE FOUND TO BE COMPRESSED BEYOND LIMITS.  WHEN CHECKED PER THE MANUAL INSTEAD OF .1250 M	AX CLEARANCE THER WAS .3750 INCH OF CLEARANCE.  ALSO FOUND AN INCORRECT FITTING INSTALLED ON LEFT BRAKE THAT ALLOWED THE	 BRAKE HOSE TO INTERFEAR WITH THE INNER GEAR DOOR.				1	L	7	1 	3O	3	O	 	2A3     	E286				 
2001050300236	20010503	00236	SO  	2001	5	3	20010502CW001    	1	20010305	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG INNER DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	555FS	5393 				317952046				INSPECTED HINGES,  ONLY FORWARD HINGES ON BOTH DOORS HAD CRACKS ON INNER RADIUS APPROX .1250 TO .1875 INCH DEEP.  REAR H	INGES WERE NOT CRACKED,  REPLACED ALL FOUR HINGES.  SUSPECT CRACKS ARE CAUSED DUE TO LOCATION OF HYD ACTUATOR FORWARD OF	 FORWARD HINGE, CAUSING MORE STRESS ON FORWARD HINGE THAN ON REAR HINGE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001050300247	20010503	00247	SW  	2001	5	3	20010502CW005    	1	20010402	G	6210	204011250113	BLADE           			BELL  	204   	UH1H        	1181407	SW  	LYC   	T53   	T53*        	41549	NE  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	340WN	2500 	1648 			6510081	LE17065BA			A CRACK WAS NOTICED INSIDE DENT AFT OF THE SPAR ON THE TOP OF THE MAIN ROTOR BLADE.  REMOVAL OF PAINT DETERMINED THE CRA	CK TO BE IN EXCESS OF 6 INCHES LONG.  THE ROTOR BLADE WAS DETERMINED TO BE UNSERVICEABLE AND REMOVED FROM SERVICE.					1	G	7	1 	4U	4	U	 	EXPA1G71	E1EA				 
2001050300023	20010503	00023	EU  	2001	5	3	20010502CW009    	1	20010106	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350B3     	8680954	EU  										STARFLEX	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	505  				3251				WORN BEYOND SERVICEABLE LIMITS.  REMOVED AND REPLACED WITH NEW UNIT,  CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001050300389	20010503	00389	NE  	2001	5	3	20010502CW010    	1	20010320	G	7810		EXHAUST PIPE    			SKRSKY	S76   	S76A        	8143006	NE  										RIGHT	MISALIGNED      	B			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	5444X					760174				THE EXHAUST ASSEMBLY WAS SENT TO A REPAIR STATION FOR OVERHAUL.  UPON REINSTALLATION IT WAS FOUND THAT THE RIGHT HAND EX	HAUST PIPE CONTACTED THE NR 5 CYLINDER INTAKE PIPE.					1	G	7	2 	3U			 	H1NE    					 
2001050300211	20010503	00211	CE  	2001	5	3	20010503CW004    	1	20010404	G	5310	05110006	DOOR FRAME      			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  					FUSELAGE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	08	3658S	3222 				17250858	24144DOD			FUEL LINES RUBBING AND STRESSED DUE TO UPPER OUTBOARD DOOR FRAME PARTIALLY COVERING HOLE AND NOT ALLOWING CLEARANCE FOR 	FUEL LINE.  CAUSE BY HOLE IN UPPER OB DOOR FRAMES NOT BEING CUT OUT TO ORIGINAL SIZE FOR CLEARANCE BY MFG.  RECOMMENDATI	ON IS TO ROUND OUT HOLE TO ORIGINAL OPENING TO ACCOMMODATE FUEL LINE.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2001050300213	20010503	00213	CE  	2001	5	3	20010503CW005    	1	20010404	G	5310	05110007	DOOR FRAME      			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300D       	17022	SO  					FUSELAGE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	08	3658S	3222 				17250858	24144DOD			FUEL LINES RUBBING AND STRESSED DUE TO UPPER OUTBOARD DOOR FRAME PARTIALLY COVERING HOLE AND NOT ALLOWING CLEARANCE FOR 	FUEL LINE.  CAUSED BY THE HOLE IN DOOR FRAMES NOT BEING CUT OUT TO ORIGINAL SIZE FOR CLEARANCE BY MFG.  RECOMMENDATION I	S TO ROUND OUT HOLES TO ORIGINAL OPENING TO ACCOMMODATE FUEL LINE.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2001051500061	20010515	00061	EA  	2001	5	15	20010503CW013    	2	20010503	G	7414	4381	MAGNETO         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					LEFT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	20421					17261276				PLASTIC SUPPORT FOR POINTS BROKEN, AND POINTS FAILED,  FACTORY SEAL STILL ON MAGNETO.  PILOT REPORTED ENGINE RUNNING ROU	GH.  MADE SAFE LANDING, CHECKED GOOD WITH REPLACEMENT MAGNETO.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001051500080	20010515	00080	NE  	2001	5	15	20010504CW002    	2	20010227	G	7200	P2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED ON BOTTOM OF PART (SIDE OF BOSS).											4	F			E311NE				 
2001051500082	20010515	00082	NE  	2001	5	15	20010504CW003    	2	20010329	G	7200	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED ON AREA ADJACENT TO BOSS.											4	F			E311NE				 
2001051500088	20010515	00088	NE  	2001	5	15	20010504CW006    	2	20010216	G	7230	787008	COMPRESSOR WHEEL								PWA   	JT8   	JT8D9A      	52048	NE  					8TH STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		26811					666322			AFTER ENGINE DISASSEMBLE, DURING INSPECTION ON EIGHTH STAGE DISK, A CRACK WAS DETECTED IN ONE OF THE TIE ROD HOLES.  CRA	CK EXTENDED RADIALLY OUTBOARD FROM THE HOLE TO DEPTH OF 0.35 IN., DUE TO OXIDATION AND HEAVY CORROSION.    IN ORDER TO H	AVE MORE INFORMATION, PART WAS SENT TO OEM FOR EVALUATION.  PART WILL BE LOCALLY SCRAPPED.									4	F			E2EA				 
2001051500091	20010515	00091	EA  	2001	5	15	20010504CW008    	2	20010330	G	7200	LW14820	SNAP RING       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					COUNTERWEIGHT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	78GH					317852121	L247368A			THIS ENGINE WAS RECEIVED ON 2/21/01 DUE TO A HOLE IN TOP OF ENGINE.  DURING DISASSEMBLY IT WAS NOTED THAT THE CRANKSHAFT	 WAS BROKEN AT THE NR 1 ROD JOURNAL.  THE SNAP RING AND PIN WERE MISSING FROM ONE OF THE COUNTERWEIGHTS.  THE PIN UPON C	OMING OUT WAS PINCHED BETWEEN THE NR 2 CONNECTING ROD AND CONNECTING ROD HAD THE CAP PULLED OFF FROM DEBREE FLYING AROUN	D IN THE ENGINE.  THE SNAP RING DID NOT HAVE ENOUGH TENTION TO KEEP IT EXPANDED IN PLACE ALLOWING IT TO COME OUT AND CAU	SE CATASTROPHIC ENGINE FAILURE.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001051500092	20010515	00092	SW  	2001	5	15	20010504CW009    	1	20010320	G	3260	880013507	SWITCH          			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3D6D  	41514	EA  					AIRSPEED	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	923DH	819  	819  			243368	L2671551A			A/S SWITCH FAILED F/T 32-30-01, SWITCH WAS REMOVED AND SENT TO OEM VENDOR. SWITCH WAS PARTED FROM MOUNT.  SWITCH WAS EXP	OXED TO MOUNT AND RECALIBRATED.  THE SWITCH WAS REINSTALLED AND PASSED.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001051500118	20010515	00118	SO  	2001	5	15	20010507CW001    	2	20010405	G	8550	C1650010102	SEPARATOR       			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470*       	17026	SO  					AIR/OIL	CONTAMINATED    	B			ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3495S	5686 				18255895				OIL FILTER INSPECTION REVEALED EXCESSIVE AMOUNT OF CONTAMINATION.  INVESTIGATION REVEALED AIR/OIL SEPERATOR INTERNAL SCR	EEN COMING APART.  YEARS OF VIBRATION MAY HAVE CAUSED SCREEN SEPARATION.  FACTORY RECOMMENDS 100 HOURS CLEANING.  THERE 	IS NO WAY TO INSPECT UNIT WITHOUT CUTTING IT OPEN.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001051500119	20010515	00119	CE  	2001	5	15	20010507CW003    	1	20010418	G	2421	99105921	ALTERNATOR      			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	456BR	15   				P21000717				AIRCRAFT UNDER IMC WHEN LOW VOLT LIGHT CAME ON AND VOLTAGE DROP TO 23.0 VOLTS.  PILOT SHUT EVERYTHING OFF AND DECLARED A	N EMERGENCY WITH CASCADE APPROACH.  LANDED WITHOUT INCIDENT.  PART WAS UNDER WARRANTY SO COULD NOT DISASSEMBLE TO FIND O	UT CAUSE OF FAILURE, PART IS PROPRIETARY FOR MFG.				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001051500120	20010515	00120	SO  	2001	5	15	20010507CW004    	2	20010413	G	7322	6397172	FUEL CONTROL    			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550D      	17042	SO  					CONTROL ARM	DEFECTIVE       	B			T9ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		280  								AIRCRAFT WAS INSPECTED FOR FUEL SYSTEM PROBLEMS.  IT WAS DISCOVERED THAT THE CONTROL ARM ON THE THROTTLE BODY WAS SHIPPI	NG ON THROUGH SHAFT.  THIS CONDITION DID CAUSE THE AIRCRAFT TO ENCOUNTER A STOCK THROTTLE CONDITION, IN THE FULL THROTTL	E POSITION.				1	H	7	1 	3O	3	O	 	3A24    	E3SO				 
2001051500128	20010515	00128	CE  	2001	5	15	20010507CW010    	1	20010423	G	5521		SPAR            			CESSNA	188   	A188B       	2073005	CE  	CONT  	O520  	IO520*      	17032	SO  					RT ELEVATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	731CS					18802796T				FOUND RIGHT ELEVATOR SPAR CRACKED AT OUTBOARD ATTACH POINT.  HORIZONTAL STABILIZER HAD PREVIOUS REPAIRS WERE LOCATED DIR	ECTLY FORWARD OF CRACK IN ELEVATOR SPAR.					1	L	7	1 	3O	3	O	 	A9CE    	E5CE				 
2001051500144	20010515	00144	CE  	2001	5	15	20010507CW020    	1	20010329	G	5753	05239016	SKIN            			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					LEFT TE FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	476SP	1168 				M2S8022				DURING A PHASE 2 INSPECTION PERFORMED, SEVERAL CRACKS WERE NOTICED ON THE TRAILING EDGE RIVETS ON THE LOWER LEFT FLAP SK	IN, AT APPROX 2-3 FEET FROM THE INBOARD EDGE.  6 RIVETS HAD CRACKS STARTING TO FORM FROM THEM.  THE CRACKS ARE ABOUT .12	50 TO .2500 OF AN INCH LONG.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001051600408	20010516	00408	CE  	2001	5	16	20010508CW002    	1	20010508	G	2750	26111447	BRACKET         			CESSNA	208   	208B        	2073701	CE  										FLAP	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	64BP	3789 				0604				PRIMARY FLAP MOTOR DRIVE COUPLER FAILED.  STAND BY SYSTEM USED TO EXTEND FLAPS.  FLAP LIMIT SWITCHES NOT INCORPORATED IN	 STAND BY SYSTEM.  OPERATIONAL SWITCH OF STAD BY SYSTEM HELD TOO LONG AND FLAP MOTOR CONTINUED TO RUN PAST LIMIT SWITCH 	LOCATION AND TWISTED FLAP DRIVE ASSEMBLY OUT OF MOUNTING BRACKET.  RECOMMENDATION, PILOT BE MORE AWARE OF SYSTEM OPERATI	ON OR INCORPORATE SWITCHES INTO STAND-BY SYSTEM.			1	H	7	1 	3T			 	A37CE   					 
2001051600409	20010516	00409	EU  	2001	5	16	20010508CW003    	1	20010412	G	2121	M3348A	MOTOR           	DYNAIR      		SAAB  	SF340 	SF340A      	7850100	EU  										FAN	INOPERATIVE     	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	05					162					ARMATURE ASSEMBLY SHOWS SIGNS OF AN INTERFERENCE FIT.  RECOMMEND OVERHAUL ONLY TO APPROVED OVERHAUL MANUAL USING ONLY AP	PROVED PARTS.					2	L	7	2 	4T			RT	A52EU   					 
2001051600547	20010516	00547	EU  	2001	5	16	20010508CW004    	1	20010412	G	2121	M3348A	MOTOR           	DYNAIR      		SAAB  	SF340 	SF340A      	7850100	EU  										FAN	WRONG PART      	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					170					FAN RETURNED TO MFG FOR UPGRADE TO C209-6901 CONFIGURATION, THE FAN WAS TESTED AND FOUND TO EXHIBIT EXCESSIVE VIBRATION.	  WHEN THE FAN WAS DISASSEMBLED, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED PER MFG OVERHAUL MA	NUAL.  THE ARMATURE AND STATOR FIELD WINDINGS ARE NOT OF MFG DESIGN.  MFG OVERHAUL MANUAL DOES NOT ALLOW FOR REWINDING O	F THE ARMATURE OR FIELD WINDINGS.  THE ARMATURE ASSY HAS NUMBERS STAMPED INTO IT, WHICH CAUSES AN OUT OF ROUND CONDITION	.  ARMATURE HAS A COMMUTATOR THAT IS NOT MFG PART INSTALLED ON IT.  THE IMPELLER IS AT THE WRONG LOCATION, CAUSING IT TO	 RUB AGAINST THE FRONT END BELL.  THE FIELD WINDINGS HAVE A THERMAL SWITCH ADDED THAT IS NOT PER OVERHAUL MANUAL.	2	L	7	2 	4T			RT	A52EU   					 
2001051600548	20010516	00548	EU  	2001	5	16	20010508CW005    	1	20010412	G	2121		MOTOR           	DYNAIR      		SAAB  	SF340 	SF340A      	7850100	EU  										FAN	UNAPPROVED PART 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					174					MOTOR ASSEMBLY IS NOT A DYNAMIC AIR ENGINEERING PART.   MOTOR ASSEMBLY DOES NOT MEET DAE DRAWING AND OVERHAUL MANUAL REQ	UIREMENTS.					2	L	7	2 	4T			RT	A52EU   					 
2001051600552	20010516	00552	EU  	2001	5	16	20010508CW006    	1	20010412	G	2121	M3348A	MOTOR           	DYNAIR      		SAAB  	SF340 	SF340A      	7850100	EU  										FAN	UNAPPROVED PART 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					225					FAN RETURNED TO DAE FOR UPGRADE TO C209-690D CONFIGURATION.  THE FAN WAS TESTED AND FOUND TO EXHIBIT EXCESSIVE VIBRATION	.  WHEN THE FAN WAS DISASSEMBLED, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED PER THE DAE OVERHA	UL MANUAL.  THE ARMATURE AND STATOR FIELD WINDING ARE NOT OF DAE DESIGN.  DAE OVERHAUL MANUAL DOES NOT ALLOW FOR THE REW	INDING  OF THE ARMATURE OR FIELD WINDINGS.   THE ARMATURE ASSY HAS AN OVERSIZE COMMUTATOR INSTALLED WHICH MAKES THE BRUS	HES EXTEND PAST THE DESIGNED LIMIT, THE IMPELLER IS AT THE WRONG LOCATION, AND ARMATURE IS NOT BALANCED.  THE FIELD WIND	INGS ARE REWOUND AND HAVE UNACCEPTABLE AIR GAP.	2	L	7	2 	4T			RT	A52EU   					 
2001051600553	20010516	00553	SO  	2001	5	16	20010508CW008    	2	20010402	G	7414	M1176	FRAME           	SLICK       		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					MOUNTING FLANGE	CRACKED         	B			QY5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	232MT				1010441	U20606200	520356			OBSERVED AN OIL LEAK FROM MAG BASE.  FOUND MOUNTING FLANGE CRACKED AROUND LOWER CLAMPING WASHER.  REMOVED MAG AND FOUND 	APPROX 2 INCH PIECE OF MOUNTING FLANGE BROKEN OFF.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001051600421	20010516	00421	SO  	2001	5	16	20010508CW009    	2	20010402	G	7414	M3975	COIL            	SLICK       		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					MAGNETO	INOPERATIVE     	B			QY5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	232MT				89070161	U20606200				MAGNETO INOPERATIVE BELOW 1,000 RPMS.  OK AT 1,700 RPMS PER THE P.O.M.   PILOTS HAD DONE A MAG CHECK AT IDLE WHICH LEAD 	TO THE DISCOVERY.  OPENED MAGNETO FOR INSPECTION.  TESTED COIL AND FOUND SECONDARY WINDING.  RESISTANCE TOO HIGH BY FACT	OR OF 10.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001051500171	20010515	00171	SW  	2001	5	15	20010508CW013    	1	20010416	G	6730	41001554	HOUSING         			BELL  	214   	214B        	1182100	SW  										SERVO ACTUATOR	GOUGED          	B			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										GOUGE PLUS LINER IND. BELOW GOUGE.						2	G	7	1 	4U			 	H6SW    					 
2001052300019	20010523	00019	CE  	2001	5	23	20010508CW016    	1	20010413	G	3233	98820041	PISTON          			CESSNA	172   	172RG       	2072438	CE  										MLG ACTUATOR	BROKEN          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	9985B	10388				172RG1107				PISTON IN MAIN GEAR ACTUATOR BROKEN AT SECOND TOOTH FROM END.  THIS LEFT GEAR TO SWING FREELY, NOT LOCKING DOWN.						1	H	7	1 	3O			 	3A17    					 
2001052300023	20010523	00023	SO  	2001	5	23	20010508CW019    	2	20010413	G	7322	6397172	THROTTLE BODY   			CESSNA	188   	188B        	2073007	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	OUT OF ADJ      	B			T9ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	731CS	280  	280  			18802796T				THROTTLE BODY AND METERING UNIT WAS FOUND TO BE OUT OF ADJUSTMENT, DURING INSPECTION THE CONTROL ARM AT THROTTLE BODY WA	S FOUND LOOSE AND ROTATING ON SHAFT.  NO ADJUSTMENT OF IDLE MIXTURE OR IDLE COULD BE PERFORMED DUE TO CHANGING CONDITION	 BETWEEN THROTTLE BODY AND METERING UNIT.				1	L	7	1 	3O	3	O	 	A9CE    	E5CE				 
2001052400131	20010524	00131	SO  	2001	5	24	20010509CW002    	1	20010326	G	2740	6270147	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  										STABILIZER	OUT OF RIG      	B			H1ES	O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			NE	01	2145M	460  	290  			28R7837069				TRIM CABLE JACKSCREW STOP PIN NOT CONTACTING TRIM DRUM BEFORE TURNBUCKLE FERRULE REACHING AFT PULLEY AND CABLE GUARD, PR	EVENTING CABLE FROM MOVING.  AC WAS IN FULL NOSE TRIM CONDITION, AC LANDED WITHOUT INCIDENT.  TRIM CABLES WERE RE-RIGGED	.				1	L	7	1 	3O			 	2A13    					 
2001052400004	20010524	00004	SW  	2001	5	24	20010509CW009    	1	20010413	G	5711		SPAR            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C9012F      	17009	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	62667					7FC326	46889912			IN RECOVERING AIRFRAME, FOUND CRACK IN RIGHT WING REAR SPAR.  AIRCRAFT WRECKED IN A NOSE OVER.  NO LOG RECORD OF REPAIR 	TO REAR SPAR.					1	H	7	1 	3O	3	O	 	A759    	E252				 
2001051000001	20010510	00001	CE  	2001	5	10	20010510AP001    	1	20010424	G	7830	23220258511	LEVER           	ARONCA      		RKWELL	NA265 	NA26580     	7630108	CE  										THRUST REVERSER	MISMANUFACTURED 	B			JV2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	316EC	369  	369  		144	38038				ON 8/9/99 1EA. P/N232-20258-511 WAS INSTALLED ON LT T/R. 2EA. P/N 232-20258-513 AND 2EA. 232-20258-514 LEVERS WERE INSTA	LLED ON RT T/R DURING REPAIR OF THESE T/R''''S.  IN JAN. 2001 THE CUSTOMER REPORTED PROBLEMS WITH THE LT T/R. INSPECTION	 OF BOTH T/RS REVEALED BROKEN DRIVE CABLES AND BENT LEVERS.  IT WAS BELIEVED AT THIS TIME THAT THE LEVERS WERE NOT PER D	RAWING AND REMAINING STOCK WAS RETURNED.			2	L	7	2 	4F			 	A2WE    					 
2001051000002	20010510	00002	CE  	2001	5	10	20010510AP002    	1	20010309	G	3240	ACM22740	VALVE           			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					MLG	CONTAMINATED    	C				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	11	1650	526  								NR 1 TIRE FLAT SPOTTED, NR 2 TIRE FLAT SPOTTED AND DEFLATED, NR 3 TIRE FLAT SPOTTED. VISUAL INSPECTION FOUND NR 1 MODULA	TOR VALVE CONTAMINATED WITH PAINT CHIPS AND SHAVINGS OF PLASTIC. FOUND  NR 2 MODULATOR VALVE PISTON O-RING DECOMPOSED/CO	NTAMINATED. REPLACED NR 1 AND 2 MODULATOR VALVE, BRAKE CONTROL VALVE, FLUSHED ENTIRE BRAKE SYSTEM HYDRAULIC LINES AND FU	NCTIONALLY TESTED BRAKE CONTROL SYSTEM.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001051000003	20010510	00003	NM  	2001	5	10	20010510AP003    	1	20010425	G	3240		LINE            			AMD   	FALC50	FALCON2000  	2730170	NM  										BRAKE SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	11	120HG	15   				200055				RIGHT MLG BRAKE LINE WAS FOUND LEAKING FROM THE B NUT THAT CONNECTS THE LINE TO THE BRAKE CALIPER FITTING. THE BRAKE LIN	E IS MADE OF CLEAR PLASTIC TUBING AND THE B NUT IS BRASS AND UTILIZES A BRASS COMPRESSION FITTING TO FORM THE SEAL AT TH	E CALIPER FITTING. SUSPECT THE LEAK IS DUE TO THERMAL EXPANSION OF PLASTIC AND BRASS CAUSED BY ELEVATED BRAKE TEMPERATUR	ES DURING SHORT FIELD BRAKING. SUGGEST THAT PLASTIC TUBING AND BRASS FITTINGS BE REMOVED AND REPLACED WITH AN STANDARD F	ITTINGS AND MEDIUM PRESSURE HOSE THAT MEETS THE APPROPRIATE MIL SPEC.		2	K	7	3 	4F			RT	A50NM   					 
2001051000004	20010510	00004	NM  	2001	5	10	20010510AP004    	1	20010425	G	5210		DOOR            			AMD   	FALC50	FALCON2000  	2730170	NM  										PAX	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	120HG	15   				200055				FOUND INSTRUMENTS AND RADIO DISPLAYS FOGGED OVER DUE TO CABIN WATER-LEAKS. LEAKS FOUND AROUND CABIN DOOR. SUSPECT LEAKAG	E DUE IMPROPER DOOR ALIGNMENT AND/OR SEALING DURING MAUFACTURING. THIS CONDITION IF NOT CORRECTED WILL CAUSE PREMATURE C	ORROSION OF THE AIRCRAFT AND ELECTRICAL MALFUNCTION OF THE AVIONICS AND INSTRUMENTATION AS WELL AS DETERIORATION OF THE 	CABIN INTERIOR. SUBMITTER HAS OBSERVED THIS DISCREPANCY ON OTHER LIKE MODELS OF THIS AIRCRAFT.			2	K	7	3 	4F			RT	A50NM   					 
2001051000005	20010510	00005	CE  	2001	5	10	20010510AP005    	1	20010104	G	3242	AC65218	MAXARET         			RAYTHN	DH125 	HAWKER800   	7450004	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					WHEEL AXLE	INOPERATIVE     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	1640	788  				258376				NR 1 AND 2 TIRES FOUND FLAT SPOTTED DURING POST-FLIGHT INSPECTION. NR 1 MAXARET UNIT DID NOT PASS ANTI-SKID FUNCTIONAL T	EST.  REPLACED NR 1 MAXARET UNIT WITH OVERHAULD UNIT.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001051000006	20010510	00006	CE  	2001	5	10	20010510AP006    	1	20010426	G	7810	1099500001	EXHAUST PIPE    	PWC         		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2354Y	546  				LJ1532	PE0179			THE LEFT ENGINE LEFT TAIL PIPE BROKE AT THE LIP HEAT INLET TUBE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2001051000007	20010510	00007	GL  	2001	5	10	20010510AP007    	1	20010327	G	3213		ATTACH FITTING  			AVIAT 	A1    	A1B         	       	GL  	LYC   	O360  	O360*       	41514	EA  					LT MLG STRUT	SHEARED         	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	03	484C					2114				TACH 80.2 HOURS LEFT MAIN GEAR ATTACHMENT(FORWARD STRUT) SHEARED OFF AT FUSELAGE ATTACHMENT POINT DURING NORMAL LANDING 	OF AIRCRAFT. THE WELDED AREA THAT THE LH FORWARD STRUT ATTACHES TO THE FRAME LOOKS TO HAVE POSSIBLE INADEQUATE PENETRATI	ON, POROUS AND CONSIDERED A COLD WELD.				1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2001051000008	20010510	00008	EA  	2001	5	10	20010510AP008    	1	20010427	G	3040	F307	RESISTOR        			DHAV  	DHC6  	DHC6300     	2802606	EA  										WINDSHIELD WIPER	BURNED          	M				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			SW	99						680				WINDSHIELD WIPER DROPPING RESISTOR SHORTED TO GROUND THROUGH DEACTIVATED WINDSHIELD WASHER RESISTOR MOUNT. THE WIPER DRO	PPING RESISTOR LEAD CHAFFED ON THE WINDSHIELD WASHER RESISTOR MOUNTING BRACKET. THIS RESULTED IN SMOKE IN THE COCKPIT DU	RING DESCENT WHILE USING WINDSHIELD WIPERS IN THE SLOW MODE.  DEHAVILLAND MODIFICATION (MOD 6/1827)DEACTIVATED THE WINDS	HIELD WASHER OPTION BY REMOVING THE WASHER SWITCH FROM THE OVERHEAD PANEL AND STOWING OR CAPPING THE POWER WIRE TO THE W	ASHER RESISTOR.		1	H	7	2 	3T			RT	A9EA    					 
2001052900001	20010529	00001	SO  	2001	5	29	20010510CW001    	1	20010308	G	2740	69623004	TUBE            			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320*       	41508	EA  					STABILIZER	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	567OU					2826467				ON THE TUBE, WHERE BOLT HOLE IS DRILLED THAT MOUNTS TO THE FRONT BRACKET ON STABILATOR, A HOLE IS IN TUBE, (90 DEGREE AN	GLE TO THE BOLT HOLE).  IT APPEARS THIS HOLE HAS SLAG IN IT AND SLAG EXIST ON INTERIOR OF THE TUBE THAT HAS BEEN THERE W	HEN THE PART WAS FABRICATED.  THIS EXTRANEOUS HOLE IS AT THE HIGH STRESS POINT IN THE TUBE AND HAS NOT BEEN ON ANY OF TH	E TUBES THAT HAVE BEEN INSPECTED FOR THE AD ON THE TUBES.   HOLE WAS FOUND WHEN REMOVING THE THICK LAYER OF BLACK PAINT 	DOWN TO THE ZINC CHROMATE IN AREA THAT FITS INTO THE STABILATOR BRACKETS.  THE AREA FIRST APPEARED AS A BLACK DOT OF PAI	NT AND CLOSER EXAMINATION REVEALED A HOLE HAD BEEN DRILLED AND FILLED WITH SOME TYPE OF MATERIAL AND PAINTED TO COVER.	1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001052400077	20010524	00077	SO  	2001	5	24	20010511CW002    	1	20010417	G	3222	6528000	FORK            			PIPER 	PA28  	PA28181     	7102807	SO  										NLG STRUT	SHEARED         	D			EEJA	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	07	8285Y					288190023				THE AIRCRAFT WAS DOING A TOUCH AND GO, WHEN THE NOSE WHEEL STARTED TO SHIMMY.  THE NOSE WHEEL FORK SHEARED OFF FROM THE 	LOWER STRUT TUBE.   COULD NOT TELL IF THERE WAS A PREVIOUS CRACK IN THE TUBE.					1	L	7	1 	3O			 	2A13    					 
2001052400078	20010524	00078	NE  	2001	5	24	20010511CW003    	2	20010425	G	7250	2A0847	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01										PART RECEIVED FOR PENETRANT INSPECTION.  PART REJECTED AT PENETRANT INSPECTION FOR INDICATION IN COUNTERBORE.											4	F			E311NE				 
2001052400133	20010524	00133	EA  	2001	5	24	20010511CW005    	2	20010501	G	8520		CRANKCASE       			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ENGINE	CRACKED         	B			BONR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19	8314B	2077 				32R8129021	L748061A	FM183		DURING ANNUAL INSPECTION, NOTICED OIL ON LEFT FORWARD SECTION OF ENGINE.  REMOVED PROP GOVERNOR AND ENGINE BAFFLING.  FO	UND SMALL CRACK IN CRANKCASE,  FORWARD OF NR 2 CYLINDER UPPER FORWARD HOLD DOWN NUT.  CONDITION PROBABLY CAUSED BY AGE, 	ENGINE HAS NEVER BEEN OVERHAULED.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P25EA	 
2001051500332	20010515	00332	EU  	2001	5	15	20010511CW007    	1	20010419	G	6520	369025400	GEARBOX         			HUGHES	369   	369FF       	       	EU  	ALLSN 	250C  	250C30      	03013	GL  					TAIL ROTOR	FAILED          	B			E6HR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	01	530HL	10003	1666 			0066FF				UPON SHUT DOWN, THE PILOT AND MECH NOTICE AN ODD NOISE COMING FROM THE TAIR ROTOR ACCOMPANIED BY A SLIGHT VIBRATION.  AI	RCRAFT WAS DUE FOR A 100 HR INSPECTION, SO T/R OIL WAS DRAINED AGAIN.  THE CHIP PLUG HAD NO CHIPS BUT DID HAVE A BLACK P	ASTE.  PASTE WAS EXAMINED AND HAD EXTREMELY SMALL METALLIC PARTICLES IN IT.  NOT ENOUGH TO ILLUMINATE CHIP LIGHT.  GEARB	OX WAS DISASSEMBLED FOR INSPECTION.  INPUT GEAR SHAFT WAS FOUND TO BE SHEARED IN TWO PIECES.  IT IS NO UNDERSTOOD WHY TH	E GEARBOX DID NOT COMPLETELY FAIL BECOMING CATASTROPHIC.  AIRCRAFT FLEW 3.5 HRS THIS DAY WITH NO EVIDENCE OF A PROBLEM. 	 GEARSHAFT HAS BEEN SENT TO A LAB FOR TESTING AND MDHC HAS BEEN INFORMED.	1	G	7	1 	3U	3	U	 	H3WE    	E1GL				 
2001052400143	20010524	00143	CE  	2001	5	24	20010511CW008    	1	20010423	G	5312	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	42397	4787 				18259003				FAILED INSPECTION DUE TO CRACKS IN CRITICAL AREAS, REPLACED.						1	H	7	1 	3O			NT	3A13    					 
2001052400013	20010524	00013	EA  	2001	5	24	20010511CW014    	2	20010419	G	7322	30802	FLOAT           	PRECISION   		PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR	DAMAGED         	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	41460				75072523	2843153	L3611936A			DURING OVERHAUL THE CARBURETOR FLOAT WAS FOUND WITH ONE OF THE CHAMBERS HALF FULL OF 100 LOW LEAD.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001052400029	20010524	00029	SW  	2001	5	24	20010514CW003    	1	20010507	G	3222	48838503	CYLINDER        			GULSTM	112   	114ARKWELL  	7630315	SW  	LYC   	O540  	TIO540*     	41532	EA  					NLG	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	57BH	3800 				14001				NOSE GEAR ACTUATING CYLINDER, PN 48838503, FAILED INTERNALLY, CAUSING NOSE GEAR COLLAPSE, RESULTING IN MINOR DAMAGE TO A	IRCRAFT					1	L	7	1 	3O	3	O	 	A12SO   	E14EA				 
2001052400030	20010524	00030	CE  	2001	5	24	20010514CW004    	1	20010418	G	5510	95620010634	STABILIZER      			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					RIGHT	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	1848W	4195 				TC1534				DURING INSTALLATION OF RIGHT HAND ELEVATOR,  IT WAS DISCOVERED THAT WHEN THE ELEVATOR WAS MOVED FROM FULL DOWN TO FULL U	P, THE STABILIZER WOULD FLEX UPWARD .4375.    INVESTIGATION DISCLOSED THAT THE STABILIZER WAS BENT DOWN 2 DEGREES AT THE	 CENTER HINGE( BOTH SPARS) A TRIPLE PATCH WAS FOUND ON THE LOWER REAR SKIN, STARTING 12 INCHES FROM THE TIP.  NO RECORD 	OF THIS REPAIR CAN BE FOUND IN THE AIRCRAFT RECORDS.  CORRECTIVE ACTION:  REMOVED AND REPLACED STABILIZER.			1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2001051500506	20010515	00506	CE  	2001	5	15	20010515AP002    	1	20010514	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LEFT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	12DT	8620 				4410040				DURING A SCHEDULED INSPECTION, THE LEFT WING CENTER SECTION CANTED RIB CAP (CWS 26.85 INCHES) WAS FOUND CRACKED. THE CAN	TED RIB UPPER CAP (P/N: 5722206-1) WAS CRACKED AFT OF THE AFT MAIN SPAR AT FS 177.45, IN THE BEND RADIUS, AND RAN AFT AP	PROXIMATELY 1.375 INCH. THE CRACK WAS FIRST NOTED USING VISUAL INSPECTION THEN VERIFIED WITH DYE PENETRANT. AFTER REMOVI	NG THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED SO THAT THE BEND WAS PARALLEL WITH 	GRAIN OF THE METAL INSTEAD OF PERPENDICULAR WHICH COULD RESULT IN THIS TYPE OF FAILURE. CESSNA CURRENTLY DOES NOT HAVE A	NY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE,THIS AREA SHOULD BE CLOSELY CHECKED DURING INSPECTIONS.	1	L	7	2 	3T			RT	A28CE   					 
2001051500081	20010515	00081	EU  	2001	5	15	20010515AP004    	1	20010504	G	3233	AC11184	ACTUATOR        			FOKKER	F27   	F27MK400    	4990626	EU  										MLG	BINDING         	M				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99		8843 				10652				LANDING GEAR UNSAFE LIGHT REMAINED ON AFTER SELECTION OF LANDING GEAR TO THE UP POSITION. MAIN LANDING GEAR UPLOCK ACTUA	TOR WAS SLOW TO RETRACT TO LOCK THE GEAR IN THE UP POSITION AND TO EXTINQUISH THE UNSAFE LIGHT.  THE ACTUATOR IS SPRING-	LOADED TO THE RETRACT POSITION.				2	H	7	2 	4T			 	A817    					 
2001051500083	20010515	00083	CE  	2001	5	15	20010515AP005    	1	20010504	G	7810	829415	EXHAUST HEADER  			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					WASTEGATE FLANGE	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6867D	31   				421C1084				THIS UNIT IS MANUFACTURED IN TWO HALVES, WHERE THE UPPER & LOWER HALVES WELDED TOGETHER (AT THE WASTE GATE FLANGE) THERE	 IS A HOLE AT THE WELD AREA ON EACH SIDE.  THE REPLACMENT PART HAS AN ADDITIONAL WELD IN THESE AREAS THAT ARE NOT PRESEN	T ON THE DEFECTIVE PART.  IT APPEARS THAT THE MANUFACTURING PROCESSES (WELDING)WERE NOT COMPLETED BEFORE THIS PART LEFT 	THE MANUFACTURE.  THIS DEFECT WAS FOUND WHILE C\W THE EXHAUST PRESSURE TEST REQUIRMENTS OF AD 2000-01-16. 			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001051500093	20010515	00093		2001	5	15	20010515AP007    	4	20010404	G	3421	7000466906	INDICATOR       																	ATTITUDE	FAILED          	D				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			EA	03	1NA		25   							AFTER A FEW FLIGHTS WITH THE RECENTLY INSTALLED ADI IN THE PILOTS POSITION, THE GLIDESLOPE INDICATOR FAILED IN THE CENTE	R POSITION (INDICATING ON GLIDE PATH).  INDICATOR REMAINED PARKED IN THIS POSITION FOR THE DURATION OF THE FLIGHT.  REMO	VED AND REPLACED UNIT.  UNIT WAS OVERHAULED BY METRO AIRCRAFT INSTRUMENTS																	 
2001052400066	20010524	00066	EA  	2001	5	24	20010516CW001    	2	20010511	G	8520	76220	STUD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 3 CLYINDER	FRACTURED       	G				A				UNSCHED LANDING         				D	A		INFLIGHT SEPARATION       	FLAME/FIRE                		CR	CRUISE         	1			AL	01	45008		1097 			318052167	L691661A			AT CRUISE FLIGHT, THE NR 3 CYLINDER SEPARATED FROM THE ENGINE CASE, WHICH RESULTED IN AN INFLIGHT FIRE.  THE ENGINE CASE	, CYLINDER HOLD DOWN STUDS THROUGH BOLT STUDS AND NR 3 CONNECTING ROD WERE SENT FOR LAB INVESTIGATION.  INVESTIGATION RE	SULTS:  THE PRIMARY CAUSE WHICH LED TO THE SEPARATION OF THE NR 3 CYLINDER WAS THAT THE THROUGH BOLT STUDS WERE MOST LIK	ELY NOT PROPERLY TORQUED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001052400003	20010524	00003	CE  	2001	5	24	20010517CW009    	1	20010427	G	2410	DOFF10300J	ALTERNATOR      			CESSNA	177   	177         	2073704	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE	SEIZED          	B			R7LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	412WS		126  			17701475				ALTERNATOR OVERHAULED, INSTALLED ON AC.  FRONT BEARING BALL CAGE BROKE APART AND ALLOWED BALLS TO COLLECT ON ONE SIDE OF	 BEARING, LOCKING THE ALTERNATOR SHAFT.  FAILURE OCCURRED ON 2/10/2001 AFTER 126 HOURS TSOH.					1	H	7	1 	3O	3	O	NT	A13CE   	E286				 
2001052900037	20010529	00037		2001	5	29	20010518CW001    	4	20010430	G	3421		GYRO            			MOONEY	M20   	M20F        	5870214	SW  										COCKPIT	CONTAMINATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	9514M	4315 	2383 			670091				DURING ANNUAL INSPECTION, FOUND LIQUID IN WINDOW OF GYRO, DISCONNECTED LINE TO HAVE WATER FLOW OUT, REMOVED INSTRUMENT. 	 OPENDED CASE AND FOUND LONG-TERM CORROSION ON ALL INTERNAL PARTS.  REPLACED WITH OVERHAULED INSTRUMENT.  NO OTHER INSTR	UMENTS CONTAINED WATER MAY HAVE GOTTEN WATER THROUGH A LEAKING EXTERIOR COWL DECK.				1	L	7	1 	3O			 	2A3     					 
2001052900269	20010529	00269	CE  	2001	5	29	20010523CW001    	1	20010501	G	2710	051178217	YOKE            			CESSNA	172   	172L        	2072432	CE  										COCKPIT	CORRODED        	D				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			SO	19	3802Q	3057 				17259902				AIRCRAFT ON FINAL APPROACH, CONTROL YOKE FAILED AT APPROX 30 FT AGL.  CONTROL YOKE FAILED JUST ABOVE PIVOT POINT BEHIND 	INSTRUMENT PANEL.  CONTROL YOKE WAS EXTREMELY CORRODED AT FRACTURE POINT.					1	H	7	1 	3O			NT	3A12    					 
2001052900271	20010529	00271	EU  	2001	5	29	20010523CW002    	1	20010407	G	6510	83A851BC3	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE SHAFT	ROTATED         	C			AALA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4035W	2671 				2912				AT A SCHEDULED INSPECTION THE BEARING PN 83A851BC3 HAD ROTATED IN THE RUBBER BUSHING PN FA3819 APPROX .3750.  WE HAVE BE	EN COMPLYING WITH SB REGARDING THE GREASING AND INSPECTION OF THESE BEARINGS AND STILL HAD A BEARING TURN.  THIS IS AN A	REA THAT CALLS FOR SPECIAL ATTENTION DURING INSPECTIONS AND DAILY PRE FLIGHTS.  AT THIS TIME WE ARE INSTALLING THE NEWER	 TYPE BEARINGS THAT THIS SB DOES NOT APPLY TO.			1	G	7	1 	3U			 	H9EU    					 
2001052900272	20010529	00272	EU  	2001	5	29	20010523CW003    	1	20010410	G	6510	350A23106320	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE SHAFT	MISSING         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	4035W	2671 			2912	2912				AT A SCHEDULED INSPECTION THE SELF ADHESIVE SEAL PN 350A-1063-20 WAS FOUND NOT TO BE INSTALLED.  THIS IS A SEAL THAT IS 	INSTALLED FOR DISSIMILAR METAL CORROSION ON THE TAIL ROTOR DRIVE SHAFT HANGAR SUPPORT AND THE HANGAR BEARINGS.					1	G	7	1 	3U			 	H9EU    					 
2001052900280	20010529	00280	CE  	2001	5	29	20010523CW005    	1	20010206	G	2780	3910104044	BEARING         			HELIO 	H295  	H295        	4300802	CE  										TORQUE TUBE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5479G	3782 				1261				TORQUE TUBE BEARING MADE FROM NYLON MATERIAL HARDENS WITH AGE AND DURING OPERATION OF SLAT TORQUE TUBE.  THE BEARING STA	RTS TO CRACK AT RIVET HOLES THAT ATTACHES IT TO WING RIB.  REPLACED WITH NEW PORTS.					1	H	7	1 	3O			 	1A8     					 
2001052900281	20010529	00281	CE  	2001	5	29	20010523CW006    	1	20010206	G	2780	3910104046	BEARING         			HELIO 	H295  	H295        	4300802	CE  										TORQUE TUBE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	5479G	3782 				1261				TORQUE TUBE BEARING MADE FROM NYLON MATERIAL HARDENS WITH AGE AND DURING OPERATION OF SLAT TORQUE TUBE THE BEARING START	S TO CRACK AT RIVET HOLES THAT ATTACHES IT TO WING RIB.  REPLACED WITH NEW PARTS.					1	H	7	1 	3O			 	1A8     					 
2001052900282	20010529	00282	SW  	2001	5	29	20010524CW001    	1	20010427	G	7603	63255555	THROTTLE ARM    			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	143TM	55   				290242	684902			WHILE WARMING THE ENGINE FOR OIL CHANGE, NOTED THAT THERE WAS AN EXCESSIVE AMOUNT OF FREE PLAY IN THE THROTTLE LINKAGE. 	 AFTER RUNNING THE ENGINE UP TO 1500 RPM, PULLED THROTTLE BACK TO IDLE, BUT THE ENGINE RPM DID NOT DECREASE.  HAD TO USE	 THE MIXTURE CONTROL TO STOP ENGINE.  INSPECTED THROTTLE LINKAGE AND FOUNDTHE THROTTLE ARM WAS LOOSE ON THE SHAFT.  TORQ	UE SEAL ON THE ATTACHING NUT WAS NOT BROKEN AND NUT DID NOT APPEAR TO HAVE MOVED SINCE INSTALLATION.  REMOVED THE THROTT	LE ARM AND FOUND THE SERRATIONS ON THE ARM WHERE THE ARM MEETS THE THROTTLE SHAFT WERE WORN AWAY. ATTACHING NUT WAS NOT 	TIGHTENED PROPERLY AT INSTALLATION.  MFG SUPPLIED NEW THROTTLE ARM , INSTALLED IT USING PROPER TORQUE PER SB.	1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2001052900283	20010529	00283	NE  	2001	5	29	20010524CW002    	1	20010427	G	6520	643566409043	HOUSING         			SKRSKY	S64   	S64E        	8142604	NE  										T/R GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194AC	6386 				64017				DURING TEARDOWN FOR OVERHAUL, A CRACK WAS VISUALLY NOTICED AT APPROX THE 2 OCLOCK POSITION(AS INSTALLED ON AIRCRAFT) IN 	THE STRADDLE MOUNT OF THE IDLER GEAR ALIGNMENT BEARING PN SB2154-1 OF CENTER HOUSING PN 6435-66409-043.  FURTHER INSPECT	ION AFTER REMOVAL OF BEARING RETAINER PN 6435-66427-103 REVEALED THE STRADDLE MOUNT WAS CRACKED IN HALF, PASSING THROUGH	 THE .275 IN DIAMETER HOLE FOR ROSAN STUD PN SF101-125A-6A.   NO SECONDARY DAMAGE DUE TO THIS FAILURE WAS NOTED.			2	G	7	2 	4U			 	H4EA    					 
2001052900290	20010529	00290	SO  	2001	5	29	20010525CW001    	1	20010226	G	5540	2344715	RUDDER HORN     			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					RUDDER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	7129Y	4374 				30151				REMOVED HORN DUE TO WEAR BETWEEN HORN AND RUDDER.  FOUND CRACKS FROM MOUNT HOLES TO TOP OF RUDDER HORNS OF SAME PART NUM	BER TO BE CRACKED IN A SIMILAR FASHION .					1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2001052900336	20010529	00336	SW  	2001	5	29	20010525CW005    	1	20010525	G	2710	145520101	CONTROL CABLE   			NAVION	NAVION	L17B        	6150108	SW  										AILERON	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5335K					NAV42235B				UPON REMOVAL OF CABLES, FOUND FRAYED SECTION LOCATED JUST OUTBOARD OF THE AILERON ROLLERS (MID-WING ABOVE THE MAIN LANDI	NG GEAR TRUNION).  PROBABLE CAUSES INCLUDE ENVIRONMENTAL DAMAGE, TIME, AND INADEQUATE MAINTENCE OF ROLLERS.  ROLLERS IN 	THIS AREA OF THIS AIRCRAFT WERE FROZEN.  CABLES HAD BEEN COATED WITH GREASE IN THIS AREA OVER THE YEARS AND FORMED A SEM	I-HARD SHELL WHICH COULD HAVE TRAPPED MOISTURE LEADING TO THE DAMAGE.  RECOMMENDATIONS ARE TO MAINTAIN CABLES AND ROLLER	S PROPERLY ESPECIALLY IN HARD TO REACH AREAS, AND THAT CABLES HAVE A FINITE LIFETIME.		1	L	7	1 	3O			 	A782    					 
2001052900337	20010529	00337	SW  	2001	5	29	20010525CW006    	1	20010525	G	2730	1455201029	CONTROL CABLE   			NAVION	NAVION	L17A        	6150106	SW  										ELEVATOR	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5335K					NAV42235				UPON REMOVAL OF CABLE, FOUND FRAYED SECTION LOCATED AT THE LOWERMOST POINT EXITING THE PULLEY.  PROBABLE CAUSES INCLUDE 	ENVIRONMENTAL DAMAGE (WHEEL WELL AREA) AND TIME.  AS PART OF ANNUAL, ALL CABLES IN THIS AIRCRAFT WERE BEING REPLACED DUE	 TO OVERALL AGE AND CONDITION WHEN THIS PROBLEM WAS FOUND.				1	L	7	1 	3O			 	A782    					 
2001052900338	20010529	00338	CE  	2001	5	29	20010525CW007    	1	20010327	G	7602	C29950J0101	CONTROL CABLE   			CESSNA	210   	210L        	2073448	CE  										ENGINE	BROKEN          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	05	1759X	367  				210L60780				ENGINE STARTED TO SPAR DOWN IN FLIGHT.  PILOT ATTEMPTED TO ADJUST MIXTURE, AFTER TURNING ON THE BOOST PUMPS.  PILOT STAT	ED, THE MIXTURE CABLE WAS LOOSE IN HIS HAND.  ENGINE SHUT DOWN AND AIRCRAFT WAS LANDED , GEAR UP IN A FIELD.  UPON EXAMI	NATION, THE MIXTURE CABLE WAS FOUND BROKEN AT THE POINT IT ENTERED THE PROTECTIVE BARREL OF THE ROD END.  CORROSION WAS 	EVIDENT.			1	H	7	1 	3O			 	3A21    					 
2001052900340	20010529	00340	SO  	2001	5	29	20010529CW001    	1	20010502	G	2740	62701113	CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  										STABILATOR	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9182W	6559 				2841130				LEFT FORWARD STABILATOR CABLE WORN AND FRAYING AT SPAR FAIRLEAD AND REAR SPAR PULLEY.  DIFFICULT TO DETECT WITHOUT REMOV	ING CABLE.					1	L	7	1 	3O			 	2A13    					 
2001052900341	20010529	00341	SO  	2001	5	29	20010529CW003    	1	20010508	G	2820	STCSA1480WE	FUEL TANK       			PIPER 	PA23  	PA23250     	7102308	SO  										WING TIP	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	21551					274714				FIBERGLASS WINGTIP FUEL TANK STC SA1480WE HAS AN EDGE DISTANCE OF .2500 INCH SCREW HOLES WHICH BROKE FIBERGLASS OUT CAUS	ING THE WINGTIP TO FALL OFF,  WHILE AIRCRAFT WAS ON GROUND.  FIBERGLASS TIP DOES NOT HAVE SUFFICIENT STRENGTH DUE TO FIB	ERGLASS THICKNESS AND EDGE DISTANCE.				1	L	7	2 	3O			 	1A10    					 
2001060700044	20010607	00044	CE  	2001	6	7	20010529CW007    	1	20010423	G	3710	632617D	GEAR            	CONT        		CESSNA	337   	337H        	2075732	CE  										VACUUM PUMP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	729AS	725  				33701938				A DETAINLED INVESTIGATION OF THE STARTER DRIVE REVEALED THAT ALL OF THE GEAR TEETH WERE WORN EXCESSIVELY ON ONE OF THE B	EVEL GEARS WHICH DRIVES THE VACUUM PUMP.					1	H	7	2 	3O			 	A6CE    					 
2001060700048	20010607	00048	CE  	2001	6	7	20010529CW010    	1	20010420	G	3230	08411132	SCREW           			CESSNA	414   	414         	2075908	CE  										MLG	DAMAGED         	B			AK6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	922AS	4803 				4140033				UPON ANNUAL INSPECTION, FOUND ADJUSTING SCREW PN 084113-2, THREADS AT THE POINT OF PULLING OUT OF EYE BOLT END FITTINGS,	 PN 0841111-3.  THIS IS THE 4TH DISCOVERY OF ADJUSTING SCREW AT THE POINT OF FAILURE WHICH, IF NOT HAD BEEN CORRECTED, W	OULD BE IMMINENT GEAR FAILURE, SINCE THIS IS THE ONLY ITEM LOCKING THE MAIN GEAR INTO POSITION AFTER EXTENSION.				1	L	7	2 	3O			RT	A7CE    					 
2001060700049	20010607	00049	CE  	2001	6	7	20010529CW011    	1	20010405	G	3230	08411113	SCREW           			CESSNA	414   	414         	2075908	CE  										MLG	DAMAGED         	B			AK6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	922AS	4803 				4140033				UPON ANNUAL INSPECTION, FOUND ADJUSTING SCREW, PN 084113-2, THREADS AT THE POINT OF PULLING OUT OF EYE BOLT END FITTINGS	, PN 0841111-3,.  THIS IS THE 4TH DISCOVERY OF ADJUSTING SCREW AT THE POINT OF FAILURE WHICH, IF NOT HAD BEEN SINCE THIS	 IS THE ONLY ITEM LOCKING THE MAIN GEAR INTO POSITION AFTER EXTENSION.				1	L	7	2 	3O			RT	A7CE    					 
2001071000059	20010710	00059	SW  	2001	7	10	20010529CW014    	1	20010313	G	7160	600382305	LATCH           			MOONEY	M20   	M20S        	5870226	SW  										ALT AIR DOOR	WORN            	B			DY1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	2192N	250  				300041				DURING ROUTINE OIL CHANGE, FOUND MAGNETIC LATCH FOR ALTERNATE AIR DOOR BOX VERY WORN AND AREA AROUND IT COVERED IN ALUMI	NUM DUST.  THE LATCH HOLDS THE DOOR IN THE CLOSED POSITION UNTIL THE AIR FILTER BECOMES CLOGGED WITH WATER/ICE (WHEN IN 	SUCH CONDITIONS) FORCING THE ALTERNATE AIR DOOR TO OPEN AUTOMATICALLY.  WE ROUTINELY FIND THESE LATCHES VERY WORN AND ON	 THE VERGE OF COMING APART.  THIS AIR BOX/LATCH SETUP IS USED ON SEVERAL MODELS, WHICH ALL HAVE THE SAME RECURRING WEAR 	PROBLEM.		1	L	7	1 	3O			RT	2A3     					 
2001071000060	20010710	00060	CE  	2001	7	10	20010530CW001    	1	20010530	G	3220	NAS4645A15	BOLT            			CESSNA	177   	177RG       	2073709	CE  										NLG	MISSING         	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	13	7537V	5311 				0834				NOSE GEAR COLLAPSED ON LANDING ROLL OUT, DOWN LOCK LINK BOLT(LOWER) WAS FOUND MISSING PN NAS4645A15, NO MEANS OF SAFETY 	MAY BE USED WITH THIS DESIGN, ONLY LOCTITE CV SEALANT AS STATED IN SERVICE MANUAL.  PART HAD 5311 HOURS.					1	H	7	1 	3O			 	A20CE   					 
2001062000053	20010620	00053	WP  	2001	6	20	20010531CW001    	1	20010507	G	6210	5320003	BLADE           			HILLER	UH12  	UH12E       	4360122	WP  										MAIN ROTOR	DELAMINATED     	B			KQTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	144HA	538  				HA3044				DOUBLER DELAMINATION NO SIGNS OF CORROSION OR IMPACT WHICH MIGHT CAUSE DELAMINATION.  CAUSE UNKNOWN						1	G	7	1 	3O			 	4H11    					 
2001062000054	20010620	00054		2001	6	20	20010531CW002    	4	20010410	G	6122	D4718	DRIVE GEAR      	HARTZL      		PIPER 	PA44  	PA44180     	7104402	SO  										PROP GOVERNOR	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4144C	1034 			227YS	4496020				GOVERNOR WAS SUBMITTED FOR INSPECTION DUE TO AN ENGINE FIRE ON THE GROUND.  DURING INSPECTION, THE DRIVE GEAR PN D 4718 	 WAS FOUND CRACKED IN THE DRIVE GEAR SPLINES THAT ENGAGE THE GOVERNOR DRIVE ON THE ENGINE.  THE GEAR CONTAINS TWO CRACKS	, ALMOST 180 DEGREES APART AND OVER .5000 INCH LONG.  HAD THE ENGINE NOT CAUGHT FIRE, THIS GEAR MOST LIKELY WOULD HAVE F	AILED IN SERVICE.			1	L	7	2 	3O			 	A19S0   					 
2001062000055	20010620	00055	CE  	2001	6	20	20010531CW003    	1	20010425	G	2731	15703072	CIRCUIT BOARD   			CESSNA	206   	TU206F      	2073353	CE  										ELEV TRIM SYSTEM	SHORTED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	8033Q	704  				420603088				SHORT CIRCUIT RESULTED IN BURNED SPOT ON BOARD AND OPEN CIRCUIT.  CAUSE APPEARS TO HAVE RESULTED FROM ELECTRICAL OVERLOA	D TO CONNECTION.  CAUSE FOR OVERLOAD-UNKNOWN.					1	H	7	1 	3O			 	A4CE    					 
2001062000061	20010620	00061	SW  	2001	6	20	20010601CW004    	1	20010509	G	6510	407340339103	BEARING         			BELL  	407   	407         	       	SW  										TAIL ROTOR	SEIZED          	D			YADA	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	19	70AP	786  				53409				PILOT FELT EXCESSIVE VIBRATION AND HEADED BACK TO BASE, AFTER SHORT PERIOD VIBRATION INCREASED, PILOT LANDED IN FIELD.  	FOUND TAIL ROTOR HANGER BEARING SEIZED AND SPUN IN BEARING HOUSING.  THE BEARING THAT FAILED IS THE FIRST BEARING AFT LO	CATED JUST FORWARD OF OIL COOLER BLOWER.				1	G	7	1 	3U			O	H2SW    					 
2001062000066	20010620	00066	CE  	2001	6	20	20010601CW009    	1	20010511	G	3240		LINE            			BEECH 	23    	C23         	1151242	CE  										BRAKE SYS	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	9743L					M1371				MOST OF THE FLEXIBLE FLUID LINES IN THIS AIRCRAFT WERE FOUND TO BE STIFF.  TWO OF THE BRAKE LINES WERE FOUND TO BE CHAFF	ING ON THE FORWARD FIREWALL AREA AND WERE WORN SMOOTH ON THE OUTSIDE.  BOTH OF THESE WERE LEAKING THROUGH THE HOSE.  ALL	 OF THE FLEXIBLE FLUID LINES IN THE BRAKE SYSTEM WERE REPLACED.  THE FLEXIBLE FLUID LINES BETWEEN THE FUEL TANKS AND SEL	ECTOR VALVE WERE ALSO REPLACED.  MOST OF THESE APPEARED TO BE ORIGINAL AND WERE ABOUT 30 YEARS OLD.  THE FLEXIBLE LINES 	IN THE ENGINE COMPARTMENT ARE BEING REPLACED ALONG WITH ENGINE MAINTENANCE AT ANOTHER LOCATION.		1	L	7	1 	3O			 	A1CE    					 
2001062000072	20010620	00072	CE  	2001	6	20	20010604CW001    	1	20010509	G	5712		RIB             			CESSNA	177   	177RG       	2073709	CE  										LT WING	CRACKED         	B			T9ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	52472					177RG1196				DURING THE INSTALLATION OF SHOULDER HARNESS KITS, THE HEADLINER WAS REMOVED.  CORROSION ON CARRY THRU SPAR FORE AND AFT 	TOP SPAR CAPS AND SKIN WAS NOTICED.  CORROSION WAS ALSO PRESENT AT LEFT AND RIGHT ROOT RIBS.  LEFT ROOT RIB HAD SMALL CR	ACK.  NO FURTHER ACTION TAKEN.				1	H	7	1 	3O			 	A20CE   					 
2001062000073	20010620	00073	CE  	2001	6	20	20010604CW002    	1	20010405	G	7810	17540071	RISER           			CESSNA	172   	172Q        	2072437	CE  	LYC   	O360  	O360*       	41514	EA  					EXHAUST SYS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	469NE					17275952				NR 3 EXHAUST RISER CRACKED AT FLANGE.  NOTED: COMMON FAILURE, PER EXHAUST REPAIR STATION.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001062000074	20010620	00074	EU  	2001	6	20	20010604CW003    	1	20010410	G	6120	21014	COLLAR          			SOCATA	MS894 	MS894A      	8402842	EU  	FRNKLN	6AV350	6A350C1     	27043	EA  					PROPELLER	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	43BF					11931	528663			PROBLEM REPORTED:  PROP WOULD NOT CYCLE W/WARM ENGINE OIL.  DISASSEMBLED ENGINE AND FOUND ONE SOCKET HAS SCREW .1562 THA	T HOLDS THE TRANSFER COLLAR TOGETHER BROKEN ALLOWING THE COLLAR AND SEALS TO BECOME LOOSE ON CRANKSHAFT OIL TO ESCAPE AN	D NOT ALL TO THE PROPELLER.  NO IMPROPER REPAIR, PREVIOUS ACTIONS.				1	L	7	1 	3O	3	O	 	7A14    	E9EA				 
2001062500167	20010625	00167	NE  	2001	6	25	20010604CW005    	1	20010426	G	5610	S16206510421	TRACK           			SKRSKY	S58T  	S58JT       	8141807	NE  										PILOT WNDOW	DEFECTIVE       	A				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			GL	23	902CH	65   				581539				TRACK ASSEMBLY ON PILOTS SLIDING WINDOW CAME APART ALLOWING WINDOW TO DEPART THE AIRCRAFT.  WINDOW FRAME AND TRACK ASSEM	BLY HAD ONLY 65 HOURS TT  APPARENT DEFECTIVE TRACK ASSEMBLY.					2	G	7	2 	4U			 	1H11    					 
2001062500168	20010625	00168	CE  	2001	6	25	20010604CW006    	1	20010514	G	3220	0542106	SPRING          			CESSNA	170   	170B        	2072306	CE  										TAIL WHEEL	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	3143A	300  				25787				TAILWHEEL SPRING BROKE AT AN EXISTING CRACK.  TAILWHEEL THEN DAMAGED THE LOWER SKINS OF THE RUDDER.						1	H	7	1 	3O			 	A799    					 
2001062500172	20010625	00172	SW  	2001	6	25	20010604CW012    	1	20010522	G	2810		FUEL CELL       			MOONEY	M20   	M20F        	5870214	SW  										FUEL SYSTEM	CONTAMINATED    	G				A				UNSCHED LANDING         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		CL	CLIMB          	1			GL	15	301LM					670323				ENGINE LOST POWER,  THEN QUIT,  DURING TAKEOFF CLIMB.  AIRCRAFT MADE OFF AIRPORT LANDING.  INVESTIGATION FOUND WATER IN 	THE RIGHT HAND FUEL SUMP.  AIRCRAFT HAD BEEN PARKED OUTSIDE THROUGH HEAVY RAIN.					1	L	7	1 	3O			 	2A3     					 
2001062500174	20010625	00174	GL  	2001	6	25	20010604CW015    	3	20010319	G	6110	HCB37N5	CLAMP           			GULSTM	690TP 	690A        	0141722	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	246T	560  	373  			11254		BV3280		CORROSION IN CLAMPS AND BEARING RACES, REJECTED ALL 3 CLAMPS AND 1 RACE.						1	H	7	2 	3T			 	2A4     		6	C	P15EA	 
2001062500176	20010625	00176	GL  	2001	6	25	20010604CW016    	1	20010511	G	7160	191965910	HINGE           			BLANCA	17    	1731A       	1220435	GL  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCC3Y	HCC3YR      	GL  	ALT AIR DOOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	9505E					7532159	L1270848A	DY270		PILOT DID NOT REPORT ANY ABNORMAL OPERATION.  AIR BOX WAS REMOVED AT ANNUAL INSPECTION FOR SERVICING AND ALTERNATE AIR D	OOR FELL ON FLOOR.  ALL HINGE PIN SEGMENTS HAD FAILED.					1	L	7	1 	3O	3	O	 	A18CE   	1E4	5	C	P25EA	 
2001062600017	20010626	00017	NE  	2001	6	26	20010605CW014    	2	20010515	G	7314	640197	SHAFT           	NASH        							GE    	CFM56 	CFM56*      	13802	NE  					FUEL PUMP	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					FB78955					UPON DISASSEMBLY I FOUND THE SHAFT IN TWO PIECES.  THE STANDARD 64-0197 SHAFT IS A SOLID ONE PIECE SHAFT.  THE SHAFT THA	T WAS REMOVED FROM THIS UNIT WAS MACHINED INTO TWO DIFFERENT PIECES, AND WAS HELD TOGETHER BY TWO PINS.  THIS IS NOT A S	TANDARD REPAIR.  ONE OF THE FINS FAILED AND SHAFT SEPARATED.									4	F			E2GL				 
2001062600018	20010626	00018	CE  	2001	6	26	20010605CW015    	1	20010502	G	5540	S100442A	BUSHING         			CESSNA	172   	172         	2072402	CE  										RUDDER HINGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25										NEW RUDDER HINGE HOT BUSHING, MISSING LARGE CHUNK OUT OF BOTTOM END OF BUSHING.						1	H	7	1 	3O			NT	3A12    					 
2001062600019	20010626	00019	CE  	2001	6	26	20010605CW016    	1	20010426	G	7714	S33291	TACHOMETER      			CESSNA	172   	172R        	2072401	CE  										COCKPIT	OUT OF TOLERANCE	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										NEW TACHOMETERS OUT OF MFG 50 RPM TOLERANCES.  DIGITAL CHECKS OF FINE ADDITIONAL 172R AND 172S AIRCRAFT SHOWED TACH TO R	EAD WITHIN PLUS OR MINUS 50 RPM.  DISCOVERED WHEN DOING AD.					1	H	7	1 	3O			NT	3A12    					 
2001062600020	20010626	00020	CE  	2001	6	26	20010605CW017    	1	20010516	G	2434	DOFF10300E	ALTERNATOR      			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  					FWD ENGINE	FAILED          	B			N9VR	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	03	297DC		31   			01697	352438			OWNER OF THIS AIRCRAFT EXPERIENCED FWD ENGINE ALTERNATOR FAILURE (AS INDICATOR BY FAILURE LIGHT)  DURING FLIGHT.  TECHNI	CIAN AND OWNER REMOVED ALTERNATOR FROM ENGINE AND DISCOVERED THE DRIVE SHAFT SHEARED.  THE GEAR RETAINING BOLT HAD RUBBE	D INTERNALLY AND BUSTED A PIECE OF THE COTTER PIN OFF, WHICH WAS FOUND ON THE MAGNETIC OIL DRAIN PLUG.  THE DRIVE GEAR A	LSO DISPLAYED SIGNS OF WEAR.  THE ALTERNATOR SHAFT FAILURE APPEARS TO BE A MATERIAL DEFECT.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001062800012	20010628	00012		2001	6	28	20010605CW018    	4	20010504	G	2562	AK450	TRANSMITTER     			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					ELT	FAILED          	B			DY1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	121RP	393  				290141				DURING ANNUAL INSPECTION, PERFORMED ELT INSPECTION IAW FAR 91.207D, AND FOUND THAT ELT DOES NOT TRANSMIT A SIGNAL EVEN T	HOUGH RED TRANSMIT LIGHT ON UNIT LIGHTS UP.  UNIT TESTED USING 3 DIFFERENT ANTENNA SOURCES AND VERIFIED THAT ELT BATTERY	 IS GOOD.  TRANSMIT LIGHT WORKS IN THE ON POSITION AND ARM POSITION WHEN THE G SWITCH IS ACTIVATED BUT STILL NO AUDIBLE 	SIGNAL HEARD FROM AIRCRAFT RADIOS OR A PORTABLE AM RADIO.			1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2001071600001	20010716	00001	SO  	2001	7	16	20010605CW019    	1	20010511	G	3260		SWITCH          			SWFTMS	GC1B  	GC1B        	9230104	SO  	CONT  	O360  	IO360C      	17025	SO  					COCKPIT	DEFECTIVE       	G				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			GL	25	2429B					3729	060654R			INVESTIGATION SUBSEQUENT GEAR UP LANDING, FINDS WIRES TO THROTTLE MICRO SWITCH FOR GEAR WARNING SYSTEM INCORRECTLY CONNE	CTED.  SWITCH FUNCTION INOPERATIVE.  WHEN WIRES CORRECTLY CONNECTED TO SWITCH, FUNCTION RESTARTED.  FLAG/SPADE CONNECTIN	G EXTREMELY LOOSE, FELL OFF AT SLIGHTEST FORCE.  WHEN CONNECTED, SWITCH DOES NOT ACTIVATED GEAR WARNING LIGHT UNTIL THRO	TTLE IS PULLED HARD TO POST IDLE. (POOR WIRE CONNECTING, MISWIRED, AND MISRIGGED SWITCH.			1	L	7	1 	3O	3	O	NC	A766    	E1CE				 
2001062800013	20010628	00013	CE  	2001	6	28	20010606CW001    	1	20010517	G	2701	05600145	YOKE            			CESSNA	172   	172P        	2072436	CE  										COCKPIT	CORRODED        	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	62258	8300 				17275236				WHILE PERFORMING ANNUAL INSPECTION AND SB, FOUND ELEVATOR CONTROL YOKE CONTAINED RUSTY WATER, CAUSING EXCESSIVE CORROSIO	N.  IF THIS PART FAILS COMPLETE LOSS OF ELEVATOR CONTROL RESULTS.  SB PERMITS DRILLING HOLE FOR RECURRING INSPECTION.  S	UGGEST SB SEB-01-3 BE MADE AN AD NOTE.				1	H	7	1 	3O			NT	3A12    					 
2001062800014	20010628	00014	EA  	2001	6	28	20010606CW002    	2	20010515	G	8530	AL75089	PISTON RING     			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360*       	41514	EA  					NR 3 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9746B	1110 				172RG1009				AIRCRAFT WAS CONSUMING A LARGE QUANTITY OF OIL.  UPON INSPECTION FOUND THE NR 3 CYLINDER OIL CONTROL RING LAND ELONGATED	 DUE TO A SMALL PIECE OF RING WHICH HAD BROKEN OFF AND BEGAN TO FLUTTER.  PROBABLE CAUSE OF SHOCK COOLING.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001062800015	20010628	00015	SO  	2001	6	28	20010606CW003    	1	20010412	G	5711	6405506	SPAR            			PIPER 	PA25  	PA25235     	7102504	SO  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	7031Z					252791				WING WAS BEING DISASSEMBLED FOR RIB REPLACEMENT.  REINFORCEMENT PLATE WAS DRILLED OFF AND CORROSION FOUND ON AFT FACE OF	 SPAR WEB AND FACE OF REINFORCEMENT PLATE.  CAUSE: MOISTURE WICKING BETWEEN PLATES AND LACK OF CORROSION PROTECTION.					1	L	7	1 	3O			 	2A10    					 
2001062800016	20010628	00016	SO  	2001	6	28	20010606CW004    	1	20010412	G	5720	6418800	DOUBLER         			PIPER 	PA25  	PA25235     	7102504	SO  										LT WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	7031Z					252791				WING WAS BEING DISASSEMBLED FOR RIB REPLACEMENT.  REINFORCEMENT PLATE WAS DRILLED OFF AND CORROSION FOUND ON AFT FACE OF	 SPAR WEB AND FACE OF REINFORCEMENT PLATE.  CAUSE:  MOISTURE WICKING BETWEEN PLATES AND LACK OF CORROSION PROTECTION.					1	L	7	1 	3O			 	2A10    					 
2001071600007	20010716	00007		2001	7	16	20010608CW004    	4	20010430	G	2210	AC66375	HOUSING         																	SERVO	CRACKED         	H			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										CRACKS IN SERVO BODY.																			 
2001071600008	20010716	00008		2001	7	16	20010608CW005    	4	20010430	G	2210	AS67244	HOUSING         																	SERVO	CRACKED         	H			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										CRACKS IN SERVO BODY.																			 
2001071600009	20010716	00009		2001	7	16	20010608CW006    	4	20010425	G	2210	AS66375	HOUSING         																	SERVO	CRACKED         	H			QH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										CRACK IN SERVO BODY.																			 
2001071600010	20010716	00010	CE  	2001	7	16	20010612CW001    	1	20010403	G	7603		THROTTLE CABLE  			CESSNA	172   	172M        	2072418	CE  										ENGINE	FAILED          	D			TG3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	7603	3857 				17267200				AFTER REMOVING ENGINE COWLING, INSP ENG CONTROLS, DISCOVERED THROTTLE CABLE HAD FAILED,  DUE TO AGE.  DESIGN IS SUCH THA	T OUTER HOUSING,  WHICH IS CONSTRUCTED OF PLASTIC, HAD DEVELOPED SMALL CRACKS.   CRACKS WERE VISIBLE IN AREAS AFT OF POI	NT OF FAILURE IN  SECTION OF CABLE FORWARD OF THE FIREWALL.  AT THE POINT IN THE CABLE THAT HAS A SWEDGED FITTING OVER T	HE OUTER HOUSING INTENDED TO SECURE CABLE TO THE BRACKET THAT MOUNTS TO  ENGINE,  THE OUTER HOUSING PLASTIC HAD CRACKED 	TO THE POINT THAT PIECES FELL OUT OF THE SWEDGED FITTING.  CLAMP HAD LOST ITS TENSION ON OUTER HOUSING AND ANY MOVEMENT 	OF THE THROTTLE CONTROL WOULD CAUSE THE OUTER HOUSING TO MOVE INSTEAD OF CARBURETOR CONTROL ARM.	1	H	7	1 	3O			NT	3A12    					 
2001071600011	20010716	00011	NE  	2001	7	16	20010612CW002    	2	20010508	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     	 	NE  					NR4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART REJECTED A F.P. I. FOR LINEAR INDICATIONS ON BOSSES.											4	F			E311NE				 
2001071600013	20010716	00013		2001	7	16	20010612CW004    	4	20010507	G	2561	AV2A	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.																			 
2001071600014	20010716	00014		2001	7	16	20010612CW005    	4	20010507	G	2561	KSE35L8	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.																			 
2001071600022	20010716	00022	CE  	2001	7	16	20010612CW013    	1	20010524	G	7603	12B57	THROTTLE ARM    			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	5302E	410  				17271828	L812076T			THROTTLE ARM FOUND CRACKED DURING 100 HOUR INSPECTION, FIRST APPEARED TO BE CASTING FLASH.  PART REMOVED, DYE CHECKED AN	D VERIFIED CRACKED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001071600023	20010716	00023	CE  	2001	7	16	20010612CW014    	1	20010501	G	3232	12810013	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	6291R	8861 				172RG0151				DURING INSPECTION, FOUND THE NECK OF ACTUATOR HOUSING BODY CRACKED .7500 WAY AROUND.  ROLLER FOR INTERNAL PISTON ARM AND	 GEAR WAS SLIDING OUT.  GEAR WAS PERFORMING NORMAL AT TIME FOUND(100 HOUR INSPECTION).					1	H	7	1 	3O			 	3A17    					 
2001071600024	20010716	00024	EA  	2001	7	16	20010612CW015    	2	20010515	G	8530	AL75089	RING            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					NR 3 CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9746B	1110 				172RG1009	L2988836A			AIRCRAFT WAS CONSUMING A LARGE QUANTITY OF OIL.  UPON INSPECTION, FOUND THE NR 3 CYL OIL CONTROL RING LAND ELONGATED DUE	 TO A SMALL PIECE OF RING WHICH HAD PIECE OF RING WHICH HAD BROKEN OFF AND BEGAN TO FLUTTER.  PROBABLE CAUSE: SHOCK COOL	ING.				1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001071600026	20010716	00026	CE  	2001	7	16	20010612CW017    	1	20010511	G	3240	0411549	BRACKET         			CESSNA	206   	TU206G      	2073357	CE  										LT MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	01	206TT	3359 				020605283				PILOT LOST LEFT BRAKE DURING TAXI.  INSPECTION REVEALED MASTER CYLINDER LOWER ATTACH BRACKETS BROKEN.						1	H	7	1 	3O			 	A4CE    					 
2001071600027	20010716	00027	CE  	2001	7	16	20010612CW018    	1	20010511	G	3240	0411550	BRACKET         			CESSNA	206   	TU206G      	2073357	CE  										LT MLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	01	206TT					U20605283				PILOT LOST LEFT BRAKE DURING TAXI.  INSPECTION REVEALED MASTER CYLINDER LOWER ATTACH BRACKETS BROKEN.  INSPECTION OF OTH	ER AIRCRAFT FOUND SAME PARTS BENT.					1	H	7	1 	3O			 	A4CE    					 
2001071600029	20010716	00029	CE  	2001	7	16	20010613CW002    	1	20010526	G	2750	98600581	CONTROL CABLE   			CESSNA	210   	T210L       	2073449	CE  										T/E FLAP	SLIPPED         	D				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CE	05	93344					21060371				DURING 100 HR INSPECTION, FOUND FLAPS NOT WORKING PROPERLY, FOUND CONTROL PUSH/PULL CABLE OUTER HOUSING WHERE HOUSING IS	 CLAMPED, SLIPPING IN CLAMP BUSHING.  ORDER NEW CABLE FROM CESSNA, IT WAS TOO SHORT, CALLED CESSNA AND FOUND THEIR STOCK	 WAS MANUFACTURED WRONG.  CESSNA HAD A NEW CABLE MADE.  INSTALLED NEW CABLE.  OPS CHECKED.  NEW CABLE WAS BINDING, CAUSI	NG WING RIB TO FLEX AND STRETCHED CABLE HOUSING.			1	H	7	1 	3O			 	3A21    					 
2001071700035	20010717	00035	SW  	2001	7	17	20010613CW006    	1	20010526	G	3020	189502	ARM             			BBAVIA	7     	7GCBC       	1220601	SW  										CARBURETOR HEAT	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	7650S	652  				92876				AN4 BOLT ACTS AS TERMINAL END OF CARBURETOR HEAT CABLE AND IS FREE TO ROTATE IN HOLE DRILLED NEAR END OF SHAFT ASSY ARM 	OF CARB HEAT BUTTERFLY VALVE IN CARB AIR INTAKE BOX.  FORE AND AFT MOVEMENT, RESULTING FROM CARB HEAT APP. HAS ELONGATED	 HOLE IN ARM AND CUT BOLT APPROX .7500 THRU ITS DIAMETER, ALLOWING APPROX .3125 FREE TRAVEL OF ARM AND FREE VERT DISPLAC	EMENT OF CARB HEAT BUTTERFLY VALVE FROM FULLY CLOSED TO APPROX .5000 OPEN.  REPAIR ACCOMPLISHED BY REAMING OUT HOLE ON A	RM TO ACCEPT BUSHING TO RETAIN AN4 BOLT OR TO ACCEPT AN5 BOLT.  THEREBY EXPANDING SURFACE BRG CONTACT BETWEEN ARM AND BO	LT.  FUTURE WEAR CAN BE MINIMIZED BY CONTINUED ATTENTION TO LUBRICATION OF BOLT.	1	H	7	1 	3O			NC	A759    					 
2001071600032	20010716	00032	CE  	2001	7	16	20010613CW008    	1	20010525	G	3233	12810003	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	646B					172RG1116				FOUND ONE ACTUATOR CRACKED.						1	H	7	1 	3O			 	3A17    					 
2001071600033	20010716	00033	CE  	2001	7	16	20010613CW009    	1	20010525	G	3233	12810003	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	9654B					172RG0947				FOUND ONE ACTUATOR CRACKED.						1	H	7	1 	3O			 	3A17    					 
2001072500070	20010725	00070	NE  	2001	7	25	20010613CW010    	2	20010601	G	7261	AS3209013	O-RING          								PWA   	PT6   	PT6A67D     	 	NE  					ENGINE	BROKEN          	F			MASR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01										PART WAS REMOVED NEW FROM FLOOR STOCK.  WHEN O-RING WAS REMOVED FROM SEALED PACKAGE IT WAS FOUND TO BE BRITTLE AND BROKE	N INTO 4 PIECES.  SEVERAL OTHER O-RINGS WERE CHECKED AND ALL WERE FOUND TO BE SERVICEABLE.										4	T			E26NE				 
2001071600034	20010716	00034	NE  	2001	7	16	20010613CW011    	2	20010530	G	7250	3028601	BLADE           								PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	SEPARATED       	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	61MA						PCE70547			BACKGROUND:  PCE 70547 SUSTAINED TYPICAL BLADE SEPARATION AND RESULTED DOWN STREAM DAMAGE.  THE 3028601 BLADE HAS A 3500	 HOUR TIME LIMIT ON THE JT15D-4 ENGINE.  THE SEPARATION OCCURS APPROX 1800 HOURS OF OPERATION DEPENDING ON ENGINE OPERAT	ION.  INSP OF BLADES REVEALED AN AVERAGE GROWTH OF.007.									4	F			E1NE				 
2001071600035	20010716	00035	NE  	2001	7	16	20010613CW012    	2	20010530	G	7250	3028601	BLADE           								PWA   	JD15  	JT15D1A     	 	NE  					ENGINE	SEPARATED       	B			IY2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	511AT	2717 					PCE76579			BACKGROUND:  THE 3028601 TURBINE BLADE INSTALLED ON THE JT15D-1A ENGINE HAVE A 3500 HOUR LIFE LIMIT.  THIS TURBINE BLADE	 TENDS TO CRACK AT THE AIRFOIL AND BREAK CAUSING EXTENSIVE DOWNSTREAM FAILURE/DAMAGE.  THE BLADE WILL TYPICALLY GROW IN 	EXCESS OF .007 INCH AND BREAK.  THIS USUALLY HAPPENS BETWEEN THE 1800-3000 HOUR MARK, DEPENDING ON ENGINE OPERATION.									4	F			E25EA				 
2001071600046	20010716	00046	CE  	2001	7	16	20010613CW023    	1	20010509	G	5711		SPAR            			CESSNA	177   	177RG       	2073709	CE  										WING	CORRODED        	B			T9ZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	52472					177R61196				DURING THE INSTALLATION OF SHOULDER HARNESS KITS THE HEAD LINER WAS REMOVED.  CORROSION WAS PRESENT AT FORE AND AFT UPPE	R, SPAR CAPS AND SKINS.  OWNER WAS ADVISED.  FURTHER INSPECTION FOUND CORROSION PRESENT UNDER LEAD SHEETS IN THE SAME AR	EA.  LEFT AND RIGHT ROOT RIB ASSEMBLIES ALSO HAD CORROSION PRESENT AS WELL AS A CRACK IN THE LEFT HAND ROOT RIB. PROPER 	INSPECTION PROCEDURE SHOULD HAVE CAUGHT THIS PRIOR TO REACHING THIS STAGE OF CORROSION.			1	H	7	1 	3O			 	A20CE   					 
2001042400287	20010424	00287	CE  	2001	4	24	2001085          	1	20010419	G	2720		CONTROL UNIT    			BEECH 	1900  	1900D       	1154162	CE  										RUDDER	MALFUNCTIONED   	A			GLBA	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CE	01	257GL					UE257				UNCOMMANDED RUDDER BOOST IN FLIGHT, PENDING CORRECTIVE ACTION						2	L	7	2 	4T			RT	A24CE   					 
2002012400099	20020124	00099	CE  	2002	1	24	2001112329       	1	20011126	G	2910	465588001045	LINE            			RKWELL	NA265 	NA26565     	7630107	CE  										HYD SYSTEM	CRACKED         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	6NR	4655 				46529				MAINTENANCE PERSONNEL NOTICED FLUID LEAKAGE FROM BELLY PANEL AFT OF LANDING GEAR FOLLOWING PILOT'S COMPLETION OF "SPOILE	R AUTO EXTEND" PREFLIGHT CHECK BY FLIGHT CREW.  VISUAL INSPECTION DETERMINED SPOILER AUTO EXTEND LINE ASSEMBLY TO BE LEA	KING PAST B-NUT AND SLEEVE WHERE IT CONNECTS TO SPOILER CONTROL DUMP VALVE. DEFECT WAS CRACK AT LIP OF DOUBLE FLARE.   M	OST PROBABLE CAUSE IS SUDDEN SHOCK FROM AUTO EXTEND ACTIONS AT LANDING AND DURING PREFLIGHT CHECKS.			2	L	7	2 	4J			 	A2WE    					 
2001073000303	20010730	00303	EU  	2001	7	30	2001F00015       	2	20010605	G	7310	1159P20106	FUEL LINE       			GULSTM	G1159 	G1159       	3953505	SO  	RROYCE	SPEY  	SPEY5118    	54523	EU  					RT ENGINE	RUPTURED        	C				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			EA	09	80AG					164				RIGHT MAIN FUEL LINE RUPTURED ON TAKEOFF WHICH CAUSED ENGINE TO SPOOL DOWN TO FLIGHT IDLE.  REPLACED FUEL LINE ON ENGINE	.  HP FUEL PUMP  WAS ALSO DAMAGED AND REPLACED.  ENGINE WAS BORESCOPED AND RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A12EA   	E2EU				 
2001071700036	20010717	00036	SO  	2001	7	17	2001F00037       	2	20010505	G	8520		SNAP RING       	CONT        		CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550*      	 	SO  					CRANKSHAFT	MISSING         	D				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	18118	850  			284276R	18503328				3-26-01 REMOVED NO. 1 AND 3 CYLINDERS TO COMPLY WITH CRANKSHAFT COUNTER WEIGHT AD.  FACTORY TECH REP REMOVED AND INSPECT	ED COUNTER WEIGHT AMOUNTING FLANGES (4), REPLACED COUNTER WEIGHTS AND ASSOCIATED PARTS, AND CYLINDERS AND ASSOCIATED PAR	TS, 50 ENGINE HOURS LATER AFT COUNTER WEIGHT PIN FELL OUT DURING START UP.  ENGINE DAMAGED SUBSTANTIAL.  ENGINE REMOVED 	AND REPLACED.			1	H	7	1 	3O	3	O	 	3A24    	E3SO				 
2001071800128	20010718	00128	CE  	2001	7	18	2001F00046       	1	20010430	G	5751	65241263	SKIN            			CESSNA	500   	550         	2076604	CE  										AILERON	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	26621	7855 				5500593				DURING A SCHEDULED PHASE INSPECTION THE LEFT AILERON WAS REMOVED.  UPON REMOVAL THE LEADING EDGE SKIN AT THE WEIGHT ATTA	CHMENT SCREWS WAS FOUND CRACKED.  THIS HAD ALLOWED THE SKIN TO CRACK ABOVE AND BELOW A SCREW APPROX. .5000.  THE RIGHT A	ILERON WAS ALSO REMOVED AND TWO OF THESE LEADING EDGE WEIGHT SCREWS WERE ALSO FOUND LOOSE.				1	L	7	2 	4F			 	A22CE   					 
2001080200261	20010802	00261	SO  	2001	8	2	2001F00048       	1	20010106	G	7120	8401002	MOUNT           			PIPER 	PA46  	PA46310P    	7104605	SO  										ENGINE	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	25120	3890 				468508097				FOUND ENGINE CONTROL CABLES CHAFFING ON THE ENGINE MOUNT DURING ENGINE CHANGE.  DAMAGE WAS FOUND TO BE BEYOND LIMITS.  S	ENT MOUNT FOR REPAIR.  ENGINE MOUNT WAS FOUND TO HAVE 6 CRACKS AND CORROSION BEYOND LIMITS .					1	L	7	1 	3O			RT	A25SO   					 
2001073000304	20010730	00304	SO  	2001	7	30	2001F00062       	2	20010202	G	8520		DRIVE GEAR      			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  					ENGINE	FAILED          	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4456W	300  	300  			E537	122716R			ENG HAD STARTER DRIVE FAILURE. INVESTIGATION, STARTER DRIVE HAD BEEN SWITCHED 5 TIMES IN 300 HRS. FOUND OIL GALLEY TO  S	TARTER DRIVE PLUGGED.    SPLIT CRANKCASE, FOUND OIL GALLEY FROM REAR CAMSHAFT BRG SURFACE TO STARTER DRIVE BRG PLUGGED. 	 THE PLUG WAS NOT IN PIECES BUT 1 SOLID PIECE OF SILICONE FROM JOURNAL TO STARTER DRIVE BRG.  NO OTHER SILICONE WAS FOUN	D IN ENGINE.  SILICONE APPEARS TO HAVE BEEN ACTUALLY INJECTED INTO OIL GALLEY, PRIOR TO  ENGINE ASSEMBLY. PREVIOUS OVERH	AUL: ENG O/H 8 YEARS(300 HRS) AGO BY LOG BOOK AND STICKER.  ALL BEARING SURFACES IN ENG DESTROYED, INCLUDING CRANKCASE A	ND OIL PUMP.  ENG OIL FILTER, SMALL AMT OF ALUMINUM.  FOUND LG AMTS OF STEEL IN OIL SUMP FROM FAILED STARTER DRIVE.	1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001071600057	20010716	00057	CE  	2001	7	16	2001F00063       	1	20010319	G	3310	76080241	OVERLAY         			LEAR  	35    	31A         	5170531	CE  										COCKPIT	CRACKED         	C				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	03	70AE	707  				188				DURING FLIGHT, PILOT OBSERVED SMOKE COMING FROM THE ENGINE INSTRUMENT PANEL LEFT ITT INDICATOR.  PILOT DECLARED EMERGENC	Y AND LANDED.  INVESTIGATION REVEALED THAT THE LIGHTING OVERLAY HAD CRACKED AND WAS ARCING AT THE CRACK.  NO ARCING TO T	HE LOCAL STRUCTURE WAS FOUND.  IT WAS DETERMINED THAT THE ENGINE INSTRUMENTS WERE NOT FLUSH WITH THE INSTRUMENT PANEL.  	ALLOWING A DEFLECTION IN THE OVERLAY.  FURTHER INSPECTION FOUND MOST ALL OF THE ENGINE INSTRUMENT MOUNTING BRACKETS TO B	E BENT AND BROKEN, POSSIBLY FROM OVER TIGHTENING.		2	L	7	2 	4F			RT	A10CE   					 
2001071600058	20010716	00058		2001	7	16	2001F00067       	4	20010419	G	2562	AK450	ELT             			CESSNA	206   	U206G       	2073356	CE  										TAIL	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2PS	86   				U20606916				ELT UNIT WEAK UPON TEST.  REMOVED AND REPLACED BATTERIES (OLD WERE  MISMATCHED) W/NEW, NO IMPROVEMENT.  OUR GOVERNMENT R	ADIO SHOP CHECKED UNIT.  1) FOUND DISSIMILAR METALS ON SOLDERING JOINTS(IE STEEL/SOLDER)  2)  UNIT WAY OFF FREQUENCY.					1	H	7	1 	3O			 	A4CE    					 
2001071700037	20010717	00037		2001	7	17	2001F00068       	4	20010427	G	3418	SL29849147173	VANE            			LEAR  	25    	25B         	5170511	CE  										STALL WARNING	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	731CW					117				DOC HOWARD MACH II STC SYSTEM.  AFTER A SCHEDULED 300 HOUR INSPECTION, AIRCRAFT WAS TEST FLOWN, FINDING AOA SYSTEM INOPE	RATIVE.  SYSTEM WAS TROUBLESHOT, FOUND TO BE SATISFACTORY ON GROUND.  IN FLIGHT AOA  REMAIN STEADY, NO STALL WARNING, PU	SH/PULLER FUNCTIONING WHILE EXPERIENCING WING AND TAIL BUFFET.  SAFETY RECOMMENDATION INITIATED.				2	L	7	2 	4J			 	A10CE   					 
2001071600060	20010716	00060	CE  	2001	7	16	2001F00070       	1	20010516	G	5310	241127657	DOOR FRAME      			LEAR  	35    	35A         	5170602	CE  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	701DA					35A180				DURING ROUTINE INSPECTION FORWARD DOOR JAMB WAS FOUND CRACKS THE WIDTH OF THE DOOR JAMB IN LINE WITH THE HINGE SEAM.  FU	RTHER DISASSEMBLY FOUND ADDITIONAL CRACKS ON THE FORMED STEP RISER, DIRECTLY BELOW THE DOOR JAMB BETWEEN THE JAMB AND TH	E DOOR SKIN.				2	L	7	2 	4F			 	A10CE   					 
2001071700039	20010717	00039	EU  	2001	7	17	2001F00071       	1	20010524	G	3240	5713001501	CONTROL HANDLE  			ISRAEL	1124  	1124        	4500102	EU  										COCKPIT	BROKEN          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	351C		3000 			264				PARKING BRAKE LEVER FELL OFF OF THE BRAKE CONTROL VALVE CAUSING THE PARKING BRAKE PORTION OF THE BRAKE CONTROL VALVE TO 	SPRING TO THE PARKING BRAKE POSITION LOCKING THE BRAKES.  MAKING THE AIRCRAFT UNABLE TO MOVE.					2	M	7	2 	4F			 	A2SW    					 
2001072500618	20010725	00618	EU  	2001	7	25	2001F00091       	1	20010601	G	2930	EVP310	VALVE           			UROCOP	EC120 	EC120B      	8680987	EU  										HYD SERVO	DEFECTIVE       	H				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			WP	25	255SD	395  				1102				DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK.  UPON ACTIVATING THE HYDRAU	LIC SWITCH ON THE COLLECTOR THE HYDRAULIC LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE A	CCUMULATOR.  THIS SHOULD NOT HAPPEN.  ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN 	IT MALFUNCTIONED AGAIN.  THE HYD POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED THIS MAL	FUNCTIONED.		1	G	7	2 	3U			NC	R0001RD 					 
2001072500620	20010725	00620	EU  	2001	7	25	2001F00092       	1	20010601	G	2930	EVP310	VALVE           			UROCOP	EC120 	EC120B      	8680987	EU  										HYDRAULIC SERVO	DEFECTIVE       	H				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	25	255SD	395  				1102				DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK.  UPON ACTIVATING THE HYDRAU	LIC SWITCH ON THE COLLECTOR THE HYD LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE ACCUMUL	ATOR.  THIS SHOULD NOT HAPPEN.  ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN IT MAL	FUNCTIONED AGAIN THE HYDRAULIC POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED THIS MALFU	NCTION.		1	G	7	2 	3U			NC	R0001RD 					 
2001071700040	20010717	00040	EU  	2001	7	17	2001F00093       	1	20010601	G	2913	EVP310	POWERPACK       			UROCOP	EC120 	EC120B      	8680987	EU  										HYDRAULIC SYS	MALFUNCTIONED   	C				K				NONE                    				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	25	255SD	395  				1102				DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK.  UPON ACTIVATING THE HYDRAU	LIC SWITCH ON THE COLLECTOR THE HYDRAULIC LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE A	CCUMULATOR.  THIS SHOULD NOT HAPPEN.  ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN 	IT MALFUNCTIONED AGAIN.  THE HYDRAULIC POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED TH	IS MALFUNCTION.		1	G	7	2 	3U			NC	R0001RD 					 
2001072500622	20010725	00622	EU  	2001	7	25	2001F00094       	1	20010601	G	2930	GHC1004	POWERPACK       			UROCOP	EC120 	EC120B      	8680987	EU  										HYD SYSTEM	DEFECTIVE       	H				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	25	255SD	400  				1102				AFTER STARTING THE HELICOPTER THE CYELIC STICK FELT STIFF AND SLUGGISH WHEN MOVED IN ANY DIRECTION.  AFTER RUNNING FOR S	EVERAL MINUTES THE CONTROLS FELT BETTER BUT NOT NORMAL AFTER REPLACING THE HYDRAULIC POWER PACK THE PROBLEM WEN AWAY.  T	HE FILTER WAS REMOVED AND WHAT APPEARED TO BE VERY FINE METALLIC PARTICLES WERE PRESENT IN THE HYDRAULIC FLUID.				1	G	7	2 	3U			NC	R0001RD 					 
2001080200262	20010802	00262	SO  	2001	8	2	2001F00097       	1	20010627	G	3222	4533307	STRUT           	PIPER       		PIPER 	PA31T 	PA31T1      	7103126	SO  										NLG	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	819SW					31T8104059				INCIDENT HAPPENED DUE TO NOSE GEAR STEERING ARM PN 4438600 ON TOP OF NOSE STRUT HOUSING, BECOMING LOOSE DUE TO ATTACHMEN	T BOLTS FOR ARM BECOME LOOSE AND SHEARED OFF.  AS A RESULT STEERING WAS MINIMAL AND UNCONTROLLABLE ON LANDING.					1	L	7	2 	3T			 	A8EA    					 
2001072700003	20010727	00003	EA  	2001	7	27	2001F00104       	1	20010710	G	6310	NAS12254N	BOLT            			SCWZER	269   	269D        	8059501	EA  										DRIVESHAFT	LOOSE           	D				R				AUTOROTATION            				I	F	J	FLT. ATTITUDE INST.       	FLT CONT AFFECTED         	WARNING INDICATION        	HO	HOVERING       	1			SW	17	296RL					0020				DURING PRACTICE AUTOROTATION, ENGINE POWERSHAFT TO KFLEX POWERTRAIN ADAPTER CAME LOOSE BY BACKING OUT,  DURING OPERATION	 MAIN ROTOR WAS NO LONGER POWERED BY ENGINE. BOLT PIN NAS1225-4N IS A BOLT WITH A SMALL CIRCLE OF PLASTIC ON THREADS FOR	 LOCKING.  EMERGENCY LANDING, NO DAMAGE.				1	G	7	1 	3U			0	4H12    					 
2001071700041	20010717	00041	NE  	2001	7	17	2001F00108       	2	20010612	G	8530	116734	CYLINDER        			DOUG  	DC3   	DC3ASC3G    	3021436	WP  	PWA   	R1830 	R1830*      	52020	NE  					ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	12BA		79   			10035				NR 13 CYLINDER BARREL CRACKED ALL THE WAY AROUND WHERE HEAD IS THREADED ONTO BARREL.  CRACK BROKE COMPRESSION RINGS RESU	LTING IN LOSS OF COMPRESSION.					2	L	7	2 	4R	4	R	 	A669    	5E4				 
2001071700042	20010717	00042	CE  	2001	7	17	2001F00109       	1	20010620	G	5744	51155496	BRACKET         	CESSNA      		CESSNA	402   	402C        	207590R	CE  										AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	57PB					402C0300				CRACKED AT AILERON YOLK ATTACH POINTS.						1	L	7	2 	3O			 	A7CE    					 
2001071700044	20010717	00044	CE  	2001	7	17	2001F00111       	1	20010625	G	2510		SPRING          	AMSAFTYEQUIP		CESSNA	182   	182Q        	2072732	CE  										HARNESS	BROKEN          	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	4603N	2    			6262	18267280				AIRCREW SQUAWKED COPILOT INERTIA REEL HARNESS LOCKED UP AND WOULD NOT RELEASE.  AMT DETERMINED COIL SPRING WITHIN INERTI	A REEL HOUSING HAD BROKEN LOOSE FROM ITS INSTALLED POSITION AND JAMMED THE ROLLER.  DATE STAMP FOR THE INERTIA REEL ASSE	MBLY WAS 0401(APR 01).  BOTH PILOT AND COPILOT INERTIA REELS WERE INSTALLED ON THIS AIRCRAFT 1 JUNE 01.  COPILOT HARNESS	 LOCKED UP ON 7 JUNE O1.  ASSEMBLY WAS RETURNED TO MFG FOR REWORK, 21 JUNE 01.			1	H	7	1 	3O			NT	3A13    					 
2001080100146	20010801	00146	EA  	2001	8	1	2001F00113       	2	20010605	G	8520	76148	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	CHIPPED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	555FS	1627 				317952046	L861561A			WHEN REMOVING NR 3 CYLINDER DUE TO LOW COMPRESSION, IT WAS NOTICED THAT THE LOBE ON THE CAMSHAFT FOR THE NR 3 INTAKE WAS	 CHIPPED.  PEELING THE FACE OF THE INTAKE BODY WHICH RIDES ON THE LOBE REVEALED THAT IT ALSO WAS CHIPPED.  BOTH OIL AND 	FILTER WERE CHANGED REGULARLY AT 50 HOURS.  OBVIOUSLY ONE OF THE PARTS WAS OR BECAME CHIPPED AND CAUSED THE OTHER TO FAI	L.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001071700046	20010717	00046	EA  	2001	7	17	2001F00114       	2	20010605	G	8520	72877	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	CHIPPED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	555FS	1627 				317952046	L861561A			WHEN REMOVING NR 3 CYLINDER DUE TO LOW COMPRESSION, IT WAS NOTICED THAT THE LOBE ON THE CAMSHAFT FOR THE NR 3 INTAKE WAS	 CHIPPED.  PEELING THE FACE OF THE INTAKE BODY WHICH RIDES ON THE LOBE REVEALED THAT IT ALSO WAS CHIPPED.  BOTH OIL AND 	FILTER WERE CHANGED REGULARLY AT 50 HOURS.  OBVIOUSLY ONE OF THE PARTS WAS OR BECAME CHIPPED AND CAUSED THE OTHER TO FAI	L.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001080100148	20010801	00148	NE  	2001	8	1	2001F00118       	3	20010702	G	6110	E3932	HUB             			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE4A	HCE4A3I     	NE  	BRG RETENTION	SCORED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	49543	10465	3463 			UE181		HJ440		PROPELLER WAS RECEIVED FOR O/H WITH EXCESSIVE GREASE LEAKAGE FROM ALL BLADES.  PROP WAS DISASSEMBLED TO START O/H PROCES	S.  WHEN HUB UNIT WAS SPLIT, THERE WAS EXCESSIVE AMOUNTS OF GREASE INSIDE. UPON FURTHER INSPECTION, THE BEARING RACE HAD	 SHATTERED INTO SEVERAL PIECES, SCORING THE INSIDE RETENTION AREA.  REWORK WAS BEYOND ALLOWABLE LIMITS.  HUB WAS RETIRED	 FROM SERVICE.			2	L	7	2 	4T	3	T	RT	A24CE   	E2NE	5	C	P10NE	 
2001080800317	20010808	00317	CE  	2001	8	8	2001F00164       	1	20010622	G	2120	973800011	DUCT            			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					CABIN PRESSURE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	78DA					BE11				WHILE TROUBLESHOOTING POOR CABIN PRESSURIZATION, FOUND FAILED HOSE IN LEFT ENGINE AIR SUPPLY LINE TO CABIN.  THIS CAUSED	 PRESSURIZATION TO WORK POORLY, BECAUSE THERE WAS NO INPUT TO CABIN FROM LEFT FLOW PACK.  SUSPECT DUCT FAILED DUE TO AGE	.				1	L	7	2 	4T	3	T	 	A14CE   	E2WE				 
2001081000154	20010810	00154	CE  	2001	8	10	2001F00165       	1	20010627	G	3222	35825174	ARM             			BEECH 	95    	95          	1153402	CE  										NLG	CRACKED         	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09										DURING A RECENT INVESTIGATION OF AN INCIDENT OF A BEECH 95 THAT THE NOSE GEAR COLLAPSED ON ROLL OUT AFTER LANDING.  IT W	AS DISCOVERED THAT THE LANDING GEAR CRANK ARM PART NUMBER 35-825174 THAT ATTACHES TO THE LANDING GEAR TRANSMISSION BOX H	AD CRACKED.  THE CRACKED ARM ALLOWED THE ARM TO FLEX ADN ROTATE ON THE SPLINES OF THE TRANSMISSION SHAFT WHICH KEEPS THE	 PUSH PULL TUBE TO THE NOSE GEAR IN THE FORWARD POSITION.  THIS ARM IS ALSO INSTALLED ON SEVERAL MODELS.  PROBABLE CAUSE	 IS FATIGUE.  RECOMMEND THAT ARM BE REMOVED AT THE NEXT INSPECTION AND INSPECTED WITH 10X MAGNIFIER.  (ATTACHED PHOTOS)		1	L	7	2 	3O			 	3A16    					 
2001082200269	20010822	00269	SW  	2001	8	22	2001F00205       	1	20010712	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	83233					7AC1897				SPAR CRACKED						1	H	7	1 	3O	3	O	 	A759    	E205				 
2001090500047	20010905	00047		2001	9	5	2001F00248       	4	20010716	G	3418	S16729	DETECTOR        			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					WING	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	35VA					18268129				UPON INSTALLING NEW LIFT DETECTION NOTED THAT WHEN WIRED AS ORIGINALLY REMOVED FROM AIRCRAFT, WITH HEAT TURNED ON, DETEC	TION WAS INOPERATIVE.  GROUND FOR HEATER WAS INSTALLED ON COMMON FOR DETECTION; CAUSING A NO POTENTIAL WHEN HEATER TURNE	D ON.				1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2001080100149	20010801	00149	WP  	2001	8	1	2001FA0000001    	2	20010515	G	8520	8976021	CAM             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ENGINE	MISMANUFACTURED 	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4441T					4410133				AFTER INSTALLING NEWLY OVERHAULED ENGINE ON AIRCRAFT, FOUND THAT THE -30 P.P.C. COULD NOT BE RIGGED.  REMOVED P.O.C. AND	 FOUND THAT THE CAM INSIDE, ALTHOUGH MARKED CORRECTLY (P/N 897602-1), THE CAM WAS MANUFACTURED WRONG.  IT HAS THE WRONG 	CAM PROFILE.  REF: SB TPE331-72-0904.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2001080100150	20010801	00150	WP  	2001	8	1	2001FA0000002    	2	20010514	G	8520	8976021	CAM             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					ENGINE	MISMANUFACTURED 	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	4441T					4410133	P77443C			AFTER INSTALLING NEWLY OVERHAULED ENGINE ON AIRCRAFT, FOUND THAT THE -30 P.P.C. COULD NOT BE RIGGED.  REMOVED THE P.P.C.	 AND FOUND THAT THE CAM INSIDE, ALTHOUGH MARKED WITH THE CORRECT P/N (8976021) WAS MANUFACTURED WRONG.  IT HAS THE WRONG	 CAM PROFILE.  REF: SB TPE331-72-0904.				1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2001071800006	20010718	00006	NM  	2001	7	18	2001FA0000003    	1	20010501	G	3244	26107012	TIRE            			DORNER	DO32  	DO328100    	2996000	NM  										RT MLG	DEFLATED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	404SS		40   			3090				DURING WALKAROUND INSPECTION AFTER LANDING IN KBHM, CREW DISCOVERED ROB MAIN LANDING GEAR TIRE WAS FLAT.  THE WHEEL O-RI	NG WAS FOUND PROTRUDING TOWARDS THE CENTER OF THE WHEEL.  EIGHT OF THE TEN WHEEL THROUGH BOLTS WERE LOOSE.  THE WHEEL WA	S RETURNED TO THE OVERHAULER FOR EVALUATION AND OVERHAUL.				2	H	7	2 	4T			RT	A45NM   					 
2001072400003	20010724	00003	EU  	2001	7	24	2001FA0000008    	1	20010521	G	5540		RIVET           			ISRAEL	1124  	1124        	4500102	EU  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	980S	1    				401				CRACKS IN DIMPLES OF RIVETS ON SKIN OF RUDDER, LOOKS LIKE THEY HAVE BEEN THERE SINCE MANUFACTURE.  FABRICATING NEW RIBS 	PER GALAXY AEROSPACE DRAWINGS AND DOING A SPAR SPLICE PER GALAXY.  SUSPECT ALL RUDDERS THAT ARE MANUFACTURED THE SAME AS	 THIS ONE ARE ALSO CRACKED.				2	M	7	2 	4F			 	A2SW    					 
2001071800007	20010718	00007	EU  	2001	7	18	2001FA0000009    	1	20010518	G	5330		SKIN            			AMD   	FALC50	FALCON50MYST	2730106	EU  										FUSELAGE	CORRODED        	G			BQVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	50TG		6133 			117				CORROSION IN AREA OF AFT FUSELAGE SKINS AT ACU EXHAUST OUTLETS.  WATER ENTRAPMENT.  REPAIRED UNDER BOMBARDIER REO NR 601	-53-30-278.					2	L	7	3 	4F			 	A46EU   					 
2001080100151	20010801	00151	NM  	2001	8	1	2001FA0000012    	1	20010521	G	3230	108510	HOUSING         			BOEING	727   	727         	UTILSYS	NM  										AFT MOUNT	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING HAS A BROKEN AFT MOUNT.   PROBABLE CAUSE: MISHANDLED						2	L	7	3 	4J			RT	A3WE    					 
2001080100152	20010801	00152	NM  	2001	8	1	2001FA0000013    	1	20010521	G	2730	401606223	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										SEAL PLATE SURFC	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1601D					HOUSING ASSEMBLY IS CRACKED ON THE SEAL PLATE SURFACE.  PROBABLE CAUSE:  HOUSING ASSEMBLY IS MADE FROM MAGNESIUM ALLOY A	ND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS.					2	L	7	3 	4F			RT	A3WE    					 
2001080100153	20010801	00153	NM  	2001	8	1	2001FA0000014    	1	20010518	G	2730	401611572	BARREL          	MOOG        		BOEING	727   	727*        	       	NM  										BARRELL BORE	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1098					BARREL ASSEMBLY HAS PITTING AND EROSION IN MAIN BORE.  PROBABLE CAUSE:  DISSIMILAR CORROSION.						2	L	7	3 	4F			RT	A3WE    					 
2001080100154	20010801	00154	NM  	2001	8	1	2001FA0000015    	1	20010518	G	2730	401644557	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										SEAL SURF, HOLES	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1098					HOUSING ASSEMBLY HAS PITTING AND CORROSION IN BOLT HOLES, CAP ASSEMBLIES, PORTS AND SEALING SURFACES.  PROBABLE CAUSE:  	DISSIMILAR CORROSION.  RECOMMENDATIONS:  REPLACE MAGNESIUM HOUSING ASSEMBLIES WITH ALUMINUM ALLOY.					2	L	7	3 	4F			RT	A3WE    					 
2001080100155	20010801	00155	NM  	2001	8	1	2001FA0000016    	1	20010518	G	2730	401611572	HOUSING         	MOOG        		BOEING	727   	727         	UTILSYS	NM  										CK VLV PORT, LAN	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					1098					ELBOW HOUSING HAS SEVERE CORROSION IN BOLT HOLES, CHEDK VALVE PORT, PACKING LANDS AND ON SEALING SURFACE FACE.  PROBABLE	 CAUSE:  DISSIMILAR CORROSION.  RECOMMENDATIONS: REPLACE MAGNESIUM ELBOW WITH ALUMINUM ALLOY.					2	L	7	3 	4J			RT	A3WE    					 
2001080100156	20010801	00156	EA  	2001	8	1	2001FA0000017    	2	20010516	G	8520	LW19332	CONNECTING ROD  			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					NR 2 CYLINDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	5640M					3240295	L1774848A			NR 2 PISTON WAS REMOVED, CONNECTING ROD BUSHING WAS FOUND TO HAVE MOVED TO THE POSITION AS SHOWN IN PHOTO AND ONLY STOPP	ED BY CONTACTING THE INSIDE OF PISTON PIN BOSS OF THE PISTON.  BUSHING SHOWED EVIDENCE OF MOVING TORSIONALLY FROM PROPER	 POSITION IN REF. TO SPLIT LINE BUT DID NOT SHOW AMOUNT OF WEAR ON OD, NOT TURNING IN THE ROD AS CONTINUOUS CONDITION.  	SLIGHT DISCOLORATION OF PORTION OF BUSHING EXTENDING BEYOND ROD BOSS INDICATING IT HAD BEEN IN THIS POSITION FOR SOME HO	URS.  NO EVIDENCE OF DAMAGE TO PISTON BOSS OR PISTON PIN OD AND BUSHING ID.  WHEN BUSHING WAS REMOVED FROM ROD, IT FRACT	URED AS IN PHOTO.  CORRESPONDING FRET LINE ON ROD BOSS ID AT POINT OF BUSHING FRACTURE.  (ATTACHED PHOTO)	1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001072500625	20010725	00625	NM  	2001	7	25	2001FA0000018    	1	20010518	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETAII   	7640110	NM  										ROTOR DRIVE	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	17	7087X	488  				2829				V-BELT, (PN A190-2) OF THE R22 DRIVE SYSTEM, MALFUNCTIONED BY COMING APART AND JUMPED OFF DRIVE PULLEYS, CAUSING LOSS OF	 DRIVE TO ROTOR DRIVE SYSTEM.					1	G	7	1 	3O			 	H10WE   					 
2001080100157	20010801	00157	SW  	2001	8	1	2001FA0000019    	1	20010601	G	5711		SPAR            			BBAVIA	7     	7CCM        	21101MW	SW  										WING SPAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2762E					7AC6345				CRACK ON BOTTOM SURFACE OF SPAR, LEFT SIDE REAR. (BUTT)  FOUND PRIOR TO CRACK INSPECTION AS PER AD OWNER DISCONTINUED AN	NUAL INSPECTION PRIOR TO FULL INSPECTION.					1	H	7	1 	3O			 	A759    					 
2001080100158	20010801	00158	SW  	2001	8	1	2001FA0000020    	1	20010607	G	5720		STRUT           			BBAVIA	7     	7CCM        	21101MW	SW  										WING STRUT	DEFECTIVE       	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 STUT.  WHEN POKED WITH AIR 	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			 	A759    					 
2001080100159	20010801	00159	EA  	2001	8	1	2001FA0000021    	2	20010524	G	8530	AEL6510212	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CYLINDER HEAD	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4350G	1379 				288490058				CRACKED FROM SPARK PLUG HOLE TO EX SEAT.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001080100160	20010801	00160	EA  	2001	8	1	2001FA0000022    	2	20010524	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	2366W	823  				288516046				CRACKED FROM TOP OF SPARK PLUG HOLE, AROUND OUTSIDE OF EX SEAT TO BOTTOM OF SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001080100161	20010801	00161	CE  	2001	8	1	2001FA0000023    	1	20010530	G	3213	S3461111	BOLT            			CESSNA	172   	172S        	2072439	CE  										LEFT STRUT	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	784SP					172S8711				BOLTS ARE INSTALLED BACKWARDS, POINTING FORWARD.						1	H	7	1 	3O			NT	3A12    					 
2001080100162	20010801	00162	CE  	2001	8	1	2001FA0000024    	1	20010530	G	3213	S3461116	BOLT            			CESSNA	172   	172S        	2072439	CE  										RIGHT STRUT	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	784SP					172S8711				BOLTS ARE INSTALLED BACKWARDS, POINTING FORWARD.						1	H	7	1 	3O			NT	3A12    					 
2001080100163	20010801	00163	CE  	2001	8	1	2001FA0000025    	1	20010530	G	5753	AN311A	BOLT            			CESSNA	172   	172S        	2072439	CE  										RT FLAP	MISINSTALLED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	784SP					172S8711				BOLTS ARE INSTALLED BACKWARDS, POINTING OUTBOARD.						1	H	7	1 	3O			NT	3A12    					 
2001080100164	20010801	00164	EA  	2001	8	1	2001FA0000027    	2	20010429	G	8500	AN657A	BOLT            								LYC   	O320  	O320E2A     	41508	EA  					PROPELLER	LOOSE           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	26RK	124  					L2383927A			PROPELLER BOLTS (AN6-57A) BROKE IN FLIGHT AT CRUISE POWER (2500 RPM) AT 7500 FT. MSL. NOTICED THAT ONE BOLT WAS MISSING 	AND THE NUT ON ANOTHER COULD BE REMOVED BY HAND.  POSSIBLE THAT TWO NUTS, (MS 20365-624) LOOSENED CAUSING VIBRATION IN P	ROPELLER WHICH CAUSED BOLT FAILURE .  NOTE:  THAT ONLY THE TWO NUTS THAT SEEMED TO BE LOOSE, WERE REPLACED 124 HOURS BEF	ORE FAILURE.  ALL  OTHER NUTS WERE STILL INTACT.  PROPELLER SEPARATED FROM ENGINE IN FLIGHT.								3	O			E274				 
2001080100165	20010801	00165	CE  	2001	8	1	2001FA0000028    	1	20010601	G	5320	365550483	GUARD           			BEECH 	36    	A36         	1151604	CE  										PULLEY	CRACKED         	C			WC7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	3243B	100  				E3243				THIS IS THE SECOND OCCURENCE OF THE PULLEY GUARD CRACKING.  THE AIRCRAFT TOTAL TIME 703.1.  ON THE FIRST OCCURENCE THE G	UARD HAD A LARGE CRACK AND A PIECE MISSING.  THIS OCCURENCE THE ENTIRE GUARD WAS FOUND MISSING.					1	L	7	1 	3O			 	3A15    					 
2001080100166	20010801	00166	EA  	2001	8	1	2001FA0000030    	2	20010524	G	8550	LW1568B	TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					OIL SUMP	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4596P	2000 				15284776				INDUCTION TUBE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE.  ENGINE OIL SUMP REPLACED TO CORRECT PROB	LEM.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001080100167	20010801	00167	EA  	2001	8	1	2001FA0000031    	2	20010605	G	8530	AEL74230P010	GUIDE           								LYC   	O360  	O360F1A6    	41514	EA  					EXHAUST	OUT OF TOLERANCE	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17							L2915236A			CYLINDER HAD LOW COMPRESSION READINGS, 20/80.  CYLINDER WAS REMOVED FROM ENGINE AND INSPECTED.  EX. GUIDE WAS INSPECTED 	AND FOUND TO BE OUT OF SERVICE LIMITS.  EX GUIDE ID WAS MEASURED, AND A READING OF .5325 WAS TAKEN.  MAX SERVICE DIMENSI	ON FOR A 300 HR CYLINDER EX GUIDE ID IS .5015/.5025 PER LYCOMING O/H MANUAL 60294-7-8.  THIS CYLINDER HAD 236 HOURS SINC	E OVERHAUL.								3	O			E286				 
2001071800008	20010718	00008	SO  	2001	7	18	2001FA0000035    	1	20010620	G	5712	1159WM4007415G	RIB             		GIV         	GULSTM	G1159 	GIV         	3980115	SO  										LT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	460QS	2298 	2298 		1360	1360				WHILE DOING A SCHEDULE VISUAL INSPECTION OF THE WING IT WAS NOTED A CRACK WAS IN RIB WEB.  THE RIB IS LOCATED NEXT TO TH	E LAST OUTBOARD LEFT WING.  CRACK IS 7 INCH LONG ALONG THE THE BOTTOM SIDE THEN TURNS UP AT BOTH ENDS FOR 1 INCH.  REMOV	ED AND REPLACED WITH NEW RIB.				2	L	7	2 	4F			RT	A12EA   					 
2001080100169	20010801	00169	EA  	2001	8	1	2001FA0000041    	2	20010524	G	8550	LW15688	SUMP            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					SUMP ASSY, OIL	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4596P					15284776				INDUCTION TUBE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE.  ENGINE OIL SUMP REPLACED TO CORRECT PROB	LEM.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001080100170	20010801	00170	CE  	2001	8	1	2001FA0000042    	1	20010601	G	5753	12210107	FLAP TRACK      			CESSNA	206   	TU206G      	2073357	CE  										WING	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9851Z					U20606701				THE LEFT HAND INBOARD FLAP TRACK IS WORKING LOOSE.  THIS WAS INDICATED BY CRACKED COVE SKIN ATTACH BRACKETS.						1	H	7	1 	3O			 	A4CE    					 
2001080100171	20010801	00171	SO  	2001	8	1	2001FA0000043    	1	20010525	G	7111	23810000	ALT AIR DOOR    			PIPER 	PA30  	PA30        	7103002	SO  										RIGHT ENGINE	LOOSE           	D				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			GL	03	8379Y					301534				ON TAKEOFF ROLL, THE RIGHT ENGINE WOULD NOT DEVELOP FULL POWER.  UPON FUTURE INVESTIGATION FOUND THE ALT AIR DOOR CAME L	OOSE AND WAS BLOCKING THE EJECTOR INTAKE.  UPON FINDING THIS WE INSPECTED THE LEFT ALT AIR BOX AND FOUND THE ALT AIR DOO	R LAYING IN THE COWLING.				1	L	7	2 	3O			 	A1EA    					 
2001080100173	20010801	00173	GL  	2001	8	1	2001FA0000044    	1	20010424	G	3230	5533525	PIN             			NAMER 	T6    	SNJ4        	6400414	GL  										MLG	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7083C	2290 				881447				BINDING OF PIN WOULD NOT ALLOW LEFT MAIN GEAR TO LOCK DOWN, CAUSING GEAR TO COLLAPSE ON LANDING.  UPON INSPECTION, PIN D	OES NOT APPEAR WORN.  MANUAL DOES NOT CALL OUT FOR LUBING PIN.  A SLIGHT OIL FILM ON PIN MAKES IT LOCK NORMAL.					1	L	7	1 	3R			 	A2575   					 
2001080100174	20010801	00174	SO  	2001	8	1	2001FA0000045    	1	20010606	G	5540	6342004	RUDDER BAR      			PIPER 	PA32  	PA32260     	7103206	SO  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4803S	11045				321188				DURING 100 HOUR INSPECTION, FOUND LEFT RUDDER BAR CRACKED AT WELD WHERE STRAIGHT TUBE CONNECTS TO CARRY OVER TUBE.  SPEC	ULATE AGE AND USAGE CAUSED CRACK.. THIS COMPONENT HAS BEEN FOUND CRACKED SEVERAL TIMES IN THE PAST ON OTHER SIMILAR AIRC	RAFT.  LATER MODEL AIRCRAFT HAVE A REINFORCEMENT PLATE WELDED ON THIS AREA BY THE FACTORY.				1	L	7	1 	3O			 	A3SO    					 
2001080200264	20010802	00264	CE  	2001	8	2	2001FA0000046    	1	20010615	G	6120	8976021	CAM             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  					PITCH CONTROL	MISMANUFACTURED 	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07					P143091					RECEIVED A NEWLY OVERHAULED P.P.C. FROM MANUFACTURER, WAS UNABLE TO RIG.  FOUND P.P.C. CAM HAD THE RIGHT PN BUT THE WRON	G CAM PROFILE MANUFACTURE IN IT.  REF: SB TPE331-72-0904.					1	L	7	2 	3T	3	T	RT	A28CE   	E2WE				 
2001080100176	20010801	00176	SO  	2001	8	1	2001FA0000047    	1	20010505	G	7810		EXHAUST PIPE    			PIPER 	PA18  	PA18150     	7101828	SO  										ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	4136E	538  				187809082				FOUND WELD ON WYE PIPE CRACKED AT ANNUAL INSPECTION.  (NO PARTS AVAILABLE AT THIS TIME) ALSO FOUND INNER BAFFLE ON SAME 	PIPE CRACKED.					1	H	7	1 	3O			 	1A2     					 
2001080100177	20010801	00177		2001	8	1	2001FA0000048    	4	20010519	G	2320	CI248	ANTENNA         			CESSNA	182   	T182        	2072736	CE  										VHF ANTENNA	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3525R					18280977				AIRCRAFT FLEW IN WITH BOTH VHF COMM ANTENNA  BROKEN.  AIRCRAFT TOTAL TIME WAS 5 HOURS.  PROBABLE CAUSE NOT KNOWN.						1	L	7	1 	3O			 	3A13    					 
2001080100178	20010801	00178		2001	8	1	2001FA0000049    	4	20010519	G	2320	CI248	ANTENNA         			CESSNA	182   	T182        	2072736	CE  										VHF ANTENNA	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3525R	5    				18280977				AIRCRAFT FLEW IN WITH BOTH ANTENNA BROKEN.  AIRCRAFT TOTAL TIME WAS 5 HOURS.  PROBABLE CAUSE NOT KNOWN.						1	L	7	1 	3O			 	3A13    					 
2001080100179	20010801	00179	CE  	2001	8	1	2001FA0000052    	1	20010606	G	5510	9664000093	PLATE           			BEECH 	80    	65B80       	1152812	CE  										RUDDER	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	19CR	3278 				LD372				DURING ANNUAL INSPECTION, UPPER AND MID RUDDER ATTACH FITTING PLATES (THESE CONTAIN THE BEARINGS) WERE FOUND TO BE SEVER	ELY EXFOLIATED.  THE UPPER RUDDER ATTACH PLATE EXFOLIATED TO THE POINT THAT THE ATTACH POINT HAD FAILED.  THE RUDDER COU	LD BE MOVED APPROXIMATELY SIX INCHES OUT OF ITS PLANE OF ROTATION DUE TO THE UPPER ATTACH POINT FAILURE.  SUSPECT THAT I	NSUFFICIENT OR INFREQUENT INSPECTION OF THE AERA ALLOWED THE CORROSION TO PROGRESS TO THE EXTENT OF ATTACH POINT FAILURE	.		1	L	7	2 	3O			 	3A20    					 
2001071800009	20010718	00009	SO  	2001	7	18	2001FA0000053    	1	20010622	G	3250	74381	SWIVEL          			GULSTM	GV    	GULFSTREAMGV	3980116	SO  										NLG	RUPTURED        	B				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			WP	05	1540	520  				580				NOSE WHEEL STEERING SWIVEL, (AT NOSE LANDING GEAR ASSY) RUPTURED, DEPLETING THE LEFT HYDRAULIC RESERVOIR.  NOTE: THIS RE	SERVOIR PROVIDES HYDRAULIC POWER TO THE FLAPS, LEFT THRUST REVERSER AND THE BRAKES.					2	L	7	2 	4F			RT	A12EA   					 
2001080200266	20010802	00266	SO  	2001	8	2	2001FA0000055    	1	20010605	G	2730	42901002	TUBE            			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR CONTROL	ELONGATED       	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	13FS	3692 				318352024				WHILE C/W UNDER PANEL ITEMS ON ANNUAL CHECKLIST, FOUND ARM ON THE ELEVATOR CONTROL TUBE VERY LOOSE.  DISASSEMBLY SHOWED 	HOLE WHERE ARM MOUNTS TO TUBE VERY ELONGATED.  PART REPLACED WITH NEW PART.  SUGGEST PHYSICALLY CHECKING EACH ARM FOR UN	WANTED MOVEMENT WHEN DOING INSPECTION, NOT JUST VISUAL INSPECTION.				1	L	7	2 	3O			 	A20SO   					 
2001080200267	20010802	00267	CE  	2001	8	2	2001FA0000056    	1	20010613	G	3233	12815041	ACTUATOR        			CESSNA	177   	177RG       	2073709	CE  										MLG	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	34072					177RG0960				DURING CRUISE FLIGHT PILOT REPORTED BUFFET AND LOSS OF GEAR UP INDICATION.  PILOT SLOWED TO GEAR SPEED AND DESENDED TO V	FR CONDITIONS AND RETURNED TO DEPARTURE AIRPORT.  SELECTED GEAR DOWN AND COULD NOT GET GEAR DOWN INDICATION.  EMERGENCY 	EXTENDED GEAR AND OBTAINED A GEAR DOWN INDICATION.  UNEVENTFUL LANDING.  ON INSPECTION FOUND THE LEFT MAIN GEAR DOWN LOC	K ACTUATOR #1281504-1 HAD RUPTURED END SHAFT SEAL AND MOST OF HYDRAULIC FLUID HAD LEAKED FROM SYSTEM.  DISSASEMBELED AND	 FOUND NO DEFECTS EXCEPT FAILED SEAL.REPLACED SEAL AND FUNTION TEST OK. 		1	H	7	1 	3O			 	A20CE   					 
2001080100180	20010801	00180	CE  	2001	8	1	2001FA0000057    	1	20010606	G	5320	9542001549	CHANNEL         			BEECH 	35    	V35A        	1151544	CE  										FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8359N					D8753				UPON REMOVAL OF THE LARGE FLOORBOARD AFT OF THE SPAR, IT WAS NOTED THAT THE TEW MIDDLE/CENTER CHANNEL ASSEMBLIES WERE CO	RRODED.  THE CORROSION WAS SO BAD THAT A TWO INCH AREA AND ONE INCH AREA ON THE OTHER THAT PROVIDES THE MOUNTING FOR THE	 SEAT RAILS WAS MISSING.  THE CAUSE OF THE CORROSION BELIEVED TO BE DISIMILAR METAL CORRIOSION FROM THE SCREWS.  LOOKED 	AT ALL THE OTHER SCREWS THAT SECURE THE CHANNELS AND STIFFENERS AND THEY WERE JUST STARTING TO CORRODE, SO THEY ALL GOT 	REPLACED.		1	L	7	1 	3O			 	3A15    					 
2001080100182	20010801	00182	GL  	2001	8	1	2001FA0000058    	1	20010327	G	3213	35017502	STRUT           			AVIAT 	A1    	A1B         	       	GL  										MLG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	484C					2114				LANDING GEAR STRUT FAILED AT WELD DUE TO COMPLETE LACK OF WELD PENETRATION.  LANDING GEAR SEPARATED FROM AIRCRAFT AT LAN	DING.  DUE TO WELD FAILURE.					1	H	7	1 	3O			NC	A22NM   					 
2001080100183	20010801	00183	SO  	2001	8	1	2001FA0000059    	1	20010616	G	3213	2468105	STRUT           			PIPER 	PA30  	PA30        	7103002	SO  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	08	8418Y	7891 				301570				RIGHT SIDE MAIN LANDING GEAR UPPER HOUSING CRACKED FROM BOLT HOLE WHERE BROKE LINE ATTACHES INTO THE INNER MOST AREA OF 	THE STRUT 1 INCH LONG ON EACH SIDE.  LEAKING FLUID.  POTENTIAL COMPLETE SEPARATION OF GEAR LEG.					1	L	7	2 	3O			 	A1EA    					 
2001080100186	20010801	00186	SW  	2001	8	1	2001FA0000060    	1	20010611	G	2460		HARNESS         			MOONEY	M20   	M20K        	5870220	SW  										FUSELAGE	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	252YC					251074				WHEN REPAIRING AVIONICS POWER SYSTEM, CB PANEL PULLED LOOSE AND OUT FOR MAINTENANCE.  DISCREPANCY NOTED:  FUSELAGE UNDER	 WINDSHIELD CHAFING POWER CABLES TO CB S AND RELAYS.  NO CHAFE STRIP NOTED IN THIS AREA BEHIND CB PANEL AND CHAFING EVID	ENCE ON LARGE POWER WIRES.  GLARESHIELD REMOVAL TO INSPECT.  PROBLEM NOT RELATED TO AVIONICS PROBLEM THAT WAS REPAIRED.				1	L	7	1 	3O			 	2A3     					 
2001080100187	20010801	00187	CE  	2001	8	1	2001FA0000061    	1	20010611	G	3210	084212219	LINK            			CESSNA	404   	404         	2075901	CE  										LINK ASSY DRAG	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	165SA					4040622				LINK ASSEMBLY DRAG.  PN 0842122-19						1	L	7	2 	3O			RT	A25CE   					 
2001080100188	20010801	00188	CE  	2001	8	1	2001FA0000062    	1	20010611	G	2710	581510326CR	CONTROL CABLE   			CESSNA	404   	404         	2075901	CE  										LT AFT AILERON	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	165SA					4040622				LEFT HAND AFT AILERON CABLE.  PN 5815103-26CR    ( BLENDED )						1	L	7	2 	3O			RT	A25CE   					 
2001080100201	20010801	00201	EA  	2001	8	1	2001FA0000063    	2	20010516	G	8550	06B23072	GASKET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					OIL FILTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	737TC					17269654				AD2000-18-23 WAS C/W BY INSTALLING NEW GASKET PT NR 06B23072 UNDER 34 HOURS, GASKET BLEW OUT AND ALL THE OIL WAS BLOWN O	UT.  AIRCRAFT  RETURNED TO AIRPORT SAFELY.  INSPECTION OF GASKET REVELED THAT THE RUBBER GASKET HAD DESOLVED AND BECAME 	VERY SOFT.  A NEW GASKET WAS INSTALLED AS PER INSTRUCTIONS IN THE SB.  NO FURTHER PROBLEMS HAVE BEEN ENCOUNTERED WITH TH	IS AIRCRAFT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001080100202	20010801	00202	CE  	2001	8	1	2001FA0000064    	1	20010614	G	2730	123460020	ELEVATOR        			CESSNA	182   	182S        	2072701	CE  										RT SIDE ELEVATOR	WEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	132ME	276  				18280690				WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, SEVERAL WRINKLES AND LOOSE RIVETS WERE DISCOVERED ON BOTH ELEVAT	ORS ALONG WHERE THE BALANCE TAB ATTACHES TO THE ELEVATOR SPAR.  THE STRUCTURE AROUND THIS AREA APPEARED VERY WEAK AND FL	EXIBLE.  CESSNA WAS CONTACTED FOR TECHNICAL ASSISTANCE.  AT CESSNAS REQUEST, NEW REPLACEMENT ELEVATORS WERE INSTALLED, A	ND THE OLD ONES WERE RETURNED FOR AN ENGINEERING EVALUATION.  ALL INSPECTORS ARE URGED TO VIGILANT FOR SUCH CONDITION ON	 OTHER AIRCRAFT OF THIS TYPE.		1	H	7	1 	3O			NT	3A13    					 
2001080100203	20010801	00203	NE  	2001	8	1	2001FA0000066    	1	20010515	G	5540	27103	PUSHROD         			CONAER	LA4   	LA4200      	5110310	NE  										AFT FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	911CY	2194 				532				REMOVED FORWARD LOWER ROD END FROM RUDDER PUSHROD ASSEMBLY, DUE TO VISIBLE CORROSION.  FOUND EXTENSIVE CORROSION INTERNA	LLY ON ARM AND ROD ASSEMBLY.					1	H	7	1 	3O			 	1A13    					 
2001080100204	20010801	00204	CE  	2001	8	1	2001FA0000067    	1	20010503	G	3222	35825174	ARM             			BEECH 	95    	95          	1153402	CE  										NLG	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2765Y					TD136				UPON LANDING ROLL-OUT THE NOSE GEAR COLLAPSED.  THE CRACK ON THE SPLINE PORTION OF ARM CAUSED THE ARM TO FLEX AND OPEN C	AUSING MATING GEARS TO SEPARATE AND THE NOSE GEAR TO COLLAPSE.  PROBABLE CAUSE IS FATIGUE.  REOCCURRING INSPECTIONS ARE 	RECOMMENDED.				1	L	7	2 	3O			 	3A16    					 
2001071800010	20010718	00010	CE  	2001	7	18	2001FA0000068    	1	20010702	G	7930	30702464	INDICATOR       			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					RT ENGINE	DEFECTIVE       	B				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CE	01	82CR	4950 				46549	P83263			IN PROCESS OF PRE-FLIGHT INSPECTION NOTICED RIGHT ENGINE OIL FILTER BY-PASS INDICATOR PIN HAD POPPED.  INSPECTED OIL FIL	TER AND TOOK SOAP SAMPLE (NEW OIL FILTER INSTALLED).  AFTER TEST RUN AND LEAK CHECK, NOTICED PIN PARTIALLY POPPED AGAIN.	  REMOVED BY-PASS INDICATOR ASSEMBLY AND NOTICED MINIMAL RESISTANCE FOR PIN EXTENSION.  REPLACED ASSEMBLY WITH NEW UNIT.	  DEFECTIVE UNIT HAS ASSEMBLY DATE OF 3Q/87.  ADDITIONALLY THE FOLLOWING NUMBERS APPEAR ON ASSEMBLY:99193SOCN307246-4 N 	AND MFR 05228-7579668.		2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2001080100205	20010801	00205	CE  	2001	8	1	2001FA0000069    	1	20010614	G	2730	12346001	ELEVATOR        			CESSNA	182   	182S        	2072701	CE  										LT SIDE ELEVATOR	WEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	132ME					18280690				WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, SEVERAL WRINKLES AND LOOSE RIVETS WERE DISCOVERED ON BOTH ELEVAT	ORS ALONG WHERE THE BALANCE TAB ATTACHES TO THE ELEVATOR SPAR.  THE STRUCTURE AROUND THIS AREA APPEARED VERY WEAK AND FL	EXIBLE.  CESSNA WAS CONTACTED FOR TECHNICAL ASSISTANCE.  AT CESSNAS REQUEST, NEW REPLACEMENT ELEVATORS WERE INSTALLED, A	ND THE OLD ONES WERE RETURNED FOR AN ENGINEERING EVALUATION.  ALL INSPECTORS ARE URGED TO BE VIGILANT FOR SUCH CONDITION	 ON OTHER AIRCRAFT OF THIS TYPE.		1	H	7	1 	3O			NT	3A13    					 
2001080100207	20010801	00207	GL  	2001	8	1	2001FA0000072    	3	20010703	G	6110		SHAFT           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	PROPELLER SHAFT	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	421LF					421C0059	234899R	742786		AIRCRAFT PROPELLOR WENT INTO FEATHER ON APPROACH.  AFTER LANDING, RESTARTED ENGINE AND PROPELLOR FELL OFF.  PROP SHAFT S	HEARED IN HALF.  ENGINE HAD A PROP STRIKE 400 HOURS PREVIOUS.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2001080100209	20010801	00209	CE  	2001	8	1	2001FA0000074    	1	20010531	G	7112	9691910016	AIR BOX         			BEECH 	95    	95B55       	1152729	CE  										RT ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	38088	2356 	69   			TC2366				RIGHT ENGINE AIRBOX DISPLAYS MORE THAN NORMAL WEAR DUE TO VIBRATION INDUCED CRACKING OF AIRBOX COMPONENTS.						1	L	7	2 	3O			RT	3A16    					 
2001080100210	20010801	00210	SO  	2001	8	1	2001FA0000075    	1	20010509	G	2700	KSC270720V	BEARING         			EMB   	145   	EMB145      	       	SO  										HINGE BEARING	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13										DURING RECEIVING INSPECTION FLAT NUT IS TESTED ON HOUSING.  WILL SPIN FREELY ON BUT THEN LOCKS UP 50 TO 80 PER CENT FAIL	 RATE.					2	L	7	2 	4F			RT	T00011AT					 
2001071300015	20010713	00015	CE  	2001	7	13	2001FA0000076    	1	20010625	G	2434	DOFF10300J	BRUSHES         			CESSNA	172   	172M        	2072418	CE  										ALTERNATOR	WORN            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	01	9627Q		600  			17265711				BRUSHES WORN TOTALLY OUT, ALLOWING SPRINGS AND WIRES TO DAMAGE ROTOR SLIP RINGS.  POOR QUALITY BRUSHES NOT TO LAST LONGE	R.					1	H	7	1 	3O			NT	3A12    					 
2001080100211	20010801	00211	CE  	2001	8	1	2001FA0000077    	1	20010627	G	7603	359440465	THROTTLE        			BEECH 	33    	E33A        	1151424	CE  										COCKPIT	MISALIGNED      	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	464SR					CE275				THE THROTTLE CONTROL KNOB BUTTON RETAINING SCREW LOOSENED ALLOWING THE THROTTLE CONTROL KNOB BUTTON TO MISALIGN AND JAM 	DURING THROTTLE APPLICATION.  THE THROTTLE CONTROL KNOB BUTTON RETAINING SCREW WAS FOUND APPROX 8 TURNS LOOSE.					1	L	7	1 	3O			 	3A15    					 
2001080100212	20010801	00212	CE  	2001	8	1	2001FA0000078    	1	20010710	G	5312	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  										FUSELAGE	CRACKED         	B			QRQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	3301R	4504 				18258601				CRACKS IN THE UPPER OUTBOARD CORNERS OF THE RUDDER CABLE CUT-OUTS ON THE 0712616-1 BULKHEAD ASSEMBLY.  AREA IN WHICH CRA	CK OCCURS IS RELATIVELY THIN GAUGE MATERIAL THAT APPARENTLY PROVIDES LITTLE STRUCTURAL STRENGTH.  THE FLANGES IN THIS AR	EA DO LITTLE MORE THAN SERVE AS A FASTENING POINT FOR AN AERODYNAMIC FAIRING.  IT IS DOUBTFUL IF THIS DEFECT IMPAIRS THE	 STRUCTURAL STRENGTH OF THE BULKHEAD ASSEMBLY AS THE 0712616-4 STIFFENER THAT ATTACHES TO THE -1 BULKHEAD IS MUCH HEAVIE	R GAUGE MATERIAL.		1	H	7	1 	3O			NT	3A13    					 
2001080100213	20010801	00213	SW  	2001	8	1	2001FA0000080    	1	20010710	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  										LT WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	83280					1947				DURING INSPECTION, FOUND LT WING FORWARD SPAR CRACKED AT UNDERSIDE OF SPAR OUT BOUND OF LIFT STRUT ATTACH POINT.  THIS W	ING WILL BE REPAIRED WITH NEW SPAR INSTALLED.					1	H	7	1 	3O			 	A759    					 
2001080100214	20010801	00214	SW  	2001	8	1	2001FA0000081    	1	20010625	G	5711		SPAR            			BBAVIA	7     	7FC         	2110124	SW  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	9052B					7FC140				BOTH FRONT SPARS HAD SEVERE CRACKS AT ATTACH POINTS INTO BUSHINGS.						1	H	7	1 	3O			 	A759    					 
2001080200268	20010802	00268	NE  	2001	8	2	2001FA0000082    	1	20010405	G	5720	21610075	ANGLE           			CONAER	LA4   	LA4250      	5110320	NE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14		1574 				31				WHILE PREPARING PRE-PURCHASE CONDITION REPORT ON ABOVE AIRCRAFT.  THE LEFT LOWER SPAR DOUBLER WAS FOUND CRACKED.  VISUAL	 INSPECTION SHOWED LOWER SPAR ANGLE CRACKED.					1	H	7	1 	3O			 	1A13    					 
2001080100215	20010801	00215	NE  	2001	8	1	2001FA0000083    	1	20010405	G	5730	21610063	DOUBLER         			LAKEAC	LAKE  	250LAKE     	5110322	NE  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	9224D	1574 				31				WHILE PREPARING PRE-PURCHASE CONDITION REPORT ON ABOVE AIRCRAFT, THE LEFT LOWER SPAR DOUBLER WAS FOUND CRACKED.  VISUAL 	INSPECTION SHOWED LOWER SPAR ANGLE CRACKED.					1	H	7	1 	3O			NC	1A13    					 
2001080100224	20010801	00224	GL  	2001	8	1	2001FA0000085    	3	20010601	G	6110	C5046	PLATE           			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C218   	GL  	AFT BLKHD ATTACH	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21										THIS PROPELLER INSTALLATION UTILIZES 2 SPINNER AFT BULKHEAD ATTACH PLATES, PN A1639-9.  BOTH PLATES WERE FOUND TO BE CRA	CKED WITHIN 50 HR OF INSTALLATION OF PROP AFTER OVERHAUL.  BECAUSE BULKHEAD ATTACHMENT PLATES ARE INSTALLED UNDER ATTACH	MENT NUTS, PN A1639-9, THAT HOLDS THE PROP TO THE ENGINE IS SUBJECTED TO VERY HIGH CONTACT FORCES DUE TO THE SMALL SHOUL	DER ON THE NUT(A1639-9).  THE LIKELIHOOD OF THIS FAILURE WILL INCREASE WITH THE NUMBER OF TIMES THESE FASTENERS ARE TORQ	UED.  IPC CALLS FOR THE INSTALLATION OF A WASHER BETWEEN ATTACHMENT PLATE AND NUT, EXCEPT THERE IS NOT SUFFICIENT CLEARA	NCE TO ALLOW THE INSTALLATION OF THE WASHER.	1	H	7	1 	3O			RT	3A13    		5	C	P7EA	 
2001080100225	20010801	00225	NE  	2001	8	1	2001FA0000086    	1	20010424	G	2752	MS28775115010	O-RING          	GERDES      		LAKEAC	LAKE  	250LAKE     	5110321	NE  										SHAFT	DETERIORATED    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	CGPXH	1868 				741				DURING LOCAL FLIGHT, PILOT NOTICED HYDRAULIC PUMP CYCLING CONSTANTLY.  PILOT ELECTED TO LAND AND CHECK.  LANDING GEAR WO	ULD NOT FULLY EXTEND.  PILOT COULD NOT GET LANDING GEAR FULLY UP OR DOWN.  EMERGENCY LANDING MADE WITH PARTIAL GEAR ON G	RASS STRIP WITH MINIMAL DAMAGE.  FOUND T/E FLAP ACTUATOR SHAFT SEALS (3 ORINGS) LEAKING FLUID CAUSING LACK OF SUFFICIENT	 PRESSURE TO OPERATE GEAR AND FLAPS.			1	H	7	1 	3O			NC	1A13    					 
2001080100227	20010801	00227	GL  	2001	8	1	2001FA0000087    	3	20010228	G	6110	C5152	COUNTERWEIGHT   	MCAULY      		CESSNA	208   	208         	2073702	CE  						MCAULY	3AF34C	3AF34C*     	GL  	ARM	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	LVWYZ	1720 			952445	0522				DURING MAGNETIC PARTICLE INSPECTION, AN INDICATION WAS FOUND IN THE TRANSITION BETWEEN THE COUNTERWEIGHT ARM AND THE ATT	ACHMENT AREA, WHERE IT JOINS THE BLADE ROOT.  THE CRACK APPEARS LIKE A HAIR LINE BUT STRONG INDICATION, ONCE IT WAS GROU	ND TO MAXIMUM DEPTH ALLOWABLE THE CRACK STARTED TO GROW IN WIDTH AS WELL AS CHANGED ITS DIRECTION BY 90 DEGREE, SO THE C	RACK DEVELOPED A PATTERN TYPICAL FROM A FORGING FOLD.  A PERIODICAL INSPECTION COULD BE A GOOD PREVENTATIVE TECHNIQUE.			1	H	7	1 	3T			NT	A37CE   		5	C	P22EA	 
2001080200269	20010802	00269	CE  	2001	8	2	2001FA0000091    	1	20010525	G	5530	04310093	FITTING         			CESSNA	150   	152         	2071835	CE  										VERTICAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	714TD					15279413				DURING ROUTINE 100 HR INSPECTION, MINOR CORROSION WS FOUND ON BOTH LEFT AND RIGHT VERTICAL STABILIZER ATTACH FITTINGS, A	PPROX BS 200.4. UPON REMOVAL OF CORROSION, A CRACK WS FOUND IN THE RADIUS OF THE RIGHT FITTING APPROXIMENTLY .7500 OF TH	E WAY ACROSS AND APPROX .50 PERCENT OF THE THICKNESS DEEP.  PROBABLE CAUSE:  ROUTINE STRESS  SOLUTION: TIME LIFE REPLACE	MENT OF ATTACH FITTINGS.			1	H	7	1 	3O			NT	3A19    					 
2001080100229	20010801	00229	EA  	2001	8	1	2001FA0000092    	2	20010612	G	8530	O5K21114	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					INTAKE ARM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	66934	347  				15281670	L2129415			DURING ROUTINE INSPECTION, FOUND NR 1 CYLINDER TO BE CRACKED ABOVE THE INTAKE VALVE GUARD AREA.  WHEN PRESSURIZED, THE E	NTIRE LENGTH OF THE CRACK PRODUCED BUBBLES.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001080100230	20010801	00230	CE  	2001	8	1	2001FA0000093    	1	20010607	G	3232	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	9515B	4503 				172RG0846				DEFECT WAS DISCOVERED WHILE PERFORMING SB MAIN LANDING GEAR ACTUATOR INSPECTION.  PART HAD CRACKED IN THE SUSPECTED AREA	, THE SADDLE SHAPED HOLE AND CIRCUMFERENCE OF THE 2.28 INCH DIA. BORE AND STEP, NEAR THE ROLLER BEARING ASSEMBLY.  THERE	 WAS NO EVIDENCE OF PILOT ERROR OR ABUSE.  PART OTHERWISE INDICATED NORMAL WEAR.  PROBABLE CAUSE:  STRESS RISER INHERENT	 TO DESIGN, OR PART NOT DESIGNED TO BE STRONG ENOUGH.  RECOMMENDATION:  REDESIGN PART.			1	H	7	1 	3O			 	3A17    					 
2001080100231	20010801	00231	CE  	2001	8	1	2001FA0000094    	1	20010607	G	3232	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	9515B	4503 				172RG0846				DEFECT WAS DISCOVERED WHILE PERFORMING SB MAIN LANDING GEAR ACTUATOR INSPECTION.  PART HAD CRACKED IN THE SUSPECTED AREA	, THE SADDLE-SHAPED HOLE AND CIRCUMFERENCE OF THE 2.28 INCH DIA BORE AND STEP, NEAR THE ROLLER BEARING ASSY.  THERE WAS 	NO EVIDENCE OF PILOT ERROR OR ABUSE.  PART OTHERWISE INDICATED NORMAL WEAR.  PROBABLE CAUSE:  STRESS-RISER INHERNTTO DES	IGN, OR PART NOT DESIGNED TO BE STRONG ENOUGH.  RECOMMENDATION:  REDESIGN PART.			1	H	7	1 	3O			 	3A17    					 
2001080100232	20010801	00232	CE  	2001	8	1	2001FA0000095    	1	20010102	G	2822	476411	PUMP            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					AFT OB WING TIP	INTERMITTENT    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	5336C	167  				310R1542				ON THE LEFT SIDE OF AC, WE HAVE REPLACED THE CIRCULATING PUMP NUMEROUS TIMES WHILE RIGHT SIDE HAS BEEN FINE.  MOST RECEN	T DATES OF REPLACEMENT AS FOLLOWS: 12-9-99 TACH 3443.5, 9-18-2000 3715.3, 12-29-2000 3882.4.  AS STATED EARLIER ALL 3 OF	 THESE WERE ON THE LEFT SIDE.  ON 12-29-2000, WE INSPECTED THE WIRING AND BOTH INLET AND OUTLET HOSES/LINES FOR OBSTRUCT	IONS.  EACH PUMP WHEN REMOVED WAS VERY INTERMITTEN AND WOULD WORK WHEN THE CASING WAS TAPPED ON.  PUMP NEEDS IMPROVEMENT	.		1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2001080100233	20010801	00233	EU  	2001	8	1	2001FA0000097    	3	20010524	G	6111	6607132886	BLADE           	ROTOL       												ROTOL	R4204	R130420412  	EU  	OUTER SLEEVE	CRACKED         	C			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		26510	5020 		DR6869386			DR6869386		PROPELLER RECEIVED FOR OVERHAUL.  BLADE SN 616 WAS FOUND TO HAVE A CRACKED OUTER SLEEVE AT ROOT END OF BLADE.  BLADE REJ	ECTED FROM FURTHER SERVICE.															6	C	P890	 
2001080100235	20010801	00235	CE  	2001	8	1	2001FA0000098    	1	20010606	G	5530		RIB             			CESSNA	172   	172         	2072402	CE  										RUDDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5838A	419  				28438				UPPER RUDDER RIB WAS FOUND BROKEN AT THE OPENING FOR UPPER HINGE BOLT INSTALLATION ACCESS.  THIS TYPE OF DAMAGE IS A REO	CCURRING PROBLEM DUE TO A LACK OF PROPER GUST LOCKS FOR THE RUDDERS, WIND SLAPPING OF THE RUDDER WITH THE ARM OF THE BAL	ANCE WEIGHT CAUSING CRACKS IN THE RIB WEAK POINT EVEN WITH THE ADDED DOUBLER.  PROPER SECURING THE RUDDER WHEN OUTSIDE, 	MAY PREVENT FURTHER DAMAGE.			1	H	7	1 	3O			NT	3A12    					 
2001080100236	20010801	00236	SO  	2001	8	1	2001FA0000099    	1	20010608	G	7820	8523304	MUFFLER         			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ENGINE	CRACKED         	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	9265B	757  				3246029				UPON REMOVAL OF HEATING SHROUDS FOR INSPECTION, FOUND SIDNIFICANT DISTORTION OF MUFFLER WAS CRACKED AT UPPER LEADING EDG	E WELD.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001080100242	20010801	00242	CE  	2001	8	1	2001FA0000100    	1	20010618	G	2730	0411258	BELLCRANK       			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200*       	17020	SO  					ELEVATOR BLCRK	ELONGATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	3343J	3456 				15066043				FOUND ELEVATOR BELLCRANKS CABLE ATTACH POINTS ELONGATED.  RIGHT ATTACH WAS ELONGATED BY .215, LEFT ATTACH WAS ELONGATED 	BY .248, THE AN23-11 ATTACH BOLT IS .184.  DRILLED OVERSIZE AND PUT NAS 75-3-004 STEEL BUSHING PRESSED IN, TO BRING BACK	 CORRECT TOLERANCE.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001080100243	20010801	00243	SO  	2001	8	1	2001FA0000101    	1	20010628	G	7820	8523310	MUFFLER         			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					RIGHT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	9265B	757  				3246029				UPON REMOVAL OF HEATING SHROUDS FOR INSPECTION, FOUND SIGNIFICANT DISTORTION OF MUFFLER CAN.  THE MUFFLER WAS CRACKED AT	 UPPER LEADING EDGE WELD.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001080100244	20010801	00244		2001	8	1	2001FA0000102    	4	20010604	G	3421	101490159	GYRO            			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1C    	41514	EA  					ATTITUDE	FAILED          	B			OF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	9453Z	294  				17280193				GYRO TUMBLED IN FLIGHT AND WOULD NOT RE-ERECT.  MAINTENANCE TROUBLESHOOTING REVEALED NO DEFECTS WITH INSTRUMENT AIR SYST	EM.  GYRO WAS REPLACED WITH A SERVICEABLE OVERHAULED UNIT.  SYSTEM RETESTED AND REPLACEMENT GYRO FUNCTIONS NORMALLY.   A	IRCRAFT AND SYSTEM HAVE BEEN MAINTAINED AS PER MANUFACTURERS RECOMMENDATIONS SINCE NEW.				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001080100245	20010801	00245	GL  	2001	8	1	2001FA0000103    	3	20010320	G	6110		SNAP RING       	MCAULY      		CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	NR 1& 2 BLDE RET	FAILED          	D			IT6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5612J				74517	18263467	459837			EXTERNAL SNAP RING ON PROPELLER BLADE CAME OFF AFTER PREFLIGHT ENGINE HAD STOPPED ON INITIAL START, THEN WAS RESTARTED. 	 SNAP RING CAME OFF BLADE SHANK BUT WAS RETAINED BY SPINNER.  THEN AIRPLANE WAS FLOWN FOR 2 HOURS WITH FIVE TOUCH AND GO	 LANDINGS, WITHOUT FAILURE OF PROPELLER.  PROPELLER WAS THEN REMOVED AND TAKEN BACK TO OVERHAUL SHOP WHERE TEAR-DOWN WAS	 COMPLETED.  FINDING WAS SNAP-RING WAS NOT SEATED PROPERLY.  THE BLADE TO PISTON LINK  WAS DAMAGED AND REPLACED.  THE PR	OPELLER BLADE WAS DRESSED AT SHANK.		1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA	 
2001080100246	20010801	00246	SO  	2001	8	1	2001FA0000104    	1	20010621	G	5711	6207006	SPAR            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					OB OF MAIN GEAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	86CA	3194 				3240957				WHILE RE-SKINNING THE LEFT UPPER INBOARD WING SKIN, WE FOUND CORROSION IMMEDIATELY OUT BOARD OF THE LEFT MAIN LANDING GE	AR CASTING ON THE LOWER AFT SIDE OF THE MAIN SPAR INSIDE THE WING.  THE CORROSION SEEING TO BE CENTRALIZED AROUND ONE RI	VET AND RADIATING OUTWARD FROM THAT RIVET.  THERE IS NO OTHER CORROSION IN THAT AREA OF THE WING.				1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001080100247	20010801	00247	SW  	2001	8	1	2001FA0000106    	1	20010702	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	O200  	O200A       	17020	SO  					LIFT STRUT ATTCH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1703E					7AC5268	690748A			FOUND A SMALL LONGITUDINAL CRACK BETWEEN THE PLYWOOD DOUBLER PLATE AT THE FORWARD LIFT STRUT ATTACH FITTING AND THE NEXT	 OUTBOARD RIB ALONG THE REAR FACE OF THE SPAR.  WITH A MIRROR IN THE NEXT OUTBOARD RIB BAY, THE CRACK PROTRUDED ABOUT TH	REE INCHES.  WHEN THE FABRIC WAS REMOVED THE CRACK RAN FROM THREE INCHES INBOARD OF THE PLYWOOD DOUBLER AT THE LIFT STRU	T ATTACH FITTING TO ABOUT THREE INCHES OUTBOARD OF THE SAME DOUBLER.  THE CRACK WAS ONLY VISIBLE ON THE AFT FACE OF THE 	SPAR.		1	H	7	1 	3O	3	O	 	A759    	E252				 
2001080100248	20010801	00248	EA  	2001	8	1	2001FA0000107    	2	20010626	G	8520		CRANKSHAFT      			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	BROKEN          	B			GSZR	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SW	19	377RC		140  			61P057579632	L570161A			ENGINE FAILED ON TAKE OFF.   FACTORY REP. REPORTED BY PHONE THAT CRANKSHAFT HAD BROKEN.						1	M	7	2 	3O	3	O	RT	A17WE   	E14EA				 
2001080100249	20010801	00249	CE  	2001	8	1	2001FA0000108    	1	20010627	G	3710	0701030807	HOSE            			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					VACUUM SYSTEM	DISINTEGRATED   	B			HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9953H					18268139				CUSTOMER REPORTED LOW VACUUM INDICATION BUT GYROS RUNNING OK.  INITIAL INVESTIGATION ALL HOSES LOOKED OK, HOWEVER WHEN H	OSES WERE TOUCHED, FELL APART.  THE ABOVE REFERENCED PN IS FOR ONE OF THE VACUUM GAUGE HOSES, HOWEVER ALL INSTRUMENT HOS	E WERE OF THE SAME TYPE AND ALL FELL APART WHEN TOUCHED.  BOTH GYROS WERE REMOVED FROM INLET FITTINGS (SCREENS ON INLET 	PORTS STOPPED MATERIAL FROM GETTING IN INSTRUMENTS).  A TEMPORARY IN LINE FILTER WAS INSTALLED ON THE INLET SIDE OF VACU	UM PUMP TO PREVENT MATERIAL FROM GOING INTO THE PUMP AND THE AIRCRAFT WAS GROUND RUN.  NO DATES WERE FOUND ON THE HOSES.	  THE NUMBER 04A WAS ON SEVERAL HOSES EVERY 6 INCHES.  THEY APPEAR TO BE ORIGINAL HOSES.	1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2001080100250	20010801	00250	SO  	2001	8	1	2001FA0000112    	1	20010627	G	3210	AN310A	BOLT            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320*      	41508	EA  					MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	7993Y					301098				THE AN3-10A BOLT, HOLDING THE MAIN GEAR SPRING ATTACH BRACKET ON TO THE STRUT HOUSING, BROKE.  IT CAUSED THE BRACKET TO 	JAM AGAINST THE GEAR FORWARD ATTACH FITTING AND WOULD NOT LET THE GEAR GO DOWN.  AIRCRAFT LANDED WITH THE GEAR UNSAFE.					1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2001080100251	20010801	00251	EA  	2001	8	1	2001FA0000113    	2	20010704	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					HEAD	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4381L	306  				288516016	L1341139A			CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EXSEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001080100253	20010801	00253	EA  	2001	8	1	2001FA0000114    	2	20010709	G	8530	AEL6510241	CYLINDER        			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O360  	O360*       	41514	EA  					CYLINDER HEAD	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	4328D	1293 				288416019				CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EXSEAT TO BOTTOM SPARK PLUG HOLE.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001072500615	20010725	00615	SW  	2001	7	25	2001FA0000115    	1	20010608	G	2810	206362002103	CAP             			BELL  	407   	407         	       	SW  										FUEL CELL	BINDING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01		35   				53444				FUEL FILLER CAP DOES NOT SEAT PROPERLY DUE TO CLOSE TOLERANCE BETWEEN AIRFRAME SPACERS AND CAP.  THIS OCCURS 8 OR 9 TIME	S OUT OF TEN CLOSURES.  THE FUEL LEAKS DOWN THE SIDE OF THE AIRFRAME AND GETS SUCKED INTO AIR CONDITIONING FAN THRU COND	ENSER.  FUEL SPRAY BECOMES PRESSURIZED SPRAYING UP INTO AFT COMPARTMENTS BELOW BAGGAGE COMPARTMENT. AIRCRAFT INVERTERS A	LSO WET WITH FUEL SPRAY, COULD BE SOURCE OF IGNITION AND POSSIBLE IN FLIGHT FIRE. RECOMMENDATION, OPEN UP CLEARANCE BETW	EEN CAP DIAMETER AND AIRFRAME SPACERS. THIS AIRCRAFT HAS HAD PART 1 OF ASB 407-01-41 INCORPORATED.		1	G	7	1 	3U			O	H2SW    					 
2001072700260	20010727	00260	NE  	2001	7	27	2001FA0000117    	1	20010727	G	6321	7636309103102	DISK            	SKRSKY      		SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					ROTOR BRAKE	CRACKED         	C				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			EA	17	317MX	930  			C207002824	760499	20523			DURING A SCHEDULED MAINTENANCE EVENT THE MAIN ROTOR BRAKE DISC WAS FOUND TO BE FRACTURED, COMPLETELY THROUGH, FROM THE O	UTER TO THE INNER CIRCUMFERENCE, AND THERE WERE SOME VISUAL CRACKS EMANATING FROM AROUND THE MOUNTING HOLES.  THE CREW H	AD MENTIONED, THAT DURING ROTOR BRAKING, HAD FELT SOMETHING AND NOTICED AN INCREASE IN VIBRATION.  THIS COMPONENT IS MOU	NTED BETWEEN THE ENGINE INLETS, SURROUNDED BY NUMEROUS FUEL AND HYDRAULIC LINES, AND SHARES THE SAME DRIVE AS THE TAIL R	OTOR.  IF THIS WERE TO SEPARATE DURING GROUND OR FLIGHT OPERATIONS THE RESULT WOULD BE CATASTROPHIC.  SIKORSKY AIRCRAFT 	(610-954-9613) WILL RECEIVE THE ASSEMBLY ON 7-29-01, AND FOWARD IT TO SIKORSKY ENGINEERING.	1	G	7	2 	3U	3	U	NC	H1NE    	E00054EN				 
2001080100254	20010801	00254	GL  	2001	8	1	2001FA0000118    	1	20010706	G	2820		CHECK VALVE     			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O550  	IO550*      	 	SO  					RT HEADER TANK	MISINSTALLED    	B			NF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	960CM	31   				0041	685781			RIGHT FUEL QUANTITY GAUGE FALLS TO ZERO WHEN RIGHT TANK WAS SELECTED.  FOUND FUEL QUANTITY TRANSMITTER WAS CORRECT, INBO	ARD TRANSMITTER MOUNTED IN THE HEADER TANK WAS GOING TO ZERO WHEN FUEL WAS BEING USED FROM THE RIGHT TANK.  CAUSE:  THE 	FUEL INLET CHECK VALVE WAS GLUED CLOSED DURING ASSEMBLY OF THE AIRCRAFT.  THE ENG WOULD USE MORE FUEL THAN THE RATE THE 	HEADER TANK COULD FILL, THIS CONDITION COULD CAUSE ENGINE STOPPAGE.DURING REPAIRS IT WAS FOUND THE NORMAL OPERATING SYST	EM CAN NOT KEEP EITHER HEADER TANK FULL. FUEL QUANTITY INDICATION IS NOT ACCURATE WHEN ENGINE IS USING FUEL FROM THAT TA	NK.	1	H	7	1 	3O	3	O	NC	A00009CH	E3SO				 
2001080100255	20010801	00255	EA  	2001	8	1	2001FA0000119    	2	20010718	G	8500	RJ0506041	DOOR            	RAJAYXXXXXXX		MOONEY	M20   	M20D        	5870210	SW  	LYC   	O360  	O360*       	41514	EA  					TURBO DOOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	191PA	500  				248				DURING ANNUAL INSPECTION, PART WAS OBSERVED TO BE EXTREMELY LOOSE.  REMOVED PART FROM ASSEMBLY. FOUND PORTION  OF HINGE 	MISSING, HINGE PIN 95 PER CENT WORN THROUGH AND SIDE BRACKETS WORN 90 PER CENT THROUGH.  REMOVED ASSEMBLY AND REPLACED D	OOR AND FRAME WITH SERVICEABLE PART.  FOUND BYPASS FLUTTER VALVE FOR CARB HEAT MISSING.  INSTALLED NEW PART AND SECURED.				1	L	7	1 	3O	3	O	 	2A3     	E286				 
2001080100256	20010801	00256	CE  	2001	8	1	2001FA0000120    	2	20010712	G	7320	S29991	SWIVEL          			CESSNA	337   	T337G       	2075726	CE  	CONT  	IO360 	IO360*      	17025	CE  					MIXTURE CONTROL	SEPARATED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	265	6    	6    			P3370232				INSTALLED BALL JOINT OR SWIVEL PN S2999-1 ON MIXTURE CONTROL CABLE FRONT AND REAR ENGINES AT TIME OF ENGINE INSTALLATION	.  A/C WAS TEST FLOWN AND FERRIED TO PAINT SHOP AND RETURNED.  PREVIOUS TO ANY ADDITIONAL ADJUSTMENT AND WHILE IN THE CO	CKPIT PERFORMING A MAINTENANCE CHECK AND OPERATING THE MIXTURE CONTROL, THE SWIVEL SEPARATED ON THE REAR ENGINE CABLE.  	FURTHER OPERATION, IT WAS NOTED THE FRONT ENGINE MIXTURE CONTROL BALL JOINT SWIVEL CAME APART.  MFG WAS NOTIFIED.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080100258	20010801	00258	CE  	2001	8	1	2001FA0000121    	1	20010711	G	2497		WIRE            			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300*      	17022	SO  					INST PANEL	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	6651E	1904 				56151				AIRCRAFT BROUGHT TO BE CLEAN-UP WIRING BEHIND INSTRUMENT PANEL.  UPON FURTHER INSPECTION I IMMEDIATELY DISCONNECTED THE 	SHIPS BATTERY DUE TO THE FACT THE WIRING WAS IN SUCH A DISARRAY I COULD NOT BELIEVE IT WORKED AND IF SO WHY IT HAD NOT C	AUSED A FIRE.  IE: EXPOSED SOLDER SPLICES THAT WERE IN POWER FEED LINES.  4 DIFFERENT SPLICES PLUS 1 FUSE IN LESS THAN 1	6 INCHES IN THE AME 18AWG WIRE.  FUSES IN LINE WITH FUSES, WIRE STRANDS TWISTED, POORLY SOLDERED AND HOOKED TO THE LINE 	SIDE OF MASTER SWITCH.  ALL DEFECTS WERE CORRECTED AND AC APPROVED FOR RETURN TO SERVICE.		1	H	7	1 	3O	3	O	NT	3A17    	E298				 
2001080100259	20010801	00259	CE  	2001	8	1	2001FA0000122    	1	20010621	G	2140	C3A051	HEATER          			BEECH 	60    	A60         	1153604	CE  	LYC   	O541  	TIO541*     	41536	EA  					CABIN	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	08	81AG	323  	323  			P219				DURING PRESSURE DECAY TEST FOUND GASKETS.  CANASTER A09077 AND NOZZLE 29D-28 LEAKING.  REPLACED AND HEATER PASSED PRESSU	RE DECAY TEST.					1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2001080100260	20010801	00260	CE  	2001	8	1	2001FA0000123    	1	20010629	G	5711	5262	SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					WING	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	86960					44674				DURING INSPECTION OF RIGHT WING, A CRACK WAS FOUND ON THE AFT SIDE OF THE FORWARD WOOD SPAR, 79 INCHES OUTBOARD FROM THE	 BUTT RIB.  THE 5 INCH LONG, HORIZONTAL CRACK WAS LOCATED AT THE COMPRESSION MEMBER AND RAN THROUGH THE HOLES FOR THE DR	AG WIRES.  UNDETERMINED CAUSE.				1	H	7	1 	3O	3	O	 	A759    	1E12				 
2001080200001	20010802	00001	SO  	2001	8	2	2001FA0000128    	1	20010711	G	2730	8283302	ROD             			PIPER 	PA46  	PA46310P    	7104605	SO  										ELEVATOR CONTROL	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	248SP	2321 				468608024				ELEVATOR PUSH PULL CONTROL ROD VERY RUSTY AND PITTED.  LOCATED IN TAIL SECTION WHERE MOISTURE AND CONTAMINATION ACCUMULA	TE.					1	L	7	1 	3O			RT	A25SO   					 
2001080200138	20010802	00138	EA  	2001	8	2	2001FA0000129    	2	20010629	G	7310		SERVO           	PREAIR      	RSA5AD1     	CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	FUEL INJECTION	MALFUNCTIONED   	C				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			SW	99	948SP	1119 			70168504	172S8144	L2812651A	SL029		RPM SET TO 1500 FOR PURGING FUEL VAPORS PRIOR TO TAXI, TAXI AND RUN UP WERE NORMAL.  WHEN FULL THROTTLE WAS APPLIED FOR 	TAKE OFF THE ENGINE WOULD NOT DEVELOP FULL POWER.  IT WOULD ONLY DEVELOP 2000 RPM. MAINTENANCE INSTALLED CLEAR FUEL LINE	 ON OUTLET LINE FROM FUEL INJECTION SERVO IAW PRECISION AIRMOTIVE TROUBLESHOOTING TECHNIQUES.  THE THROTTLE AND MIXTURE 	WERE OPENED TO SIMULATE ENGINE OPERATION, VAPOR BUBBLES WERE OBSERVED FOR APPROXIMATELY 10 MINUTES FLOWING FROM THE FUEL	 SERVO.  AFTER 10 MINUTES, THE LINE FILLED WITH FUEL AND THE ENGINE HAD COOLED.  THE ENGINE WAS STARTED AND ALL OPERATIO	N NORMAL WITH FULL POWER BEING DEVELOPED.  AIRCRAFT RELEASED FOR TEST FLIGHT.  TEST FLOWN SATISFACTORY.	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001080200139	20010802	00139	CE  	2001	8	2	2001FA0000130    	1	20010629	G	7100	LW12427	CYLINDER        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE	OVERHEATED      	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	494SP	1116 				172S8035	L2790951A	SD013		PILOT REPORTED ENGINE STARTED RUNNING ROUGH IN FLIGHT AND LOOSING ALTITUDE.  MADE EMERGANCY LANDING, WENT OFF END OF RUN	WAY AND WENT UPSIDE DOWN.  AIRCRAFT RIGHTED AND MOVED TO HANGER.  MAINTENANCE FOUND #2 CYLINDER EXHAUST PUSHROD BENT IN 	HALF & BROKEN, THE PUSHROD HOUSING BENT AND PULLED LOOSE FROM CASE WITH SUBSIQUENT OIL LOSS.  THE INTAKE PUSHROD & HOUSI	NG WAS BENT.  WHEN THE VALVE COVER WAS REMOVED BOTH VALVES WERE CLOSED AND NOT STUCK.  THE VALVES WERE REMOVED FROM THE 	CYLINDER AND FELL OUT OF THE GUIDES FREELY, THEY WERE FREE OF CARBON DEPOSITES AROUND STEMS.  BOTH VALVE SEATS WERE BURN	ED & THE INTAKE VALVE WAS ALSO BURNED AROUND THE SEATING AREA.	1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001080200149	20010802	00149	CE  	2001	8	2	2001FA0000131    	1	20010703	G	5711		SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  											UNSECURE        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8680V	775  								AIRCRAFT REGISTERED AS BELLANCA.  MODEL IS 7KCAB.  DESIGN NOW OWNED BY AMERICAN CHAMPION. WOOD SPAR WING INSPECTED IN AC	CORDANCE WITH AD 2000-25-02.   SEVERAL RIB/SPAR ATTACHMENT NAILS MISSING.  PER SERVICE LETTER SL-417 THE SPAR "DAMAGE" C	AUSED BY THE MISSING NAILS WAS NOT SIGNIFICANT ENOUGH TO  REQUIRE REPAIR.  NEW NAILS INSTALLED IN ACCORDANCE WITH INSTRU	CTIONS FROM AMERICAN CHAMPION.			1	H	7	1 	3O			 	A759    					 
2001080200150	20010802	00150	CE  	2001	8	2	2001FA0000133    	1	20010430	G	3110	04110591	SHOCK MOUNT     			CESSNA	210   	210D        	2073414	CE  										INSTR PANEL	BROKEN          	C				B				EMER. DESCENT           				O			OTHER                     			DE	DESCENT        	1			SW	99	3738Y	3304 				21058238				AFTER FLYING THROUGH TURBULANCE THE PILOT COULD NOT LEVEL OFF ATER A DECENT DUE TO LIMITED ELVEATOR CONTROL.  A NOSE FIR	ST LANDING WAS ACCOMPLISHED WITH THE AIRCRAFT/ENGINE RECEVING SUBSTANTIAL DAMAGE.  INITIAL OBSERVATIONS REVEALED THE ELV	EATORS ONLY GOING TO NEAR LEVEL FLIGHT POSITION.  INVESTIGATION FOUND THAT THE HEADING SITUATION INDICATOR WAS MOUNTED D	IRECTLY ABOVE THE CONTROL COLUMN WHICH WAS BEING HIT BY THE CONTROL COLUMN STOP.  THE INSTRUMENT PANEL WAS RECONFIGURED 	TO ITS PRESENT LAYOUT IN 1994.  THE INSTRUMENT PANEL SHOCK MOUNTS INTHE LOWER RIGHT AND LOWER CENTER WERE BROKEN.  THE D	ATES ON THE PANEL SHOCK MOUNTS WERE ALL PREVIOUS TO 1963, THE DATE THE AIRCRAFT WAS MANUFACTURED.	1	H	7	1 	3O			 	3A21    					 
2001080200172	20010802	00172	CE  	2001	8	2	2001FA0000135    	1	20010705	G	2421	DOFF10300FR	ALTERNATOR      			CESSNA	172   	R172G       	2072421	CE  	CONT  	O360  	IO360DB     	17025	SO  						MISOVERHAULED   	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7753L		170  			R1720429	239773R			DURING MAINTENANCE 100 HOUR INSPECTION, FOUND ALTERNATOR INTERNAL FAN SHIELD SEPERATED FROM FAN DUE TO SHEARED RIVITS AN	D THE DRIVE SHAFT OIL SEAL WAS LEAKING.  REPLACED ALTERNATOR WITH UNIT OVERHAULED BY DIFFERENT MANUFACTURER, OPERATIONAL	 CHECKED SATISFACTORY.				1	H	7	1 	3O	3	O	 	3A17    	E1CE				 
2001080200182	20010802	00182	CE  	2001	8	2	2001FA0000136    	1	20010705	G	3710	P10UCB86	FITTING         			CESSNA	182   	182S        	2072701	CE  										VACUUM SYSTEM	BROKEN          	B				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			WP	07	7260Q	16   				18280957				THE PILOT REPORTED THAT THERE WAS ZERO VACUUM INDICATED ON THE GAUGE AND THAT THE HSI GYRO WOULD NOT ERECT.  A VISUAL IN	SPECTION BY A MAINTENANCE TECHNICIAN REVEALED THAT THE VACUUM SUPPLY LINE REDUCER FITTING WAS BROKEN IN TWO.					1	H	7	1 	3O			NT	3A13    					 
2001080200184	20010802	00184	SO  	2001	8	2	2001FA0000137    	1	20010702	G	3260	8929103	DOWNLOCK SWITCH 			PIPER 	PA44  	PA44180     	7104402	SO  										MLG	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		2490 				4496013				WHILE CONDUCTING A SCHEDULED INSPECTION,THE TECHNICIAN DISCOVERED SEVERAL WIRES WERE BROKEN OF THE DOWN LIMIT SWITCH.THE	RE WERE NO PROBLEMS REPORTED BY THE PILOT AT THIS TIME.ALSO WHEN PLACING THE AIRCRAFT ON JACKS AND PERFORMING A LANDING 	GEAR TEST THERE WERE NO PROBLEMS FOUND.EVERYTHING SEEMED NORMAL.  WHEN THE LANDING GEAR WAS RETRACTED SEVERE TENSION OCC	URED ON THE WIRES AND WERE THEREFORE PULLED FROM THE SWITCH ASSY.A PROBLEM COULD HAVE OCCURED IF ALL THE WIRES HAD BROKE	N.  BOTH THE LT AND RT DOWN LIMIT SWITCHES WERE REPLACED AND THE WIRES REROUTED.   ATTENTION SHOULD BE PAID TO THE ROUTI	NG OF THE WIRES,WHEN THE LANDING GEAR RETRACTS.	1	L	7	2 	3O			 	A19S0   					 
2001080200187	20010802	00187	CE  	2001	8	2	2001FA0000138    	1	20010709	G	3242		BRAKE           			CESSNA	172   	172M        	2072418	CE  										MLG	INOPERATIVE     	P				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	12790					17262262				PRIOR TO TAXI THE PARKING BRAKE WAS FOUND INOP; HOWEVER, THE BRAKES OPERATED NORMALLY.  THE AIRCRAFT WAS TAXIIED TO THE 	RUNUP AREA AND CONDUCTING THE RUNUP USING THE STANDARD BRAKES. AFTER RUNUP, THE PILOT WAS INSTRUCTED TO TAXI INTO POSITI	ON AND HOLD. WHILE TAXIING INTO POSITION THE LEFT BRAKE FAILED. THE PILOT HAD THE COPILOT HID THE BRAKES ON THE RIGHT SE	AT. THE LEFT BRAKE WAS INOP ALSO. THE AIRCRAFT VERRED RIGHT OFF THE APPROACH END OF THE RUNWAY STRIKING A RUNWAY LIGHT. 	AFTER SECURING THE ENGINE, THE PROPELLER WAS EXAMINED FOR STRIKES. ONE BLADE HAD SURFACE DAMAGE TO THE PAINT ON THE TIP.	 THE OTHER BLADE HAD A 3/16 INCH NICK ON THE LEADING EDGE ABOUT 2 INCHES FROM THE TIP AND THE TIP WAS BENT AFT ABOUT 1/2	1	H	7	1 	3O			NT	3A12    					 
2001080200189	20010802	00189	CE  	2001	8	2	2001FA0000139    	1	20010709	G	3213	SA530348	PISTON          			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					STRUT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	2051Y	840  				17249551	24597R			DURING REPAIRS TO CYCL NR 4 FOR LOW COMPRESSION FOUND 1INCH CRACK IN PISTON SKIRT STARTING AT BOTTOM OF PISTON.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2001080200194	20010802	00194	SW  	2001	8	2	2001FA0000140    	1	20010712	G	2810		SUMP            			GULSTM	680   	680E        	0141604	SW  										FUEL TANK	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	69278	4800 				680E78150				MAIN FUEL SUMP REMOVED FROM ACFT. TO FACILITATE MAIN TANK REMOVAL FROM ACFT.  VISUAL INSPECTION OF INSIDE OF PART REVEAL	ED CONSIDERABLE CORROSION ON BOTTOM INSIDE SUMP.  AFTER CLEANING, OBSERVED ONE AREA WHERE CORROSION THROUGH WALL TO OUTE	RSKIN ON CASTING HAD ALMOST COMPLETE PENETRATION.  UNABLE TO DETERMINE INTERNAL CORRODED CONDITION OF PART WHILE PART WA	SINSTALLED ON ACFT.			1	H	7	2 	3O			 	2A4     					 
2001080200196	20010802	00196	SO  	2001	8	2	2001FA0000141    	2	20010426	G	7414	10682016	GEAR            	CONT        	D6LN3000    	PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					DISTRIBUTOR	BROKEN          	G				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			EA	01	39503					32R7885224	L1795748A			ON TAKE OFF AT APPROXIMATLEY 500 FEET THE ENGINE FAILED.  THE AIRCRAFT LANDED IN GRASS AT END OF RUNWAY WITHOUT INCIDENT	. INSPECTION SHOWED THAT BOTH DISTRIBUTOR GEARS HAD FAILED, TEETH MISSING.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001080200198	20010802	00198	EA  	2001	8	2	2001FA0000142    	2	20010512	G	8530	FRST14	CYLINDER        								LYC   	O720  	IO720A1B    	41546	EA  					ENGINE	BROKEN          	B				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	99			278  							BARREL TO HEAD SEPERATION DURING FLIGHT.											3	O			1E15				 
2001080200202	20010802	00202	GL  	2001	8	2	2001FA0000143    	1	20010713	G	3221		BUSHING         	CIRRUS      		CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O550  	IO550*      	 	SO  					MLG	LOOSE           	H				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			EA	21		27   	27   		0021	0012	685745			ON LANDING, NOSE WHEEL HAD SEVERE OSCILLATION/SHIMMY.  INSPECTION AFTER TAXI FOUND NOSE WHEEL FAIRING CRACKED AND TIRE D	AMAGED AROUND CIRCUMFERENCE.  FURTHER INSPECTION FOUND THAT THE BUSHING ON THE RIGHT BOTTOM NLG MOUNT TO THE ENGINE MOUN	T SHIFTED OUT OF ITS SEAT IN THE NLG WISHBONE MOUNT CAUSING THE BOLT TO RIDE ON THE HOLE IN THE NLG WISHBONE MOUNT.  WE 	BELIEVE THAT THE PROBLEM IS A RESULT OF POSTION/TYPE OF BUSHINGS ON ASSEMBLY.			1	H	7	1 	3O	3	O	NC	A00009CH	E3SO				 
2001080200204	20010802	00204	EA  	2001	8	2	2001FA0000145    	2	20010718	G	7313	25765362	SERVO           			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  					FUEL INJECTOR	FROZEN          	D				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			SW	99	949SP	1053 	543  			172S8145	L2812051A			SECOND FLIGHT OF THE DAY, TEMP 89F, DA 9444. ENGINE START WAS DIFFICULT, TAXI AND ENGINE RUN UP NORMAL.  AIRCRAFT TOOK T	HE RUN WAY FOR TAKE OFF. WHEN THROTTLE WAS OPENED TO FULL POWER, ENGINE HAD POPPING NOISE AND WOULD ONLY DEVELOP 2000 RP	M. TAKE OFF WAS ABORTED FOR LOW POWER. A CLEAR LINE WAS INSTALLED FROM THE FUEL INJECTION SERVO TO THE FLOW DIVIDER IAW 	PRECISION AIRMOTIVE TROUBLE SHOOTING MANUAL AND EXCESSIVE VAPOR IN THE LINE WAS DISPLACING THE FUEL WHEN THE ENGINE WAS 	RUN.  THE ENGINE WAS ALLOWED TO COOL COMPLETELY AND RESTARTED, NO VAPOR WAS DETECTED AND ALL OPERATION WAS NORMAL INCLUD	ING FUEL FLOW WITH THE ENGINE DEVELOPING FULL POWER. AIRCRAFT TEST FLOWN AND RELEASED.	1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001080200206	20010802	00206	SO  	2001	8	2	2001FA0000146    	2	20010724	G	8520	646778	CONNECTING ROD  								CONT  	O520  	IO520C      	17032	SO  					ENGINE	GOUGED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		3    					816945R			FACTORY REBUILT ENGINE WITH 3.3 TTIS WAS BEING DISASSEMBLED FOR INSPECTION DUE TO A PROPELLER STRIKE.  ONE OF THE #6 CON	NECTING ROD BOLTS COULD NOT BE REMOVED WITH REASONABLE PRESSURE AND HAD TO BE DRIVEN OUT OF THE CAP.  INSPECTION OF THE 	BOLT REVEALED THAT A BURR AND EVIDENCE OF GALLING HAD OCCURRED ON THE SHANK AT THE POINT WHERE ROD AND CAP PARTING SURFA	CES MEET.  THE CAP WAS DAMAGED WITH SIGNIFICANT GOUGING WHERE THE BOLT HAD TO BE DRIVEN OUT LEAVING IT UNSERVICEABLE.								3	O			E5CE				 
2001080200208	20010802	00208	SW  	2001	8	2	2001FA0000149    	1	20010728	G	3246	40041	WHEEL           			AIRTRC	AT300 	AT301       	0390103	SW  										MLG	FATIGUED        	G				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			GL	21	4361S	5100 				3010041				DURING TAKEOFF, RIGHT MAIN WHEEL HALF (OUTBOARD) SEPARATED. PILOT UNABLE TO REGAIN CONTROL AND WENT IN ROAD DITCH AND LA	NDED INVERTED. MINOR INJURY TO PILOT. WHEEL NUT, BEARING AND SPACER WERE STILL ON AXLE UPON ARRIVAL AT ACCIDENT SCENE. O	UTER BEARING RACE HAD PULLED THROUGH WHEEL HALF RACE SHOULDER AND ALL 9 WHEEL BOLTS WERE EITHER BROKE UNDER TENSION OR H	AD NUTS PULLED OFF BOLTS LEAVING BOLTS INTACT WITH NUT THREADS STILL EMBEDDED IN BOLT THREADS. CAUSE OF WHEEL FAILURE UN	KNOWN AT THIS TIME. IMPROPER WHEEL ASSEMBLY OR INSTALLATION OF OVERSIZE TIRES AND TOO MUCH AIR PRESSURE ARE POSSIBILITIE	S OF FAILURE.	1	L	7	1 	3R			 	A9SW    					 
2001080200210	20010802	00210	CE  	2001	8	2	2001FA0000150    	1	20010731	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										RT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2624D	4196 				4410122				DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RH CENTER WING CANTED RIB CAP P/N: 5722206-2 (RH CWS26.85) HAD A VI	SUALLY SUSPECT AREA ALONG THE BEND RADIUS BETWEEN THE CENTER WING MAIN SPAR (FS177.45) AND FS188.95". FURTHER INSPECTION	 USING FLUORESCENT PENETRANT REVEALED (2) CRACKS IN THE RADIUS, THE ORIGINAL SUSPECT AREA (FS185.35) AND ONE STARTING AT	 THE MAIN SPAR (FS177.45) PROTRUDING AFT. BOTH CRACKS ARE APPROXIMATELY .75" LONG. AFTER REMOVAL OF THE RIB CAP, CLOSE E	XAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED SO THAT THE BEND WAS PARALLEL WITH THE GRAIN OF THE METAL 	INSTEAD OF PERPENDICULAR WHICH COULD RESULT IN THIS TYPE OF FAILURE. CESSNA CURRENTLY DOES NOT HAVE ANY SPECIFIC INSPECT	1	L	7	2 	3T			RT	A28CE   					 
2001080200213	20010802	00213	CE  	2001	8	2	2001FA0000151    	1	20010731	G	2800		FITTING         			LEAR  	25    	25B         	5170511	CE  										DEFUEL SYSTEM	CLOGGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	751GA					122				WHILE DEFUELING THE AIRCRAFT PREPATORY TO PAINTING, IT WAS DISCOVERED THAT NO FLOW COULD BE ACHIEVED THROUGH THE RIGHT D	EFUEL FITTING.  THE DEFUEL WAS ACCOMPLISHED BY TRANSFERRING ALL OF THE FUEL TO THE LEFT TANK AND REMOVING IT THROUGH THA	T VALVE.  WHEN WE OPENED THE RIGHT TANK A SHOP RAG WAS FOUND PLUGGING THE DEFUEL PORT.  IT HAD OBVIOUSLY BEEN LEFT IN TH	E TANK DURING PRIOR MAINTENANCE.			2	L	7	2 	4J			 	A10CE   					 
2001080200229	20010802	00229	SO  	2001	8	2	2001FA0000154    	2	20010426	G	7414	10682016	GEAR            	CONT        	D6LN3000    	PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  	HARTZL	HCC2Y	HCC2YK1     	GL  	DISTRIBUTOR	BROKEN          	G				A				UNSCHED LANDING         				Y	G		ENGINE STOPPAGE           	MULTIPLE FAILURE          		TO	TAKEOFF        	1			EA	01	39503				D040001GR	32R7885224	L1795748A	CH32104A		AFTER TAKE OFF AT APPROX 500FT AGL, THE ENGINE STOPPED RUNNING.  AIRCRAFT MADE EMERGENCY LANDING IN A FIELD WITH NO DAMA	GE OR INJURIES.  INSPECTION OF MAGNETO REVEALED THAT BOTH DISTRIBUTOR GEARS HAD FAILED.  MAGNETO WAS REBUILT BY TCM 04/0	7/2000 AND INSTALLED ON 5/12/2000.				1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001080200231	20010802	00231	EA  	2001	8	2	2001FA0000155    	2	20010516	G	8520	SL13S19646	GEAR            			PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	IO320B1A    	41508	EA  					CRANKSHAFT	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21										DURING COMPLICANCE WITH AD 96-09-10 - COMPLIED ALSO WITH AD 91-14-22 CRANKSHAFT GEAR RETAINING BOLT.  ORDERED NEW CRANKS	HAFT GEARS PN SL13S19464 FOR LH AND RH ENGINES. WHEN INSTALLING NEW GEARS IT WAS DISCOVERED ONE HAD THE TIMING MARK ON T	HE CORRECT TOOTH AND THE OTHER GEAR HAD THE TIMING MARK INSTALLED ONE TOOTH OFF.  THESE ARE THE FIRST OF THESE GEARS WE 	HAVE PURCHACED.  NOTIFIED SUPERIOR AIR PARTS 5-15-2001.  SUGGEST ALL OPERATORS USING THIS GEAR LOOK FOR PROPER TIMING MA	RKS ON THE GEAR BEFORE INSTALLATION- IMPROPERLY TIMED GEARS TRAINS COULD RESULT IN ENGINE DAMAGE AND STOPPAGE.		1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2001080200236	20010802	00236	EA  	2001	8	2	2001FA0000156    	2	20010514	G	7314	RG9570R1	PUMP            								PWA   	PT6   	PT6A6       	52043	EA  					ENGINE	LEAKING         	B				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SW	99	451DM	164  					PCEPRO212			PILOT REPORTED FUEL SMELL IN CABIN, LATER NOTIFIED FUEL LEAKING FROM ENGINE COMPARTMENT. TECHNICIAN FOUND LOW PRESSURE F	UEL PUMP LEAKING AT RELIEF AND SCREWS LOOSE. PUMP REMOVED AND REPLACED WITH NEW UNIT. (REFERENCE TEXTRON LYCOMING AD 98-	18-12 AND TEXTRON LYCOMING SERVICE BULLETIN 529 DEALS WITH SAME PROBLEM FOUND WITH THIS PUMP OF SAME CRANE/LEARROMEC "AN	" ROTARY FUEL PUMP MODEL SERIES.)								3	T			E4EA				 
2001080200239	20010802	00239	GL  	2001	8	2	2001FA0000157    	3	20010517	G	6110		SNAP RING       			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  	MCAULY	3AF32C	3AF32C512   	GL  	BLADE TO HUB	DAMAGED         	B				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	11	818JC	59   	59   			TH1620	L676535	L901873		THE AFOREMENTIONED AIRCRAFT ARRIVED FOR ENGINE OIL & FILTER CHANGE. UPON COMPLETION OF SERVICE, A PRE-ENGINE RUN / WALK 	AROUND INSPECTION WAS PERFORMED. DURING THIS WALK AROUND INSPECTION THERE WAS A CONSIDERABLE AMOUNT OF EXCESSIVE PLAY NO	TED IN ONE OF THE RT PROPELLER BLADES. REMOVED THE RT PROPELLER SPINNER ASSEMBLY FOR FURTHER INVESTIGATIONS AND NOTED TH	E SNAP RING THAT SECURES THE BLADE INTO THE PROPELLER HUB ASSEMBLY TO BE PARTIALLY INTACT WITH A SMALL PORTION ACTUALLY 	SECURING BLADE IN THE HUB ASSEMBLY. THE PROPELLER WAS IMMEDIATELY REMOVED AND ROUTED TO THE PREVIOUS OVERHAUL FACILITY F	OR INSPECTION AND REPAIR. PROPELLER TSO: 51.9.PROBABLE CAUSE: IT APPEARS THAT THE SECURING SNAP RING WAS NOT CORRECTLY	1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P22EA	 
2001080200242	20010802	00242	CE  	2001	8	2	2001FA0000158    	1	20010522	G	3010	2H598	VALVE           			CESSNA	310   	T310R       	2074246	CE  										DEICE SYSTEM	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	310KH					310R1507				DURING INSTALLATION OF AIRCRAFT SURFACE KNOWN ICE KIT FOUND SURFACE DEICE FLOW VALVE #2H59-8 (MFG. BY PARKER HANNIFIN, A	IRBORNE) S/N 9AT-83 TO CAUSE UNCOMMANDED DEICE BOOT INFLATIONS.  INSTALLED SECOND NEW VALVE S/N 9AT-91 OBTAINED FROM A D	IFFERENT DISTRIBUTOR WITH SAME RESULTS.  SPOKE WITH AIRBORNE TECH SUPPORT AND WAS GIVEN A MANUFACTURES POST ASSEMBLY INS	PECTION TEST PROCEDURE. TESTED THREE MORE VALVES FROM VARIOUS DISTRIBUTORS S/N 9AT-85, 6AT-48, 6AT-55 AND VARIFIED BOTH 	VISUALLY AND OPERATIONALLY THAT ALL WERE DEFECTIVE. DEFECT CAN BE SEEN AT TOP OF VALVE WHERE SOLENOID PLATE IS RIVETED T	O BODY. A LARGE GAP EXISTS ALLOWING PRESSURE AIR ESCAPE CAUSING VALVE ACTUATION.    NO ADDITIONAL SUPPLY OF VALVES AVAIL	1	L	7	2 	3O			 	3A10    					 
2001080200244	20010802	00244	CE  	2001	8	2	2001FA0000159    	1	20010501	G	8120	4709089011	WASTEGATE VALVE 			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					ENGINE EXHAUST	UNDERTORQUED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										FOUND THE 7 ACTUATOR TO BYPASS VALVE MOUNTING BOLTS (REF. GARRETT MANUAL TP30-4001-1 PG. 10-11 ITMES NR 7 AND 10) WITH L	ITTLE TO NIL MEASURABLE TORQUE.  THIS IS THE SECOND ACTUATOR ON WHICH WE HAVE DISCOVERED THIS PROBLEM.   DURING INSTALLA	TION INSPECTION, A WRENCH JUST HAPPENED TO BE PLACED ON THESE BOLTS WHICH WERE THEN OBSERVED TO BE LOOSE.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001080200245	20010802	00245	EA  	2001	8	2	2001FA0000160    	2	20010604	G	8530	RL499751A	CYLINDER        								LYC   	O360  	IO360B1E    	41514	EA  					ENGINE	SEPARATED       	G				O				OTHER                   				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			SW	01	3708T	3500 								THE NUMBER ONE CYLINDER HEAD SEPERATED FROM THE CYLINDER RESULTING IN AN ACCIDENT DESTROYING THE AIRCRAFT AND INJURING T	HE PILOT. NOTE: THE ENGINE EXCEEDED THE MANUFACTURERS CALENDER TBO OF 12 YEARS AND 2000 HOURS.										3	O			1E10				 
2001080200246	20010802	00246	EU  	2001	8	2	2001FA0000161    	1	20010608	G	7100	UAE651	SEAL            			AMD   	FALCON	FALCON20    	2730103	EU  										LEFT ENG PYLON	BROKEN          	C				E				ENGINE SHUTDOWN         				L			NO TEST                   			IN	INSP/MAINT     	1			EA	01		9728 				325				WHILE PERFORMING POST MAINTENANCE ENGINE RUN FOR AN UNRELATED ACTION, THE LEFT ENGINE FAILED TO RESPOND TO THROTTLE MOVE	MENT. UPON FURTHER INVESTIGATION THE LEFT ENGINE TORSION TUBE ASSY (P/N MY20571-53810) WAS FOUND BROKEN APPART INSIDE TH	E ENGINE PYLON BETWEEN FUSELAGE STATION FR31 AND FR32.  THE BREAK WAS LOCATED AT THE INBOARD SECTION OF THE TORSION TUBE	 IDENTIFIED AS A "SEAL" AS SHOWN IN FALCON 20 IPC CHAP, 76-10-20, PAGE 50-0, ITEM  50, P/N UAE651. INTEGRATED INTO THIS 	PART IS A METAL "UNIVERSAL-JOINT TYPE CONFIGURATION WHICH HAD CRACKED COMPLETELY THROUGH.		2	L	7	2 	4F			RT	A7EU    					 
2001080800318	20010808	00318	SW  	2001	8	8	2001FA0000163    	2	20010803	G	8520	4109	STUD            			WACO  	YMF   	YMF         	9600412	EA  	JACOBP	R755  	R755*       	35006	SW  					NR 4 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	53WC	252  				FSC062				FOUND BROKEN CYLINDER BASE STUD ON NR 4 CYLINDER.  AFTER REMOVING BROKEN STUD, FOUND TWO OTHERS BENT,  SENT STUDS FOR EV	ALUATION TO SEE IF THEY MET DESIGN INTENT.  THE STUDS DID NOT MEET SPECIFICATIONS.					1	Q	7	1 	3R	3	R	 	ATC542  	TC237				 
2001080700004	20010807	00004		2001	8	7	2001FA0000164    	4	20010425	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	430CP	42   				172S8692	L2938051A			UPON A POSTFLIGHT INSPECTION, THE PROPELLER SPINNER BULKHEAD ASSEMBLY WAS DISCOVERED CRACKED.  THE CORNER PORTION OF THE	 BULKHEAD WAS COMPLETELY RIPPED AWAY AND THE EDGE OF THE SPINNER WAS PEELING UP.  PROBABLE CAUSE:  MANUFACTURING DEFECT 	SUSPECTED.				1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001080700003	20010807	00003	CE  	2001	8	7	2001FA0000165    	1	20010804	G	2460	727725	CIRCUIT BREAKER 			BEECH 	1900  	1900D       	1154162	CE  										COCKPIT	FAILED          	B				A				UNSCHED LANDING         				B	G		SMOKE/FUMES/ODORS/SPARKS  	MULTIPLE FAILURE          		CR	CRUISE         	1			SW	99	84802					UE53				DURING FLIGHT, SMOKE WAS OBSERVED COMING FROM THE REAR OF A CB PANEL. CB'S PULLED PROGRESSIVELY TO IDENTIFY ONE CAUSING 	SMOKE. OTHERS RESET AFTER ISOLATING FAULTY ONE. AIRCRAFT LANDED. ON GROUND, FAILED CB REPLACED. FURTHER TROUBLE SHOOTING	 REVEALED.  POWER WIRE TO WING ICE INSPECTION LIGHT CHAFFED AGAINST STRUCTURE NEAR LIGHT ASSY. WIRE REPAIRED.				2	L	7	2 	4T			RT	A24CE   					 
2001080800319	20010808	00319	GL  	2001	8	8	2001FA0000166    	2	20010531	G	7323	2526146	BEARING         	HONEYWELL   		SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C20B     	03013	GL  					PT GOVERNOR	DISINTEGRATED   	Z				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	PTYDC		652  		BR31687	760220				SPOOL BEARING ASSEMBLY DISINTEGRATED.  INNER AND OUTER RACES ARE ALL THAT REMAINS.  NEARLY ALL EVIDENCE OF BALLS FROM BE	ARING MISSING.  REASON FOR FAILURE POSSIBLY DUE TO BEARING BALL RETAINER FAILURE.					1	G	7	2 	3U	3	U	 	H1NE    	E4CE				 
2001080800321	20010808	00321	EA  	2001	8	8	2001FA0000167    	2	20010201	G	8520	SL13885	MAIN BEARING    			CESSNA	185   	A185E       	2072818	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	694BK	54   				1851582	L474361A			DURING SCHEDULED OIL AND FILTER CHANGE ON ENGINE REFERENCED, FOUND BEARING PARTICLES WITHIN OIL FILTER.  DISASSEMBLED EN	GINE TO FIND FRONT MAIN BEARING EXHIBITING DELAMINATION OF THE LINER SURFACE.  FAULTY MANUFACTURING OF BEARING IS SUSPEC	T.				1	H	7	1 	3O	3	O	 	3A24    	E14EA				 
2001081600096	20010816	00096	CE  	2001	8	16	2001FA0000168    	1	20010803	G	3230	358250944	PLUNGER         			BEECH 	56    	56TC        	1152736	CE  	LYC   	O541  	TIO541E1B4  	41536	EA  					NLG	FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			SW	01	5455U					TG22				PILOT DEPARTED SANTA FE, NM AND RETRACTED GEAR.  THE TOWER NOTICED THE NOSE GEAR STILL HANGING DOWN.  PILOT LOWERED GEAR	, THE MAINS LOCKED DOWN BUT THE NOSE DID NOT LOCK DOWN.  PILOT LANDED AND THE NOSE GEAR COLLAPSED.  THE AFT END ATTACH F	ITTING OF THE PLUNGER ASSEMBLY (P/N 35-825094-4) FAILED.  TOTAL TIME AND CYCLES ON THE NOSE GEAR IS UNKNOWN.				1	L	7	2 	3O	3	O	 	3A16    	E10EA				 
2001080800326	20010808	00326		2001	8	8	2001FA0000169    	4	20010710	G	2561	KS9P0Z01	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED MFG RECOMMENDED 2 PSI INFLATION TEST I/A/W MANUAL 25-60-1  DOM: NOVEMBER 1982																			 
2001080800329	20010808	00329	SO  	2001	8	8	2001FA0000170    	1	20010706	G	7722	481389	PROBE           			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					TIT SYSTEM	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	135CC	49   				4636192	L1012361A			PART FAILED IN 49 HOURS.  THIS PART IS REPLACED DURING AN AD REQUIREMENT EVERY 250 HOURS BUT ONLY LASTED 49 HOURS.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001080800333	20010808	00333	CE  	2001	8	8	2001FA0000171    	1	20010706	G	2810	S23591	CHECK VALVE     			CESSNA	172   	172R        	2072401	CE  										LT FUEL TANK	MISINSTALLED    	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	09	361ES	1731 				17280011				WHEN FUEL TANKS WERE FILLED TO ABOVE 35 GALLONS, HIGH AMBIENT TEMPERATURE CAUSED FUEL TO LEAK FROM VENT TUBE.  REMOVED L	EFT FUEL BAY INSPECTION PLATE AND FOUND THAT THE FUEL VENT TUBE INVERTED CHECK VALVE S2359-1 ALSO INVERTED FROM FACTORY.	  ROTATED 180 DEGREES TO CURRENT POSITION.  INSPECTION PLATE SHOWED NO SIGN OF EVER BEEN REMOVED.				1	H	7	1 	3O			NT	3A12    					 
2001080800336	20010808	00336	CE  	2001	8	8	2001FA0000172    	1	20010615	G	5210	051701912	HINGE PIN       			CESSNA	172   	172R        	2072401	CE  										CABIN DOOR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	172WY	1722 				17280334				DURING A PHASE II INSPECTION, FOUND LEFT AND RIGHT LOWER CABIN DOOR HINGE PINS, BROKEN.  IT APPEARS THAT THE CABIN DOOR 	WAS NOT INSTALLED PROPERLY FROM THE FACTORY, CAUSING UNDUE STRAIN ON LOWER HINGES.					1	H	7	1 	3O			NT	3A12    					 
2001080800339	20010808	00339	WP  	2001	8	8	2001FA0000173    	1	20010607	G	6510		DRIVE SHAFT     			ROBSIN	R22   	R22         	7640102	WP  										TAIL ROTOR	FAILED          	F			YV3R	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	05										DURING RUN-UP PRIOR TO TAKE-OFF, AN R22 TAIL ROTOR DRIVE CUT LOOSE AND SEVERED THE TAIL BOOM.  HELICOPTER WAS ABOUT TO F	LY TO A MAINTENANCE FACILITY FOR 100 HOUR INSPECTION.  PRELIMINARY SURVEY INDICATES THAT THE INCIDENT WAS INITIATED BY T	HE TAIL ROTOR DRIVE SHAFT DAMPER BREAKING OFF INSIDE THE TAIL BOOM.  THIS ALLOWED THE DRIVE SHAFT TO WHIP, FRACTURE, AND	 CUT OFF THE TAIL BOOM.			1	G	7	1 	3O			 	H10WE   					 
2001080800340	20010808	00340	EA  	2001	8	8	2001FA0000174    	1	20010601	G	4920	32020725	CHECK VALVE     			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF341A      	 	NE  					APU	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	604MU					5406				DURING REPLACEMENT OF THE CHECK VALVE, FOUND PIECES OF CHECK VALVE FLAPPERS, REPLACED WITH PN 320-2832-1-1 SN 635 OPERAT	IONAL CHECKED SATISFACTORY.  NOTE: ALL PIECES REMOVED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001080800341	20010808	00341	CE  	2001	8	8	2001FA0000175    	1	20010530	G	7120	241302411	BRACKET         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	VO360*      	41514	EA  					ENGINE MOUNT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	9578B	6324 				172RG0895				DURING ENGINE CHANGE, THE ENGINE MOUNT WAS REMOVED FOR INSPECTION.  MOUNT WAS REMOVED FOR INSPECTION.  THE FIREWALL ATTA	CH POINTS FOR THE ENGINE MOUNT WERE THEN INSPECTED.  THE UPPER LEFT BRACKET WAS FOUND CRACKED AT THE ENGINE MOUNT BOLT H	OLE.  THE BRACKET INBOARD 2 RIVETS THAT ATTACH IT TO THE LONGERON HOT SECTION WERE MISSING.  SUSPECT THIS CAUSED THE CRA	CK.			1	H	7	1 	3O	3	O	 	3A17    	1E1				 
2001080800342	20010808	00342	SO  	2001	8	8	2001FA0000176    	1	20010627	G	3233	SFA2325	ACTUATOR        			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540*     	41532	EA  					MLG	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	23	36202	55   				32R7887028	L5351UA			ACTUATOR LEAKS FLUID FROM SHAFT SEAL.  SEAL  PN 762-084 WAS FOUND SPLIT ON I.D.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001081000155	20010810	00155	EA  	2001	8	10	2001FA0000177    	2	20010713	G	8540	LW10284	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540*    	41533	EA  					ENGINE	BROKEN          	B			DECR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	3556F	883  				318052066				ONE TOOTH ON GEAR SEPARATED AND LODGED BETWEEN CRANKSHAFT GEAR AND OIL PUMP HOUSING.  THIS CAUSED THE REMAINING TEETH OF	 THE CRANKSHAFT GEAR TO ROUND OFF AND DISENGAGE FROM THE OTHER GEARS.  THIS ALSO CAUSED 2 IDLER GEARS AND THE OIL PUMP D	RIVE GEAR TO SHEAR SEVERAL TEETH AS WELL.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001081000156	20010810	00156	SW  	2001	8	10	2001FA0000178    	1	20010611	G	3233	1020004	ACTUATOR        			MOONEY	M20   	M20M        	5870222	SW  										LANDING GEAR	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	09	321JL	741  				270162				ACTUATOR FAILED BOTH MANUALLY AND ELECTRICALLY RESULTING IN A GEAR UP LANDING.						1	L	7	1 	3O			RT	2A3     					 
2001081000158	20010810	00158	CE  	2001	8	10	2001FA0000179    	1	20010808	G	7160	05521644	AIR BOX         			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	DAMAGED         	B			EL6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	737MP					17269524				NOTED:  DURING ANNUAL INSPECTION, CARBURETOR AIR BOX OUTLET/INLET FOR CARBURETOR HEAT SWEDGED ONTO AIR BOX.  ROUND METAL	 FLANGE VIBRATING AND CHAFING WHERE SWEDGING DONE.  GETS LOOSE AND CHAFES ITSELF TO PIECES.  COULD EVENTUALLY BREAK, ALL	OWING HOSE TO FALL OFF AND CARBURETOR TO INGEST THIN PIECES OF METAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001081000159	20010810	00159	NE  	2001	8	10	2001FA0000180    	2	20010709	G	7321		FUEL CONTROL    			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					RT ENGINE	MALFUNCTIONED   	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	07	88GJ					5000155	PCE76335			DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT.  ENGINE IGNITION WAS SELECTED ON TO N	O EFFECT.  AN EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE.  SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED.					1	L	7	2 	4F	4	F	 	A22CE   	E25EA				 
2001081000161	20010810	00161	EA  	2001	8	10	2001FA0000181    	2	20010516	G	8550	06B23072	GASKET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	DEFECTIVE       	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	19	737TC					17269654	L446076			AD 200-18-23 WAS C/W BY INSTALLING NEW GASKET PT 06B23072 UNDER OIL FILTER ADAPTER PLATE.  WITHIN 34 HOURS, GASKET BLEW 	OUT AND ALL THE OIL WAS BLOWN OUT.  AIRCRAFT RETURNED TO AIRPORT SAFELY.  INSPECTION OF GASKET REVELED THAT THE RUBBER G	ASKET HAD DISSOLVED AND BECAME VERY SOFT.  A NEW GASKET WAS INSTALLED AS PER INSTRUCTIONS IN THE SB 543A, NO FURTHER PRO	BLEMS HAVE BEEN ENCOUNTERED WITH THIS AIRCRAFT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001081000167	20010810	00167	CE  	2001	8	10	2001FA0000182    	1	20010614	G	3710	653487	GASKET          			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					VACCUUM PUMP	MISSING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	132ME	276  				18280690	L2728048A			WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, AND OIL LEAK WAS NOTICED COMING FROM THE LOWER VACUUM PUMP DRIVE	 PAD.  FURTHER INSPECTION REVEALED THAT THE GASKET FOR THE PUMP WAS MISSING.  A NEW GASKET WAS INSTALLED AND A LEAK CHEC	K WAS PERFORMED.				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001081000187	20010810	00187	EA  	2001	8	10	2001FA0000185    	1	20010423	G	2750		FLAP            			BLANCA	1413  	14132       	1201004	EA  	FRNKLN	6A4150	6A4150B3    	27024	EA  					LT WING	DEPARTED        	C				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			WP	07	74285					1398	13505			LT FLAP SEPARATED FROM A/C AT ABOUT 500 FT WHILE TURNING DOWNWIND TO AIRPORT. A/C WAS BEING CONFIGURED FOR LANDING AT TH	E TIME OF SEPARATION. 80 MPH GEAR DOWN AND THE FLAP HANDLE WAS PULLED FOR FULL FLAP. AN IMPULSE WAS FELT IN THE HANDLE W	HICH I FIRST THOUGHT WAS A BROKEN FLAP CABLE AND IMMEDIATELY RETRACTED THE FLAPS OR IN THIS CASE THE FLAP. THE A/C WAS S	TABLE AND CONTROLLABLE SO MORE POWER WAS ADDED AND LANDED FASTER THAN NORMAL. MOISTURE HAD COLLECTED IN THIS AREA AND CO	MPROMISED THE WOOD AND GLUE CAUSING THE FAILURE OF THE OUTBOARD HINGE RIB, INSPECTION AT THIS AREA IS ONLY POSSIBLE BY C	UTTING A HOLE.  THE INBOARD RIB OF THE FLAP FAILED, THIS WAS SECONDARY AFTER THE OUTBOARD HINGE SEPARATED FROM THE WING.	1	L	7	1 	3O	3	O	 	A773    	E238				 
2001081600098	20010816	00098	CE  	2001	8	16	2001FA0000186    	1	20010809	G	5712	57222062	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	441DB					4410300				DURING A SCHEDULED INSPECTION THE LEFT AND RIGHT CANTED RIB CAPS P/N 5722206-1 AND 5722206-2 WERE FOUND CRACKED APPROXIM	ATELY 1 INCH BEHIND THE FORWARD SPAR.  WHILE ACCOMPLISHING THE REPAIR TO THIS AREA, ANOTHER CRACK WAS FOUND IN THE LEFT 	WING/FUSELAGE CLOSEOUT P/N 6720001-3.  THE CLOSEOUT CANNOT BE SEEN UNTIL THE WING FAIRINGS ARE REMOVED, THUS IT CANNOT B	E SEEN DURING NORMAL INSPECTION.			1	L	7	2 	3T			RT	A28CE   					 
2001081600099	20010816	00099	CE  	2001	8	16	2001FA0000187    	1	20010810	G	5720		ANGLE           			CESSNA	441   	441         	2076020	CE  										WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	441JC					4410156				DURING A SCHEDULED INSPECTION, THE LEFT CANTED RIB CAP P/N 5722206-1 WAS FOUND CRACKED APPROXIMATELY 1 INCH AFT OF THE F	ORWARD WING SPAR.  WHILE REPAIRING THIS CRACK THE UPPER WING TO FUSELAGE CLOSEOUT ANGLE P/N 5720001-3 WAS FOUND CRACKED.	  THESE CLOSEOUT ANGLES CANNOT BE SEEN UNLESS THE WING TO FUSELAGE FAIRINGS ARE REMOVED AND THUS ARE NEVER INSPECTED DUR	ING NORMAL MAINTENANCE.			1	L	7	2 	3T			RT	A28CE   					 
2001081600100	20010816	00100	SO  	2001	8	16	2001FA0000188    	1	20010810	G	7430	103572101	IGNITION SWITCH 			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					INSTRUMENT PANEL	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	06										A NEW SWITCH WAS INSTALLED TO COMPLY WITH AD 76-07-12.  THE NEW SWITCH WOULD NOT ENERGIZE THE STARTER CONTACTOR.  A SECO	ND SWITCH WAS ORDERED.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001082000031	20010820	00031	EA  	2001	8	20	2001FA0000189    	2	20010720	G	8520	72877	LIFTER          			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	8715E	2600 				287625149	L4434627A			DURING TEAR DOWN FOR OVERHAUL A PIECE OF METAL WAS FOUND IN OIL SUMP.  FURTHER INSPECTION FOUND THAT THE HEAD OF LIFTER 	BODY FOR NR 1 CYLINDER EXHAUST VALVE WAS HALF GONE.  (PIECE IN OIL SUMP)  FROM WEAR ON REMAINING PART, APPEARS THAT IT H	AD BEEN THAT WAY FOR SEVERAL HOURS. PART HAD AT LEAST 2600 HOURS SINCE OVERHAUL.				1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001082000032	20010820	00032	EA  	2001	8	20	2001FA0000190    	2	20010720	G	8530	SL17540	EXHAUST VALVE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	07	8715E	2600 	2600 			287625149	L4434627A			AIRCRAFT WAS ON A TRAINING FLIGHT, STEM BROKE AT VALVE HEAD.  ENGINE LOST POWER BUT WAS ABLE TO LAND.  ENGINE CHANGED.  	PROBABLE CAUSE OF BREAKAGE:  OLD AGE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001082000033	20010820	00033	CE  	2001	8	20	2001FA0000191    	1	20010817	G	7112	17500117	SHROUD          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	CHAFED          	B			EL6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	737MP					17269524				NOTED:  DURING ANNUAL INSPECTION ON NUMEROUS AIRCRAFT, SCREEN INSIDE OF CARB HEAT SHROUD VIBRATING AND CHAFING ITSELF TO	 PIECES BE ALLOWED TO BE SUCK INTO THE CARB INLET.  (SHROUD LOCATED ON CYLINDER STACK ASSEMBLY WITH CLAMPS).					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001082100025	20010821	00025		2001	8	21	2001FA0000192    	4	20010820	G	2561	P0723105	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MANUFACTURE RECOMMENDED 2 PSI CELL TEST IAW 21-60-7.  DATE OF MFG. SEPT 1986.																			 
2001082100026	20010821	00026	EA  	2001	8	21	2001FA0000193    	2	20010730	G	8520	LW13818	CRANKCASE       			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C    	41514	EA  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	9235G					2837055	L2545951A			AT INSPECTION AN AREA OF OIL IS NOTICED BEHIND PROP- IT APPEARS TO LOOK LIKE THE SPLIT CASE SEAM IS LEAKING.  CLEAN AREA	 AND USE NDT DEVELOPER.  RUN-UP PLANE AND CRACK APPEARS.  THERE ARE SEVERAL STYLES OF CASE FOR THIS ENGINE.  BUT ON A CE	RTAIN STYLE SEEMS TO CRACK.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001082100027	20010821	00027	SW  	2001	8	21	2001FA0000194    	1	20010806	G	3020	19940	CONTROL ARM     			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	VO360*      	41514	EA  					ENGINE	FAULTY          	B			RJWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	437AC	182  				39398				WHEN MOVING CARBURETOR HEAT CONTROL, CARB HEAT CONTROL ARM (PN 1-9940) CONTACTS JAM NUT ON THE THROTTLE CONTROL ROD CLEV	IS (PN A31800), MOVING THE THROTTLE OUT OF POSITION.					1	H	7	1 	3O	3	O	 	A21CE   	1E1				 
2001082300015	20010823	00015	NE  	2001	8	23	2001FA0000195    	2	20010703	G	8530	366249	CYLINDER        			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340*      	52016	NE  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3164H	6375 				3010539				THE NR 3 CYLINDER HEAD CRACKED AT THE ROCKER BOSS, ENGINE LOST POWER, AIRCRAFT EMERGENCY LANDED IN A FIELD.  2ND OCCURAN	CE.					1	L	7	1 	3R	3	R	 	A9SW    	5E2				 
2001082300022	20010823	00022	SO  	2001	8	23	2001FA0000196    	2	20010724	G	8500		ENGINE          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE BAY	FAILED          	B			CGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	5688K		200  			TC765	1921768LR			PILOT REPORTED SEVERE ENGINE VIBRATION FOLLOWING POWER REDUCTION ON INITIAL CLIMB-OUT AFTER DEPARTURE FROM AIRPORT.  ENG	INE SHUTDOWN AND FEATHERED.  NOTED CATASTROPHIC LEFT ENGINE FAILURE UPON INITIAL INSPECTION.  NR 5 CONNECTING ROD OBSERV	ED WITH CLEAN BREAK THROUGH LARGE HOLE IN CRANKCASE;  NR 6 CONNECTING ROD SEVERELY BENT.  NR 5, NR 6 PISTONS DAMAGED SEV	ERELY AND SEIZED IN CYLINDERS.  OBSERVED CAMSHAFT BROKEN;  FOUND PISTON PIN LOOSE WITH OTHER CRANKCASE AND CYLINDER BROK	EN PARTS.  EXACT FAIL MODE UNDETERMINED.  ENGINE RECORDS NOT SUPPLIED.		1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2001082300024	20010823	00024	EU  	2001	8	23	2001FA0000197    	2	20010616	G	8550	956470	LINE            			DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					OIL SUCTION	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	442PC					10042	4412740			OIL SUCTION LINE/ NR 3 CONNECTING ROD BROKE AT CRANKSHAFT.  ROD PROTRUDED THROUGH ENGINE CASING.  SB ADDRESSES SUBJECT O	IL LINES TO BE INSPECTED FOR KINKS AND SHARP BENDS.  ALSO, NONCOMPLIANCE COULD RESULT IN ENGINE DAMAGE.  SUSPECT THAT OI	L MAY HAVE BEEN RESTRICTED FROM ENTERING INTO ENGINE CASING DUE TO DEFECTIVE OIL LINES.  DEFECTIVE OIL LINES.  RECOMMEND	 AD AT 100 HR INTERVALS.			1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2001082300026	20010823	00026	EU  	2001	8	23	2001FA0000198    	2	20010616	G	8550	956476	LINE            			DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					OIL PRESS	DEFECTIVE       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	442PC					10042	4412740			OIL PRESSURE LINE-NR 3 CONNECTING ROD BROKE AT CRANKSHAFT.  ROD PROTRUDED THROUGH ENGINE CASING.  SERVICE INSTRUCTION AD	DRESSES SUBJECT OIL LINES TO BE INSPECTED FOR KINKS AND SHARP BENDS.  ALSO, NONCOMPLIANCE COULD RESULT IN ENGINE DAMAGE.	  SUSPECT OIL MAY HAVE BEEN RESTRICTED FROM ENTERING INTO ENGINE CASING DUE TO DEFECTIVE OIL LINES.  RECOMMEND AD AT 100	 HR INTERVALS.			1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2001082300027	20010823	00027	CE  	2001	8	23	2001FA0000199    	1	20010711	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B			LW5T	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	9515B	4503 				172RG0846				BOTH ACTUATORS WERE INSPECTED IAW SB,  CRACKS WERE FOUND IN THE AREA THAT  ACCOMPLISHMENT INSTRUCTIONS INDICATED.  PARTS	 WERE REMOVED FROM SERVICE.					1	H	7	1 	3O			 	3A17    					 
2001083001069	20010830	01069	SW  	2001	8	30	2001FA0000200    	1	20010712	G	2842	206379006101	TOTALIZER       			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250B  	250B*       	 	GL  					FUEL SYS	INTERMITTENT    	D				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	21	656NA					45391				TOT INDICATOR RED LIGHT FLASHED ON INTERMITTENTLY CAUSING PILOT TO MAKE PRECAUTIONARY LANDING.						1	G	7	1 	3U	3	T	 	H2SW    	E10CE				 
2001082300074	20010823	00074	CE  	2001	8	23	2001FA0000202    	1	20010627	G	3230	5081032019	SOCKET          			BEECH 	1900  	1900D       	1154162	CE  										TORQUE ARM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			9947 							DURING LIQUID PENETRANT INSPECTION IAW MM NDT WE HAVE FOUND CRACKS ON THE LOWER LUGS WERE THE TORQUE ARM ATTACHED, DEPTH	 OF CRACKS ARE UNKNOWN, BUT VISUAL INSPECTION WILL REVEAL CRACKS WITH ANY USE OF MAGNIFICATION DEVICES OR PENETRANT DYE.	  WHEN WE RECEIVED UNITS, THEY NEVER HAVE THE DASH NUMBER JUST THE SERIES 50-810320.  ALL SOCKETS SHOULD BE CONSIDERED. 	 CAUSE IS UNKNOWN.			2	L	7	2 	4T			RT	A24CE   					 
2001082300075	20010823	00075	SO  	2001	8	23	2001FA0000206    	2	20010815	G	7414	1051324	SPRING          	CONT        		CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					IMPULSE COUPLING	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	PK-MP	11   			E189909FR	U20605864	818029R			THE MAGNETO IMPULSE COUPLING SPRING BROKE ABOUT 6 INCHES FROM THE OUTER END OF THE SPRING.  THE FAILURE WAS DISCOVERED B	ECAUSE THE IMPULSE COUPLING WOULD NOT ENGAGE DURING THE ENGINE STARTING PROCESS.					1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001082300081	20010823	00081	CE  	2001	8	23	2001FA0000207    	1	20010815	G	3397	LF11	WIRE            			CESSNA	208   	208         	2073702	CE  										BEACON	CHAFED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	99	9Q-CA	9647 				20800010				WIRES LF11 AND LF12 ARE ROUTED THROUGH THE VERTICAL STABILIZER WITHOUT PROTECTION OR SUPPORT.  THESE WIRES POWER THE FLA	SHING RED BEACON MOUNTED ON THE TOP OF THE FIN.  BOTH WIRES CHAFED AGAINST THE EDGE OF THE HOLE IN THE STABILIZER RIB TH	ROUGH WHICH THEY WERE ROUTED AND WORE THROUGH THE INSULATION CAUSING A SHORT CIRCUIT AND THE BREAKER TO OPEN.				1	H	7	1 	3T			NT	A37CE   					 
2001082300082	20010823	00082	GL  	2001	8	23	2001FA0000208    	1	20010810	G	3201	12446105	FAIRING         			CIRRUS	SR    	SR20        	05628AJ	GL  										NLG	LOOSE           	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	747CD	69   				0047				BRACKETS THAT HOLD THE NOSE WHEEL FAIRING TO THE NOSE GEAR FORK PART NUMBER 1799-001, ARE HELD TO THE FORK BY BOLTS THAT	 ARE NOT DRILLED FOR SAFETY WIRE, THEY DO NOT THREAD INTO SELF LOCKING NUTS PLATES, NOR DO THEY CALL OUT FOR LOCK WASHER	S.  THE BOLTS LOOSEN UP, THE FAIRING MOVES AROUND, AND LEAVES THE AIRPLANE.  EXAMINED OTHER SAME MODEL AIRCRAFT, AND FOU	ND LOOSE FAIRINGS.  BROUGHT THIS CONDITION TO THE OPERATORS ATTENTION. CONDITION NOTED BY: JACK D. TOBIN A&P 2250313.			1	H	7	1 	3O			NC	A00009CH					 
2001082300083	20010823	00083	NE  	2001	8	23	2001FA0000209    	2	20010822	G	8530	11874	PUSHROD         								PWA   	R1340 	R1340AN1    	52016	NE  					EXHAUST	FAILED          	G			ISSG	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	27							21730			ENGINE FAILED DUE TO FAILURE OF NR 1 EXHAUST PUSHROD. UNEVENTFUL LANDING MADE.											3	R			5E2				 
2001083100005	20010831	00005	GL  	2001	8	31	2001FA0000210    	3	20010717	G	6111	FC8477A4	BLADE           													HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	CRACKED         	B			ME4R	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CL	CLIMB          	1			SO	19			835  					AU3069E		PILOT REPORTED ON TAKE OFF THAT THE PROPELLER WOULD NOT MAKE FULL POWER.  PILOT RETURNED TO THE FIELD.  PRIOR TO TOUCHDO	WN, PILOT EXPERIENCED A VIBRATION.  IMMEDIATELY AFTER TOUCHDOWN, THE VIBRATION INCREASED SIGNIFICANTLY, AND THE ENGINE S	HUT DOWN.  A FIELD INSPECTION REVEALED THE PROPELLER TO BE OUT OF TRACK OVER ONE INCH (1 IN).  THE PROPELLER WAS REMOVED	 AND SENT FOR INSPECTION/ EVALUATION.  UPON DISASSEMBLY OF THIS PROPELLER A VISUAL INSPECTION REVEALED A LARGE CRACK APP	ROXIMATELY 270 DEGREES AROUND THE NR 2 BLADE SHANK.  THE HUB APPEARS TO BE CRACKED IN THE NR 2 BLADE ARM AS WELL.												5	C	P920	 
2001090500048	20010905	00048	CE  	2001	9	5	2001FA0000211    	1	20010808	G	1100		PLACARD         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	FOD             	C				O				OTHER                   				C	R		F.O.D.                    	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			GL	09	67464	42   	42   			15281850	L1402115			DURING TOUCH AND GO LANDING AS CARB HEAT WAS APPLIED, ENGINE LOST POWER.  REMOVING CARB HEAT DID NOT IMPROVE PERFORMANCE	.  DURING INVESTIGATION  AND CARB REMOVAL, FOUND STARTER LUBRICATION DECAL LODGED IN VENTURI.  AFTER REMOVAL AND REINSTA	LLATION OF CARB.  ENGINE POWER RETURNED TO NORMAL.  RECOMMEND THESE DECALS BE REMOVED PRIOR TO STARTER AND CARBURETOR IN	STALLATION ON ENGINE.  ( FOUND WARRANTY WARNING DECAL ON OVERHAULED CARB)			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001083100167	20010831	00167	EA  	2001	8	31	2001FA0000212    	2	20010813	G	8520	LW17162	CRANKSHAFT      			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					ENGINE	BROKEN          	G				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	03	8424W		1564 			282651	L741036A			CRANKSHAFT FRONT MAIN JOURNAL, FRACTURED AT THE REAR RADIUS OF THE CRANKSHAFT FLANGE.  PROPELLER SEPARATED FROM THE AIRC	RAFT.  LOSS OF OIL AND OIL PRESSURE, ENGINE SEIZED UP AND QUIT. THIS CRANKSHAFT WAS PURCHASED BY THE  AIRPLANES INSURANC	E COMPANY AT THE LAST OVERHAUL, (6-4-99), HISTORY AND TOTAL TIME OF CRANKSHAFT IS UNKNOWN.  CRANKSHAFT MAY HAVE BEEN SUB	JECT TO A PRIOR PROPELLER STRIKE DAMAGE ACCIDENT,  AS NOTED BY THE SPIRAL TYPE FRACTURE OF THE FRONT CRANKSHAFT JOURNAL.			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001083100168	20010831	00168	SO  	2001	8	31	2001FA0000213    	1	20010810	G	2752	452860	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					FLAP ACTUATOR	BROKEN          	B				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SO	01	54828					277554125				FLAP ACTUATOR ROD END BEARING, BROKEN ON SHORT FINAL.  REPLACED BEARING PN 452860.						1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2001090500049	20010905	00049		2001	9	5	2001FA0000214    	4	20010606	G	2340	600591463	INTERPHONE      			CNDAIR	CL604 	CL604       	       	EA  										EQUIP BAY	UNSERVICEABLE   	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	09	15SP	570  				5402				ON TAXI IN, CREW EXPERIENCED A LOUD CONTINUOUS SQUEAL IN THEIR HEADSETS AND ALSO OVER THE COCKPIT SPEAKERS.  COMMUNICATI	ON WAS IMPOSSIBLE WITH THE TOWER.  OUR CUSTOMER SERVICE REP HAD US DISCONNECT THE HEADPHONE/MIC JACK ASSEMBLY IN THE AFT	 EQUIPMENT BAY.  THE SQUEAL WENT AWAY.  A NEW UNIT WAS ORDERED AND INSTALLED.  A NEW UNIT WAS ORDERED AND INSTALLED.  TH	E SYSTEM IS ONLY ACTIVE WITH WEIGHT ON WHEELS , BUT IT COULD STILL POSE A SERIOUS COMMUNICATION PROBLEM ON THE GROUND AT	 A BUSY AIRPORT.		2	L	7	2 	4F			RT	A21EA   					 
2001090500050	20010905	00050	SO  	2001	9	5	2001FA0000216    	1	20010727	G	7920	63201000	LINE            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360*       	41514	EA  					OIL SYSTEM	CORRODED        	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	7299W	1830 				281121				ON THE THIRD FLIGHT AFTER UPDATING THE OIL PUMP IN THE ENGINE PER AD, AN OIL FILM WAS NOTED AT THE FIREWALL ADJACENT TO 	THE SPOT WHERE THE OIL PRESSURE LINE PASSES THROUGH A GROMMET (DISC, FIREWALL PN 63915-003).  OIL WAS ALSO PRESENT ON TH	E FIREWALL BLANKET ON THE INSIDE OF THE COCKPIT.  AFTER DISASSEMBLING THE DISC A RETAINERS FROM THE FIREWALL, ABOUT 10-1	5 LBS PRESSURE WAS EXERTED ON THE ALUMINUM OIL LINE ASSEMBLY.  IT SEPARATED INTO TWO PIECES DUE TO CORROSION OF THE META	L, INSIDE THE AREA WHERE IT PASSES THROUGH THE DISC/RETAINER ASSEMBLY.  THIS PART HAS A TOTAL TIME OF ONLY 1830 HOURS IT	 IS A 1963 AIRCRAFT.	1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001083100169	20010831	00169	EA  	2001	8	31	2001FA0000217    	2	20010720	G	8530	72057	VALVE SEAT      			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O360  	O360*       	41514	EA  					INTAKE PORT	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	272CC					9925CC	L37352736A			DURING COMPRESSION CHECK, LOW CYLINDER PRESSURE WAS DISCOVERED.  LEAKAGE WAS DETERMINED TO BE BETWEEN NUMBER FOUR CYLIND	ER INTAKE VALVE AND VALVE SEAT.  AFTER REMOVING INTAKE VALVE, FURTHER INSPECTION REVEALED POOR CONDITION OF VALVE SEAT I	N REGARDS TO A LACK OF A DISTINCT CONTACT WEAR PATTERN WITH VALVE.  APPROXIMATELY ONLY ONE QUARTER OF THE DIAMETER OF TH	E VALVE SEAT SHOWED CLEAN CONTACT WITH THE VALVE WHILE THE OTHER THREE QUARTERS APPEARED ROUGH WITH EVIDENCE OF COMPRESS	ION BLOWBY.  LEAKAGE CAUSED BY POOR SEAL BETWEEN VALVE AND SEAT DUE TO POSSIBLE IMPROPER VALVE SEAT INSTALLATION, VALVE 	LAPPING OR VALVE GUIDE BOSS NOT TRUE WITH VALVE SEAT FACE.	1	H	7	1 	3O	3	O	 	1A2     	E286				 
2001083100170	20010831	00170	CE  	2001	8	31	2001FA0000218    	1	20010718	G	5730	052301158	SKIN            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					RT WING	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2168E	7177 				17271177				ON INSPECTION OF RIGHT WING ASSEMBLY, MECH NOTICED THAT A LOT OF RIVETS HAD POPPED FROM CORROSION UNDER THE LEADING EDGE	 SKIN AT THE FORWARD SPAR.  THE WING WAS REMOVED FROM THE AIRCRAFT, BROUGHT TO THIS FACILITY FOR REPAIR.  WING WAS DISAS	SEMBLED FOR REPAIR AND CORROSION REMOVAL.  THE WING WAS FOUND TO HAVE MORE THAN AVERAGE AMOUNT OF HEAVY CORROSION TO SKI	NS, RIBS, SPARS AND STRINGERS.  FOUR NOSE RIBS WHERE CORRODED THOUGH REQUIRING REPLACEMENTS.  ALSO ALL SKINS WERE REPLAC	ED.  THE REMAINDER OF THE PARTS REQUIRED REMOVAL OF CORROSION, CLEANING AND TREATING OF PARTS.  OWNER STATED THAT THE WI	NG WAS NOT THAT BAD A YEAR AGO.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001083100171	20010831	00171	CE  	2001	8	31	2001FA0000219    	1	20010621	G	5700	12NB108	NUT             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470*      	17026	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	70CL					TC2263				DURING INSPECTION FOR ANNUAL, CRITERION AND FREQUENCY FOR WING BOLT INSPECTION.  RECEIVED NEW HARDWARE.  SENT OUT HARDWA	RE FOR MAGNETIC PARTICLE PROCESS PER MM.  NDT PERSONAL INFORMED OF CONDITION OF NEW NUTS, STATING ROUGH INSIDE SURFACE A	ND LINEAR INDICATION ON INSIDE APPEARING AS CRACK INDICATIONS.  BOTH NUTS WERE RED TAGGED AND BOTH PARTS RETURNED WITH 8	130S FOR FURTHER INSPECTION.			1	L	7	2 	3O	3	O	RT	3A16    	E1CE				 
2001083100172	20010831	00172	SO  	2001	8	31	2001FA0000220    	1	20010806	G	7820	6751700	MUFFLER         			PIPER 	PA32  	PA32RT300   	7103215	SO  	LYC   	0540  	IO540K1G5D  	41532	SO  					ENGINE	SPLIT           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	3516M	2049 				32R7885009	L1753348A			THE CENTER MUFFLER HOUSING SPLIT OPEN AT THE UPPER WELD SEAM ALLOWING EXHAUST TO DAMAGE THE UPPER ALUMINUM MUFFLER ASSEM	BLY SHROUD AND THE ENGINE INDUCTION COVER.  SUGGEST THAT A VERY CLOSE INSPECTION BE DONE BY BOTH VISUAL AND PRESSURE CHE	CK METHODS OF ALL MUFFLER AND EXHAUST STACK WELD SEAMS.				1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001083100173	20010831	00173	GL  	2001	8	31	2001FA0000221    	3	20010726	G	6110	2202	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	35272					317952142		DJ8665A		RELEVANT INDICATION						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001083100174	20010831	00174	GL  	2001	8	31	2001FA0000222    	3	20010726	G	6110	3252L	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	35272					317952142		DJ8665A		RELEVANT INDICATION						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500051	20010905	00051	EU  	2001	9	5	2001FA0000223    	1	20010712	G	6320	C632A2115101	HOUSING         			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					MAIN ROTOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	120GB	597  	597  			1063	34076			MFG CONCESSION APPLIED TO MGB- INSTALLATION OF BEVEL GEAR AND BEVEL PINION GEAR. DISASSEMBLY OF MGB FOR MODIFICATION, CO	RROSION WAS ON SUPPORT STUDS OF THE LOWER HOUSING AND THE BORES OF MAIN MODULE OF THE AFFECTED STUDS, INSP REVEALED CORR	OSION IN THE BORES. CLEANED AND TREATED THE BORES AND STUDS TO ACCEPTABLE STANDARDS, RECORDS OF THE MGB WERE REVIEWED, I	NDICATING THE COMPONENT WAS MANUFACTURED 8/98, WITH TOTAL TIME SINCE NEW-597.3 HOURS. THE OVERHAUL INTERVAL OF THE MGB I	S 2000 HRS. THE MM WAS FOLLOWED FOR THE PROCEDURES OF DISASSEMBLY, ASSEMBLY AND COMPLETION OF THIS MODIFICATION, AND NO 	MENTION OF CORROSION IN THIS AREA OF THE MGB. FOLLOWED THE SPM FOR CORROSION CONTROL TO MAGNESIUM.  PROBABLE CAUSE OF TH	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2001091700136	20010917	00136	EU  	2001	9	17	2001FA0000224    	1	20010808	G	7600	C761A1014101	LEVER           			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					ANTICIPATR LEVER	MISINSTALLED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	162TA	1225 				1001				AFTER INSTALLATION OF THE NEW ANTICIPATOR COMPONENTS UNDER THE CARGO COMPARTMENT FLOOR ON THE LEFT SIDE .  WE COULD NOT 	ACHIEVE THE CRITERIA MENTIONED WITH ADJUSTMENTS AND TESTS.  UPON FURTHER INSPECTION, WE DISCOVERED THE ANTICIPATOR LEVER	 SECURED TO THE COLLECTIVE SHAFT FORWARD OF THE INSTALLED SB WAS INSTALLED FROM FACTORY  180 FROM A NORMAL POSITION.  WH	ICH WHT NEW MODIFICATION WE INSTALLED, CAUSING THE ADJUSTMENTS FOR THE ANTICIPATOR AT THE FUEL CONTROL TO BE INCORRECT. 	 ONCE THE ANTICIPATOR LEVER WAS REMOVED, AND INSTALLED CORRECTLY, WE WERE ABLE TO ACHIEVE CORRECT ADJUSTMENTS WITH THE A	NTICIPATOR SIDE OF THE FUEL CONTROL UNIT.	1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2001083100175	20010831	00175		2001	8	31	2001FA0000225    	4	20010717	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	O320  	IO320*      	41508	EA  	MCAULY	1A170	1A170E      	GL  	SPINNER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	430CP					172S8692	L2938051A	UC057		UPON A POSTFLIGHT INSPECTION, THE PROPELLER SPINNER BULKHEAD AND SPINNER ASSEMBLY WERE DISCOVERED CRACKED.  THE CORNER P	ORTION OF THE BULKHEAD WAS COMPLETELY RIPPED AWAY AND THE EDGE OF THE SPINNER WAS PEELING UP AND TORN. PROBABLE CAUSE: M	ANUFACTURING DEFECT SUSPECTED.				1	H	7	1 	3O	3	O	NT	3A12    	1E12	5	N	P857	 
2001083100176	20010831	00176	CE  	2001	8	31	2001FA0000226    	1	20010728	G	5711		SPAR            			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520*      	17032	SO  					LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	2764T					TE372				CRACK DEVELOPED ON TOP OF LEFT WING.  INVESTIGATION REVEALED LOWER FORWARD WING SPAR HINGES AND PINS WORN OUT RESULTING 	IN EXCESS OF MOVEMENT IN THE LEADING EDGE OF WINGS.  NEW WING SPARS					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001083100177	20010831	00177	EA  	2001	8	31	2001FA0000227    	2	20010730	G	7200	PT6A41	ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LEFT	FAILED          	G				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	03	2025M	10206	1596 			BB384	PCE80823			LEFT ENGINE SHUT DOWN DUE TO CHIP DETECTOR LIGHT ON ENGINE SURGING AND OIL PRESSURE FALLING OFF. ON INITIAL INSPECTION S	USPECTS COMPRESSOR, NR1 OR NR 2 MAIN LINE BEARING FAILURE.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001083100178	20010831	00178	SO  	2001	8	31	2001FA0000228    	1	20010622	G	2740	62701114	CONTROL CABLE   			PIPER 	PA28  	PA28161     	7102803	SO  										STABILIZER	FRAYED          	H			CDHS	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	9182W	7000 				2841130				RIGHT FORWARD STABILATOR CABLE- THIS LOCATION HAS SEVERAL PULLIES THAT DO NOT HAVE BEARINGS, WHEN THEY GET STUCK (NOT MU	CH CABLE DEFLECTION AND THEREFORE NOT MUCH PRESSURE TO TURN THE PULLEY) THE CABLE WEARS THIN AND EVENTUALLY FRAYS.  DIFF	ICULT TO DETECT WITHOUT CLEANING CABLE AND CHECKING WITH FINGERNAIL OR RAG.  THIS CABLE LOOKED FINE BUT HAD 50 PERCENT B	ROKEN STRANDS WHEN IT WAS REMOVED AND BIRDGAGED.			1	L	7	1 	3O			 	2A13    					 
2001090500052	20010905	00052		2001	9	5	2001FA0000229    	4	20010716	G	3418	S16729	DETECTOR        			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470*       	17026	SO  					LT WING	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	35VA					18268129				UPON INSTALLING NEW LIFT DETECTION, NOTED THAT WHEN WIRED AS ORIGINALLY REMOVED FROM AIRCRAFT, WITH HEAT TURNED ON, DETE	CTION WAS INOPERATIVE.  GROUND FOR HEATER WAS INSTALLED ON COMMON FOR DETECTION;  CAUSING A NO POTENTIAL WHEN HEATER TUR	NED ON.				1	L	7	1 	3O	3	O	NT	3A13    	E273				 
2001083100179	20010831	00179	SO  	2001	8	31	2001FA0000230    	2	20010829	G	8540	632617	BEVEL GEAR      			CESSNA	337   	337D        	2075717	CE  	CONT  	O360  	IO360CB     	17025	SO  					ACCESSORY DRIVE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	51WM					3371140	236532R			TROUBLESHOT LOSS OF VACUUM ON REAR ENGINE AND DETERMINE ACCESSORY DRIVE ASSEMBLY GEAR BOX FOR VACUUM PUMP AND HYDRAULIC 	PUMP INOPERABLE.  REMOVE AND DISASSEMBLED GEAR BOX AND FOUND BEVEL GEAR PN 632617 STRIPPED OF ALL GEAR TEETH.  ENGINE HA	D BEEN RECENTLY OVERHAULED.  OIL LEVEL AT CORRECT CAPACITY.  POSSIBLE CAUSE OF FAILURE MAY BE DUE TO IMPROPER GEAR MESH 	OF BEVEL GEARS FROM WORN OR INCORRECT SHOULDER THICKNESS ON BUSHING.  MFG IS NOW AWARE OF THE GEAR MESH PROBLEM AND HAS 	CORRECTED IT VIA A SB AND ISSUED THE MODIFIED ADAPTER ACCESSORY DRIVE FOR REPLACEMENT.		1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001083100180	20010831	00180	SO  	2001	8	31	2001FA0000231    	2	20010816	G	7230	6375506	VALVE SEAT      			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520*      	17032	SO  					CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	00	70083					18501950	282858			DURING A ROUTINE COMPRESSION CHECK, A LEAK WAS FOUND IN THIS CYLINDER (AIR WAS ESCAPING FROM IN BETWEEN COOLING FINS).  	UPON REMOVAL OF CYLINDER, 2 CRACKS APPROX. 1 INCH AND .7500 INCH LONG, WERE FOUND TO BE EMANATING FROM THE EXHAUST VALVE	 SEAT.				1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2001083100181	20010831	00181	SO  	2001	8	31	2001FA0000232    	1	20010816	G	2434	78483000	STRUT           			PIPER 	PA28  	PA28R200    	7102811	SO  										ALTERNATOR	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	17	318MC	926  				28R35155				ALTERNATOR FRONT ATTACHMENT STRUT FOUND CRACKED.						1	L	7	1 	3O			 	2A13    					 
2001083100182	20010831	00182	CE  	2001	8	31	2001FA0000233    	1	20010717	G	3246	5010720	BOLT            			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MLG WHEEL	BROKEN          	C			WXHM	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	440DS	1000 				RK8				1 MAIN WHEEL TIE BOLT BROKE AND DEPARTED AIRCRAFT, RESULTING IN UNSEATING OF WHEEL HALF SEALING O-RING AND SUBSEQUENT LO	SS OF AIR PRESSURE.  BOLT WAS MAGNAFLUXED 14 HOURS PREVIOUS WITH NO DEFECTS NOTED.					2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2001083100183	20010831	00183	EU  	2001	8	31	2001FA0000234    	1	20010702	G	6210	355A11002009	BLADE           			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	42AT	2220 				5462				FOUND CRACK ON PREFLIGHT.  NO SURE CAUSE FOR CRACK.  CRACK BEYOND LIMITS.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001083100184	20010831	00184	EA  	2001	8	31	2001FA0000235    	1	20010806	G	3222	6A0720401	LINK            			DHAV  	DHC2  	DHC2MK3     	2800107	EA  										NLG	BROKEN          	D				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			NM	01	227N					1686TB				UPON LANDING AT BFI, BOTH NOSE WHEEL BEGAN TO SHIMMY, PILOT PULLED NOSE WHEELS OFF OF RUNWAY UPON TOUCHDOWN AGAIN, SEVER	E SHIMMY OCCURRED.  RIGHT NOSE GEAR LINK RAM END BROKE ALLOWING GEAR TO DEPART FROM AIRCRAFT.					1	H	7	1 	3T			 	A806    					 
2001091000210	20010910	00210	CE  	2001	9	10	2001FA0000238    	1	20010831	G	3233	2653361203	CLEVIS PIN      			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					MLG ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	82CR	8760 	600  			46549				CRACKED PIN FOUND AS A RESULT OF CONDUCTING MAGNETIC PARTICLE INSPECTION OF MAIN LANDING GEAR ACTUATOR ROD CLEVIS PIN AN	D ATTACHING HARDWARE IN ACCORDANCE WITH SMIP ATA CODE 323076.  CRACK IS LOCATED IN RELIEF AREA RADIUS DIRECTLY UNDER CLE	VIS PIN HEAD.				2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2001090500053	20010905	00053	SO  	2001	9	5	2001FA0000239    	1	20010720	G	2842		O-RING          			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6*        	52043	EA  					FUEL PROBE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			NM	09	700LT				2260	31T7920046				AFTER FUELING AIRCRAFT, FUEL STARTED LEAKING FROM RIGHT NACELLE FUEL PROBE COVER.  FOUND O-RING BETWEEN MOUNT PLATE AND 	TOP OF PROBE EXTRUDED IN 2 AREAS.  FUEL WAS RUNNING OUT OF THOSE AREAS.  DEFUELED AND REPLACED PROBE WITH SERVICEABLE UN	IT.				1	L	7	2 	3T	3	T	 	A8EA    	E2NE				 
2001091000307	20010910	00307	SO  	2001	9	10	2001FA0000240    	1	20010801	G	2460	688498	RELAY           			PIPER 	PA46  	PA46500TP   	       	SO  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	DAMAGED         	B			NM4R	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	15	71562	17   								PILOT REPORTED SMOKE IN COCKPIT AND THEN CABIN FAN CIRCUIT BREAKER POPPED.  FOUND LOAD BUS RELAY PN 688498 LOCATED BELOW	 RIGHT CIRCUIT BREAKER PANEL, WITH A HOLE BURNED IN IT.  WITH CIRCUIT BREAKER PULLED, THE SMOKE WENT AWAY.  PILOT RETURN	ED AIRCRAFT TO FACTORY FOR REPAIR.				1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2001090500110	20010905	00110	SW  	2001	9	5	2001FA0000241    	1	20010522	G	7160	646207	TUBE            			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550G      	17042	SO  					NR 6 CYLINDER	CRACKED         	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	46WB	68   				290226	679484			INDUCTION TUBE AT NR 6 CYLINDER IS COMPLETELY CRACKED AT FLANGED END.						1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2001090500111	20010905	00111	SO  	2001	9	5	2001FA0000243    	1	20010827	G	3230	3807802	DOWNLOCK BRACKET			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	BROKEN          	G				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AL	01	200HM	351  				32R7680025				NOSE GEAR DROPPED OUT OF WHEEL WELL IN FLIGHT.  FOUND DOWNLOCK BROKEN WHERE NOSE ACTUATOR ROD ATTACHES.  THIS HAS HAPPEN	ED ON MORE THAN ONE OCCASION WITH SAME TYPE OF AIRCRAFT IN THE PAST.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001090500112	20010905	00112	CE  	2001	9	5	2001FA0000244    	1	20010824	G	5753	0523920	BEARING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	C85   	C85*        	17008	SO  					FLAP TRACK	WORN            	B			DVPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	9489Z	473  				U20606525				INNER BEARING WAS PUSHED OUT TO ONE SIDE SHOWING EXCESSIVE WEAR.						1	H	7	1 	3O	3	O	 	A4CE    	E233				 
2001091000308	20010910	00308	CE  	2001	9	10	2001FA0000245    	1	20010906	G	5210	169420036147	STRUCTURE       			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	VO360*      	41514	EA  					LT DOOR	BROKEN          	D				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		AP	APPROACH       	1			EA	21	20087	8100 				M2063				PILOTS REPORTED SEVERE BUFFET DURING SLOW FLIGHT, APPROACH TO LANDING, ROUND-OUT, AND FLARE.  BUFFET WAS AGGRAVATED BY L	EFT SLIP.  FOUND BOTTOM DOOR GASKET MISSING AND FIBERGLASS DOOR STRUCTURE BROKEN AT LAST RIVET ON DIAGONAL GUSSET.  THIS	 ALLOWED AIR ESCAPING FROM CABIN TO DISRUPT AIRFLOW OVER THE WING AND STABILATOR.  FABRICATED HAT SECTION CHANNEL FROM  	0.032 2024-T3, BONDED TO FIBERGLASS CHANNEL WITH HYSOL EA9309, AND RIVETED THROUGH OUTSIDE SKIN.  INSTALLED NEW DOOR GAS	KET.  FOUND RIGHT CABIN DOOR BROKEN ALSO.  SUSPECT CAUSE IS DUE TO PILOTS LEAVING DOORS OPEN AND UNATTENDED TO COOL CABI	N AND WIND OPENING DOOR HARD AGAINST THE STOP.	1	L	7	1 	3O	3	O	 	A1CE    	1E1				 
2001091000309	20010910	00309	CE  	2001	9	10	2001FA0000246    	1	20010906	G	7120	10598000021	CHANNEL         			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	VO360*      	41514	EA  					ENGINE MOUNT	BROKEN          	B			G2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	6714R					ME320				BOTH UPPER OUTBOARD ENGINE MOUNT CHANNELS BROKEN THROUGH JUST ABOVE NUT PLATE HOLE.  MAY HAVE BEEN CAUSED BY STRESSES IM	POSED BY THE COUNTER ROTATING ENGINES AND/OR UNREPORTED HARD LANDINGS.					1	L	7	2 	3O	3	O	 	A29CE   	1E1				 
2001091300185	20010913	00185	SO  	2001	9	13	2001FA0000247    	1	20010706	G	2140	23D04	VALVE           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					HEATER	DEFECTIVE       	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	68SE					273780				AFTER COMPLYING WITH AD AND SB, VALVE WAS DEEMED AIRWORTHY AND REINSTALLED IN AIRCRAFT. CONNECTED A PRESSURE GAUGE TO VE	RIFY THAT SETTING WAS CORRECT BECAUSE OF THE QUANTITY OF SOOT IN THE EXHAUST PIPE AND STREAM.  WHILE REMOVING TEE FITTIN	G AND GAUGE,THE FUEL DID NOT STOP DRIPPING FROM THE VALVE OUTLET. ENERGIZED THE FUEL PUMP BRIEFLY TO PRESSURIZE THE VALV	E AND THE FUEL DID NOT STOP, PN OF VALVE IS NOT READABLE. IT APPEARS TO HAVE BEEN SALVAGED FROM ANOTHER AIRCRAFT BECAUSE	 THE PAINT ON IT DOES NOT MATCH THIS AIRCRAFT.  NEW VALVE IN ORDER.		1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2001091000311	20010910	00311	NE  	2001	9	10	2001FA0000248    	2	20010708	G	7321		FUEL CONTROL    			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  					RT ENGINE	MALFUNCTIONED   	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			EA	07	88GJ					5000155	PCE76335			DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT.  ENGINE IGNITION WAS SELECTED ON TO N	O EFFECT.  AND EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE.  SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED.					1	L	7	2 	4F	4	F	 	A22CE   	E25EA				 
2001091000314	20010910	00314	EA  	2001	9	10	2001FA0000250    	2	20010814	G	7414	AB3571651	COIL            			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					MAGNETO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9240M	478  				1193	L252751A			WHILE REPAIRING LEFT BENDIX S20 SERIES MAGNETO, FOUND MAGNETO COIL CRACKED.  REPLACED COIL WITH A NEW TCM COIL PN 10-357	165  COIL.  ALSO FOUND CRACK IN DISTRIBUTOR BLOCK, REPLACED.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001091300186	20010913	00186	EA  	2001	9	13	2001FA0000251    	2	20010814	G	8550		IMPELLER        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					OIL PUMP	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9240M	478  				1193	L252751A			OIL PUMP IMPELLERS S1B 524, FOUND OIL PUMP GEARS TO BE STEEL TYPE BUT NO DOCUMENTATION AS TO WHAT PN THE GEARS WERE.  FO	UND GEARS HAD FOREIGN MATERIAL HAD PASSED THROUGH THE OIL PUMP.  OIL PUMP GEARS WERE NOT AIRWORTHY REGARDLESS OF PART NU	MBERS.  INSTALLED IMPELLER KIT PN 05K19423S.  (ATTACHED PHOTOS)				1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001091300188	20010913	00188	EA  	2001	9	13	2001FA0000252    	2	20010814	G	8550	78531	HOUSING         			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					OIL PUMP	GALLED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	9240M	478  				1193	L252751A			WHEN COMPLYING WITH AD, OIL PUMP IMPELLERS, S1B524, FOUND OIL PUMP BODY GALLED DUE TO FOREIGN MATERIAL PASSING THROUGH O	IL PUMP ASSEMBLY.  REPLACED OIL PUMP BODY WITH NEW PART.  (PHOTOS ATTACHED)					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001091000426	20010910	00426		2001	9	10	2001FA0000253    	4	20010822	G	2561	AC2D21344101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED MFG RECOMMENDED TWO(2) PSI INFLATION TEST IAW MM.  DATE OF MFG:  JAN 1988																			 
2001091300189	20010913	00189	GL  	2001	9	13	2001FA0000254    	2	20010716	G	7261	2060405441	TUBE            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	98KR	5885 				45683				MAIN GEARBOX TO OIL COOLER TRANSFER TUBE LEAKING DUE TO CORROSION PITTING.  AREA WHERE TUBE RUNS THRU AREA IS FILLED WIT	H LOOSE FIBERGLASS SOUND PROOFING WHICH HOLDS MOISTURE AND CAUSES CORROSION.  RECOMMEND REMOVING INSULATION FROM THESE A	REAS.				1	G	7	1 	3U	3	T	 	H2SW    	E10CE				 
2001091000427	20010910	00427	NE  	2001	9	10	2001FA0000255    	2	20010725	G	8530	28160	VALVE SPRING    			WTHRLY	620   	620B        	9630605	CE  	PWA   	R985  	R985AN1     	52008	NE  					NR 1 CYLINDER	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	05	2035N	6170 				1591	15642			ENGINE BEGAN BACKFIRING AND POWER DECREASED, AIRCRAFT LANDED AS A RESULT OF RUNNING THROUGH A FENCE.  FOUND NR 1 CYLINDE	R INTAKE VALVE SPRINGS BROKEN.  REPLACED SPRINGS, OPERATION NORMAL.  APPEARED TO BE SMALL RUST PITS IN BREAK AREAS.					1	L	7	1 	3R	3	R	NC	A26WE   	5E1				 
2001091300190	20010913	00190	EA  	2001	9	13	2001FA0000256    	2	20010724	G	7310	601800	GASKET          			PIPER 	PA46  	PA46500TP   	       	SO  	PWA   	PT6   	PT6*        	52043	EA  					ENGINE	LEAKING         	D				O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			EA	25	310JM	47   				4697069				FUEL WAS LEAKING IN FLIGHT AND ON GROUND.  GASKET ON FILTER ASSY.  E6 BYPASS GASKET LEAKING.						1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2001091300191	20010913	00191	CE  	2001	9	13	2001FA0000257    	1	20010802	G	5341	0512122	BLOCK           			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300*      	17022	SO  					WING ATTACH	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	7912T					56612				DISSIMILAR METAL CORROSION ON WING ATTACH POINTS.  BLOCK ARE ATTACHED TO FUSELAGE SPAR ASSEMBLY PN 05121246 WITH (4) AW3	20A BOLTS.  REMOVE FOR INSPECTION.					1	H	7	1 	3O	3	O	 	3A17    	E298				 
2001091300219	20010913	00219	CE  	2001	9	13	2001FA0000258    	1	20010802	G	5341	0411129	BLOCK           			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300*      	17022	SO  					WING ATTACH	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	7912T	2142 				56612				DISSIMILAR METAL CORROSION ON WING ATTACH POINTS.  BLOCKS ARE ATTACHED TO FUSELAGE SPAR ASSEMBLY.  PN 0511162-S WITH (4)	 AN3-21A BOLTS.  REMOVE FOR INSPECTION.					1	H	7	1 	3O	3	O	 	3A17    	E298				 
2001091300222	20010913	00222	CE  	2001	9	13	2001FA0000259    	1	20010703	G	5712		RIB             			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360H1A  	41514	EA  					LT&RT WING	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	80TA	1511 				63280	L2167853A			FOUND LOOSE AND/OR MISSING NAILS AT RIB/FRONT SPAR CONNECTION. 2 RIBS ON RT WING AND 2 RIBS ON LT WING FOUND DAMAGED WHI	LE INSPECTING PER REGMENTS OF AD.					1	H	7	1 	3O	3	O	 	A21CE   	1E10				 
2001091300225	20010913	00225	SO  	2001	9	13	2001FA0000260    	1	20010721	G	2434	LAY6421	BRUSHES         			PIPER 	PA32  	PA32301     	7103207	SO  										ALTERNATOR	WORN            	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	42993					328306025				ALTERNATOR BRUSHES WORN, BATTERY WEAK.						1	L	7	1 	3O			 	A3SO    					 
2001091300226	20010913	00226	EA  	2001	9	13	2001FA0000261    	2	20010613	G	8550	70484	SCREEN          			CESSNA	172   	172L        	2072432	CE  	LYC   	O360  	O360*       	41514	EA  					OIL FILTER	CRUSHED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4250Q	120  				17260150	L3603436A			METAL IN FILTER.  FOUND SCREEN CRUSHED (FROM FACTORY BUILDUP) ALLOWED METAL TO CONTAMINATE ENGINE.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001091300228	20010913	00228	EA  	2001	9	13	2001FA0000262    	2	20010613	G	8520		CRANKCASE       			CESSNA	172   	172L        	2072432	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	4250Q					17260150	L3603436A			TOOLING-MACHINE CHATTER LEFT ROUGH, UNFINISHED AREA FOR CYL BASE O-RING TO SEAT AGAINST ALL FOUR CASE CYLINDER HOLES.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001091300229	20010913	00229	EA  	2001	9	13	2001FA0000263    	2	20010613	G	8530	LW11775	PISTON PIN      			CESSNA	172   	172L        	2072432	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4250Q	120  				17260150	L3603436A			METAL IN FILTER.  PISTON PIN PLUG- EXCESSIVE WEAR.  ONE PIN WORN DOWN .500 INCH.  ALL PLUGS WORN.						1	H	7	1 	3O	3	O	NT	3A12    	E286				 
2001091300230	20010913	00230	SO  	2001	9	13	2001FA0000264    	1	20010807	G	3080	A110240	PROBE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					CARB ICE DETECT	DEFECTIVE       	D			HE8M	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	09	83416	658  				288116160	L1082939A			ICEMAN CARBURETOR, ICEMAN DETECTOR ALERTS EVEN WHEN THERE IS NO ICE.  THERE APPEARS TO BE A MALFUNCTION OF THE PROBE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001091300231	20010913	00231	CE  	2001	9	13	2001FA0000265    	1	20010801	G	5753	052390	ROLLER          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					T/R FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	738DB	5300 				17269886				FLAP ROLLER FOUND NOT TURNING.  REMOVED AND FOUND CRACKS.  THIS IS NOT THE FIRST TIME THIS CONDITION WAS FOUND.  LACK OF	 PROPER MAINTENANCE.  DIRTY AND DRY ROLLER BEARINGS.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001091300232	20010913	00232	SO  	2001	9	13	2001FA0000266    	1	20010807	G	3080	A110240	PROBE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  					CARB ICE DETECT	DEFECTIVE       	D			HE8M	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	47979	318  				287816175	L779939A			CARBURETOR ICE DETECTOR ALERTS EVEN WHEN THERE IS NO ICE.  THERE APPEARS TO BE A MALFUNCTION OF THE PROBE.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001091300234	20010913	00234	SW  	2001	9	13	2001FA0000267    	1	20010618	G	2710	730048503	TUBE            			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O520  	TSIO520*    	17040	SO  					AILERON	CORRODED        	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	389CS	880  				250860				FATAL INTERNAL CORROSION, CAUSED BY TRAPPED MOISTURE INSIDE PUSH PULL CONTROL TUBE FOR AILERON.  CORROSION WAS FOUND DUR	ING ANNUAL INSPECTION.					1	L	7	1 	3O	3	O	 	2A3     	E8CE				 
2001091300236	20010913	00236	SW  	2001	9	13	2001FA0000268    	1	20010820	G	7603	TCM646224A	THROTTLE ARM    			MOONEY	M20   	M20R        	5870225	SW  	CONT  	O550  	IO550*      	 	SO  					COCKPIT	WORN            	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	53WM	322  				290191	679406			THE PRESSED IN BUSHING AT THE END OF THE THROTTLE ARM WAS WORN THRU.  THE BRONZE SECTION. (ATTACHED PHOTO)						1	L	7	1 	3O	3	O	RT	2A3     	E3SO				 
2001091400061	20010914	00061	CE  	2001	9	14	2001FA0000269    	1	20010912	G	3340	4502131REVR1	LANDING LIGHT   			CESSNA	650   	650         	2076802	CE  										EXTERIOR	DEFECTIVE       	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	01	733H					6500210				BOUGHT OVERHAULED LIGHT FROM CESSNA, (OVERHAULED BY GRIMES).  RETRACTABLE LIGHT RETRACTS, EXTENDS, AND LIGHTS UP BUT WIL	L NOT ADJUST TO ALLOW FOR PROPER ALIGNMENT OF THE BEAM OF LIGHT.  THE BEAM OF LIGHT POINTS AT THE GROUND RATHER THAN OUT	 IN FRONT OF THE AIRPLANE.  MAINTENANCE MANUAL INSTRUCTIONS WERE FOLLOWED BUT ADJUSTMENT PROCEDURES HAD NO EFFECT.  THE 	OVERHAUL COULD NOT HAVE BEEN COMPLETED IN A CORRECT MANNER, THIS PART HAS ZERO TIME IN SERVICE.			2	L	7	2 	4F			 	A9NM    					 
2001091400073	20010914	00073	CE  	2001	9	14	2001FA0000270    	1	20010912	G	3340	4502131	MOTOR           			CESSNA	650   	650         	2076802	CE  										LANDING LIGHT	FAILED          	C				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			GL	10	733K					6500222				UNIT RECEIVED AND INSTALLED.  OPERATED UNIT 3 CYCLES AND ON 4 EXTENSION UNIT WOULD NOT EXTEND AND MOTOR SEIZED AND SMELL	ED OF BURNING ELECTRICAL WIRING.   UNIT WAS PURCHASED THRU CESSNA AS AN OVERHAULED PART BY AN OUTSIDE VENDOR.  THE UNIT 	HAS A HISTORY OF EARLY FAILURE AFTER OVERHAUL.  THIS COMPANY HAS HAD FIVE WARRANTY ACTIONS CLAIMED ON THIS PART NUMBER.				2	L	7	2 	4F			 	A9NM    					 
2001091400074	20010914	00074	CE  	2001	9	14	2001FA0000271    	1	20010912	G	3340	4502131	MOTOR           			CESSNA	650   	650         	2076802	CE  										LANDING LIGHT	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			GL	10	733K					6500222				UNIT RECEIVED AND INSTALLED.  WHEN LIGHT IS RETRACTED, UNIT CONTINUES TO RUN WITH A GRINDING NOISE AND MOTOR WILL NOT SH	UT OFF.  UNIT WAS NOT ADJUSTED ON INSTALLATION.  UNIT WAS PURCHASED THRU CESSNA AS AN OVERHAULED PART BY AN OUTSIDE VEND	OR.  THE UNIT HAS A HISTORY OF EARLY FAILURE AFTER OVERHAUL.  THIS COMPANY HAS HAD FIVE WARRANTY ACTIONS CLAIMED ON THIS	 PART NUMBER.			2	L	7	2 	4F			 	A9NM    					 
2001091400076	20010914	00076	CE  	2001	9	14	2001FA0000272    	1	20010912	G	3340	4502131	LANDING LIGHT   			CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					EXTERIOR	DAMAGED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	733H					6500210				RECEIVED THIS PART FROM CESSNA WITH UNDAMAGED PACKING.  THE GROUND LUG WAS BENT, LOOSE AND HAD DAMAGED THREADS.  THIS PA	RT WAS PROPERLY PACKED WITH SPRAYED IN FOAM.  THIS PART WAS DAMAGED PRIOR TO BEING PLACED IN THE BOX.					2	L	7	2 	4F	4	F	 	A9NM    	E6WE				 
2001091400078	20010914	00078	CE  	2001	9	14	2001FA0000273    	1	20010912	G	3340	4502131	MOTOR           			CESSNA	650   	650         	2076802	CE  										LANDING LIGHT	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	01	733H	113  	113  			6500210				RETRACTABLE LIGHT WOULD NOT EXTEND.  IT SEEMS TO ME THAT AN AIRCRAFT PART SHOULD BE CAPABLE OF STAYING IN SERVICE FOR MO	RE THAN 113.7 HOURS.					2	L	7	2 	4F			 	A9NM    					 
2001091700139	20010917	00139	NM  	2001	9	17	2001FA0000274    	1	20010808	G	2760	654494715	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					10268					HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS.  INSTALL HOUSING PN 65-44947-15.  NOTE:  HOUSING IS PN 65-44947-15	 AND IS THE REPLACEMENT TO SOLVE PROBLEMS OF CRACKS NOTED ON PREVIOUS HOUSING DASH NUMBERS PER SL.					2	L	7	2 	4F			RT	A16WE   					 
2001091700140	20010917	00140	NM  	2001	9	17	2001FA0000275    	1	20010808	G	2760	654494710	HOUSING         			BOEING	737   	737*        	       	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		15735								HOUSING IS CRACKED ON THE LOWER SHOULDER NEAR BEARING MOUNT LUG.  INSTALL HOUSING PN 65-44947-15.						2	L	7	2 	4F			RT	A16WE   					 
2001091700142	20010917	00142	NM  	2001	9	17	2001FA0000276    	1	20010808	G	2760	65C268636	HOUSING         	BOEING      		BOEING	737   	737*        	       	NM  										ACTUATOR	CRACKED         	B			IU6D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			30072		WN0009					HOUSING IS CRACKED AND BROKEN AT THREADED AREA. FATIGUE/OVERSTRESSED.						2	L	7	2 	4F			RT	A16WE   					 
2001091700148	20010917	00148	NM  	2001	9	17	2001FA0000277    	1	20010723	G	2730	401606223	HOUSING         			BOEING	727   	727         	UTILSYS	NM  										SEAL PLATE	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING ASSEMBLY IS CORRODED ON THE SEAL PLATE SURFACE, IN THE CHECK VALVE PORTS AND BOLT HOLES.  HOUSING ASSEMBLY IS MA	DE FROM MAGNESIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS.					2	L	7	3 	4J			RT	A3WE    					 
2001091700149	20010917	00149	NM  	2001	9	17	2001FA0000278    	1	20010716	G	2730	401606223	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										SEAL PLATE	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1433D					HOUSING ASSEMBLY IS CORRODED ON THE SEAL PLATE SURFACE, IN THE CHECK VALVE PORTS AND BOLT HOLES.  HOUSING ASSEMBLY IS MA	DE FROM MAGNESIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS.					2	L	7	3 	4F			RT	A3WE    					 
2001091700150	20010917	00150	NM  	2001	9	17	2001FA0000279    	1	20010716	G	2760	654494710	HOUSING         	BOEING      		BOEING	727   	727         	UTILSYS	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		41454			0970					HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS.  INSTALL HOUSING PN 65-44947-15.						2	L	7	3 	4J			RT	A3WE    					 
2001091700152	20010917	00152	NM  	2001	9	17	2001FA0000280    	1	20010716	G	2760	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		50886			0893					HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS.  INSTALL HOUSING PN 65-44947-15.						2	L	7	2 	4F			RT	A16WE   					 
2001091700153	20010917	00153	NM  	2001	9	17	2001FA0000281    	1	20010717	G	3230	65179547	HOUSING         	BOEING      		BOEING	727   	727         	UTILSYS	NM  										ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					RC707					THE HOUSING HAD A CRACK IN THE CENTER OF THE BARREL.						2	L	7	3 	4J			RT	A3WE    					 
2001091700154	20010917	00154	CE  	2001	9	17	2001FA0000282    	1	20010811	G	3233	12416195F	ACTUATOR        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520*      	17032	SO  					MLG	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	8137L					21060624				LEFT MAIN GEAR ACTUATOR CRACKED, RESULTING IN THE LOSS OF HYDRAULIC FLUID.  AIRCRAFT MADE A GEAR UP LANDING, AIRCRAFT HA	S SUBSTANTIAL DAMAGE TO HORIZONTAL STABILIZER AND ELEVATOR.					1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001091700110	20010917	00110	SO  	2001	9	17	2001FA0000286    	2	20010825	G	7414	4301	MAGNETO         			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	INOPERATIVE     	C				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	99	2750S					15066650	54877A			INSTALLED NEW LEFT AND RIGHT SIDE SLICK (UNISON) MAGNETOS AND IGNITION HARNESS. TEST RUN OK.  ON FIRST FLIGHT AFTER 15 M	IN. ENGINE POWER LOSS OCCURED. AFTER LANDING FOUND LEFT MAG INOP.  REMOVED MAG AND FOUND THAT COIL INSULATION HAD BURNED	 THROUGH AND HIGH VOLTAGE WAS ARCING TO CASE OF MAG THROUGH COIL INSULATION.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001091700112	20010917	00112	NE  	2001	9	17	2001FA0000287    	2	20010807	G	8500		ENGINE          			WSK   	M18   	M18DROMADER 	9810102	EU  	WSK   	PZL   	PZLM18      	67203	NE  	WSK	US132	US132000A   	NE  	NACELLE	MALFUNCTIONED   	G				K				NONE                    				O			OTHER                     			AG	AGRICULTURE    	1			SW	11	4206B					1Z00507				FLYING IN CRUISE WHEN BUTTERFLY ON INTAKE STARTED FLUCUATING. PULLED UP AND REDUCED POWER. APPROXIMATELY 10 SECONDS LATE	R LOST POWER. ACFT. HIT LOW LEVEE SKIDDED ACROSS FIELD AND HIT SECOND LEVEE. UPON STRIKING SECOND LEVEE ACFT. ROLLED OVE	R ON ITS NOSE AND SKIDDED TO A REST UPSIDE DOWN IN A RICE FIELD.				1	L	7	1 	3O	4	R	 	A47EU   	E10NE	5	C	P4NE	 
2001091700120	20010917	00120	SO  	2001	9	17	2001FA0000292    	1	20010905	G	3220	AN3105MS24665	COTTER PIN      			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG	MISSING         	B				A				UNSCHED LANDING         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		LD	LANDING        	1			GL	21	279ND	599  				2844034				DURING A TRAINING FLIGHT, UPON GEAR RETRACTION THE CFI HEARD A THUMP FROM THE NOSE AREA.THE GEAR UNSAFE LIGHT DIDNT EXTI	NGUISH. MLG EXTEND WAS ATTEMPTED , DIDNT RECEIVE A NLG DOWN AND LOCKED INDICATION. RETRACTION AND EMERGENCY EXTEND WAS A	TTEMPTED. PERFORMED A FLYBY AND WERE INFORMED THE NLG WAS TRAILING. UPON LANDING THE NLG COLAPSED  UPON INSPECT BY MAINT	, IT WAS FOUND COTTERPINS WERE MISSING FROM THE NLG SPRING ARM ASSY PIVOT BOLT. ALLOWED THE BOLT TO BACK OUT OF POSITION	 ALLOW RELEIVING THE TENSION ON THE ARM NOT ALLOWING TO TRAVEL TO FULL DOWN AND LOCK. INSPECTION OF THE BOLT SHOWED NO E	VIDENCE OF A BROKEN COTTER PIN OR DAMAGE TO THE THREADS OF THE BOLT. 3 WASHERS REMAINED ON THE THREAD SIDE OF THE BOLT.	1	L	7	1 	3O			 	2A13    					 
2001091700133	20010917	00133	NM  	2001	9	17	2001FA0000294    	1	20010907	G	6700	500N711311	CONTROL ROD     			DOUG  	600N  	600N        	3027377	NM  										NOTAR FAN	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	957SD					RNO11				DURING REMOVAL OF THE AFT FAN (NOTAR) CONTROL ROD P/N 500N7113-11 WE FOUND SOME CONTACT DAMAGE. IT APPEARS THIS ROD IS M	AKING CONTACT WITH THE FAN GEARBOX OUTPUT GEARSHAFT I.D. 					1	G	7	1 	3U			NC	H3WE    					 
2001091700155	20010917	00155	GL  	2001	9	17	2001FA0000295    	1	20010726	G	7100		PISTON          			AMTR  	MONG  	MONG        	0565379	GL  										ENGINE	BURNED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	426RT	60   				214				NR 1 PISTON ON 2 CYCLE EXPERIMENTAL POWER PLANT BURNED THRU RESULTING IN LOSS OF POWER, RESULTING IN CRASH.  DTW 2001 05	6- C-NR 1 01LA0155.					1	Q	7	1 	3O			NC	EXPA1Q71					 
2001091700135	20010917	00135	NM  	2001	9	17	2001FA0000296    	1	20010907	G	6700	500N711311	CONTROL ROD     			DOUG  	600N  	600N        	3027377	NM  										NOTAR FAN	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	958SD					RNO18				DURING REMOVAL OF THE AFT FAN (NOTOR) CONTROL ROD P/N 500N7113-11 WE FOUND SOME CONTACT DAMAGE. IT APPEARS THIS ROD IS M	AKING LIGHT CONTACT WITH THE FAN GEARBOX OUTPUT GEARSHAFT I.D. AND THE FAN SUPPORT SHAFT I.D.					1	G	7	1 	3U			NC	H3WE    					 
2001091700156	20010917	00156	NM  	2001	9	17	2001FA0000297    	1	20010829	G	6230	A4801	BOOT            	ROBSIN      		ROBSIN	R22   	R22BETAII   	7640110	NM  	LYC   	O360  	VO360*      	41514	EA  					SWASHPLATE	SPLIT           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	2223P	153  			3573	2962				FOUND SWASHPLATE BOOT SPLIT OPEN AT THE CENTER FOLD.  SPLIT WAS APPROX 4 TO 6 INCHES IN LENGTH.						1	G	7	1 	3O	3	O	 	H10WE   	1E1				 
2001091800001	20010918	00001	SO  	2001	9	18	2001FA0000298    	1	20010626	G	2720	62701008	CONTROL CABLE   			PIPER 	PA32  	PA32301T    	7103209	SO  										RUDDER	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	8108W					328024002				DURING ANNUAL INSPECTION, FOUND LEFT AFT RUDDER CABLE TURNBUCKLE THREADED SWAGED END BROKEN AT THREADED END THAT SCREWS 	INTO TURNBUCKLE BARREL.  SAFETY WIRE WAS ONLY THING THAT PREVENTED COMPLETE LOSS OF RUDDER CONTROL.					1	L	7	1 	3O			 	A3SO    					 
2001091900251	20010919	00251	GL  	2001	9	19	2001FA0000300    	2	20010623	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					NACELLE	MALFUNCTIONED   	C				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			SW	99	34698					4324				DEPARTING THE AIRPORT, THE ENGINE FLAMED OUT OR SURGED.  THE ENGINE WAS RUN ON A TEST CELL. TEST CELL SHOWED:  1)A CYCLI	NG ANTI-ICE VALVE SOLENOID.  2)  A RICH FUEL FLOW.  3) A WARPED OUTER COMBUSTION CHAMBER.    THIS TOGETHER, COULD CAUSE 	A SURGE.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001091900253	20010919	00253	GL  	2001	9	19	2001FA0000301    	2	20010727	G	7320		SPRING          	BENDIX      		BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					CONTROL ARM	DEFECTIVE       	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3209G		1694 		330958	51567	895634			THE FUEL CONTROL OVERCENTER SPRING IS SO STRONG THAT IS WILL RUN THE RPM AND TOUQUE UP UNCOMMANDED.  THIS TIME IT CAUSED	 AN OVER TORQUE OF 115 PERCENT FOR 1 SECOND.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091900003	20010919	00003	SO  	2001	9	19	2001FA0000302    	1	20010702	G	7160	71713	TUBE            			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	LO360E1A6   	41514	EA  					NR 3 CYLINDER	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9290P	1508 	99   			4496019	RL48371A			FOUND NR 3 INTAKE TUBE LEAKING AT 100 HOUR INSPECTION.  REMOVED TUBE AND FOUND A CRACK AT FLANGE CRACK APPEARS TO HAVE B	EEN REPAIRED BUT WELD DOESNT COVER THE WHOLE CRACK.					1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001091900001	20010919	00001	EA  	2001	9	19	2001FA0000305    	2	20010918	G	8510	LW13792	SEAL            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	ENGINE	FAILED          	C				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	7331Y		80   			30292	L76455			DURING A CROSS-COUNTRY FLIGHT BETWEEN CNO AND SPF (31 AUG 01 THRU 3 SEP 01), OIL STREAKS FROM THE NOSE BOWLS OF BOTH ENG	INES INCREASED WITH EACH LEG.  UPON RETURN TO CNO, COWLS AND PROPELLERS HAVE BEEN REMOVED.  DURING INSPECTION OF ENGINE 	NOSE SEALS, BOTH SEALS HAVE BEEN "BLOWN OUT" OF THE CASE, AND ARE HANGING FROM THE CRANKSHAFT BETWEEN THE CASE AND PROP 	FLANGE. BOTH ENGINES HAVE 80 HOURS SINCE OVERHAUL BY LYCOMING. ENGINE OIL ANALYSIS WILL BE PERFORMED AND FILTERS CUT OPE	N FOR INSPECTION.		1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2001091900002	20010919	00002	CE  	2001	9	19	2001FA0000307    	1	20010918	G	5280		BRACKET         			BEECH 	36    	A36         	1151604	CE  										MLG DOOR	CRACKED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	373DR					E3373				WHILE PERFORMING ANNUAL INSPECTION A CRACKED BRACKET WAS FOUND AT THE REAR RIGHT INBOARD GEAR DOOR HINGE.  UPON REMOVING	 THE WING-TO-FUSELAGE CLOSEOUT PANEL IT WAS DISCOVERED THAT THE FORWARD TWO INBOARD GEAR DOOR HINGE BRACKETS WERE ALSO C	RACKED.  CAUSE UNKNOWN.				1	L	7	1 	3O			 	3A15    					 
2001092000003	20010920	00003	EA  	2001	9	20	2001FA0000309    	2	20010821	G	7313		INJECTOR        			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	MALFUNCTIONED   	C				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	17	172RC					17280204				ENGINE FAILED TO DEVELOP FULL POWER AFTER LONG POWER OFF DECENT AT HIGH DENSITY ALTITUDE CONDITIONS.  CORRECTIVE ACTIONS	 TAKEN:  FUEL INJECTOR SERVO REPAIRED BY CRS/NE2R  WO R01-042240.  FLOW DIVIDER MODIFIED IAW SI.  C/W SI AND SB.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001092000006	20010920	00006	SO  	2001	9	20	2001FA0000310    	1	20010904	G	2922	53E19600	VALVE           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	TIO540*     	41532	EA  					THERMAL BYPASS	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4087R	1087 				3240405				NUT CAME OFF THE THERMOSTATIC BYPASS VALVE AND FELL INTO THE OIL SUMP.   CUSTOMER COMPLAINT, HIGH OIL TEMPERATURE.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001092000007	20010920	00007	CE  	2001	9	20	2001FA0000311    	1	20010822	G	8011	S1577A1	CONTACTOR       			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	4373R	138  				R18200595				CONTACTOR FAILED/ CLOSED CAUSING STARTER TO BURN OUT.  THIS IS SECOND FAILURE OF A NEW CONTACTOR IN LESS THAN 140 HOURS.	  (ONE STARTER CONTACTOR, ONE MASTER CONTACTOR)					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001092000012	20010920	00012	EU  	2001	9	20	2001FA0000312    	1	20010919	G	7160	430110217	MODULATOR       			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101600A  	41560	NE  					AIRFLOW	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	7059N					7154				WHILE TROUBLESHOOTING ENGINE FOR SURGING PROBLEM.  AIRFLOW MODULATOR WAS CHANGED.  FILTER ELBOW HAS TO BE TRANSFERED TO 	NEW MODULATOR.  FOUND FILTER SCREEN TO BE LOOSE INSIDE ELBOW AT THIS TIME.  BROKEN FILTER HAD NO EFFECT ON THIS SURGING 	PROBLEM.  MUST INSPECT FILTER ELBOW WHEN CHANGING AIRFLOW MODULATOR.				1	G	7	2 	3U	3	U	NC	H13EU   	E5NE				 
2001092400007	20010924	00007	EU  	2001	9	24	2001FA0000313    	1	20010530	G	3510	A1B0BR14	PRESSURE SWITCH 			STBROS	SD3   	SD330       	8100602	EU  										OXYGEN SYSTEM	LEAKING         	C			U4FM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	173Z	1    				SH3116				WHILE SERVICING THE OXYGEN SYSTEM, THE HIGH PRESSURE TRANSDUCER SHAFT SEAL BLEW OUT.  THIS PRESSURE SWITCH IS PART OF AN	 STC MODIFICATION TO CERTIFY THE AIRCRAFT AS A SD3-30, .  THIS IS SECOND OCCURANCE OF THIS FAILURE.  THE FIRST FAILURE W	AS ASSUMED TO BE THAT THE WRONG PN, LOW PRESSURE TRANSDUCER HAD BEEN INSTALLED.  UPON REPLACEMENT OF THE SECOND UNIT TAE	 MAXIMUM PRESSURE OF 750 PSIG IS FAR BELOW THE 1800 PSIG SYSTEM PRESSURE.			2	H	7	2 	4T			 	A41EU   					 
2001092100002	20010921	00002	GL  	2001	9	21	2001FA0000314    	3	20010805	G	6110	HCE5N3	PROPELLER       			PIAGIO	P180  	P180        	6960204	EU  	PWA   	PT6   	PT6*        	52043	EA  	HARTZL	HCE5N	HCE5N3      	GL  	NR 2	DAMAGED         	C				O				OTHER                   				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			WP	11	705PA	347  	127  			1014		HF42		AIRCRAFT LANDED RENO, PILOTS NOTICED DIFFICULTY GETTING PROP INTO BETA AND SLIGHT VIBRATION DURING ROLLOUT.  AT HANGER, 	PILOTS NOTICED LOWER NG ON NR 1 ENGINE ADN ON SHUTDOWN.  NR 1 PROP STAYED IN A FLIGHT PITCH ANGLE WHILE NR 2 PROP WENT T	O FEATHER PER NORMAL OPS.   ON TEARDOWN AT PROP SHOP, NR 1 PROP WAS FOUND TO HAVE INTERNAL DAMAGE.				1	H	7	2 	3O	3	T	RT	A59EU   	E2NE	5	C	PZONE	 
2001092000027	20010920	00027	GL  	2001	9	20	2001FA0000315    	2	20010801	G	7230	6890550	SCROLL          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	108FH	4205 				2770	CAE831748			WHILE TROUBLESHOOTING CAUSE OF HIGH TOT, AIR LEAK WAS DISCOVERED AROUND UPPER PORTION OF COMPRESSOR.  FURTHER INVESTIGAT	ION REVEALED A CRACK APPROXIMATELY 3.810 INCHES LONG IN AREA BETWEEN CUSTOMER BLEED AIR PORT AND FORWARD OF DIFFUSER.  C	RACK DID NOT ORIGINATE AROUND WELD.  APPLYING HAND PRESSURE UPON BLEED AIR PORT, THE SCROLL MATERIAL CAN BE SEEN LIFTING	 UP.   A COMBINATION OF VIBRATORY STRESS AND METAL FATIGUE ARE FACTORS.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001092000002	20010920	00002	CE  	2001	9	20	2001FA0000316    	1	20010919	G	7120	045100336	MOUNT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	GROOVED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5362M	3357 	1003 			15284562	L2084215	R776391		1. DURING A ROUTINE INSPECTION, TWO ENGINE MOUNT DIAGONALS WERE FOUND TO HAVE WORN AREAS ON THEM CAUSED BY THE BATTERY T	RAY FLEXING DOWN AGAINST THE MOUNT AND FROM A STAINLESS STEEL TAG ON THE OIL PRESSURE LINE.2. THE CLAMP THAT SUPPORTS TH	E BATTERY TRAY ON THE MOUNT SHOULD BE CHECKED ON A REGULAR BASIS TO MAKE SURE IT IS TIGHT AND WILL NOT ALLOW ANY CONTACT	 WITH THE MOUNT.3. ALL LINES ADJECENT TO THE MOUNT SHOULD BE CHECKED TO ENSURE THAT NO TAGS WILL CAUSE ANY CONTACT WITH 	THE MOUNT.		1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001092100003	20010921	00003	GL  	2001	9	21	2001FA0000317    	3	20010814	G	6110	B4459	PIN             	MCAULY      		CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PROPELLER	CRACKED         	C			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	403GC				733162	402B0305		733162		PROPELLER SHOWS RELEVENT INDICATION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001092100004	20010921	00004	EU  	2001	9	21	2001FA0000318    	1	20010830	G	5753	T700A5755060000	CARRIAGE        			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6*        	52043	EA  					LEFT FLAB IB	WORN            	C			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5HT	1950 				9				AFTER REMOVAL OF LEFT FLAP, DISCOVERED LEFT INBOARD CARRIAGE, PART LISTED ABOVE AND ACTUATOR NUT COVER,  PN T700A2750029	000, WORN FROM CONTACT WITH ACTUATOR NUT.  WEAR APPEARS TO BE FROM WORN BUSHINGS IN CARRIAGE AND ACTUATOR NUT COVER AS W	ELL AS WEAR IN LOCATOR PINS IN ACTUATOR NUT.  FOUND SAME WEAR IN RIGHT INBOARD FLAP CARRIAGE, PN T700A5755060001 AND ACT	UATOR NUT COVER COVER PN T700A2755063000 AND ACTUATOR NUT COVER PN T700A2750029000.			1	L	7	1 	3T	3	T	RT	A60EU   	E2NE				 
2001092100005	20010921	00005	SO  	2001	9	21	2001FA0000319    	2	20010904	G	7414		GEAR            			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					MAGNETO	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	54GV	427  				20700447	818885R			DURING ENGINE RUN UP TO ANALYZE A FUEL FLOW PROBLEM, IT WAS DISCOVERED THAT THE RIGHT MAGNETO WAS DEAD.  SUBSEQUENT INVE	STIGATION REVEALED THAT THE RIGHT MAGNETO WAS INTERNALLY LOCKED AND FOUND THAT THE MAGNETO DRIVE GEAR AND THE ACCESSORY 	DRIVE GEAR WAS UNSERVICEABLE.  MAGNETO BEING SENT TO MFG FOR EVALUATION.				1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001092100006	20010921	00006	CE  	2001	9	21	2001FA0000320    	1	20010820	G	3510	510010951	LINE            			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6*        	52043	EA  					OXYGEN SYSTEM	DETERIORATED    	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	900MS	5390 				4250079				LEFT SIDE WALL WAS REMOVED TO INSTALL RADIO EQUIPMENT.  THE VERTICAL DUCT FOR AIR TO OVERHEAD WEMAC SHOWED DEFINITE SIGN	S OF BURNING AND SEVERE DETERIORATION.  UPON FURTHER EXAMINATION, THE OXYGEN LINE CROSSING DUCT HAD SEVERE CORROSION WHE	RE CONTACT BETWEEN THE LINE AND DUCT HAD OCCURRED, AND HAD 2 HOLES IN THE LINE.  WHEN THE OXYGEN WAS TURNED ON, OXYGEN W	AS SPRAYED ON DUCT AND BEHIND SIDEWALL OF AIRCRAFT.  MANUFACTURED NEW LINE TO REPLACE CORRODED LINE.  INSTALLED NEW DUCT	.  SPIRAL WRAPPED OXYGEN LINE WHERE CONTACT WITH DUCT OCCURS.		1	L	7	2 	3T	3	T	RT	A7CE    	E2NE				 
2001092400008	20010924	00008	CE  	2001	9	24	2001FA0000322    	1	20010605	G	2421	99105921	ALTERNATOR      			CESSNA	206   	U206G       	2073356	CE  										ENGINE	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	02	9933Z	187  				U20606754				OPERATOR REPORTED EXCESSIVE NOISE IN HEADSET FROM RADIOS.  TROUBLESHOOTING FOUND NOISE DISAPPEARED WITH ALTERNATOR OFF L	INE.  FURTHER INVESTIGATION FOUND MAGNETIC COMPASS DEVIATION OF 20 DEGREES WITH ALTERNATOR ON LINE.  ELECTRICAL SYSTEM W	IRING GROUNDS,  BONDING AND SHIELDING CHECKED.  IN LINE NOISE FILTERS HAD NO AFFECT ON NOISE EMISSION.  INSTALLED THREE 	ALTERNATORS, SN:  A-160134, A-160136, AND A-160130 WITH NO CHANGES IN NOISE OR COMPASS DEVIATION.  INSTALLED ALTERNATIVE	 MFG/ELECTRO SYSTEMS ALTERNATOR, PART NUMBER E3FF10300AA, WHICH ELIMINATED RADIO NOISE AND MAGNETIC COMPASS DEVIATION.		1	H	7	1 	3O			 	A4CE    					 
2001092400009	20010924	00009	CE  	2001	9	24	2001FA0000323    	1	20010918	G	2752	505211516	PISTON          	BEECH       		BEECH 	B300  	B300        	1159232	CE  										FLAP ACTUATOR	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	988ME	4611 			935A91	FL77				RIGHT OUTBOARD FLAP ACTUATOR CRACKED AT BASE OF PISTON WHERE THE END PLUG IS ATTACHED.  THE CRACK WAS 1.5 INCHES LONG AN	D RESULTED IN THE LOSS OF THE LUBRICATING OIL FROM OUT OF THE PISTON AND SCREW ASSEMBLY.  THE LOSS OF OIL WAS THE FIRST 	INDICATION OF A PROBLEM, AND IT WAS WHILE INVESTIGATING THE OIL LEAK THAT THE CRACK WAS DISCOVERED.THIS CRACK COULD RESU	LT IN A SIGNIFICANT LOSS OF STRUCTURAL STRENGTH OF THE ACTUATOR WHICH COULD RESULT IN THE STRUCTURAL FAILURE OF THE ACTU	ATOR ASSEMBLY.		2	L	7	2 	4T			RT	A24CE   					 
2001092400002	20010924	00002	SW  	2001	9	24	2001FA0000324    	1	20010827	G	5313	17031725	STRINGER        			GULSTM	690TP 	690D        	3970405	SW  										LT WING INBD	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	120EK	5552 				15026				WHILE REPLACING FUEL BAG, STRINGER 6A, LEFT WING INBOARD WAS FOUND TO BE AFFECTED BY GENERAL SURFACE AND PITTING CORROSI	ON.  THE CORROSION ON THE STRINGER WAS LOCATED BETWEEN WING STATION 24 AND 39, AND AFFECTED THE STRINGER UP TO AN APPROX	IMATE DEPTH OF .08 INCHES.  THE CORROSION WAS POSSIBLY CAUSED BY WATER BEING TRAPPED BETWEEN THE STRINGER AND THE FUEL B	AGS.  WATER MAY HAVE ENTERED THROUGH WING ACCESS PANELS LOCATED ABOVE FUEL BAGS.  THE ADDITION OF DRAIN HOLES IN THIS AR	EA, AND A POSITIVE SEAL ON UPPER WING INSPECTION PANELS MIGHT PREVENT THIS CORROSION FROM OCCURING.  (M)		1	H	7	2 	3T			 	2A4     					 
2001092400003	20010924	00003		2001	9	24	2001FA0000325    	4	20010824	G	6113	055032110	SPINNER         			CESSNA	172   	172S        	2072439	CE  						MCAULY	1A170	1A170E      	GL  	PROPELLER	DAMAGED         	A				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	435ER					172S8652				NUTPLATE BROKEN OFF.  CHANGED NUMEROUS SPINNERS AND BACK PLATES BECAUSE THE PRE-DRILLED HOLES DO NOT LINE UP WITH THE NU	TPLATES ON THE SPINNER BACK PLATE.  THIS IS A COMMON PROBLEM WITH THIS A/C MODEL R/S.  (M)					1	H	7	1 	3O			NT	3A12    		5	N	P857	 
2001092400004	20010924	00004	CE  	2001	9	24	2001FA0000326    	1	20010811	G	5610	303	WINDSHIELD      			CESSNA	150   	152         	2071835	CE  										COCKPIT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	714TW					15279429				WINDSHIELD CRACKED DIRECTLY ABOVE COMPASS BLOCK AND SMALL SECTION 12 INCHES BY 6 INCHES WITH COMPASS ATTACHED.  SUSPECT 	CRACK DEVELOPED ABOVE COMPASS BLOCK, PERHAPS BY FUELER LEANING ON WINDSHIELD, AND THEN CONTINUED TO DEVELOP CRACK UNTIL 	SECTION LOST INTERGRITY AND FELL INWARD INTO CABIN.  (M)				1	H	7	1 	3O			NT	3A19    					 
2001092400005	20010924	00005	GL  	2001	9	24	2001FA0000327    	1	20010829	G	7120		MOUNT           			CIRRUS	SR    	SR20        	05628AJ	GL  										ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	168CD	144  				1079				MADE A HARD LANDING, THE AIRCRAFT HAD PORPOISED HITTING HARD ON 2ND OSC.  UPON INSPECTION IT WAS FOUND THAT THE LDG SHOC	K PUCKS WERE DEFORMED AND THE REBOUND PUCKS, ONE OF WHICH WAS MISSING, WITH THE MOUNT WASHERS BENT.  ALSO, THE SHOCK PUC	K MOUNT PLATE STUD'S WERE BENT, CLOSER INSPECTION REVEALED LIND SEED OIL AT THE WEB CLUSTER ADJACENT TO THE SHOCK MOUNT 	PLATE OF THE DIAGONAL SUPPORT TUBE, SHOCK MT SUPPORT TUBE AND A STIFFENER TUBE A DYE-PIN INSPECTION REVEALED A .5 INCH C	RACK THROUGH THE WELD AT THE CLUSTER.  (M)		1	H	7	1 	3O			NC	A00009CH					 
2001092400006	20010924	00006	EA  	2001	9	24	2001FA0000328    	2	20010715	G	8500		BLOCK           			BEECH 	23    	B23         	1151240	CE  	LYC   	O360  	O360*       	41514	EA  					ENGINE	CRACKED         	G				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			SW	99	9815S					M1799	2100436A			AIRCRAFT WS ON FINAL APPROACH TO OCF, ENGINE WAS NOISY AND QUIT.  AIRCRAFT MADE EMERGENCY LANDING ON HORSE RACE TRACK.  	OPENED COWLING, FOUND 3 INCH CRACK AFT, LEFT, TOPSIDE OF ENGINE BLOCK.  ENGINE HAS 2776 HOURS SINCE OVERHAUL.  15 DAYS O	UT OF ANNUAL INSPECTION.  (M)				1	L	7	1 	3O	3	O	RT	A1CE    	E286				 
2001092500002	20010925	00002	CE  	2001	9	25	2001FA0000329    	1	20010801	G	7603	AN54A	BOLT            			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE CONTROL	BACKED OUT      	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	424RA	2393 				BB1583				AN5-4A BOLT IN BOTTOM PIVOT POINT ROD ATTACHMENT BACKED OUT CAUSING LOSS OF ENGINE CONTROL.  AN936B516 LOCK WASHER WAS P	RESENT.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001092500003	20010925	00003	GL  	2001	9	25	2001FA0000330    	2	20010817	G	7230	230397911	SPLINE ADAPTER  			AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR ASSY	FAILED          	C			LN3R	O				OTHER                   				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	01	55NW	15348	1814 			7267	CAE834892			ENGINE SHUTDOWN DURING FLIGHT DUE TO FLAMEOUT.  CAUSE: FAILURE OF SPLINED ADAPTER IN COMPRESSOR ASSEMBLY.						1	G	7	2 	3U	3	U	 	H7EU    	E4CE				 
2001092500004	20010925	00004	SO  	2001	9	25	2001FA0000331    	1	20010806	G	3230	PA402427	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					DRAGLINK	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	63887	9000 				277854032				BOLT SHEARED IN HALF, ALLOWING RIGHT MAIN LANDING GEAR TO COLLAPSE ON LANDING ROLL.  BOLT SUSPECTED TO BE ORIGINAL.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001092500109	20010925	00109		2001	9	25	2001FA0000332    	4	20010924	G	2565	1061323418	SLIDE           			BOEING	737   	737         	UTILSYS	NM  										SERVICE DOOR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15						23812				LT AFT SERVICE DOOR SLIDE FAILED TO FULLY INFLATE, WHILE COMPLYING WITH BOEING TASK CARD B25-61-35-C, OPERATIONAL CHECK 	OF ESCAPE SLIDE SYSTEMS.  BOTTLE PSI WAS IN RED RANGE PRIOR TO TEST.					2	L	7	2 	4F			RT	A16WE   					 
2001092500001	20010925	00001	CE  	2001	9	25	2001FA0000333    	1	20010902	G	3244	505C66	TIRE            			BEECH 	58    	58P         	1152744	CE  										MLG	FAILED          	G				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	15	582TA	1208 	905  			TJ191				NOSE TIRE FAILED AND NOSE GEAR COLLAPSED.						1	L	7	2 	3O			 	A23CE   					 
2001100100015	20011001	00015	CE  	2001	10	1	2001FA0000337    	1	20010813	G	3211	24900022	BUSHING         			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					GEAR ACTUATOR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	5199U	137  				172RG0279	L1358536A			BUSHING ,  INSTALLED ON MAIN GEAR ACTUATOR AS PART OF AD, HAS WORKED ITS WAY OUT OF HOUSING.  PART HAS 137 HOURS SINCE I	NSTALLED.  THIS IS SECOND BUSHING FOUND BAD WITH FEW HOURS.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001100100016	20011001	00016	CE  	2001	10	1	2001FA0000338    	1	20010730	G	3230	244110010	PIVOT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	VO360*      	41514	EA  					RT MLG	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	9656B	921  				172RG0949				RIGHT MAIN LANDING GEAR PIVOT PN 24411001-10 BROKEN, SHEARING OFF GEAR FROM PIVOT.  THIS PART WAS INSTALLED ON  01/20/20	00, BEING THE NEW IMPROVED PIVOT.  ON 05/28/2001 PIVOT WAS INSPECTED AND DYE PENTRANT FOR CRACKS PER AD AND SB.  SERVICE	 KIT 172-151 INSTALLED.  113 HOURS LATER ON 07/27/2001 PIVOT BROKE.  AIRCRAFT LANDED WITH NO DAMAGE.				1	H	7	1 	3O	3	O	 	3A17    	1E1				 
2001100200007	20011002	00007		2001	10	2	2001FA0000339    	4	20010712	G	2562		LEAD            			BBAVIA	7     	7EC         	2110120	SW  	CONT  	C90   	C90*        	17009	SO  					ELT BATTERY	SEVERED         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4392C					7EC421				NEGATIVE LEAD FROM LOWER BATTERY COMPARTMENT TO TRANSMITTER WAS SEVERED DUE TO CORROSION.  LOWER AND UPPER BATTERY.  CON	TACTS WERE CORRODED AND PLATING HAD FLAKED OFF.  ONE OF THE EIGHT DURACELL BATTERIES WAS DEAD BUT NO CORROSION ON IT AND	 HAD NO BATTERY LEAKAGE.  THIS FINDING WAS MADE DURING THE ANNUAL INSPECTION ON THIS AIRCRAFT.  THE BATTERIES WERE ALL W	ITHIN THEIR DUE DATES.			1	H	7	1 	3O	3	O	 	A759    	E252				 
2001100100017	20011001	00017	CE  	2001	10	1	2001FA0000340    	1	20010801	G	2752	505212224	ACTUATOR        			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6*        	52043	EA  					RT TE FLAPS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	711HA	1818 				BB1417				NORMAL FLIGHT OPERATION THE CENTER SHAFT OF THE ACTUATOR CRACKED THE ENTIRE LENGTH CAUSING FLAP BOUNCING SIMILAR TO BAD 	ROLLERS.  RECOMMEND INSPECTING TOP AND BOTTOM OF ACTUATOR CENTER SHAFT DURING REGULAR PHASE INSPECTIONS.					1	L	7	2 	4T	3	T	 	A24CE   	E2NE				 
2001100100018	20011001	00018	CE  	2001	10	1	2001FA0000341    	1	20010822	G	7921	537312	PLATE           			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470D      	17026	SO  					OIL COOLER	WRONG PART      	G				O				OTHER                   				W	J		INADEQUATE Q C            	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	09	2209F					310L0009				ENGINE HAD LOST OIL PRESSURE DURING FLIGHT.  AFTER A SAFE LANDING IT WAS DETERMINED THAT THE OIL HAD LEAKED OUT FROM THE	 BETWEEN THE OIL COOLER PLATE AND THE ENGINE.  THE OIL COOLER PLATE ATTACHMENT NUTS WERE FOUND TO BE LOOSE.  THE GASKET 	BETWEEN THE PLATE AND THE ENGINE WAS THE INCORRECT ONE.  CONSULT THE APPROPRIATE PARTS BOOK AND INSTALL THE CORRECT PART	.  PROPERLY TORQUE ALL FASTENERS TO THE CORRECT SPECIFICATIONS.			1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2001100100019	20011001	00019	CE  	2001	10	1	2001FA0000342    	1	20010806	G	2150	73838430	ACM             			CESSNA	750   	750         	2076810	CE  	ALLSN 	AE3007	AE3007C     	 	GL  					CABIN COOLING	SEIZED          	G				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	11	750EC	1113 				7500007				FORWARD AIR CYCLE MACHINE SEIZED DURING ROUTINE USAGE.  PROBABLE CAUSE IS BEARING FAILURE.  UNIT WAS OPERATED NORMALLY, 	AND WAS SERVICED AS SCHEDULED.					2	L	7	2 	4J	4	F	RT	T00007WI	TE6CH				 
2001100100020	20011001	00020	CE  	2001	10	1	2001FA0000343    	1	20010927	G	2910	6000100369	LINE            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					HYD SYSTEM	FAILED          	G				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	01	991DB	661  				177				LEFT HYDRAULIC PRESSURE LINE FROM ENGINE TO HYDRAULIC MANIFOLD BROKE AT FLARE.  3 MILE FINAL EMPTIED HYDRAULIC RES INTO 	EQUIPMENT BAY/BAGGAGE COMPT.  LINE REMOVED AND SENT TO MFG FOR EVALUATION.  NOTE:  RIGHT HYDRAULIC PRESSURE LINE REMOVED	 AND REPLACED AS WELL AND SENT IN FOR EVALUATION.				2	L	7	2 	4F	4	F	RT	A10CE   	E35NE				 
2001100200008	20011002	00008	SO  	2001	10	2	2001FA0000344    	1	20010815	G	2121	313B57	ARMATURE        	DYNAMICAIR  		PIPER 	PA31  	PA31P350    	7103111	SO  										FAN	WRONG PART      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	CFZIC				702					FAN RETURNED TO MFG FOR OVERHAUL, THE FAN WAS DISASSEMBLED AND FOUND TO HAVE AN ARMATURE OF NOT MFG DESIGN.  INSTALLED T	HE ARMATURE LAMINATIONS ARE NOT COATED, ALLOWING THE ARMATURE TO RUST.  THE WINDINGS HAVE EXCESSIVE COATING WHICH CAUSED	 THE ARMATURE TO RUB THE BRUSH HOLDER.  THIS WAS COMPENSATED BY SOMEONE REPOSITIONING THE BRUSH HOLDER FURTHER AWAY FROM	 THE COMMUTATOR WHICH CAUSED AN IN ACCURATE BRUSH LOAD.			1	L	7	2 	3O			RT	A8EA    					 
2001100100036	20011001	00036	GL  	2001	10	1	2001FA0000345    	2	20010304	G	8510		BEARING         			AMTR  	LANCAR	LANCAIRES   	       	GL  	AMTR  	CHEVY8	CHEVYV8     	 	GL  					BELT DRIVE	FAILED          	C				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			WP	07	350N					ES0261	1C947072			FLYING AT 5000 FEET, SAW SMOKE COME OUT OF FRONT OF COWL.  PULLED POWER BACK.  SMOKE QUIT.  INCREASED POWER TO TRY TO MA	KE AIRPORT.  PROPELLER QUIT TURNING. AFTER CRASH, BELT MOSTLY GONE.  LOOKS LIKE LOWER FRONT BEARING ON DRIVE SEIZED OR O	VER HEATED AND CAUSED THE BELT TO FAIL.				1	L	7	1 	  	3	V		EXPA1L71	EXPE3V				 
2001100100038	20011001	00038	SO  	2001	10	1	2001FA0000346    	1	20010726	G	3213	6531904	CYLINDER        			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	VO360*      	41514	EA  					LANDING GEAR	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	15299	7733 				287305051				CYLINDER, LANDING GEAR STUB AXLE AND OLEO PISTON ASSY						1	L	7	1 	3O	3	O	 	2A13    	1E1				 
2001100100039	20011001	00039	SO  	2001	10	1	2001FA0000347    	1	20010725	G	3213	7873805	AXLE            			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	VO360*      	41514	EA  					PISTON ASSY	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	15299	7733 				287305051				CYLINDER, LANDING GEAR STUB, AXLE AND OLEO PISTON ASSY						1	L	7	1 	3O	3	O	 	2A13    	1E1				 
2001100100054	20011001	00054	CE  	2001	10	1	2001FA0000348    	1	20010727	G	2435		BEARING         	LUCAS       		LEAR  	45    	45LEAR      	5170805	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					STARTER GEN	FAILED          	C				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	13	100KK	679  			97514	065				AIRCRAFT EXPERIENCED RIGHT GENERATOR FAILURE.  GENERATOR LINE CONTACTOR FAILED TO OPEN AUTOMATICLY AND CREW WAS UNABLE T	O SELECT GENERATOR OFF.  RIGHT AIRCRAFT MAIN POWER BUSS EXPERIENCED SPIKING WHICH RESULTED IN DAMAGING 3 OR THE MAIN POW	ER DISTRIBUTION PANELS ALONG WITH MELTING THE SOLDER OUT OF THE STARTER/GENERATOR SPEED PICKUP CONNECTOR.  CREW ENDED UP	 HAVING COMPLETE LOSS OF RIGHT MAIN BUSS AND ASSOCIATED SYSTEMS.			2	L	7	2 	4F	4	F	RT	T00008WI	E6WE				 
2001100100055	20011001	00055	EA  	2001	10	1	2001FA0000349    	2	20010723	G	8530		CYLINDER        			PIPER 	PA31  	PA31P350    	7103111	SO  	LYC   	O540  	TIO540V2AD  	41532	EA  					NR 5	DAMAGED         	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			EA	09	184JB	2307 				31P8414049	L856061A			WHILE IN CRUISE CONFIGURATION AT 16500 FEET, 32 INCH HG/2200 RPM THE PILOT NOTED A SHUTTER FOLLOWED BY A DROP IN MANIFOL	D PRESSURE RESULTED.  WITHIN 60 SECONDS THE MANIFOLD PRESSURE FLUCTUATED RAPIDLY, FOLLOWED BY A LOUD BANG.  THE ENGINE W	AS SECURED AND AN UNEVENTFUL LANDING FOLLOWED.  INSPECTION OF THE ENGINE REVEALED THE NR 5 CYLINDER ASSEMBLY HAD SEPARAT	ED FROM THE ENGINE.  THE PISTON AND CONNECTING ROD WERE ATTACHED AND IN THE CYLINDER, THE ROD CAP HAD SEPARATED AND WAS 	FOUND IN THE CRANKCASE.		1	L	7	2 	3O	3	O	RT	A8EA    	E14EA				 
2001100100056	20011001	00056	CE  	2001	10	1	2001FA0000350    	1	20010710	G	7713	47083621	CONTROLLER      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					INTERNAL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	525RH		358  			402C0525	823318R			UNABLE TO CONTROL MANIFOLD PRESSURE						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001100100057	20011001	00057	CE  	2001	10	1	2001FA0000351    	1	20010907	G	4990	3862332113	COVER           	GARRTT      		RAYTHN	DH125 	HAWKER800XP 	       	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					APU OIL FILTER	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	811TA				T601	258516	T601			WHEN REMOVING THE APU OIL FILTER COVER, THE RETAINING EARS THAT HOLD THE END OF THE COVER, THE RETAINING EARS THAT HOLD 	THE COVER IN PLACE BREAKS OFF.  RECOMMEND MANUFACTURING A FILTER COVER WITH A HEX FITTING ON THE END OF THE COVER, IT WO	ULD MAKE IT EASIER TO TWIST OFF THE COVER.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001100200009	20011002	00009	CE  	2001	10	2	2001FA0000352    	1	20010924	G	2460		BUSS            			CESSNA	172   	172R        	2072401	CE  										ELECTRICAL	DAMAGED         	C				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			SW	99	2458G	870  				17280893				PILOT REPORTED LOSS OF HALF OF AVIONICS BUSS, INCLUDING ONE NAV/COM AND GPS AND SMOKE AND A BAD ODOR IN THE COCKPIT.    	WIRE NR  2H1002 (22 GAUGE) BURNED FROM THE NAV. LIGHT C/B SWITCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11	 TO JV001, PIN 1.  THE RED LEAD FROM THE TAIL NAV LIGHT ASSEMBLY SHORTED OUT TO A NUT-PLATE ON THE RUDDER THAT HOLDS THE	 RUDDER TIP ON, BUT DOES NOT DISPLAY EVIDENCE OF OVERHEATING, OTHER THAT THE PINHEAD SIZED BURN MARK.			1	H	7	1 	3O			NT	3A12    					 
2001100200010	20011002	00010	EU  	2001	10	2	2001FA0000353    	1	20010928	G	2720	PC43301A1	CONTROL CABLE   			RHNFLU	EXT300	EA300L      	70218DG	EU  										RUDDER	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	25AP	66   	66   			094				ROUTINE ANNUAL INSPECTION REVEALED AFT RUDDER CABLE THIMBLE EYES WERE LOOSE IN THE LOOP AT THE ATTACHMENT TO THE RUDDER.	 THE THIMBLE COULD BE REMOVED FROM THE LOOP. THE NICROPRESS CRIMP WAS MADE TOO FAR FROM THE THIMBLE. REPLACED THE RUDDER	 CABLES WITH NEW ONES.				1	M	7	1 	3O			NC	EA67U   					 
2001100200012	20011002	00012	CE  	2001	10	2	2001FA0000354    	1	20010806	G	5753	0523921	ROLLER          			CESSNA	172   	172N        	2072434	CE  										TE FLAPS	DAMAGED         	B				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	99	737ME					17269516				AIRCRAFT RETURNED FROM FLIGHT WITH RIGHT FLAP DAMAGED.  FLAP WAS STUCK AT ABOUT 20 DEGREES AND WAS TWISTED AND JAMMED IN	 TRACKS.  FOUND INBOARD AFT.  ROLLER WORN AND SPLITTING.  INBOARD FLAP TRACK ALSO DAMAGED.  SUSPECT WORN OUT FLAP ROLLER	 OR EXCESSIVE AIRCRAFT SPEED WHEN LOWERING FLAPS.  RECOMMENDED YEARLY OR 500 HOURS FLAP ROLLER INSPECTION AND LUBE.  (M)				1	H	7	1 	3O			NT	3A12    					 
2001100200013	20011002	00013	SO  	2001	10	2	2001FA0000355    	1	20010817	G	2823	3138400	CONTROL CABLE   			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					TANK SELECTOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	23TA					277854114				CABLE BROKE JUST BELOW SWIVEL FITTING OR THE RIGHT WING FUEL TANK SELECTOR HANDLE.  RECOMMEND THAT THE AD INCLUDE THE FU	EL SELECTOR CABLE ALSO BE INSPECTED.					1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001100200021	20011002	00021	EA  	2001	10	2	2001FA0000356    	2	20010829	G	8530	AEL6510241	CYLINDER HEAD   			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	B			MW2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	2366W	953  				288516046	R917539A			CYLINDER CRACKED FROM TOP SPARK PLUG AROUND OUT SIDE OF EX SEAT TO BOTTOM SPARK PLUG HOLE.  SAME AS ALL THE REST.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001100200022	20011002	00022	SO  	2001	10	2	2001FA0000357    	1	20010830	G	7170	S6250	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  					OIL DRAIN	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	44RK					347770296				THE OIL SUMP DRAIN PANEL (ON THE LOWER COWL) WAS INSTALLED BACKWARDS.  THIS ALLOWED THE OIL DRAIN VALVE TO CONTACT THE P	ANEL AND DEPRESS THE VALVE.  CONTACT ONLY OCCURS WHEN THE ENGINE IS RUNNING.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001100200023	20011002	00023	EA  	2001	10	2	2001FA0000358    	2	20010912	G	8500	LW16819	CRANKCASE       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320*       	41508	EA  					ENGINE	CRACKED         	B			NDDG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	739LK					17270626	R839376T			ENGINE FOUND TO BE CRACKED.  THE FRACTURE OCCURRED ON THE LEFT HAND CASE HALF RUNNING FROM THE 9 OCLOCK POSSITION OF THE	 NR 2 CYLINDER PAD TO THE MAIN BEARING BOSS AREA.  THIS CRACK WAS CAUSED BY POOR SCAVENGING OF AIR DURING THE CASTING PR	OCESS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001100200024	20011002	00024	EA  	2001	10	2	2001FA0000360    	2	20010713	G	7414		MAGNETO         			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	SEPARATED       	B			MGFR	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	23	47337					28R7737159				TRANSIENT PILOT LANDED WITH LOSS OF OIL PRESSURE.  OIL WAS OVER AIRCRAFT BELLY AND ENGINE COMPARTMENT.  INVESTIGATION FO	UND RIGHT MAGNETO HANGING BY DISTRIBUTOR WIRES AND LEFT MAGNETO VERY LOOSE.  AIRCRAFT ANNUAL APPROXIMATELY 20 HOURS PRIO	R.  CONCLUSION:  MAGNETOS MAY NOT HAVE BEEN RETIGHTENED DURING ANNUAL-IF THEY WERE RETIMED.				1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001100200025	20011002	00025	CE  	2001	10	2	2001FA0000361    	1	20010920	G	5712		RIB             			CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520*    	17040	SO  					LEFT WING	CRACKED         	B			BIOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	375AB	3505 				21061352				LEFT WING RIB CRACKED WHERE LEFT FLAP BELLCRACK SUPPORT BRACKETS ARE MOUNTED, CRACK RUNS FROM INBOARD LOWER SUPPORT BRAC	KET RIVET HOLE APPROX. ONE(1) INCH IN LENGTH DOWN AND TO THE LEFT.  PROBABLE CAUSE:  FLAPS EXTENDED AT TOO HIGH OF AN AI	RSPEED.				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001100200027	20011002	00027	CE  	2001	10	2	2001FA0000362    	1	20010920	G	3246	3190	TUBE            			CESSNA	185   	A185F       	2072821	CE  	LYC   	O540  	TIO540*     	41532	EA  					FLOAT PUMP	DISCONNECTED    	D				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			AL	05	185JS					18503095				ONE AFT COMPARTMENT PUMP OUT TUBE WAS DISCONNECTED NOT ALLOWING THE WATER TO BE PUMP FROM FLOAT.  AIRCRAFT SWAMPED RIGHT	 FLOAT ON TURN AND STARTED TO SINK.					1	H	7	1 	3O	3	O	 	3A24    	E14EA				 
2001100200028	20011002	00028	EA  	2001	10	2	2001FA0000363    	2	20010829	G	7414		SHAFT           			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320*       	41508	EA  					MAGNETO	SHEARED         	D				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			GL	13	7071G	521  				17258771				PILOT REPORTED 700 RPM DROP ON LEFT MAGNETO.  MAGNETO REMOVED AND INSPECTED.  FOUND DRIVE SHAFT/ MAGNETO/ ROTOR SHEARED 	IN HALF.  MAGNETO REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001100200001	20011002	00001	CE  	2001	10	2	2001FA0000364    	1	20010928	G	2810	6207010144	LINE            			CESSNA	650   	650         	2076802	CE  										HYD SYSTEM	CHAFED          	B				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			GL	15	72ST	5921 				6500072				THE AIRCRAFT WAS MANUFACTURED WITH THE HYDRAULIC PRESSURE AND RETURN LINES CONTACTING EACH OTHER. THE RETURN LINE EVENTU	ALLY WORE THROUGH AND STARTED TO LEAK, THE PRESSURE LINE WAS ALSO SEVERLY WORN AND REQUIRED REPLACEMENT. THE REPAIR IS E	XTENSIVE BECAUSE THE LINES ARE SWAGED REQUIREING THE REPLACEMENT OF MANY LINES AND FITTINGS. NOT ALL OF THESE LINES ARE 	AVAILABLE FROM CESSNA. THE AREA WHERE THE LINES ARE IN CONTACT CAN BE VERY DIFFICULT TO INSPECT. IN MOST CASES THE AREA 	IS ONLY VISIBLE WITH A MIRROR. THEY CHECKED ANOTHER CESSNA 650 THAT WAS IN THE SHOP AND IT HAD ONLY .010 BETWEEN THE LIN	ES. IT WOULD BE ADVISABLE FOR OTHER OPERATORS OF THIS MODEL AIRCRAFT TO HAVE THESE LINES INSPECTED AT THE EARLIEST POSSI	2	L	7	2 	4F			 	A9NM    					 
2001100200002	20011002	00002	CE  	2001	10	2	2001FA0000365    	1	20010813	G	2730		SCREW           			CESSNA	441   	441         	2076020	CE  										ELEVATOR CONTROL	LOOSE           	B				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	99	181MD	10133				4410295				EXCESS FRICTION IN PITCH, (ELEVATOR) CONTROL.  DISASSEMBLY OF CONTROL, REVEALED RETAINING SCREW HAD BACKED OUT OF NYLON 	SLIDE.  UNCONTAINED PARTS OCCASSIONALLY POSITIONED THEMSELVES THROUGH OUT NORMAL MOTION OF THE CONTROL SO AS TO CREATE E	XCESS FRICTION.  (M)				1	L	7	2 	3T			RT	A28CE   					 
2001100200003	20011002	00003	SO  	2001	10	2	2001FA0000366    	1	20010820	G	1400		TAPE            			PIPER 	PA28  	PA28140     	7102802	SO  										CARB SHROUD	LOOSE           	B				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	9831W					2823335				PILOT COMPLAINED OF ROUGH RUNNING ENGINE LOW STATIC RPM ONLY OBTAINABLE BY LEANING MIXTURE, FOUND APPROX 1 SQUARE INCH O	F TIN FOIL LODGED IN CARB VENTURI, EXAMINATION OF HEAT SHROUD ON EXHAUST PIPE RUB AREA WAS WRAPPED WITH ALUMINUM FOIL TA	PE TO TAKE UP PLAY, MORE LOOSE FOIL READY TO DISLODGE AND MAKE ITS WAY TO SNUFF AIR IN CARB.  (M)				1	L	7	1 	3O			 	2A13    					 
2001100200004	20011002	00004		2001	10	2	2001FA0000367    	4	20010816	G	2312	VP10	ANTENNA         			BEECH 	33    	35C33       	1151408	CE  										VHF SYSTEM	CRACKED         	B				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	99	6124V					CD856				A/C ARRIVED WITH AN ANTENNA 'FLUTTERS' SQUAK.  UPON INSPECTION OF VHF COMM ANTENNA, IT WAS NOTED THAT THE ANTENNA WAS IN	STALLED WITH NO SUPPORTING DOUBLER.  UPON ANTENNA REMOVE, A 5.5 INCH RADIAL CRACK WAS DISCOVERED AROUND THE ANTENNA BASE	.  THE ADJOINING STRINGER IS ALSO CRACKED.  THE SKIN UNDER THE ANTENNA AS CORRODED DUE TO NO SEALANT BEING APPLIED TO TH	E ANTENNA BASE AFTER INSTALLATION.  (M)			1	L	7	1 	3O			 	3A15    					 
2001100200005	20011002	00005	EA  	2001	10	2	2001FA0000368    	2	20010625	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	D				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SW	99	47702	1147 				287890120				THE AIRCRAFT WAS AT NORMAL CRUISE, THE PILOT STATED THAT IT STARTED TO LOSS POWER AND RAN ROUGH.  AFTER LANDING AT A ALT	ERNATE AIRPORT THE AIRCRAFT STOPPED RUNNING.  AFTER PULLING THE CYLINDER, THE TOP OF THE EXHAUST VALVE WAS MISSING.  THE	 STEM AND RETAINING CLIPS WHERE STILL IN PLACE.  THE TOP OF THE VALVE HAD BEEN FOUND IN THE INTAKES.  CAUSE OF THE MALFU	NCTION UNKNOWN.  TOTAL TIME ON THE VALVE IS 1146.8 HOURS.  (M)			1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001100300003	20011003	00003	GL  	2001	10	3	2001FA0000370    	1	20010829	G	5510	81611	TERMINAL        			AVIAT 	A1    	A1B         	       	GL  	LYC   	O360  	O360A1D     	41514	EA  					HORIZONTAL STAB	BROKEN          	B			V2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	711HY					2025				FORWARD HORIZONTAL STABILIZER STRUT UPPER TERMINAL WAS FOUND BROKEN ON PREFLIGHT.  BREAK OCCURED ON .3125 (5/16) THREADE	D PORTION AT UPPER END OF THREADS.					1	H	7	1 	3O	3	O	NC	A22NM   	E286				 
2001100300004	20011003	00004	CE  	2001	10	3	2001FA0000371    	1	20011002	G	3230		LANDING GEAR    			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1A    	41514	EA  					MAINS	FROZEN          	B			BLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	8253G					177RG0153				NOSE GEAR IN UP POSITION HAD HYDRAULIC LOCK.  KEEPING THE NOSE GEAR IN THE UP POSITION EXTENDED GEAR, MAIN GEAR LOCKED D	OWN, NOSE GEAR DID NOT FULLY EXTEND DUE TO HYDRAULIC LOCK IN THE RETURN LINE.					1	H	7	1 	3O	3	O	 	A20CE   	1E10				 
2001100300005	20011003	00005	CE  	2001	10	3	2001FA0000372    	1	20010824	G	5312	24120043	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	VO360*      	41514	EA  					FUSELAGE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	6190R					172RG0110				FOUND CRACKS ON RIGHT AND LEFT HAND SIDES OF BULKHEAD JUST FORWARD OF BATTERY.						1	H	7	1 	3O	3	O	 	3A17    	1E1				 
2001100300006	20011003	00006	CE  	2001	10	3	2001FA0000373    	1	20010829	G	2720	98820104	ROD             			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320*       	41508	EA  					PILOTS LT PEDAL	FAILED          	B			FFGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	51403	5726 				17274308				ACTUATION ROD TO RUDDER PEDAL BROKE AT BASE OF THREADS AT FORK.  THERE WAS NO DAMAGE TO RUDDER PEDAL OR BRAKE MOUNT FOUN	D.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001100300008	20011003	00008		2001	10	3	2001FA0000374    	4	20010212	G	6122	MS914401	GASKET          	MCAULY      		AMTR  	VANS  	RV8         	       	GL  	LYC   	O360  	IO360A1B6   	41514	EA  					GOVERNOR	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	27	88PV				010038	80024				GASKET PN MS914401 THAT IS SUPLIED WITH THE NEW GOVERNOR DOES NOT COVER THE FULL FACE MATING SURFACE OF THE GOVERNOR EXP	OSING APPROX. .0625 INCH OF THE LOWER SCREW HOLE.  THE LOWER SCREW HOLE INTERSECTS AN OIL PRESSURE CAVITY ON THE ENGINE 	MATING SERVICE.  THE SHORT GASKET LEAKS OIL FROM LOW RPM.  DURING AN INITIAL FLIGHT OVER 4 QUARTS OF OIL LEAKED IN LESS 	THAN 15 MINUTES OF FLIGHT.			1	L	7	1 	3O	3	O	NT	EXPA1L71	1E10				 
2001100300001	20011003	00001	CE  	2001	10	3	2001FA0000375    	1	20011002	G	5753		FLAP            			CESSNA	172   	172N        	2072434	CE  										WING	MISINSTALLED    	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	38PA					17270182				PROBLEMS FOUND AFTER RECENT PAINT AND INTERIOR:SEAT BELTS INSTALLED BACKWARDS,RIGHT FLAP INSTALLED WITHOUT ALL SPACERS R	ESULTING IN DAMAGE TO FLAP,AILERON HINGE PINS NOT SECURED,NOSE TIRE INSTALLED BACKWARDS,FRONT COWLING SCREWS MISSING.					1	H	7	1 	3O			NT	3A12    					 
2001100300002	20011003	00002	SO  	2001	10	3	2001FA0000376    	1	20011002	G	2400	467067	ISOLATOR        			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  	HARTZL	HCC2Y	HCC2YF1     	GL  	ELECTRICAL	BURNED OUT      	D				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	27	3543M	3150 				28R7803176	299526R	AM1855		IN CRUISE FLIGHT NOTICED THE AMP GAUGE WAS SHOWING THE ALTERNATOR PUTTING OUT OVER 45 TO 50 AMPS.  DME DROPPED OF LINE, 	LOST THE TRANSPONDER SIGNAL.  VFR CONDITIONS AND CANCLED FLIGHT.  LANDED AT THE CLOSEST AIRPORT.  STARTED AIRCRAFT.  RAD	IOS WORKING.  30 TO 45 MIN INTO THE FLIGHT,  AVIONICS STARTED TO DROP OFF LINE.  MAINT. TECH FOUND BATTERY WAS DEAD.   B	ATTERY WAS CHARGED AND REINSTALLED.  RUN UP OF THE AIRCRAFT SHOWED NO ALT PROBLEM AT ALL AND BUSS VOLTAGE WAS 13.75 BUT 	STILL HAD 35AMP DRAW. ONE OF FOUR PLASTIC INSULATOR THAT INSULATES THE DIODE & COOLER ASSEMBLY FROM THE HOLD DOWN SCREWS	 HAD POSSABLY BEEN TIGHTENED TO TIGHT. METAL DIODE ASSY WAS SHORTED TO GROUND. REPLACED THE SCREW AND INSULATOR.	1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P920	 
2001100400001	20011004	00001	EU  	2001	10	4	2001FA0000377    	1	20010903	G	5751	212111407	LINK            			CASA  	C212  	C212200     	2410304	EU  	GARRTT	TPE331	TPE331*     	01514	WP  					ATTACH BOLT	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	316ST					289				DURING ROUTINE INSPECTION FOUND RIGHT AILERON OUTBOARD HINGE LOOSE.  THE OUTBOARD LINK WAS CRACKED AT THE WING ATTACH BO	LT LOWER LUG.  NO DAMAGE TO THE WING OR AILERON WAS FOUND.					2	H	7	2 	4T	3	T	RT	A43EU   	E2WE				 
2001100400002	20011004	00002		2001	10	4	2001FA0000378    	4	20010927	G	3497	2H1002	WIRE            			CESSNA	172   	172R        	2072401	CE  										NAVIGATION LIGHT	BURNED          	C			XVES	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	19	2458G	874  				17280893				PILOT REPORTED LOSS OF HALF AVIONICS BUSS, SMOKE AND BAD ODOR IN COCKPIT.  T/S,  FOUND WIRE BURNT FROM NAV LIGHT C/B SWI	TCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11 TO JV001, PIN 1.  RED LEAD FROM TAIL NAV LIGHT HOUSING SHORT	ED OUT TO NUT-PLATE ON RUDDER THAT HOLDS RUDDER TIP ON, BUT DOES NOT DISPLAY EVIDENCE OF OVERHEATING, OTHER THAN PINHEAD	 SIZED BURN MARK.  SEVERAL OTHER WIRES WERE DAMAGED WHEN WIRE NR 2H1002 MELTED.    NOTE:  ALL THREE NAV-LAMPS FEED INTO 	A SINGLE TWO FOOT LENGTH OF 22 GAUGE WIRE BEFORE CONNECTING THE 5 AMP BREAKER.  MOST OF LENGTH OF WIRE TO TAIL IS DAMAGE	D, LAST SECTION TO BREAKER IS BURNED BARE.  THIS SECTION THAT MELTED INTO ADJACENT WIRES IN BUNDLE.  ONCE WIRE BURNED TH	1	H	7	1 	3O			NT	3A12    					 
2001100400003	20011004	00003	CE  	2001	10	4	2001FA0000379    	1	20010909	G	5320		PANEL           			CESSNA	177   	177B        	2073708	CE  	LYC   	O360  	O360*       	41514	EA  					TRANSPONDER	LOOSE           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	13519					17702432				OWNER/OPERATOR REPORTED THAT CONTROL YOKE WOULD NOT PULL BACK TO RAISE THE ELEVATOR.  ON INSPECTION IT WAS FOUND THAT TH	E PANEL MOUNT TRAY FOR THE TRANSPONDER ON THE RIGHT SIDE OF THE PANEL HAD DROPPED .2500 OF INCH AND WAS CONTAINING AND R	ESTRICTING AFT MOVEMENT OF THE CONTROL YOKE.  THE AIRCRAFT COULD NOT ROTATE ON TAKEOFF AND IT WAS A CLOSE CALL.  AN ADDI	TIONAL SUPPORT WAS INSTALLED ON THE BACK OF THE TRAY.  AVIONICS INSTALLER OVER-LOOKED THE POSSIBILITY OF THE TRAY DROPPI	NG DOWN.  UNDER PANEL AREA SHOULD BE INSPECTED AT EACH ANNUAL, 100 HOUR AND AFTER NEW AVIONICS INSTALLATION.		1	H	7	1 	3O	3	O	 	A13CE   	E286				 
2001100900025	20011009	00025	CE  	2001	10	9	2001FA0000380    	1	20010911	G	3240	5100106159	LINE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					BRAKE ASSY	CHAFED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	05	414AN	4224 				414A0819				BRAKE LINE ROUTED UNDER THE CO-PILOTS SEAT PEDESTAL AREA IS CHAFFING ON HEAT DUCT TUBING.  SLIDING A 193-6 LOW PRESSURE 	HOSE OVER THE BRAKE LINE WILL KEEP THE BRAKE LINE FROM DEVELOPING A HOLE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001100900026	20011009	00026	CE  	2001	10	9	2001FA0000381    	1	20010911	G	3240	5100106159	LINE            			CESSNA	414   	414A        	2075907	CE  										BRAKE ASSY	CHAFED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	2702L	4375 				414A0608				RIGHT BRAKE LINE ROUTED UNDER CO-PILOT SEAT PEDISTAL AREA IS CHAFFING ON HEAT DUCT TUBING.  SLIDING A 193-6 LOW PRESSURE	 HOSE OVER THE BRAKE LINE WILL KEEP THE BRAKE LINE FROM DEVELOPING A HOLE.					1	L	7	2 	3O			 	A7CE    					 
2001100900027	20011009	00027	CE  	2001	10	9	2001FA0000382    	1	20010906	G	3240		BOLT            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					BRAKE CYLINDER	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	81JD	4577 				172RG1184	L3108636A			LEFT LANDING GEAR WOULD NOT EXTEND IN FLIGHT.  AIRCRAFT WAS HOISTED UP AND THE GEAR EXTENDED AND LOCKED.  FOUND A BOLT M	ISSING FROM THE LEFT BRAKE CYLINDER.  PERFORMED SEVERAL GEAR RETRACTIONS AND OPS CHECKED OK.					1	H	7	1 	3O	3	O	 	3A17    	E286				 
2001100900023	20011009	00023	CE  	2001	10	9	2001FA0000383    	1	20010929	G	2410	646655A1	DRIVE GEAR      	TELEDYNECRIT		CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ALTERNATOR	DAMAGED         	B				A				UNSCHED LANDING         				E	H		VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			SW	99	112MJ					421C0907	292300R			L. ALTERNATOR FAILED DURING FLIGHT AND A VIBRATION WAS NOTED ABOUT 20 MINUTES LATER.  THE ENGINE OIL PRESSURE DROPPED AB	OUT 25 PSI AND A PRECAUTIONARY LANDING WAS MADE.  UPON REMOVAL OF THE ALTERNATOR IT WAS DISCOVERED THE DRIVE HUB WAS NEA	RLY DESTROYED AND THE DRIVE GEAR BOLTS WERE MISSING AND THE GEAR WAS LOOSE ON THE BULLGEAR SHAFT.  THE REMNANTS OF THE D	RIVE GEAR WERE LOCATED IN THE OIL PAN ALONG WITH THE CASTLE NUT AND COTTER PIN. (SEE PHOTO)THIS IS THE SECOND OCCURRENCE	 OF THIS TYPE FAILURE IN THE PAST 2 WEEKS, THE OTHER WAS ON THE I. ENGINE OF A 421C WITH ABOUT 1400 HOURS ON THE ENGINE 	AND LESS THAN 100 HOURS ON THE ALTERNATOR SMOH.  NEITHER ALTERNATOR EXHIBITED ANY BEARING PROBLEMS. WE HAVE BEEN UNABL	1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001121900121	20011219	00121	GL  	2001	12	19	2001FA0000384    	2	20011005	G	7230	230397911	ADAPTER         	ALLSN       		AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  					COMP COUPLING	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		2450 			CAC30224P	5030	CAE840216			COUPLING HAS EXCESSIVE FRETTING WEAR ON OD SURFACE.  CONTINUED OPERATION MAY HAVE CAUSED FAILURE.  SAME CONDITION NOTED 	ON OTHER COUPLINGS OF THE SAME PART NUMBER.  THIS PART NUMBER IS CURRENTLY UNDER INVESTIGATION BY ROLLS-ROYCE (ALLISON E	NGINE COMPANY)DUE TO FAILURES OF LIKE PARTS.				1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001100900024	20011009	00024	SO  	2001	10	9	2001FA0000385    	2	20011003	G	8530	646279	PISTON          			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300C      	17022	SO  	MCAULY	1B175	1B175MFC    	GL  	ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99						56291	12558OC	8464		WHILE PREPARING TO INSTALL A NEW STEEL CYLINDER AND PISTON, NOTICED THAT THE NEW PISTON WAS CRACKED ALL THE WAY THROUGH 	THE FOURTH RING GROOVE.  THE PISTON SKIRT WAS ALSO BULGED IN THE AREA OF THE CRACK.					1	H	7	1 	3O	3	O	 	3A17    	E298	5	N	P857	 
2001101500077	20011015	00077		2001	10	15	2001FA0000386    	4	20010918	G	2300	S2870	SWITCH          			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					PILOT PTT	INOPERATIVE     	B			LC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	3261M	548  				18280347				THE PILOTS SIDE PUSH TO TALK SWITCH WENT BAD WITH ONLY 548.0 TACH TIME.  REPLACE THE BAD SWITCH WITH A NEW ONE.  THE NEW	 SWITCH WAS BAD ALSO, THEN REPLACED THE NEW SWITCH THE SECOND NEW SWITCH TESTED OK.  WHEN INSTALLING SWITCHES, WAS CAREF	UL NOT TO OVERHEAT SWITCH.				1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001101500079	20011015	00079	SW  	2001	10	15	2001FA0000387    	1	20010709	G	5711		SPAR            			BBAVIA	7     	7CCM        	21101MW	SW  	CONT  	C90   	C90*        	17009	SO  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2959E					7AC6545				DURING INSPECTION TO COMPLY WITH AD, CRACKS WERE FOUND INBOARD AND LEFT FRONT SPAR, INBOARD END RIGHT REAR SPAR.  .001 F	EELER GAGE COULD BE INSERTED .1250 OR MORE INTO CRACKS.					1	H	7	1 	3O	3	O	 	A759    	E252				 
2001101500087	20011015	00087		2001	10	15	2001FA0000388    	4	20010711	G	6113	055032110	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170*      	GL  	SPINNER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	3526J	72   				172S8829				THE AREA AROUND THE NUTPLATE NEAREST TO THE PROPELLER ON THE AFT SPINNER BULKHEAD HAD CRACKED AND BROKEN FREE OF THE BUL	KHEAD IN FLIGHT.  THE SECTION OF THE SPINNER ATTACHED TO THE BROKEN PIECE WAS PULLED AWAY FROM THE BULKHEAD.  THE SPINNE	R HAD STARTED TO DEVELOPE CRACKES ALONG THE BEND RADIUS.  BOTH THE SPINNER AND AFT SPINNER BULKHEAD WERE REPLACE WITH FA	CTORY NEW.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001101500090	20011015	00090	SO  	2001	10	15	2001FA0000389    	1	20010418	G	7120	1020691	SUPPORT         			AMRGEN	AA1   	AA1         	0630610	SO  	LYC   	O320  	O320E2G     	41508	EA  					MOUNT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5985L	2229 				AA10285				CORROSION DISCOVERED IN UPPER SURFACES OF BOTH LEFT AND RIGHT SUPPORTS.  DETECTED BY PREPING THE SUPPORTS FOR PAINT WITH	 A STAINLESS STEEL WIRE BRUSH AND SLIGHT RAISED LINE WAS NOTICED.  PICKING REVEALED A LARGE AREA OF POWDER CORROSION AND	 EXFOLIATION BELOW THE SURFACE.  THE OTHER SUPPORT WAS PICKED AT, THOUGHT THE SURFACE LOOKED OK AND IT WAS ALSO CORRODED	 AS MUCH AS THE FIRST ONE.  THE SUPPORTS MUST BE REPLACED WHICH IS WELL COVERED IN THE AIRCRAFT MM.  INNERGRANULAR CORRO	SION IS USUALLY THE RESULT OF DEFECTIVE HEAT TREATING DURING MANUFACTURING AND THIS PART IS USED ON ALL MODELS OF THIS P	RODUCT LINE.	1	L	7	1 	3O	3	O	 	A11EA   	E274				 
2001101500091	20011015	00091	SO  	2001	10	15	2001FA0000390    	2	20010922	G	7322	NA53B	CARBURETOR      			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					ENGINE	INOPERATIVE     	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	85122					7AC3855				ENGINE FAILURE, BELIEVE DUE TO FUEL STARVATION.  GOOD FUEL FLOW UP TO CARBURETOR.  NO CONTAMINATION FOUND WITH GASCOLATO	R.  UPON CARBURETOR DISASSEMBLY FOUND VERY FINE DIRT IN CARBURETOR FUEL STRANER AND FLOAT CHAMBER.  ALSO, FOUND MAIN AIR	 BLEED JET NEARLY TOTALLY OBSTRUCTED WITH GUMMY LIKE FOREIGN MATTER.  PROBABLE CAUSE:  FUEL FLOW IMBALANCE.  ONE EITHER 	OBSTRUCTION OF AIR JET OR FUEL JET.			1	H	7	1 	3O	3	O	 	A759    	E205				 
2001101500093	20011015	00093	CE  	2001	10	15	2001FA0000391    	1	20010903	G	5312	07126167	BULKHEAD        			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  					REAR FUSELAGE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	9024G	6880 				18260564	451652			IN COMPLYING WITH AD, (CRACKS AND LOOSE BOLTS IN FIN AND RUDDER) CRACKS WERE FOUND IN THE AREA IN THE AFT BULKHEAD BETWE	EN THE RUDDER CABLE CUTOUT AND THE BULKHEAD FLANGE.  1 CRACK EACH SIDE, BULKHEAD WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001101500094	20011015	00094	CE  	2001	10	15	2001FA0000392    	1	20010816	G	8011		BEARING         	ELECTROSYS  		BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					FWD BUSHING	DEPARTED        	B			HUNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	6013M				A040394	ME102	L2555136A			IN STARTER DRIVE END CASTING, THE (FORWARD) BUSHING DEPARTED FROM THE CASTING THIS IS THE FORWARD PIVOT BUSHING/BEARING 	FOR THE BENDIX DRIVE SHAFT.  432.24 HOURS OF FLIGHT TRAINING, OVERHAULED BY MFG.					1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2001101500023	20011015	00023	CE  	2001	10	15	2001FA0000393    	1	20010927	G	2730	380210417005	SUPPORT         			RKWELL	NA265 	NA26580     	7630108	CE  										FUSELAGE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	380GK					38044				DURING SCHEDULED INSPCTION FOUND SMALL PIECE OF A BEARING BOSS IN HELL HOLE.  UPON INVESTIGATION FOUND ELEVATOR TORQUE T	UBE SUPPORT MISSING PIECE. ALSO FOUND RT SUPPORT CRACKED IN THE SAME POSITION.  REPLACED BOTH RT AND LT ELEVATOR SUPPORT	 BRACKETS.				2	L	7	2 	4F			 	A2WE    					 
2001101500026	20011015	00026	EU  	2001	10	15	2001FA0000394    	1	20011010	G	2510	350A77125807	SEAT            			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA		6098U					2718				COCKPIT SEAT CRACKED						1	G	7	1 	3U			 	H9EU    					 
2001101500065	20011015	00065	EA  	2001	10	15	2001FA0000395    	2	20011008	G	7313	LW18265	INJECTOR        			CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	ENGINE	CLOGGED         	B				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			WP	07	428SA	597  	27   			172S8547	L2914851A	UC063		PILOT REPORTED THAT DURING CLIMBOUT THE ENGINE BEGAN RUNNING ROUGH, AT WHICH TIME HE RETURNED TO THE AIRPORT (PHX).  TEC	HNICIAN COULD NOT DUPLICATE THE MALFUNCTION ON A GROUND RUN UP. THE FUEL INJECTOR NOZZLES WERE REMOVED & INSPECTED AND T	HE NR 2 INJECTOR WAS FOUND TO BE PLUGGED.  THE INJECTOR NOZZLES WERE CLEANED & REINSTALLED.  THE ENGINE RUNUP WAS NORMAL	 AND SMOOTH, AND THE AIRCRAFT WAS FLOWN BACK TO PHOENIX.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2001101500068	20011015	00068	GL  	2001	10	15	2001FA0000396    	1	20011010	G	7160		DUCT            			CIRRUS	SR    	SR22        	       	GL  										AIR BOX	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2345B	27   				0077				ALTERNATE ENGINE AIR BOX ATTACHED TO ENGINE THROTTLE BODY WITH ONE HOSE CLAMP AND CUSHION CLAMP AT FACTORY. MAINTENANCE 	MANUAL FIG 71-601 CORRECTLY SHOWS TWO HOSE CLAMPS AND ONE CUSHION CLAMP WHICH ACTS AS SUPPORT FOR ALTERNATE AIR CONTROL 	CABLE.   LACK OF SECOND HOSE CLAMP ALLOWS ALTERNATE AIR BOX TO ROTATE CAUSING DUCT DAMAGE.				1	H	7	1 	3O			NC	A00009CH					 
2001101500069	20011015	00069	CE  	2001	10	15	2001FA0000397    	1	20011011	G	5313	CM32091	STRINGER        			CESSNA	500   	550         	2076604	CE  										FUSELAGE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	205SC	9156 	9156 			5500156				DURING AN AVIONICS INSTALLATION EVENT WITH THE AIRCRAFTS' INTERIOR REMOVED IT WAS NOTED THAT THE FUSELAGES' UPPER CROWN 	SKIN, ABOUT THE CENTERLINE HAD BEEN PREVIOUSLY MODIFIED AT ONE TIME TO "BLANK OUT" A ANTENNA INSTALLATION NO LONGER IN U	SE. EXTREMELY POOR WORKMANSHIP AND NON STANDARD PRACTICES WERE EXHIBITED IN THE INSTALLATION OF TWO INTERNAL DOUBLERS, T	HAT INCLUDED LARGE HOLES CUT IN THE UPPER CENTERLINE STRINGER ABOUT BL 0.00 AT APPROX. FUSELAGE STATION 240.00. THE TWO 	HOLES CREATED SIGNIFICANT VOIDS IN THE "T"S' FLANGE, IN CONTACT WITH THE FUSELAGE SKIN, WHICH WERE UNREINFORCED.		1	L	7	2 	4F			 	A22CE   					 
2001103100104	20011031	00104	CE  	2001	10	31	2001FA0000398    	1	20010928	G	7603	1023890091	THROTTLE CABLE  			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT THROTTLE	CHAFED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	145Z	242  				TJ289				PILOT COMPLAINED, RIGHT THROTTLE VERY STIFF, THROTTLE HAD BEEN REPLACED FOUR MONTHS EARLIER FOR SAME REASON.  UPON REMOV	AL IT WAS DISCOVERED THAT THE CABLE, WHICH WAS COVERED WITH FIRE SLEEVE, HAD BEEN CHAFFING ON THE LOWER PART OF THE TURB	OCHARGER COMPRESSOR HOUSING CLAMP, WHERE IT HAD CHAFFED THE CABLE HAD INDICATIONS OF BEING OVERHEATED.  CABLE SHOULD HAV	E BEEN ROUTED ABOVE THE EXHAUST WHERE IT WOULD HAVE BEEN PROTECTED BY THE EXHAUST HEAT SHIELD.  WHEN REPLACING PARTS WIT	H NO CLEAR GUIDANCE ON ROUTING, NEED TO MAKE SURE TO FOLLOW INSTALLATION GUIDE.		1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001103100105	20011031	00105	CE  	2001	10	31	2001FA0000399    	1	20010901	G	2710		BRACKET         			CESSNA	206   	P206D       	2073338	CE  	CONT  	O520  	IO520*      	17032	SO  					AILERON PULLEY	MISMANUFACTURED 	C				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	25	8734Z					P2060534				DURING ANNUAL INSPECTION, THE ABSENCE OF THE SAFETY COTTER PIN (-23) WAS NOTED (PORT SIDE) (AILERON PULLEY BRACKET) CONS	TRUCTION OF THE BRACKET WAS SUCH THAT A COTTER PIN COULD NOT HAVE BEEN INSERTED AT THE FACTORY. (SEE DIAGRAM)					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001103100107	20011031	00107	CE  	2001	10	31	2001FA0000400    	1	20010828	G	3242	1138932	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT MLF BRAKE	BROKEN          	C				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	19	26496					5500607				FOLLOWING A NORMAL LANDING AND ROLL OUT FOR A RIGHT TURN ON TO THE TAXI WAY THE RIGHT MAIN WHEEL LOCKED UP.  AFTER JACKI	NG THE MAIN WHEEL AND PULLING THE TIRE, A PIECE OF STATOR WAS FOUND COMPLETE BROKEN OUT OF THE STATOR CAUSING THE WHEEL 	TO LOCK.  THIS BRAKE ASSY AND THE LEFT HAD BOTH BEEN CHANGED AT THE SAME TIME.  SB AND MFG WERE DONE ELIMINATING THE NEE	D TO SEPARATE THE BRAKE ASSYS FOR INSPECTION.  AS CAN BE SEEN BOTH STATORS WERE CLOSE TO FAILURE.  THE LEFT ASSY WAS OPE	NED UP AND STATORS WERE CRACKED TO POINT WHERE FAILURE WAS MATTER OF TIME.  BOTH BRAKES HAD 585 LANDINGS.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001110100056	20011101	00056	SO  	2001	11	1	2001FA0000401    	1	20010618	G	3710	72979	GEAR            			AMRGEN	AA1   	AA1B        	0631206	SO  	LYC   	O235  	O235C2C     	41505	EA  					VACUUM PUMP	WORN            	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	07	1409R	3165 				AA1B0509	L1197115			REMOVE VACUUM PUMP DRIVE SHAFT GEAR, OIL LEAKING INTO VACUUM PUMP,  WORN SPOT ON SHAFT DAMAGED OIL SEAL CAUSING OIL LEAK	.					1	L	7	1 	3O	3	O	 	A11EA   	E223				 
2001112800065	20011128	00065	SO  	2001	11	28	2001FA0000402    	2	20011002	G	8550		OIL FILTER      			EXTRA 	EA400 	EA400       	       	EU  	CONT  	O550  	TSIOL550C   	 	SO  					ENGINE	CHAFED          	G				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			WP	07	14EX					15				AIRCRAFT EXPERIENCED AT TOTAL ENGINE FAILURE DUE TO LOSS OF OIL PRESSURE.  THE CAUSE WAS TO A B-NUT ON A T-FITTING LOCAT	ED ON THE METERED PRESSURE TEST PORT FOR THE THROTTLE BODY HAD WORN A HOLE THRU THE OIL FILTER HOUSING.  THE THROTTLE HO	USING IS MOUNTED ON RUBBER TUBING AND MOVES THRU VIBRATION AND MAKING CONTACT.  THERE NEEDS TO BE MORE CLEARANCE BETWEEN	 THE FITTING AND OIL FILTER.			1	H	7	1 	3O	3	O	RT	A43CE   	E4SO				 
2001103100109	20011031	00109	EA  	2001	10	31	2001FA0000403    	2	20010731	G	8530		EXHAUST VALVE   			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					NR 1 CYLINDER	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	1084Z	1964 				241132				NR 1 CYLINDER BROKEN, AN EXHAUST VALVE WHICH DESTROYED THE PISTON AND CYLINDER HEAD.  ALSO, FOUND NR 1 INTAKE TUBE SEAL 	PN 77569, TORN AND TWISTED WHICH COULD HAVE CAUSED A LEAN MIXTURE ON THAT CYLINDER.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001103100110	20011031	00110	CE  	2001	10	31	2001FA0000404    	1	20011001	G	7120	265102215	MOUNT           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A11      	52043	NE  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	9750B					208B0100				DURING NON ROUTINE INSPECTION OF ENGINE MOUNT, A CRACK WAS FOUND IN THE WELD OF THE LOWER RIGHT ATTACH POINT (RING TO AI	RCRAFT SUPPORT)  SHIMMY DAMPENER WAS IN GOOD CONDITION WITH NO LEAKS DETECTED.  NOSE GEAR BUSHINGS WERE ALSO SATISFACTOR	Y.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2001103100111	20011031	00111	SO  	2001	10	31	2001FA0000405    	2	20010926	G	7414	6310	MAGNETO         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5519A	497  				CE1337	820453R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IN ACCORDANCE WITH THE MM.  REMOVED THE REAR COVER OF MAGNETO AND FO	UND A GRAY COLOR POWDER ON THE CAP AND AROUND THE COIL.  THIS WAS FOUND ON THE MAGNETOS THAT HAD FAILED IN FLIGHT WITH A	BOUT THE SAME FLIGHT TIME ON THEM.   MFG WAS INFORMED OF FAILURES.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001103100112	20011031	00112	NM  	2001	10	31	2001FA0000406    	1	20010829	G	3250		ROD             			UNIVAR	415   	415C        	0420302	NM  	CONT  	C75   	C75*        	17005	SO  					NLG STEERING	BROKEN          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			GL	19	94157					1480				STEERING ROD KNUCKLE BROKE AS AIRCRAFT WAS BEING REPOSITIONED AFTER LOG.  THIS ROD HAS BROKEN NUMEROUS TIMES IN THE PAST	, KNOW OF 3 RODS BREAKING IN THE PAST.					1	L	7	1 	3O	3	O	 	A718    	E233				 
2001103100113	20011031	00113	EU  	2001	10	31	2001FA0000407    	2	20010904	G	7421	NCKB8ES	SPARK PLUG      			AMTR  	AVID  	AVIDFLYERHH 	95708FU	GL  	ROTAX 	532   	ROTAX532    	55555	EU  					ENGINE	BROKEN          	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	47065					063				THE CERAMIC PORTION OF THE SPARK PLUG BROKE COMPLETELY AROUND AND ALLOWED THE SPARK PLUG WIRE TO FALL OFF WITH THE PIECE	 OF CERAMIC INSIDE THE WIRE AND CAP.  ENGINE WOULD NOT MAINTAIN POWER ON 1 CYLINDER CAUSING FORCED LANDING AND DAMAGE TO	 AIRCRAFT.				1	H	7	1 	3O	3	I	NC	EXPA1H71	EXPE3I				 
2001103100114	20011031	00114	GL  	2001	10	31	2001FA0000408    	1	20010119	G	3244		TIRE            			AMTR  	EAGLE 	CHRISEAGLE2 	       	GL  	LYC   	O360  	IO360A1C    	41514	EA  					LANDING GEAR	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	316					419				TIRE FAILURE, STRIPPED RIB.  CAUSE: UNDETERMINED, PENDING EVALUATION BY MFG.						1	Q	7	1 	3O	3	O	 	EXPA1Q71	1E10				 
2001103100115	20011031	00115	SO  	2001	10	31	2001FA0000409    	1	20010904	G	7820	0990D113	MUFFLER         			AMRGEN	AA1   	AA1         	0630610	SO  	LYC   	O235  	O235C       	41505	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	5903L	2330 				AA10203				DURING ANNUAL INSPECTION, MUFFLER WAS FOUND CRACKED IN THE AREA WHERE TAIL PIPE IS WELDED TO CAN.  742 HOURS SINCE LAST 	INSPECTION. (ATTACHED PHOTOS)					1	L	7	1 	3O	3	O	 	A11EA   	E223				 
2001110100057	20011101	00057	EA  	2001	11	1	2001FA0000410    	2	20010223	G	8520		SEAL            			AMTR  	LONGEZ	LONGEZ      	05690Z8	GL  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	BLEW OUT        	G				A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	03	93RF	675  				1787L				ENGINE CRANKCASE BREATHER HOSE MAY HAVE ICED UP CAUSING CRANKCASE PRESSURE TO BUILDUP, BLOWING CRANKSHAFT SEAL OUT OF CR	ANKCASE.  ALL ENGINE SEIZED UP AND QUIT.  PILOT MADE AND EMERGENCY LANDING, NO DAMAGE TO AIRCRAFT.					1	M	7	1 	3O	3	O	RT	EXPA1M71	E223				 
2001103100116	20011031	00116		2001	10	31	2001FA0000411    	4	20011004	G	2300	S28701	SWITCH          			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					COCKPIT	FAILED          	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	3261M					18280347				PUSH TO TALK SWITCH FAILED AFTER 1 HOUR OF OPERATION.  HAS HAPPENED FOUR TIMES IN A ROW.						1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001112800066	20011128	00066	SW  	2001	11	28	2001FA0000412    	1	20010830	G	7810	6422209052	TAB             			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360LB   	17025	SO  					ENGINE	BROKEN          	B			TZ3R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	01	231EC	65   				250167	247414R			SECURING/ATTACHING TAB WELDED TO EXHAUST RISER ASSEMBLY FOR CYLINDER NR 4 BROKE OFF CAUSING SUDDEN LOSS OF ENGINE MANIFO	LD PRESSURE AND POWER RESULTING IN IMMEDIATE LANDING OF AIRCRAFT.  (NR 4 CYLINDER RISER SEPARATED FROM NR 6 RISER WHEN T	AB BROKE.				1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2001110100060	20011101	00060	GL  	2001	11	1	2001FA0000413    	1	20010829	G	5730		STRUCTURE       			BLANCA	1419  	14193A      	1220408	GL  	CONT  	O470  	IO470*      	17026	SO  					WING	DETERIORATED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	8507R	2619 				4269				DURING ANNUAL INSPECTION, IN THE AREA OF THE WING WALK, WOOD DETERIORATION WAS FOUND AT THE AFT, IB UPPER SKIN SEPARATED	 FROM THE FORWARD EDGE, OB EDGE AND AFT TRAILING EDGE, THE ENTIRE WING WALK AREA FABRIC WAS LOOSE FROM THE STRESSED SKIN	 PANELS THE OWNER THEN, NOT BELIEVING SB REQUIRED AND NOT WILLING TO PROPERLY REMOVE THE EFFECTED SKIN, A CABINET MAKER 	AND HIMSELF SLIP IN ON AN OFF DAY.  THE DAMAGE THAT WAS DONE TO THE SPAR THREE DIFFERENT SPOTS AT WS 6 TO WS 10.5 SEVERE	LY DAMAGED THE SPAR DUE TO COMPRESSION CAUSED BY THE CHISEL.  WHAT WAS TO BE SKIN CHANGE, NOW INCLUDES SPAR CHANGE/SPLIC	E.  SENT PICTURES TO MFG WAS INFORMED DAMAGE WAS SEVERE.	1	L	7	1 	3O	3	O	 	1A3     	E1CE				 
2001110100058	20011101	00058	CE  	2001	11	1	2001FA0000414    	1	20010921	G	2821	07560058	FUEL STRAINER   			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					FUEL SYSTEM	BACKED OUT      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	4447R	5648 				R18200601				DURING ANNUAL INSPECTION NOTICED FUEL STRAINER STANDPIPE HAD BACKED OUT AND WAS ABLE TO PULL IT OUT OF TOP ASSEMBLY WITH	 FINGERS.					1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001103100117	20011031	00117	SW  	2001	10	31	2001FA0000415    	1	20011004	G	5711		SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5074X	2714 				40				WHILE INSPECTING WING SPARS IN COMPLIANCE WITH AD, THE FRONT SPAR IN THE RIGHT WING WAS FOUND TO HAVE A  COMPRESSION CRA	CK AT THE BUTT END AND THE REAR SPAR IN THE LEFT WING WAS FOUND TO HAVE A LONGITUDINAL CRACK APPROXIMATELY 14 INCHES INB	OARD FROM THE TIP.				1	H	7	1 	3O	3	O	NC	A759    	E274				 
2001110100059	20011101	00059	CE  	2001	11	1	2001FA0000416    	1	20011011	G	3220	22430151	CLAMP           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					NLG	BENT            	D				O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			GL	25	2063S	2954 				R18201292				NOSE GEAR FAILED TO EXTEND, BUT FELL OUT WHEN AIRCRAFT WAS LIFTED FROM RUNWAY.  ON JACKS, GEAR OPS WAS NORMAL.  THIS CLA	MP WAS BENT WHICH MAY HAVE ALLOWED SHIMMY DAMPENER TO JAM THE GEAR.  MAY HAVE BEEN DAMAGED FROM TUG OVER TURNING THE GEA	R.				1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001110100061	20011101	00061	CE  	2001	11	1	2001FA0000417    	1	20010830	G	3213	AN310S	NUT             			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520F   	17032	SO  					RT MLG	FAILED          	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	09	781SL	149  				421B0343				AIRCRAFT WAS TAXING FROM THE MAIN RUNWAY TO THE GATE, PILOT FELT AND HEARD BUMPING NOISE UPON MAKING A RIGHT TURN.  AS H	E WAS MAKING RIGHT TURN ONTO RAMP TORQUE LINKS SEPARATED CAUSING THE RIGHT WHEEL AND PISTON ASSEMBLY TO ROTATE ABOUT 135	 DEGREES, CAUSING DAMAGE TO THE TO THE OB GEAR DOOR.  THE NUT STRIPPED ITS THREADS, SHEARED THE COTTER KEY AND DEPARTED 	THE AIRCRAFT.  BOLT REMAINED IN UPPER TORQUE LINK.  NEW MLG SCISSORS WASHER REPLACEMENT KIT WAS INSTALLED, KIT DOES NOT 	 INCLUDE A NEW NUT AND SUGGEST USING OLD NUT.  NEW NUT WAS USED.  THE LEFT GEAR BOLT WAS INSPECTED AND FOUND NUT WAS WOB	BLY ON BOLT THREADS.  NEW KITS AND NUT WERE INSTALLED ON BOTH SIDES.	1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001103000109	20011030	00109	NM  	2001	10	30	2001FA0000419    	1	20010820	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					3488					HOUSING IS CRACKED INSIDE THE MOUNTING BOLT HOLE.  FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF B	OLT ON INSTALLATION.					2	L	7	2 	4F			RT	A16WE   					 
2001103000110	20011030	00110	NM  	2001	10	30	2001FA0000420    	1	20010821	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					339					HOUSING IS CRACKED ALONG THE TOP CASTING SEAM.  FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF BOLT	 ON INSTALLATION.					2	L	7	2 	4F			RT	A16WE   					 
2001103000111	20011030	00111	NM  	2001	10	30	2001FA0000421    	1	20010821	G	3240	511531	HOUSING         	PNEUDRAULICS		BOEING	737   	737         	UTILSYS	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					788					HOUSING IS CRACKED INSIDE THE MOUNTING BOLT HOLE.  FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF B	OLT ON INSTALLATION.					2	L	7	2 	4F			RT	A16WE   					 
2001103000112	20011030	00112	NM  	2001	10	30	2001FA0000422    	1	20010821	G	2761	654494713	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					9858					HOUSING BEARING LUG IS BROKEN ON BOTH SIDES OF BEARING.						2	L	7	2 	4F			RT	A16WE   					 
2001103000113	20011030	00113	NM  	2001	10	30	2001FA0000423    	1	20010821	G	2761	654494715	HOUSING         			BOEING	727   	727         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4621					HOUSING IS CRACKED ALONG FIRST SHOULDER ON SAME SIDE AS PORTS.						2	L	7	3 	4J			RT	A3WE    					 
2001103000114	20011030	00114	NM  	2001	10	30	2001FA0000424    	1	20010821	G	2761	654494713	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4468					HOUSING IS CRACKED ALONG FIRST SHOULDER ON SAME SIDE AS PORTS.						2	L	7	2 	4F			RT	A16WE   					 
2001103000115	20011030	00115	NM  	2001	10	30	2001FA0000425    	1	20010821	G	2761	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		43737			0785					HOUSING IS CRACK ON ID OF PORT.						2	L	7	2 	4F			RT	A16WE   					 
2001103000116	20011030	00116	NM  	2001	10	30	2001FA0000426    	1	20010821	G	2761	654494713	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					8143					HOUSING IS CRACKED ALONG THE SECOND SHOULDER OPPOSITE THE PORTS.						2	L	7	2 	4F			RT	A16WE   					 
2001103000117	20011030	00117	NM  	2001	10	30	2001FA0000427    	1	20010821	G	2761	654494710	HOUSING         	BOEING      		BOEING	737   	737         	UTILSYS	NM  										SPOILER ACTUATOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		45922	15683		4348					HOUSING IS CRACKED UNDER THE RETRACT PORT.						2	L	7	2 	4F			RT	A16WE   					 
2001110100062	20011101	00062	NE  	2001	11	1	2001FA0000429    	2	20010926	G	7250	769104	TURBINE         								PWA   	JT8   	JT8D15      	52051	NE  					ENGINE	CRACKED         	B			W9DR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		7914 								THE 4TH STAGE TURBINE DISK BALANCE WEIGHT FLANGE HAS MULTIPLE CRACKS (APPROX. 80) INITIATING FROM THE SCALLOP AND BALANC	E WEIGHT HOLES.  CRACK LENGTH VARIES FROM .001 TO .5 INCH.  IT WAS NOTED THAT ONE CRACK IS PROGRESSING PAST ONE OF THE T	WO OIL DRAIN HOLES AND INTO THE RADIUS OF THE DISK OUTER RIM.									4	F			E2EA				 
2001103100119	20011031	00119		2001	10	31	2001FA0000430    	4	20011008	G	2561	PO723E105P	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED, MFG RECOMMENDED 2 PSI CELL TEST IAW MANUAL.																			 
2001103100120	20011031	00120	GL  	2001	10	31	2001FA0000431    	3	20010828	G	6110	1851	BEARING         	HARTZL      							PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER ASSY	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					BU16907			BU16907		RELEVANT INDICATION.											4	T			E4EA	6	C	P15EA	 
2001103100121	20011031	00121		2001	10	31	2001FA0000432    	4	20010809	G	2564	R0097104	LIFE RAFT       																	CABIN	POROUS          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										LIFE RAFT TOO POROUS.																			 
2001110100070	20011101	00070	SW  	2001	11	1	2001FA0000433    	1	20010831	G	2910	41002418	CYLINDER        	TEXTRON     		BELL  	214   	214B1       	1182105	SW  										SERVO ACTUATOR	CRACKED         	B			B80R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		7513 	1371 		1885B					SURFACE MATERIAL DEFECT/CRACK.						2	G	7	1 	4U			 	H6SW    					 
2001110100063	20011101	00063	GL  	2001	11	1	2001FA0000434    	3	20010905	G	6110	C4503	FORK            													HARTZL	HCC4Y	HCC4YR2     	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1113 						FH596		PROPELLER WAS RECEIVED FOR STANDARD 60 MONTH OVERHAUL IAW MFG SL.  CURRENT PROPELLER TIMES ARE: TTSN1113.80 TSO N/A.  TH	IS IS THE PROPELLERS FIRST OVERHAUL.   DURING THE INSPECTION OF THE PROPELLER COMPONENTS, FOR PART NUMBER C-4503, SERIAL	 NUMBER N0901 WAS FOUND CRACKED IN THE FORWARD INBOARD EAR.  ALSO, THE CORRESPONDING BLADE, PART NUMBER FC7663D6Q WITH S	ERIAL NUMBER H37377 HAS A BENT BLADE PIN AND BEARING RACE PART NUMBER A-2202 WAS FRETTED.  HARTZELL PROPELLER WAS NOTIFI	ED VIA PHONE.  ALL CONDEMNED PARTS WERE RED TAGGED AND ENTERED ON MFG FORM 101DA BEFORE RETURNING TO CUSTOMER.  THE REMA	INING PARTS CHECK GOOD.  PROPELLER WAS REASSEMBLED WITH REPLACEMENT PARTS AND RETURNED TO SERVICE.											5	C	P52GL	 
2001110100069	20011101	00069	SW  	2001	11	1	2001FA0000437    	1	20010831	G	2910	41002418	CYLINDER        	TEXTRON     		BELL  	214   	214B1       	1182105	SW  										SERVO ACTUATOR	CRACKED         	B			B80R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07		7513 	1371 		1885B					SURFACE MATERIAL DEFECT/CRACKED.						2	G	7	1 	4U			 	H6SW    					 
2001110100068	20011101	00068		2001	11	1	2001FA0000441    	4	20010814	G	3421	5546257001	CONNECTOR       	COLLINS     																VERTICAL GYRO	CORRODED        	B			M71R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	15					6055					EXCESSIVE CORROSION ON CONNECTOR BETWEEN PINS N,P, AND M.  THIS RESULTED IN ATTITUDE INDICATOR FLAGGING AND SHOWING IMPR	OPER ATTITUDES.																		 
2001110100067	20011101	00067		2001	11	1	2001FA0000442    	4	20010914	G	2561	S5600AV2A	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST TYPE AV-2(A) MFG MARCH 1983 FAILED.  MFG RECOMMENDED 2 PSI CELL TEST I/A/W  25-60-55.																			 
2001110100071	20011101	00071	GL  	2001	11	1	2001FA0000443    	3	20010913	G	6111	S90AT2	BLADE           													MCAULY	2A34C	2A34C66     	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										MCAULEY BLADE PART S90AT-2 WITH SERIAL NUMBER OD044YSC WAS RECEIVED FOR OVERHAUL.  BLADE TIMES ARE UNKNOWN.  BLADE RECEI	VED AS A SINGLE BLADE WITH FERRULE INSTALLED.  AFTER FERRULE REMOVAL, DURING BLADE BUTT, FLORESCENT PENETRATE INSPECTION	, BLADE WAS DISCOVERED CRACKED IN THE LAST THREAD, FORWARD SIDE, FROM 1:00 TO 5:00 O'CLOCK POSITION.  BLADE WAS RED TAGG	ED.													5	C	P3EA	 
2001110500035	20011105	00035		2001	11	5	2001FA0000444    	4	20010727	G	3421	5546257001	CONNECTOR       	COLLINS     																VERTICAL GYRO	CORRODED        	B			M71R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	15					6224					EXCESSIVE CORROSION ON CONNECTOR BETWEEN PINS N AND P.  CORROSION CAUSED BY INTERNAL CONDENSATION.  THIS IS RESULTED IN 	ATTITUDE INDICATOR FLAGGING AND SHOWING IMPROPER ATTITUDES.																		 
2001110100111	20011101	00111		2001	11	1	2001FA0000445    	4	20010921	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.  THE MFG RECOMMEDNDED CELL PRESSURE TEST IAW 25-60-01.  DOM: JUNE 1980																			 
2001110100112	20011101	00112	GL  	2001	11	1	2001FA0000446    	3	20010925	G	6114	1A103TCM6958	HUB             													MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										DURING INSPECTION, PROPELLER HUB WAS FOUND TO HAVE FORGING LAP IN HUB AREA.																5	N	P50GL	 
2001110100113	20011101	00113		2001	11	1	2001FA0000448    	4	20010926	G	2561	KS9P0101	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.  THE MFG RECOMMENDED TWO PSI TEST IAW MANUAL. DOM FEB 1982																			 
2001110100114	20011101	00114		2001	11	1	2001FA0000449    	4	20010922	G	2561	KS9P0101H02	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST FAILED.  THE MFG RECOMMENDED 2 PSI CELL TEST IAW MANUAL.  DOM JAN 1981																			 
2001110100115	20011101	00115	SW  	2001	11	1	2001FA0000450    	1	20010925	G	6410	406016100119	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					TAIL ROTOR	DEBONDED        	B			IIFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AK					53269				FOUND OVAL SHAPED AREA ON OUTSIDE OF TAIL ROTOR BLADE DEBONDED.  11 INCHES FROM BLADE ROOT TO 17 INCHES FROM BLADE ROOT.	  1 INCH FROM TRAILING EDGE TO 3 INCHES FROM TRAILING EDGE OF BLADE.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001110500049	20011105	00049	EU  	2001	11	5	2001FA0000451    	1	20010925	G	6210	117150041	BLADE           			BOLKMS	117   	BK117A1     	5626010	EU  										MAIN ROTOR	DELAMINATED     	B			YIVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		6969 								M/R BLADE WAS RECEIVED FOR INSP AND EVAL.  ABRASION STRIP CRACK WAS IDENTIFIED AT BLADE STATION 2305.  PORTION OF ABRASI	ON STRIP WAS REMOVED TO ALLOW EVALUATION OF UNDERLYING SURFACE.  SKIN WAS ALSO CRACKED WITH DELAMINATION SURROUNDING ARE	A.  REVIEW OF BLADE RECORDS INDICATE THAT MFG PERFORMED REPAIR ON INNER WEIGHT 1 AND 2,  CRACK IN ABRASION STRIP FROM A 	DRILL MARK ON INSIDE OF ABRASION STRIP IN AREA OF THIS REFERENCED REPAIR.  REPAIR PERFORMED BY MFG IS FOR INSTALLATION O	F PINS THROUGH INNER WEIGHTS 1 AND 2.  THREE DRILL MARKS ON INSIDE SURFACE OF ABRASION STRIP THAT LINE UP WITH PINS INST	ALLED FROM UPPER SURFACE.	1	G	7	2 	3U			 	H13EU   					 
2001110100116	20011101	00116	GL  	2001	11	1	2001FA0000453    	3	20010911	G	6110	840118	TUBE            													HARTZL	HCB5M	HCB5MP3     	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		445  						EVA2042		PROPELLER WAS FOR RECEIVED FOR STANDARD 60 MONTH OVERHAUL.  CURRENT PROPELLER TIMES ARE TTSN 445.0 AND TSO N/A.  THIS IS	 THE PROPELLER`S FIRST OVERHAUL.  DURING THE INSPECTION OF THE PROPELLER COMPONENTS, HUB PART NUMBER 840-118, SERIAL NUM	BER EVA2042 WITH PILOT TUBE PART NUMBER B-4020 WAS FOUND CRACKED IN NR 1 BLADE POSITION, 1.00 INCH FROM THE HUB SHOULDER	 FROM 11:00 TO 1:00 POSITION.  THE CRACKED PILOT TUBE WAS REMOVED AND REPLACED AND THE HUB CHECKED SERVICEABLE, AFTER RE	PAIR.  THE CORRESPONDING BLADE, NR 1 CHECK SERVICEABLE WITH NO DEFECTS NOTED.  PROPELLER WAS REASSEMBLED AFTER OVERHAUL 	AND RETURNED TO SERVICE.											6	C	P44GL	 
2001110500036	20011105	00036	EA  	2001	11	5	2001FA0000454    	2	20011004	G	7322		CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	DEFECTIVE       	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SW	03	49445					15283460	RL1860315			PILOT TOOK OFF IN AIRCRAFT, TURNED DOWNWIND AND ENGINE STARTED RUNNING ROUGH AND LOSING POWER.  PILOT LANDED AC AND ENGI	NE QUIT AS HE PULLED OFF RUNWAY.  ALL SYSTEMS CHECKED POINTED TO INSTALLED NEW REBUILT CARBURETOR AND ENGINE  FUNCTIONED	 NORMALLY.  PROBABLE CAUSE FLOAT STICKING IN CARBURETOR.  RECOMMENDATIONS TO PREVENT RECURRENCE.  CARBURETOR RETURNED TO	 MFG FOR EVALUATION.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001110100117	20011101	00117	NE  	2001	11	1	2001FA0000455    	2	20011009	G	8530		CYLINDER        			MAULE 	MT7235	MT7235      	5470209	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					ENGINE	SEPARATED       	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	11	390AT					18028C	L2559148A			CRUISE FLIGHT.  SUSPECT MFG DEFECTIVE CYLINDER WALL.  NITRIDE CYLINDER.  CYLINDER SEPARATION.						1	H	7	1 	3O	3	O	NC	3A23    	1E4				 
2001110100118	20011101	00118	CE  	2001	11	1	2001FA0000456    	1	20010815	G	3240	5100106159	LINE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					BRAKE SYS	CHAFED          	C				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CE	05	36887	4094 				414A0835				RIGHT BRAKE LINE HAD A HOLE CHAFFED IN IT FROM BEING IN CONTACT WITH THE LINE HEATER DUCT LINE UNDER THE CO-PILOTS SEAT.	  THE BRAKE LINE RUNS UNDER THE HEAT DUCT AND IS VERY DIFFICULT TO SEE.  THIS IS AN ORIGINAL PART.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001110100119	20011101	00119	EA  	2001	11	1	2001FA0000457    	2	20011016	G	8520		CRANKSHAFT      			UNIVAR	108   	1083        	9230408	NM  	FRNKLN	6A4165	6A4165*     	27025	EA  					ENGINE	BROKEN          	D			MS2R	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CE	09	833C	378  				1083833	911174017			CRANKSHAFT BROKEN IN FLIGHT, LANDED WITHOUT INCIDENT.  CRANKSHAFT BROKEN ON THE FORWARD SIDE OF JOURNAL NR 1 CYLINDER.						1	H	7	1 	3O	3	O	 	A767    	E238				 
2001110100120	20011101	00120	SO  	2001	11	1	2001FA0000458    	2	20010928	G	8520	SA628488	LIFTER          			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	5424Y	326  				U20605287	512594			DURING ROUTINE OIL CHANGE, METAL WAS FOUND IN FILTER.  ENGINE WAS REMOVED AND DISASSEMBLED.  CAUSE WAS FOUND TO BE LIFTE	R FACE AND CAM LOBE SPALLING ON CYLINDER CAM LOBES NR5 AND NR6 INTAKE.  NO CORROSION NOTED.  TWO OTHER INTAKE LIFTERS EX	HIBIT PREMATURE WEAR, REMAINING CAM LOBES CHECK.  OKAY FOR WEAR.  CAMSHAFT WAS INSTALLED.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2001110500037	20011105	00037	SO  	2001	11	5	2001FA0000459    	2	20010928	G	8530	SA643766	CYLINDER        			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520*    	17040	SO  					ENGINE	OUT OF TOLERANCE	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			WP	01	761RD	336  				21062450	269614R			CUSTOMER COMPLAINED OF INTERMITTENT ROUGHNESS.  REMOVAL OF CYLINDERS REVEALED STICKING INTAKE VALVES.  GUIDE TO VALVE TO	LERANCE TOO TIGHT, BELOW MFG MINIMUM LIMITS.  MFG CLAIMS TOLERANCE TOO TIGHT FROM NORMAL OPERATION.  NO BUILD UP NOTED O	F ANY KIND ON VALVE STEM OR INSIDE DIAMETER OF VALVE GUIDE.  TOLERANCE WAS INCORRECTLY MACHINED AT PART/CYLINDER MANUFAC	TURE OR ASSEMBLY.  RECOMMEND DISASSEMBLY AND INSPECTION OF NEW CYLINDER ASSEMBLIES TO CHECK TOLERANCES.			1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001110500038	20011105	00038	WP  	2001	11	5	2001FA0000460    	2	20011022	G	7260	30702123	GEARSHAFT       	HONEYWELL   							GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE	SEPARATED       	B			IY2R	E				ENGINE SHUTDOWN         				O			OTHER                     			CL	CLIMB          	1			SW	15		7629 			P2528		P83190			83190 WAS REMOVED FROM SABRE 65 DUE TO AN IN-FLIGHT SHUTDOWN DURING CLIMB.  TRANSFER HORIZONTAL BEVEL GEARSHAFT EXHIBITE	D SEPARATED GEAR TEETH, THUS CAUSING IFSD DUE TO NO AGB ROTATION.										4	F			E6WE				 
2001121100010	20011211	00010	SO  	2001	12	11	2001FA0000461    	1	20011021	G	5102	45	FITTING         			BALWKS	FIRE  	FIREFLY715  	1050518	SO  										FUEL SYSTEM	LEAKING         	B			F65R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	3214V	104  								THIS SET OF FUEL HOSES WERE OBTAINED FROM THE HOLDER OF A PMA.  THEY WERE INSTALLED IN MAY OF 1998.  THE HOSE WAS FOUND 	TO BE LEAKING AT THE CONNECTION WHERE THE RUBBER HOSE MEETS THE FITTING.  THE LEAK DOES NOT APPEAR TO BE CAUSED BY MISHA	NDLING BUT BY A POOR FITTING.				1	B	0	0 	  			 	A14SO   					 
2001110500039	20011105	00039	SO  	2001	11	5	2001FA0000462    	2	20011017	G	8530		CYLINDER        			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					ENGINE	MALFUNCTIONED   	G				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	17	421CR					421B0224				LEFT ENGINE EXPERIENCED A VIBRATION.  PILOT ELECTED TO LAND .  REPLACED NR 2 CYLINDER.  CLEANED VALVE GUIDES ON REMAININ	G CYLINDERS.  REPLACED SPARK PLUG ON NR 1 CYLINDER.  FLIGHT CHECK GOOD.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001110500040	20011105	00040	EU  	2001	11	5	2001FA0000463    	1	20010924	G	2730		ELEVATOR        			GROB  	ASTIR 	G102IIIB    	1660106	EU  										TAIL	FLUTTER         	C				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	11	49JJ					5606CB				WHILE CRUISING IN LEVEL FLIGHT AT 100 KTS, INDICATED, 5000 MSL, THE PILOT INITIATED A CLIMB ESTIMATED BETWEEN 2.0-2.5 G`	S.  AS SOON AS THE CLIMB WAS INITIATED FLUTTER WAS NOTED IN THE PITCH MOTION OF THE STICK (ELEVATOR FLUTTER).  BACK PRES	SURE WAS RELAXED AND THE FLUTTER STOPPED.  THE GLIDER LANDED WITHOUT FURTHER INCIDENT.  GLIDER IS CURRENTLY BEING EXAMIN	ED AT MFG.			1	K	0	0 	  			RC	G33EU   					 
2001110500041	20011105	00041	WP  	2001	11	5	2001FA0000465    	1	20011012	G	3246	152058	WHEEL           	BENDIX      		DOUG  	DC8   	DC8*        	       	WP  										LANDING GEAR	CRACKED         	B			INWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					H3501OB					NON DESTRUCTIVE TESTING INSPECTION SHOWED CRACK INDICATION AT BASE OF THE VALVE.						2	L	7	4 	4J			F	4A25    					 
2001112800068	20011128	00068		2001	11	28	2001FA0000466    	4	20011004	G	2562	7A1169SHARC7	SWITCH          																	ELT	INOPERATIVE     	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	15		1385 								WOULD NOT ACTIVATE - G SWITCH DEFECTIVE.  WILL ACTIVATE IF TURNED ON, USING MECHANICAL SWITCH.																			 
2001112800069	20011128	00069		2001	11	28	2001FA0000467    	4	20010824	G	3422	060001701	GYRO            																	COCKPIT	DEFECTIVE       	B			M2QA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										OUT OF BOX FAILURE, SLOW TO ERECT.  AFTER AIR IS DISCONNECTED GYRO ROLLS OVER 120 DEGREES.																			 
2001112800070	20011128	00070	CE  	2001	11	28	2001FA0000468    	1	20010329	G	2752	51152401	GEAR            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520K   	17032	SO  					FLAP ACTUATOR	DAMAGED         	G				K				NONE                    				O			OTHER                     			AP	APPROACH       	1			SW	11	421HM	3100 				421B0029				ON FINAL, THE FLAPS MADE A LOUD POPPING SOUND.  REMOVE FLAP ACTUATOR AND FOUND THAT THE GEAR BOX HAD ONE GEAR WITH THE T	EETH MISSING.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001112800071	20011128	00071	EA  	2001	11	28	2001FA0000469    	2	20011003	G	7414	10068	GEAR            			AMTR  	HDWIND	HEADWIND    	       	GL  	FRNKLN	4AC176	4AC176B*    	27006	EA  					MAGNETO	BROKEN          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			NM	09	3948	2000 				AB7				FOLLOWING TAKEOFF, AT ABOUT 200 FT, ENGINE FAILED.  AIRCRAFT LANDED IN FIELD WITHOUT FURTHER INCIDENT.  SUBSEQUENT INSPE	CTION REVEALED CAM GEAR, WHICH DRIVE BOTH MAGNETO GEARS, HAD SHATTERED.  CAM GEAR IS MADE OF MICARTA (FIBER) MATERIAL.					1	H	7	1 	3O	3	O	 	EXPA1H71	TC221				 
2001112800074	20011128	00074	EA  	2001	11	28	2001FA0000472    	2	20010912	G	8520	SL13212M03	BEARING         								LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		331  					L1195451A			ENGINE WAS REMOVED DUE TO METAL CONTAMINATION.  FOUND NR 3 CONNECTING ROD BEARING FAILED.  THE ENGINE DID NOT EXHIBIT SI	GNS OF OIL STARVATION.  CAUSE FOR THIS FAILURE COULD BE DELAMINATION OF THE ROD BEARING.										3	O			1E10				 
2001120300056	20011203	00056	SO  	2001	12	3	2001FA0000477    	1	20011015	G	2121	313B57	ARMATURE        			PIPER 	PA31  	PA31P350    	7103111	SO  										FAN	IMPROPER        	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	23					347					FAN WAS TESTED AND FOUND NOT TO RUN, FAN WAS DISASSEMBLED AND FOUND TO HAVE A BRUSH LEAD WIRE CUT.  THIS CAUSED THE FAN 	TO FAIL.  THE FAN HAS AN ARMATURE IN IT THAT IS NOT OF MFG DESIGN AND DOES NOT MEET MFG SPECIFICATIONS.  THE ARMATURE LA	MINATIONS ARE NOT PROTECTED AND THE WIRE IS NOT WOUND PER MFG SPECIFICATIONS.				1	L	7	2 	3O			RT	A8EA    					 
2001120300057	20011203	00057	EA  	2001	12	3	2001FA0000478    	2	20010623	G	7322	IO323	ACCELL PUMP     			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	IGO540*     	41532	EA  					CARBURETOR	STIFF           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5284T					R18201848	L2201140			THE CARB HAD TO BE CHANGED BECAUSE OF STIFF THROTTLE.  THE CAUSE BEING THE ACCELERTOR PUMP, LINKAGE RODS.  PRECISION SIL	-MS-1CW.  HAD NO EFFECT ON THE PUMP RODS.					1	H	7	1 	3O	3	O	RT	3A13    	1E11				 
2001120300058	20011203	00058	EA  	2001	12	3	2001FA0000479    	2	20011024	G	7322	103235	ACCELL PUMP     			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					CARBURETOR	STIFF           	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6485T					R18202039				CARBURETOR CHANGED BECAUSE OF ACCELERATOR PUMP STIFFNESS. PRECISION SIL CW AND HAD NO EFFECT ON EITHER CARBURETOR.						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001120300059	20011203	00059	NM  	2001	12	3	2001FA0000480    	1	20010717	G	5610	5717623097	WINDOW          			BOEING	737   	737317      	138447P	NM  	GE    	CFM56 	CFM56*      	13802	NE  					COCKPIT	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	253DV					23800				AIRCRAFT PARKED ON HOT RAMP WITH INTERIOR REFLECTIVE SHADES INSTALLED IN THE COCKPIT.  PRIOR TO PREFLIGHT, CREW STARTED 	APU FOR AIR CYCLE MACHINE(AIR CONDITIONING), UPON REMOVAL OF SUN SHADES IN THE COCKPIT, THE NR 2 PILOT WINDOW INNER PANE	 SHATTERED.				2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001120300060	20011203	00060	WP  	2001	12	3	2001FA0000481    	2	20010810	G	7321	89711012	FCU             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					LT ENGINE	FAULTY          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	687AE		1313 			4410087	P77369			ENGINE WOULD NOT REDUCE FUEL FLOW IN EITHER COMPUTER MODE OR MANUAL MODE TO ALLOW A NORMAL LANDING.  THE AIRCRAFT HAD TO	 BE LANDED SINGLE ENGINE INSTALLING A REPAIRED FUEL CONTROL UNIT CURED THE FAULT.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2001120300061	20011203	00061	WP  	2001	12	3	2001FA0000482    	2	20010810	G	7321	89711019	FCU             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					LT ENGINE	MISREPAIRED     	D				K				NONE                    				W	J		INADEQUATE Q C            	WARNING INDICATION        		IN	INSP/MAINT     	1			WP	07	687AE		990  			4410087	P77369			UNIT WAS INSTALLED AFTER REPAIR BY MFG.  UPON APPLYING POWER TO THE FUEL CONTROL AIRCRAFT HAD THE LEFT MONOPOLE FAIL LIG	HT ILLUMINATED.  FOUND THE WIRING AT THE FUEL CONTROL ELECTRICAL CONNECTOR MISSOLDERED, RESOLDERED WIRING AT THE CONNECT	OR UNIT OPERATIONALLY CHECKED GOOD.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2001120300062	20011203	00062	WP  	2001	12	3	2001FA0000483    	2	20010810	G	7321	89711012	FCU             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					LT ENGINE	FAULTY          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	689AE		4798 			4410281				ENGINE WOULD NOT OPERATE NORMALLY IN COMPUTER MODE. ENGINE SPEED WAS NOT BEING REGULATED PROPERLY BY FUEL CONTROL TORQUE	 MOTOR ENGINE OPERATED NORMALLY IN MANUAL MODE.  OVERHAULED FUEL CONTROL WAS INSTALLED AND ENGINE OPERATED NORMALLY IN B	OTH COMPUTER AND MANUAL MODES.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2001120300063	20011203	00063	SO  	2001	12	3	2001FA0000484    	1	20010906	G	2612	512T130B150001	THERMOSWITCH    			GULSTM	GV    	GV          	3980116	SO  	RROYCE	BR700 	BR700710A110	 	NE  					FIRE DETECTION	WRONG PART      	G				O				OTHER                   				W	N		INADEQUATE Q C            	FALSE WARNING             		NR	NOT REPORTED   	1			SO	03	15UC	263  				589				FOUND THERMAL SWITCH PN 512T130B150001 INSTALLED.  REMOVED SWITCH AND INSTALLED PN GAS850DF512-250 REV B.  THIS SWITCH C	ORRECTED PROBLEM.  THE REMOVED SWITCH CAUSED (FIRE WARNING LIGHT FOR THE LEFT AFT DUCT) TO COME ON.  NO LEAKS NOTED.  TH	E SWITCH REMOVED WAS NOT CORRECT PART NUMBER.				2	L	7	2 	4F	4	F	RT	A12EA   	E00057EN				 
2001112000091	20011120	00091	NE  	2001	11	20	2001FA0000485    	1	20011101	G	2421	28B135145AM	GENERATOR       			SKRSKY	S61   	S61N        	8142104	NE  										NR 2 ENGINE	FAILED          	C				K				NONE                    				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			SW	99	91158		363  			61424				A BURNING SMELL WAS DETECTED IN FLIGHT.  FOLLOWED BY THE NR 2 AC GEN DROPPING OFF-LINE.  THE REST OF THE FLIGHT CONTINUE	D NORMALLY.					2	G	7	2 	4U			 	1H15    					 
2001120300064	20011203	00064	EA  	2001	12	3	2001FA0000487    	2	20011009	G	7322	229164	TUBE            	PRECISION   		CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARBURETOR	SEPARATED       	C				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AL	05	7564G		1618 		CK49483	17259264	R4279327A			DURING DECENT, THE PILOT WAS UNABLE TO REDUCE POWER.  USING THE MIXTURE CONTROL, THE PILOT MADE AN UNEVENTFUL LANDING.  	MAINTENANCE PERSONNEL FOUND THE ACCELERATOR DISCHARGE TUBE LAYING ON THE BOTTOM OF THE INTAKE AIRBOX.  IT WAS DETERMINED	 THAT THE ACCELERATOR DISCHARGE TUBE SEALANT (LOCKTITE) HAD FAILED, CAUSING IT TO SEPARATE FROM THE ACCELERATOR DISCHARG	E PORT.  THIS CAUSED THE DISCHARGE TUBE TO LIFT UP THROUGH THE BOOST VENTURI BLOCKING ANY MOVEMENT OF THE THROTTLE VALVE	.		1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001120300065	20011203	00065	NM  	2001	12	3	2001FA0000488    	1	20011023	G	5302	HS54825H18	BOLT            			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47B     	 	GL  					TAILBOOM	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	959SD					RN019				DURING PREFLIGHT PILOT FOUND TAILBOOM BOLT MOVED.  MAINTENANCE REMOVED COVER FOUND BOLT SAFETIED, BUT BROKEN 2.5 THREADS	 FROM SHANK BOLT REMOVED AND REINSTALLED 265.2 HOURS BEFORE.					1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2001120300066	20011203	00066	EA  	2001	12	3	2001FA0000489    	2	20011101	G	8520	LW13884	MAIN BEARING    			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	DELAMINATED     	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	61US	60   				18280935	L2783748C			FRONT MAIN BEARING DELAMINATION.  DEFECT AREA WAS ABOUT THE SIZE OF A DIME.  THERE WAS EVIDENCE OF SUBSURFACE FLAWS IN T	HE SURROUNDING AREA.  THE CAUSE WOULD BE IMPROPER MANUFACTURING.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001112900065	20011129	00065	GL  	2001	11	29	2001FA0000490    	3	20011025	G	6110	C4503	FORK            			BEECH 	55    	E55         	1152732	CE  	CONT  	O550  	IO550C      	 	SO  	HARTZL	HCC4Y	HCC4YF2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	7226R	211  				TE1013		GL87		RELEVANT INDICATION(CRACK) FOUND BY NON DESTRUCTIVE TEST INSPECTION.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P52GL	 
2001112900067	20011129	00067	GL  	2001	11	29	2001FA0000491    	3	20011025	G	6110	C4503	FORK            			BEECH 	55    	E55         	1152732	CE  	CONT  	O550  	IO550C      	 	SO  	HARTZL	HCC4Y	HCC4YF2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	7226R	211  				TE1013				RELEVANT INDICATION (CRACK) FOUND BY NON DESTRUCTIVE TEST INSPECTION.						1	L	7	2 	3O	3	O	 	3A16    	E3SO	5	C	P52GL	 
2001112900068	20011129	00068	GL  	2001	11	29	2001FA0000492    	3	20011022	G	6111	V8433N10	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	O540*       	41532	EA  	HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	63ZZ					272421		JH652		CRACK FOUND IN BLADE SHANK BETWEEN TWO SHOULDERS APPROX 2 INCHES IN LENGTH.  THREE HUNDRED HOURS EST SINCE LAST INSPECTI	ON.					1	L	7	2 	3O	3	O	 	1A10    	E295	5	C	P24EA	 
2001120300067	20011203	00067	CE  	2001	12	3	2001FA0000493    	1	20011023	G	5312	05121411	BULKHEAD        			CESSNA	170   	170B        	2072306	CE  	CONT  	O300  	O300*       	17022	SO  					FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	3511C	2246 				26554				BULKHEAD CRACKED AT LOWER RIGHT CORNER WHERE STEERING CABLE PULLEY BRACKET ATTACHES.						1	H	7	1 	3O	3	O	 	A799    	E253				 
2001120300068	20011203	00068		2001	12	3	2001FA0000494    	4	20011023	G	2300	TED93010	CONNECTOR       			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360B1E    	41514	EA  					COMM SYSTEM	LOOSE           	B			I97R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	35331					17281037				COM 1 AND COM 2 INTERMITTENTLY INOPERATIVE.  UPON INSPECTION FOUND SMALL COLLARS THAT COME WITH 90 DEGREE CONNECTOR LOOS	E IN THE REAR OF BOTH COM 1 AND COM 2 COAX CONNECTORS.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001120300069	20011203	00069	EA  	2001	12	3	2001FA0000497    	2	20011022	G	8520		CRANKCASE       			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					ENGINE	CRACKED         	E				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	15	127KH		672  			500B102738				CRANKCASE WAS CRACKED AT NR 2 UPPER CYLINDER STUD AND LEAD INTO OIL PRESSURE GALLEY.  ENGINE LOST OIL PRESSURE AND WAS F	EATHERED.					1	H	7	2 	3O	3	O	 	6A1     	1E4				 
2001120300070	20011203	00070	CE  	2001	12	3	2001FA0000498    	1	20011025	G	5330		PANEL           			CESSNA	210   	210A        	2073408	CE  	CONT  	O470  	IO470*      	17026	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	9419X	3395 				21057719				WHILE AC WAS IN SHOP FOR PROP/ENGINE BALANCING, CRACK APPROX 4.5 INCHES LONG WAS FOUND ON REAR PANEL OF LOWER FORWARD FU	SELAGE STRUCTURE.  PANEL PN 12530181. PANEL WAS REPAIRED BY ADDITION OF DOUBLER AS SHOWN ON 377.  CRACK WAS LOCATED ON S	HEET METAL ABOVE WHEEL WELL.				1	H	7	1 	3O	3	O	RT	3A21    	E1CE				 
2001112000092	20011120	00092	CE  	2001	11	20	2001FA0000499    	1	20011108	G	2822	2017002	PUMP            			RKWELL	NA265 	NA26565     	7630107	CE  										FUEL SYS	FAILED          	B				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CE	01	82CR	1407 	1407 			46549				PILOTS REPORTED THAT IN CRUISE FLIGHT LEFT LOW FUEL PRESSURE ANNUNCIATOR ILLUMINATED AND LEFT FUEL PUMP CIRCUIT BREAKER 	POPPED A FEW SECONDS LATER.  AFTER LANDING, MAINTENANCE CREW REENGAGED CIRCUIT BREAKER, AND PUMP RAN, BUT WAS EXTREMELY 	NOISY.  THERE WERE NO PREVIOUS INDICATIONS SUGGESTING IMMINENT PUMP FAILURE.  MANDATORY OVERHAUL FREQUENCY OF PUMP IS 20	00 HOURS, THIS PUMP HAD 1,407 HOURS TOTAL TIME AND SINCE INSTALLATION APRIL 99.  SPECULATE THAT AN INTERNAL BEARING FAIL	ED BASED ON THE NOISE PUMP MADE AND THE FACT THAT THERE WAS NO METAL PARTICLE CONTAMINATION IN THE OUTPUT LINE OR IN LIN	E FILTER.  PUMP SENT TO OVERHAUL FACILITY TO DETERMINE ACTUAL FAILURE.	2	L	7	2 	4J			 	A2WE    					 
2001120300071	20011203	00071	SW  	2001	12	3	2001FA0000500    	1	20011028	G	5711		SPAR CAP        			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360*       	41514	EA  					WING	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	9671M	3514 				670007				DURING ANNUAL INSPECTION, WING CARRY THROUGH SPAR WAS FOUND TO HAVE EXFOLIATION CORROSION ON TOP SPAR CAP.						1	L	7	1 	3O	3	O	 	2A3     	E286				 
2001120300072	20011203	00072	EU  	2001	12	3	2001FA0000501    	1	20011101	G	3242	AH52430	BRAKE ASSY      			HWKSLY	DH125 	DH1253ARA   	423013P	EU  	RROYCE	VIPER 	VIPER522    	54552	EU  					MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	03	230TS					NA700				REPLACE BRAKE ASSEMBLIES UPON 3RD LANDING (TAXING THE NEXT DAY) BRAKES FAILED.						2	L	7	2 	4J	4	J	 	A3EU    	E3EU				 
2001120300073	20011203	00073	CE  	2001	12	3	2001FA0000503    	1	20011106	G	5313	31120111	STRINGER        			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	370SC	4814 				070				THE RIB IS CRACKED IN 3 EACH PLACES WERE IT ATTACHES TO SKIN CRACKS ORIGINATE FROM RIVETS AND CRACKING TOWARDS OTHER RIV	ETS.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE				 
2001120300074	20011203	00074	SO  	2001	12	3	2001FA0000505    	2	20011029	G	7324	6314272A20	FLOW DIVIDER    			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	DEFECTIVE       	C			VJ3R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	5582X	887  				CE1353	820397R			ENGINE RUN ROUGH AND SOMETIME WOULD NOT SHUT DOWN.  THE FUEL FLOW DIVIDER WOULD STICK OPEN, LETTING CONTINUOUS FUEL FLOW	 TO THE ENGINE.  THE FLOW DIVIDER WAS REMOVED AND REPLACED WITH A NEW ONE, OPERATION OF ENGINE CHECKED OUT NORMAL.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300075	20011203	00075	SO  	2001	12	3	2001FA0000506    	2	20011029	G	7414	M3004	BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T	998  			00051554	CE1547	820321			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.  WHERE IT LOOKS LIKE A SMALL SPA	RK LINE TO GROUND.  THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH).				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300076	20011203	00076	SO  	2001	12	3	2001FA0000507    	2	20011029	G	7414	M3004	BRUSHES         			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	38071	504  				CE935	820386R			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.  WHERE IT LOOKS LIKE A SMALL SPA	RK LINE TO GROUND.  THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300077	20011203	00077	SO  	2001	12	3	2001FA0000508    	2	20011029	G	7414		BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	38071	504  			K3823	CE935	820386R			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.  WHERE IT LOOKS LIKE A SMALL SPA	RK LINE TO GROUND.  THE WEAR ON THIS BRUSH IS ABOVE NORMAL.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300078	20011203	00078	SO  	2001	12	3	2001FA0000509    	2	20011029	G	7414	M3004M	BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8268T	998  			00051555	CE1547	820321			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.  WHERE IT LOOKS LIKE A SMALL SPA	RK LINE TO GROUND.  THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004M BRUSH)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300079	20011203	00079	SO  	2001	12	3	2001FA0000510    	2	20011029	G	7414	M3004	BRUSHES         	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					MAGNETO	WORN            	C			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5521A	455  			01042023	CE1338	820460R			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.  WHERE IT LOOKS LIKE A SMALL SPA	RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300080	20011203	00080	SO  	2001	12	3	2001FA0000511    	2	20011029	G	7314	64621216A	PUMP            			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  					ENGINE	LEAKING         	C			VJ3R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	5582X	887  				CE1353	820397R			LEAKING FUEL FROM CASE DRAIN.						1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120300081	20011203	00081	CE  	2001	12	3	2001FA0000512    	1	20011108	G	2131	13035616	CONTROLLER      			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN PRESSURE	MISREPAIRED     	C			U1UM	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01	5314J	3685 				5500663				UPON INSTALLATION OF A REPAIRED CABIN PRESSURE RATE CONTROLLER IT WAS FOUND THAT THE AC WOULD NOT TEST OR PRESSURIZE ON 	THE GROUND.  AFTER CHECKING THE ATTACHING SYSTEMS THE CANNON PLUG ON THE CONTROLLER WAS DISCONNECTED AND INSPECTED.  AT 	INSPECTION IT WAS FOUND THAT THE CANNON PLUG PINS WERE PUSHED BACK FAR ENOUGH AND ALSO BENT SO AS NO CONNECTION COULD BE	 MADE. IT WAS ALSO NOTED THAT ON THE INSIDE OF THE CANNON PLUG THE  INSULATION ON THE WIRES HAD NOT BEEN STRIPPED BACK. 	 THE WIRES WERE JUST CRIMPED TO THE PINS AND PUT IN TO THE CANON PLUG.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001120300083	20011203	00083	GL  	2001	12	3	2001FA0000514    	1	20011030	G	2820		FUEL LINE       			BLANCA	17    	1731ATC     	1220437	GL  	LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	CORRODED        	B			FB6R	A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	39828	1678 				7331044				AIRCRAFT EXPERIENCED A MASSIVE FUEL LEAK INSIDE OF CABIN AREA CAUSING AN INFLIGHT EMERGENCY.  DETERMINED FUEL LEAK CAUSE	D BY CORROSION OF FUEL LINE FROM FIRE WALL TO FUEL PRESSURE INDICATOR.  CORROSION CAUSED BY DISSIMILAR METAL OXIDATION W	HERE FUEL LINE WAS ROUTED AGAINST STEEL RIBBED DEFROSTER HOSE.  ALUMINUM FUEL LINE RUBBED THROUGH OUTER MATERIAL OF DEFR	OSTER HOSE RESULTING IN ALUMINUM TO STEEL CONTACT.  SUSPECT CONDITION EXISTED SINCE MANUFACTURE OF AIRCRAFT.  EXTREME HA	ZARD TO FLIGHT.		1	L	7	1 	3O	3	O	 	A18CE   	E14EA				 
2001120300108	20011203	00108	CE  	2001	12	3	2001FA0000518    	1	20011031	G	5530		RIVET           			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					VERTICAL STAB	BROKEN          	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	145Z					TJ289				RIVET HEAD MISSING ON EXTENSION FITTING OF VERTICAL STABILIZER FORWARD SPAR JUST ABOVE AREA WHERE SPAR IS BOLTED TO FUSE	LAGE BULKHEAD.  THERE IS NO EVIDENCE OF CORROSION OR CRACKING OF STRUCTURE IMMEDIATELY SURROUNDING RIVET LOCATION.  RIVE	T APPEARS TO HAVE FAILED IN TENSION.  ADJACENT RIVETS APPEAR SOUND.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001120300109	20011203	00109	CE  	2001	12	3	2001FA0000519    	1	20011031	G	5330	1024400291	SKIN            			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					FUSELAGE	CRACKED         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	145Z	7165 				TJ289				FOUND ONE INCH LONG CRACK IN AFT UPPER FUSELAGE SKIN AT BASE OF VERTICAL FIN.  CRACK STARTS AT LEFT FORWARD STABILIZER S	PAR EXTENSION CUTOUT AND EXTENDS UPWARD.  SUSPECT LACK OF PROPER RADIUS IN CORNER OF CUTOUT CREATED A STRESS RISER WHICH	 CAUSED THE SKIN TO CRACK DURING NORMAL FLEXING OF AFT FUSELAGE.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2001120300110	20011203	00110	CE  	2001	12	3	2001FA0000520    	1	20011031	G	5730	1021000115	SKIN            			BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520*    	17040	SO  					WING	CRACKED         	B			FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	145Z	7165 				TJ289				LOWER INBOARD LEADING EDGE SKIN CRACKED BETWEEN FUEL TANK DRAIN FITTING HOLE AND REAR EDGE OF SKIN.  CRACK IS THROUGH AN	D AREA APPROXIMATELY 2 INCHES WIDE THAT HAS NO RIVET CONNECTING SKIN TO FRONT SPAR STRUCTURE.  NORMAL FLEXING OF WING AP	PEARS TO BE STRESSING THE SKIN IN THIS AREA.  THIS IS THE THIRD BARON FOUND WITH THIS PROBLEM.				1	L	7	2 	3O	3	O	 	A23CE   	E8CE				 
2002012400101	20020124	00101	SO  	2002	1	24	2001FA0000521    	1	20011030	G	2710	6270102TO13	CONTROL CABLE   			PIPER 	PA28  	PA28140     	7102802	SO  										AILERON & RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23		2471 				2821855				CONTROL CABLES FOUND TO HAVE CORRODED END FITTINGS AS DESCRIBED IN NTSB LETTER OF APRIL 16, 2001 TO FAA. AILERON, RUDDER	,AND STABILATOR CABLES ALL REPLACED WITH NEW. MECHANIC NEEDS TO USE A LOW POWER(5X OR 10X) MAGNIFING GLASS TO SEE PITTIN	G CLEARLY.				1	L	7	1 	3O			 	2A13    					 
2001112000093	20011120	00093	EA  	2001	11	20	2001FA0000522    	1	20011030	G	3230		DRAG BRACE      			FRCHLD	22    	22C7A       	3370104	EA  										LANDING GEAR	FAILED          	C				O				OTHER                   				O			OTHER                     			UK	UNKNOWN        	1			SW	99										DRAG BRACE FAILURE.						1	H	7	1 	3I			 	ATC438  					 
2002012400102	20020124	00102	CE  	2002	1	24	2001FA0000524    	1	20011105	G	5511	123262224	SPAR            	CESSNA      		CESSNA	210   	T210N       	2073456	CE  										ELEVATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	843YT	4546 	100  			21063334				THE FRONT SPAR,ATTACHMENT BRACKET,UPPER AND LOWER SPARS, AND DOUBLERS OF THE HORIZONAL STABILIZER WAS CRACKED.						1	H	7	1 	3O			 	3A21    					 
2002012400103	20020124	00103	CE  	2002	1	24	2001FA0000525    	1	20011105	G	5521	123262226	SPAR            	CESSNA      		CESSNA	210   	T210N       	2073456	CE  										ELEVATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	843YT	4546 	100  			21063334				ELEVATOR SPAR CRACKED,ATTACHMENT BRACKET, AND DOUBLERS ALSO CRACKED.						1	H	7	1 	3O			 	3A21    					 
2002012400104	20020124	00104	CE  	2002	1	24	2001FA0000526    	1	20011105	G	5521	123262227	SPAR            	CESSNA      		CESSNA	210   	T210N       	2073456	CE  										ELEVATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	843YT	4546 	100  			21063334				ELEVATOR FRONT SPAR, DOUBLERS, AND ATTACHMENT CRACKED.AIRCRAFT USED IN PIPELINE PATROL.						1	H	7	1 	3O			 	3A21    					 
2002012500003	20020125	00003	SO  	2002	1	25	2001FA0000528    	1	20011105	G	2140	A23D04	VALVE           			PIPER 	PA23  	PA23250     	7102308	SO  										HEATER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	17WE	3692 				277854118				WHILE PERFORMING THE INSPECTION OF THE HEATER FUEL REGULATOR VALVE P/N A23D04 (PIPER P/N 461-731) AS REQUIRED BY AD 2001	-17-13, THE VALVE WAS FOUND TO LEAK BY VISUAL INSPECTION.  THE LEAKAGE WAS NOT EVIDENT UNTIL THE VALVE WAS REMOVED FROM 	THE SHROUD.  THE VALVE WAS REPLACED WITH A NEW VALVE AS REQUIRED.				1	L	7	2 	3O			 	1A10    					 
2002012500004	20020125	00004	CE  	2002	1	25	2001FA0000529    	1	20011105	G	5753		ARM             			CESSNA	172   	172         	2072402	CE  										TE FLAPS	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	4124F	3451 				46024				DURING AN ANNUAL INSPECTION,  ALL FOUR OF THE FLAP ARMS HAD WEAR FROM THE ROLLERS.  THE DAMAGE ON 3 OF THE ARMS WAS ABLE	 TO BE BLENDED WITH LESS THAN .020  OF MATERIAL REMOVAL AND WERE SERVICEABLE AS PER SERVICE BULLETIN. THE DAMAGE TO THE 	RT INBOARD ARM WAS UNABLE TO BE BLENDED OUT WITHIN LIMITS.  A NEW FLAP ARM KIT P/N SK180-44-1 WAS ORDERED. UPON RECEIPT 	THE NEW PARTS WERE INSPECTED AND IT WAS FOUND THAT ONE OF THE RIVETS HAD NOT BEEN BUCKED AT ALL AND 3 OTHERS HAD SHOP HE	ADS THAT WERE NOT BUCKED TO THE PROPER DIMENSIONS.  THE RIVETS WERE SQUEEZED TO THE PROPER DIMENSIONS AND THE NEW ARM AS	SEMBLY INSTALLED.	1	H	7	1 	3O			NT	3A12    					 
2002012900002	20020129	00002	GL  	2002	1	29	2001FA0000530    	1	20011104	G	5510		TIE BOLT        			AVIAT 	A1    	A1B         	2210406	GL  	LYC   	O360  	O360*       	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HORIZONTAL STAB	SHEARED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15		500  	5    				L3732036A	CH33963B		AVIAT HUSKY A1B.  BROKEN TIE-ROD BOLT DISCOVERED DURING A POST-FLIGHT PILOT'S INSPECTION. THIS PART ATTACHES THE STRUT (	LEFT SIDE STRUT (1 OF 3) = LOWER, ANTERIOR)TO THE LEADING EDGE OF THE HORIZONTAL STABILIZER.  UNABLE TO PROVIDE AVIAT PN	 AS THEIR PARTS CATALOG IS NOT REVISED FROM EARLIER HUSKY MODELS TO SHOW THIS PART AND/OR PROVIDE A NUMBER.				1	H	7	1 	3O	3	O	NC	A22NM   	E286	5	C	P920	 
2002012500005	20020125	00005	CE  	2002	1	25	2001FA0000531    	1	20011108	G	3230	08411132	SCREW           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	DOWNLOCK	BROKEN          	B			BIGR	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	115BH	7169 				340A1531				DOWNLOCK ADJUSTING SCREW BROKE FOR REASONS UNKNOWN.THIS ALLOWED LEFT MAIN GEAR TO LOSE DOWNLOCK TENSION. LEFT MAIN LANDI	NG GEAR RETRACTED UNTIL IT STOPPED AGAINST INBOARD GEAR DOOR. THIS ALLOWED PROP TO HIT THE GROUND AND DAMAGE TO LEFT FLA	PS OCCURED.				1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2002012500006	20020125	00006	NE  	2002	1	25	2001FA0000532    	2	20011108	G	8550	3020907	DIPSTICK        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ENGINE	BROKEN          	B				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			SW	15	43SA	4951 	1471 			5500086	PCE71655			FAILURE OF OIL DIPSTICK AT ATTACHMENT LOCK NUT CAUSING LOSS OF OIL AND LOWER THAN NORMAL OIL PRESSURE.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001120500073	20011205	00073	SW  	2001	12	5	2001FA0000534    	1	20011016	G	6310	3039080	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MAKING METAL    	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			WP	19	412DE	2690 	248  			36033				APPORXIMATELY 45 MINUTES INTO CRUISE FLIGHT A NR 2 ENGINE CHIP LIGHT ILLUMINATED.  THE NR 2 ENGINE WAS SHUTDOWN AND THE 	AIRCRAFT RETURNED TO BASE AND PERFORMED A RUN ON LANDING DUE TO INSUFFICIENT POWER FOR HOVERING.  THE MAINTENANCE TECHNI	CIANS PULLED THE NR 2 ENGINE CHIP DETECTORS AND FOUND SIGNIFICANT METAL DEBRIS ON THE ENGINE/COMBINING GEARBOX CHIP DETE	CTOR AND IN THE OIL FILTER. THE ENGINE OIL WAS SUBSEQUENTLY DRAINED. THE OIL SYSTEM WAS FLUSHED AND THE FILTER REPLACED.	  THE CHIP DETECTOR WAS CLEANED OF ALL DEBRIS AND THE HELICOPTER WAS RUN FOR 5 MINUTES ON THE GROUND.  THE HELICOPTER WA	S SHUT DOWN AFTER 5 MINUTES AND AGAIN METAL DEBRIS WAS FOUND ON THE ENGINE/COMBINING GEARBOX CHIP DETECTOR AND IN THE OI	1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002012500021	20020125	00021	CE  	2002	1	25	2001FA0000535    	1	20011016	G	5620	1014400421	WINDOW          			BEECH 	200   	B200        	1152922	CE  										CARGO BAY	CRACKED         	C				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	19	185XP	3185 				BB952				LEFT HAND BAGGAGE COMPARTMENT WINDOW OUTER PANE CRACKED WHILE IN CRUISE FLIGHT.  INNER PLY REMAINED INTACT AND FLIGHT CO	NTINUED UNPRESSURIZED TO HOME BASE WITHOUT FURTHER INCIDENT.					1	L	7	2 	4T			 	A24CE   					 
2001120500074	20011205	00074	GL  	2001	12	5	2001FA0000536    	2	20011003	G	7412	23064130	EXCITER         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	D				C				ABORTED TAKEOFF         				S			AFFECT SYSTEMS            			TO	TAKEOFF        	1			SW	99	17SP	245  				53444	847487			ENGINE FAILED TO START. IGNITORS WERE NOT HEARD AS NORMALLY HEARD. IGNITOR WAS REPLACED WITH NEGATIVE RESULTS. IGNITION 	EXCITOR REPLACED WITH NEW,  RESOLVING DESCREPANCY.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002012500023	20020125	00023	EA  	2002	1	25	2001FA0000537    	2	20011019	G	8550	78531	HOUSING         								LYC   	O320  	O320E3D     	41508	EA  					OIL PUMP	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07		2981 	589  				L3400727A			UPON DIASSEMBLING THE OIL PUMP, A MINIMUM OF 4 CRACKS WERE FOUND EMANATING RADIALLY FROM THE IMPELLER SHAFT BORE EXTENDI	NG THROUGH THE PUMP BODY.  NO EVIDENCE OF FOREIGN OBJECTS PASSING THROUGH THE PUMP GEARS WAS FOUND.										3	O			E274				 
2002012500026	20020125	00026	GL  	2002	1	25	2001FA0000539    	1	20011024	G	2821		FUEL FILTER     			AMTR  	KIS   	KISTR1      	056201W	GL  	AMTR  	SUBURU	SUBURU      	 	GL  					FUEL SYSTEM	CLOGGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09		6    								INTREGAL FUEL TANK, FIBERGLASS DUSTY FIBERS CLOGGED FUEL FILTER ENOUGH TO DEGRADE POWER. FORCED LANDING DUE TO LACK OF P	OWER.   AIRCRAFT HAD 6 HOURS SINCE INITAL FLIGHT. IT APPEARS THAT FIBERS FROM INSIDE THE FIBERGLASS FUEL TANK MIGRATED I	N THE FIRST FEW HOURS OF OPERATION AND CLOGGED THE IN-LINE FUEL FILTER.				1	L	7	1 	3O	3	O	NT	EXPA1L71	EXPE3O				 
2001120500075	20011205	00075	NM  	2001	12	5	2001FA0000540    	1	20011026	G	5302	500N31296	ANGLE           			DOUG  	600N  	600N        	3027377	NM  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	957SD	2125 				RN011				INSPECTED RT UPPER TAILBOOM ATTACH FITTING ON FUSELAGE . WE FOUND A CRACK IN ANGLE P/N 500N3129-6.  THIS ANGLE CAN ONLY 	BE SEEN BY REMOVAL OF THE RIVETED PANEL ON THE SIDE OF THE FUSELAGE. WE HAVE FOUND CRACKS ON ALL 3 OF OUR 600N MODELS .					1	G	7	1 	3U			NC	H3WE    					 
2001120500076	20011205	00076	NM  	2001	12	5	2001FA0000541    	1	20011026	G	5302	500N31296	ANGLE           			DOUG  	600N  	600N        	3027377	NM  										TAIL BOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	958SD	2219 				RN018				DURING INSPECTION OF THE RT UPPER TAILBOOM MOUNT WE FOUND P/N 500N3129-6 ANGLE CRACKED. TO INSPECT, YOU MUST REMOVE THE 	RIVETED CLOSURE ,ON THE SIDE OF THE FUSELAGE. WE HAVE FOUND CRACKS ,ON ALL 3, OF OUR 600N MODELS.					1	G	7	1 	3U			NC	H3WE    					 
2001120500077	20011205	00077	NM  	2001	12	5	2001FA0000542    	1	20011026	G	5302	500N3422	FITTING         			DOUG  	600N  	600N        	3027377	NM  										TAIL BOOM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	959SD	1993 				RN019				AFTER THE PILOT REPORTED UNUSUAL TAILBOOM MOVEMENT DURING HIS PREFLIGHT IHSPECTION , ONE OF OUR MECHANICS REMOVE THE TAI	LBOOM ATTACHMENT FAIRING. HE FOUND THE RT UPPER TAILBOOM ATTACH BOLT HAD FRACTURED , AND THE BOLT HEAD WAS HELD ONLY BY 	SAFETY WIRE.WE THEN REMOVED THE RIVETED CLOSURE COVERING THE NUTPLATE AND ATTACH FITTING. WE FOUND FITTING, P/N 500N3422	,CRACKED AND ANGLE P/N 500N3129-6 ,ALSO CRACKED.   WE HAVE GROUNDED ALL 3 OF OUR 600N MODELS ,   AND HAVE FOUND CRACKS O	N ALL 3 ANGLES .		1	G	7	1 	3U			NC	H3WE    					 
2002012500029	20020125	00029	CE  	2002	1	25	2001FA0000543    	1	20011030	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					LT CENTER WING	CRACKED         	B				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	15	84LJ	5155 				4410084				DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85)	 HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS BETWEEN THE CENTER WING MAIN SPAR (FS 177.45) AND FS 188.95. FURTHER 	INSPECTION USING FLUORESCENT PENETRANT REVEALED (2) CRACKS IN THE RADIUS. BOTH CRACKS ARE APPROXIMATELY 1INCH LONG. AFTE	R REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARA	LLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPARATION TYPE CRACK.		1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2002012500030	20020125	00030	CE  	2002	1	25	2001FA0000544    	1	20011030	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										LT CENTER WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	84LJ	5155 				4410084				DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCSW 26.85	) HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45). FURTHER INSPECTION USI	NG FLUORESCENT PENETRANT CONFIRMED A 1INCH CRACK. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED T	HAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYP	E CRACK.		1	L	7	2 	3T			RT	A28CE   					 
2001120300111	20011203	00111	SO  	2001	12	3	2001FA0000545    	2	20011025	G	7414	6320	MAGNETO         			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	CORRODED        	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	340KG	1200 				340A1505	R278307R			PILOT NOTED INTERMITTENT ROUGH ENGINE AND FLUCTUATING EGT.  DURING SUBSEQUENT TROUBLE SHOOTING, NOTED ONLY ONE IMPULSE C	OUPLING SOUND.   WHEN PULLING ENGINE THROUGH WITH SPARK PLUGS OUT AND TIMING WAS WAY OFF.  UPON REMOVAL FOUND THAT COULD	 BARELY TURN THE MAGNETO BY HAND.  WHEN  MAGNETO WAS OPENED, THERE WAS RUST SHOWING ON ROTOR AND COIL WEDGE WAS LOOSE.				1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001120300112	20011203	00112		2001	12	3	2001FA0000546    	4	20011026	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	753GW	287  				172S8753				REAR SPINNER BULKHEAD WAS FOUND BROKEN AT NUTPLATE NEAREST TO AFT SIDE OF NR 1 BLADE.  MATERIAL HAD COMPLETELY SEPARATED	 FROM BULKHEAD AND ALLOWED THE SPINNER TO BEND OUTWARD FROM CENTRIFUGAL FORCE.  SPINNER WAS NOT OBVIOUSLY DAMAGED.  THIS	 BULKHEAD WAS INSTALLED ON THIS AIRCRAFT AT 153.3 HOURS ACTT.  THE SPINNER WAS ALSO REPLACED AT THIS TIME DUE TO CRACKIN	G, THE SPINNER WAS REPLACED A SECOND TIME AT 394.7 HOURS ACCT DUE TO CRACKS FROM THE BLADE CUTOUT.  AT THIS TIME THE BUL	KHEAD WAS INSPECTED WITH NO SIGNS OF CRACKING.		1	H	7	1 	3O			NT	3A12    					 
2001120300113	20011203	00113	EA  	2001	12	3	2001FA0000547    	2	20010905	G	7310	LW120980140	FUEL LINE       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	10719	1068 				243141				FOUND THREE CRACKED FUEL INJECTOR LINES.  CRACKS ARE LOCATED AT THE SILVER SWEAT JOINT IN THE FILLET.  IT IS AS THOUGH T	HE JOINT WAS NOT PROPERLY PREPARED OR THE FLUX WAS NOT EFFECTIVE.  TWO OF THE TUBES HAD ONLY 1068.2 HOURS SINCE NEW.					1	L	7	1 	3O	3	O	 	2A3     	1E10				 
2001120300114	20011203	00114	EA  	2001	12	3	2001FA0000548    	2	20010905	G	7310	LW129980104	FUEL LINE       			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	3601Q	1068 				MA226				FOUND THREE CRACKED FUEL INJECTOR LINES.  THE CRACKS ARE LOCATED AT THE SILVER SWEAT JOINT IN THE FILLET.  IT IS AS THOU	GH THE JOINT WAS NOT PROPERLY PREPARED OR THE FLUX WAS NOT EFFECTIVE.  TWO OF THE TUBES HAD ONLY 1068.2 HOURS SINCE NEW.					1	L	7	1 	3O	3	O	 	A1CE    	1E10				 
2001120300115	20011203	00115	SO  	2001	12	3	2001FA0000549    	1	20010921	G	7810	LW13027	ADAPTER         			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					ENGINE	BROKEN          	B				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			WP	07	651SC					31P7630006	L34362			FLANGE ON LEFT ENGINE OUTBOARD ADAPTER BROKE OFF OF ADAPTER.  EXHAUST GASES LEAKED FROM SYSTEM CAUSING TURBOCHARGER OUTP	UT TO DROP.  PILOT SHUT DOWN ENGINE AND RETURNED TO AIRPORT.					1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2001120300116	20011203	00116	SW  	2001	12	3	2001FA0000550    	1	20011101	G	2730	200190202	SWITCH          			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					ELEVATOR TRIM	STUCK           	C				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	21	5262M					251183				DURING TRIM ADJUSTMENT, PILOT EXPERIENCED AN UNCOMMANDED NOSE DOWN ATTITUDE.  GROUND INVESTIGATION REVEALED THAT THE ELE	VATOR TRIM SWITCH HAD STUCK IN THE NOSE DOWN POSITION.					1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2001120300117	20011203	00117	SO  	2001	12	3	2001FA0000551    	2	20011114	G	8550		ADAPTER         			CESSNA	182   	182B        	2072706	CE  	CONT  	O470  	O470L       	17026	SO  					ENGINE	DEFECTIVE       	C				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			NM	08	7179E					52179	816510L4			NO OIL PRESSURE UPON ENGINE START UP.  OIL PUMP, SUCTION TUBE, AND CONNECTIONS CHECKED OK.  REMOVED FILTER ADAPTER, INST	ALLED FILTER SCREEN ENGINE HAD PROPER OIL PRESSURE.  NO APPARENT DAMAGE TO FILTER ADAPTER.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001121000109	20011210	00109	CE  	2001	12	10	2001FA0000552    	1	20011108	G	2436	S23731	CONNECTOR       			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520*    	17040	SO  					VOLTAGE REG	LOOSE           	B				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			GL	21	6410N					21062986				AIRCRAFT LOST ELECTRICAL POWER IN FLIGHT.  PLUG THAT CONNECTED VOLTAGE REGULATOR/ WARNING INDICATOR TO ALTERNATOR DID NO	T LOCK AND VIBRATED LOOSE.  BECAUSE THE LOW VOLTAGE INDICATOR DIE NOT ILLUMINATE AND THE AMMETER IS ON THE FAR RIGHT SID	E OF CABIN, PILOT WAS UNAWARE OF PROBLEM UNTIL RADIO COMMUNICATION FAILED.				1	H	7	1 	3O	3	O	 	3A21    	E8CE				 
2001120500078	20011205	00078	EU  	2001	12	5	2001FA0000553    	1	20010925	G	6210	117150041	BLADE           			BOLKMS	117   	BK117A1     	5626010	EU  										MAIN ROTOR	CRACKED         	B			YIVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		6969 								M/R BLADE WAS RECD AT MFG FOR INSP AND EVAL.  ABR STRIP CRACK WAS ID AT BLADE STAT 2305.  PORTION OF ABR STRIP WAS REMOV	ED TO ALLOW EVAL OF UNDERLYING SURFACE. SKIN WAS CRACKED WITH DELAM SURROUNDING AREA.  REVIEW OF BLADE RECORDS INDICATE 	MFG  REPAIR ON INNER WEIGHT 1 AND 2.  CRACK IN ABR STRIP PROPAGATED FROM A DRILL MARK ON INSIDE OF ABR STRIP IN AREA OF 	THIS REF REPAIR.  REPAIR PERFORMED FOR INSTALL OF PINS THROUGH INNER WEIGHTS 1 AND 2.  THREE DRILL MARKS ON INSIDE SURFA	CE OF ABRASION STRIP THAT LINE UP PINS.  PINS ARE INSTALLED FROM UPPER SURFACE, AND IS OBVIOUS THAT HOLES WERE DRILLED T	OO DEEP ALLOWING DRILL TO MARK INSIDE OF LWR LEG OF ABR STRIP.  CUST REPORTED HAVING OTHER BLADES THAT DEVELOPED ABRASIO	1	G	7	2 	3U			 	H13EU   					 
2001120300119	20011203	00119	SO  	2001	12	3	2001FA0000554    	1	20011105	G	2810		FUEL CAP        			PIPER 	PA22  	PA22108     	7102204	SO  	LYC   	O235  	O235*       	41505	EA  					RT WING	IMPROPER PART   	D				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	09	4855Z					228430				(2) PILOTS HAD FUEL STARVATION.  BOTH PILOTS, ON LANDING,  CHECK RIGHT WING TANKS AND HEARD HISSING SOUND.  EXAMINED CAP	S AND FOUND NOW VENT HOLES.  BOTH CAPS SEEMED NEW AND MADE OF ALUMINUM.  CHANGED CAPS TO VENTED STYLE, HAD NO FURTHER TR	OUBLE.				1	H	7	1 	3O	3	O	 	1A6     	E223				 
2001120300120	20011203	00120	EA  	2001	12	3	2001FA0000555    	2	20011107	G	8520	LS13521	BEARING         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	8458H	450  				288290053	L2777436A			WHILE ACCOMPLISHING 50 HOUR INSPECTION, METAL WAS FOUND IN FILTER.  TEAR DOWN OF ENGINE REVEALED THAT BEARING PART FAILE	D.  BATCH NUMBER ON BEARING WAS 5-99.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001120300121	20011203	00121	SO  	2001	12	3	2001FA0000557    	2	20011115	G	8520		CRANKSHAFT      			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	O360  	IO360E      	17025	SO  					ENGINE	FAILED          	C				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	05	76CP	410  				1054	357182			IN FLIGHT ENGINE FAILURE, CRANKSHAFT COUNTERWEIGHT AND DOUBLE ROD FAILURE, BLEW TWO ROD THROUGH CASE.(K)						1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2001120300122	20011203	00122	EA  	2001	12	3	2001FA0000558    	2	20011026	G	8520		STUD            			PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O235  	O235C1      	41505	EA  					ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	7278K					18185	611315			BROKEN CYLINDER BASE STUDS, 5 STUDS BROKEN ON NR 1 CYLINDER,  FOUND MIS-TORQUED ON NR 2, NR 3, AND NR 4, ALSO.(K)						1	H	7	1 	3O	3	O	 	1A2     	E223				 
2001120300123	20011203	00123	SO  	2001	12	3	2001FA0000564    	1	20010827	G	3230	3807802	DOWNLOCK        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG	BROKEN          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AL	01	200HM	351  				32R7680025				NOSE GEAR DROPPED OUT OF WHEEL WELL INFLIGHT.  FOUND DOWNLOCK BROKEN WHERE NOSE ACTUATOR ROD ATTACHES.  THIS HAS HAPPENE	D ON MORE THAN ONE OCCASION WITH SAME TYPE OF AIRCRAFT IN THE PAST.  SUSPECT MFG. IS MAKING PART FROM SUBSTANDARD MATERI	AL.  THIS PROBLEM HAS JUST BEEN HAPPENING IN THE PREVIOUS YEAR.  THIS PART WAS INSTALLED NEW ABOUT 350 HOUR PREVIOUSLY.(	K)			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001120300125	20011203	00125	SO  	2001	12	3	2001FA0000565    	2	20011112	G	7414	M3006	BEARING         	SLICK       		CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					MAGNETO	FAILED          	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6204N				99082637	18267796				PILOT REPORTED RIGHT MAGNETO INOPERATIVE ON RUNUP.  REMOVED RIGHT MAGNETO FOUND VERY HAD TO TURN.  DISASSEMBLED MAGNETO 	AND FOUND DRIVE END BEARING FAILED.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001120300126	20011203	00126	SO  	2001	12	3	2001FA0000566    	2	20011116	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5585Y	463  			01042020	CE1389	820461R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M	AGNETO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K	)				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120600139	20011206	00139	SO  	2001	12	6	2001FA0000567    	2	20011115	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1569P	522  			01040901	CE1300	820454R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO.  DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K)					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120600140	20011206	00140	SO  	2001	12	6	2001FA0000568    	2	20011115	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4609M	504  			00033035	CE772	820261R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K)					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120600141	20011206	00141	SO  	2001	12	6	2001FA0000569    	2	20011115	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1569P	522  			01040864	CE1300	820454R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO.  DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120600142	20011206	00142	SO  	2001	12	6	2001FA0000570    	2	20011115	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	INOPERATIVE     	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4609M	504  			00033043	CE772	820261R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K)					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001120600143	20011206	00143	CE  	2001	12	6	2001FA0000571    	1	20011116	G	5510	MS210783	NUT PLATE       			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	IO360A1A    	41514	EA  					HORZ STAB	BROKEN          	D			DF2S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	869CP	2355 				17280641				DURING 100 HOUR INSPECTION, TECHNICIAN FOUND LOWER ELEVATOR STOP NUTPLATE BROKEN AND FIBER LOCK PORTION OF PART SEPARATE	D FROM THE REST OF NUTPLATE DETAIL REPEATED ELEVATOR CONTACT WITH STOP BOLT WHEN AIRCRAFT IS PARKED AND CONTROL LOCK IS 	IN, SUCH AS IN WINDY CONDITIONS.(K)				1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001120300127	20011203	00127	EA  	2001	12	3	2001FA0000572    	2	20011106	G	8520	77672	LIFTER          			BEECH 	60    	60          	1153602	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					ENGINE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	33LB	132  	132  			P74	L163859			UPON REMOVAL OF PUSH RODS AND PUSH ROD TUBES FOR RESEAL, THE LIFTERS WERE REMOVED FOR BLEEDING.  THE LIFTERS WERE INSPEC	TED AND WERE FOUND TO HAVE SEVERE SPALLING.  MFG WAS NOTIFIED AND ENGINES ARE TO BE REMOVED AND SENT BACK FOR REPAIR. EN	GINES HAVE 132.4 HRS TT.  CAMSHAFT IS ALSO WORN.				1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2001120300128	20011203	00128	EU  	2001	12	3	2001FA0000573    	2	20011023	G	8520	996920	BEARING         			AMTR  	AVDFLY	AVIDFLYER   	       	GL  	ROTAX 	277   	ROTAX277    	55555	EU  					ENGINE	FAILED          	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			NM	08	94RS	260  	260  			3	6913440			ENGINE FAILED IN-FLIGHT DUE TO FAILURE OF CONNECTING ROD ROLLER BEARINGS ON CRANKSHAFT ASSEMBLY.   CAUSE UNKNOWN.						1	H	7	1 	3O	3	X	 	EXPA1H71	EXPE3X				 
2001120600144	20011206	00144	EA  	2001	12	6	2001FA0000576    	2	20011126	G	8520		CRANKSHAFT      			CESSNA	206   	206CESSNA   	2073302	CE  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	919LL					T20608174	L1044761A			CONFIRMED BY ENGINE MANUFACTURER-ENGINE CRANKSHAFT FAILED AT NR 5 CRANKPIN.						1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2001120600145	20011206	00145	EA  	2001	12	6	2001FA0000577    	2	20011114	G	7310	LW120980210	FUEL LINE       			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  					ENGINE	CHAFED          	B			VDNR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	09	931SJ	316  				18280931	L2781648A			DURING 100 HOUR INSPECTION, DISCOVERED NR2 CYLINDER FUEL INJECTION LINE LEAKING WHILE ACCOMPLISHING MFG SB.  FUEL LINE S	UPPORT CLAMP HAD BECOME LOOSE AND CAUSED LINE TO CONTACT NR2 CYLINDER FINS, WHICH WORE 6 GROOVES IN LINE.					1	H	7	1 	3O	3	O	NT	3A13    	1E4				 
2001120600146	20011206	00146	CE  	2001	12	6	2001FA0000578    	1	20011115	G	5512	12326003	SKIN            			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520A      	17032	SO  					HORIZ STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	210KE	1710 				21058505	715920			DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED.  WHEN FAIRING, PN 12124265 AND	 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN LENG	TH THE LEFT SKIN IN SAME LOCATION WAS CHAFFED 50 PER CENT.  .020 SKIN.  REPLACED AFFECTED SKINS AND REMOVED SHARP EDGE O	N FAIRING AND USED ANTI-CHAFE TAPE.			1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001120600147	20011206	00147	CE  	2001	12	6	2001FA0000579    	1	20011115	G	5512	12326004	SKIN            			CESSNA	210   	210D        	2073414	CE  	CONT  	O520  	IO520A      	17032	SO  					HORIZ STAB	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	210KE	1710 				21058505	112413R			DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED.  WHEN FAIRING, PN 12124265 AND	 PN 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN L	ENGTH THE LEFT SKIN IN SAME LOCATION WAS CHAFFED 50 PER CENT. REPLACED AFFECTED SKINS AND REMOVED SHARP EDGE ON FAIRING 	AND USED ANTI-CHAFE TAPE.			1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001121000110	20011210	00110	CE  	2001	12	10	2001FA0000580    	1	20011031	G	3411	S10711	PITOT LINE      			CESSNA	182   	182S        	2072701	CE  										PITOT/STATIC SYS	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9472F	296  				18280201				PITOT HEAT INSULATION, BURN MARKS WERE FOUND ON  PITOT PRESSURE LINE.  CONDITION RESULTS FROM HAVING PLASTIC LINE CONNEC	TED TO HEATED PITOT MAST. THE SB CORRECTS THIS BY ADDING PLASTIC SPIRAL WRAP TO LINE AND POWER WIRES AT THE PITOT MAST. 	 THIS PREVENTS PITOT LINE FROM DIRECTLY CONTACTING  HOT PARTS OF PITOT MAST, BUT SPIRAL WRAP INSULATION IS MADE OF SAME 	MATERIAL AS ORIGINAL PITOT LINE AND SUBJECT TO SAME HEAT DAMAGE.			1	H	7	1 	3O			NT	3A13    					 
2001120600148	20011206	00148	CE  	2001	12	6	2001FA0000581    	1	20011103	G	8120	4664120004	BEARING         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  					TURBOCHARGER	DRAGGING        	D				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	17	84DA	2278 				414A0519				AIRCRAFT LANDED WITH LEFT ENGINE FEATHER AND SECURED.  PILOT REPORTED LOW MANIFOLD PRESSURE.  INSPECTION REVEALED LEFT T	URBOCHARGER BEARINGS DRAGGING.  REPLACED TURBOCHARGER WITH OVERHAUL UNIT.  ENGINE OPERATIONALLY CHECKED OK. COMPONENT AG	E SUSPECTED AS CAUSE BUT LOGBOOKS WERE UNAVAILABLE .  TT 2278				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001121000111	20011210	00111	SO  	2001	12	10	2001FA0000582    	1	20011114	G	2140	A2300475	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					CABIN HEATER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	3581C	142  				318052091				THE HEATER FUEL REGULATOR, WAS INSTALLED NEW, IN OUR AIRCRAFT.  AD`S HAVE BEEN COMPLIED WITH.  DURING ROUTINE HEATER INS	PECTION AND CHECK, FOUND NEW TYPE REGULATOR SEEPING FUEL AROUND HOUSING SEAL.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001121000112	20011210	00112	WP  	2001	12	10	2001FA0000583    	1	20011005	G	2434		WIRE            	ELECTROSYS  		RYAN  	ST3   	ST3KR       	7830502	WP  	CONT  	O360  	TSIO360KB   	17025	SO  					ALTERNATOR	MISSING         	B			TZ3R	K				NONE                    				W	J		INADEQUATE Q C            	WARNING INDICATION        		IN	INSP/MAINT     	1			WP	01	2022				9032694	1054				NEW EXCHANGE ALTERNATOR SUPPLIED.  ALTERNATOR OUTPUT OK.  PANEL INOPERATIVE LIGHT STAYS ILLUMINATED.   INSPECTION OF ALT	ERNATOR REVEALED MISSING LEAD WIRE FROM STATOR TO STATOR.  ALT LIGHT TERMINAL ON ALTERNATOR.  ALTERNATOR REQUIRES ADDITI	ONAL LEAD WIRE FOR AIRCRAFT WITH PANEL DOWN OPERATIVE LIGHT CONNECTED TO STATOR TERMINAL ON ALTERNATOR.				1	L	7	1 	3R	3	O	 	A749    	E9CE				 
2001121000113	20011210	00113	EA  	2001	12	10	2001FA0000584    	2	20011114	G	8530	LW12429	CYLINDER        			PIPER 	PA25  	PA25        	7102502	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					ENGINE	DELAMINATED     	B			YYBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03							L529661A			LYCOMING CYLINDER PN LW12429 WITH A CERMINILL COATING FROM ECI DELAMINATED.  THE AREA WAS ABOUT 1.5 INCHES IN LENGTH AND	 ABOUT .250 WIDE AT THE TOP OF THE CYLINDER BORE, ABOVE THE PISTON RING TRAVEL.  THE PROBABLE CAUSE WAS CORROSION UNDER 	THE CERMINILL COATING.  THIS IS A PLATING DEFECT. THE ECI BATCH NUMBER ON THE CYLINDERS ARE 46463-3, 46463-10, 40739-3D,	 AND 40739-6D.			1	L	7	1 	3O	3	O	 	2A10    	E14EA				 
2001121000114	20011210	00114	SO  	2001	12	10	2001FA0000585    	1	20011124	G	5102	GL0115721688	FUEL LINE       			BALWKS	FIRE  	FIREFLY715  	1050518	SO  										FUEL SYSTEM	LEAKING         	B			F65R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	15	3214V	110  				F7912				THIS SET OF FUEL HOSES WERE OBTAINED FROM THE HOLDER OF A PMA. THEY WERE INSTALLED IN MAY.  THE HOSE WAS FOUND TO BE LEA	KING AT THE CRIMP CONNECTION AT THE END OF THE HOSE.  THE LEAK DOES NOT APPEAR TO BE CAUSED BY MISHANDLING, BUT BY A POO	R CRIMP JOB.  THIS IS THE SECOND HOSE FROM THIS SET THAT HAVE STARTED LEAKING FROM THE SAME LOCATION.				1	B	0	0 	  			 	A14SO   					 
2001121000115	20011210	00115	CE  	2001	12	10	2001FA0000586    	1	20010430	G	2720	04115261	MOUNT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					RUDDER PEDAL	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	17	49792	8393 				15283517				PILOTS RIGHT HAND LOW RUDDER PEDAL ASSEMBLY MOUNT CRACKED AROUND WELD CAUSING ON GROUND LOSS OF DIRECTIONAL CONTROL AND 	MADE BRAKING DIFFICULT.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001121000116	20011210	00116	EA  	2001	12	10	2001FA0000587    	2	20011102	G	8520	69373	BEARING         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CONNECTING ROD	DEBONDED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	714VV	1076 				15279475	L1843715			PLATING ON BEARING UNBONDED FORM BACKING (ROD SIDE NOT THE CAP SIDE)  DATE CODE ON BACK OF BEARING IS 200.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001121000117	20011210	00117	SO  	2001	12	10	2001FA0000588    	1	20011120	G	2710	62701124	CONTROL CABLE   			PIPER 	PA28  	PA28181     	7102807	SO  										AILERON	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	41487	2125 				2843179				DURING A ROUTINE INSPECTION, SUBSTANTIAL WEAR WAS FOUND WHERE THE AILERON BALANCE CABLE RUNS THROUGH THE RIGHT SIDE OF T	HE FUSELAGE.  CABLE WEAR WAS PROBABLY CAUSED BY IMPROPER CABLE ALIGNMENT DURING ASSEMBLY BY MFG.  THIS IS THE SECOND OCC	URRENCE OF THIS TYPE OF DEFECT FOUND IN OUR FLEET.(K)				1	L	7	1 	3O			 	2A13    					 
2001121000118	20011210	00118	SO  	2001	12	10	2001FA0000589    	2	20011126	G	8520	642396	CRANKSHAFT      			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	BROKEN          	B			VA1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	717BD	2059 				414A0337	521140			CRANKSHAFT BROKE IN 3 SECTIONS, HAD 595.9 SMOH.  NO SIGNS OF OIL STARVATION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001121000119	20011210	00119	NE  	2001	12	10	2001FA0000590    	1	20011017	G	7922		NUT             			LAKEAC	LAKE  	250LAKE     	5110322	NE  	LYC   	O540  	TIO540*     	41532	EA  					VERNATHERM	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	59CA	616  				129	L29861A			REMOVED VERNATHERM TO COMPLY WITH MFG SB (CHECK NUT TIGHTNESS).  WHEN VALVE REMOVED, THE NUT WAS MISSING.  AFTER A THROU	GH SEARCH THE NUT WAS FOUND IN THE INBOARD HOSE,  OIL COOLER END OF THE COPILOT SIDE OF OIL COOLER (2 OIL COOLER ARE ON 	THIS INSTALLATION).(K)				1	H	7	1 	3O	3	O	NC	1A13    	E14EA				 
2001121100011	20011211	00011	GL  	2001	12	11	2001FA0000591    	3	20010611	G	6111	8381010	CLAMP           													HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1928 						H1766		PROPELLER RECEIVED FOR STANDARD OVERHAUL, DUE TO TIME IAW MFG SL. (TSO)1982.9.  AFTER PROPELLER DISASSEMBLY, THE FOLLOWI	NG COMPONENTS ARE CONDEMNED:  BLADE (PN MV8433-4, SN 36637R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. BLADE (PN MV8433	-4, SN C85096R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. CLAMP (PN 838-1010, SN 44) CRACKED THROUGH THE INNER CLAMP AT	TACHMENT HOLE. CLAMP (PN 838-1010, SN 57) CRACKED THROUGH INNER CLAMP ATTACH. HOLE.  PILOT INDICATED NO ABNORMAL OP.													5	C	P24EA	 
2001121100012	20011211	00012	GL  	2001	12	11	2001FA0000592    	3	20010611	G	6111	8381010	CLAMP           													HARTZL	HCA2	HCA2MVK2    	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1928 						H1766		PROPELLER RECEIVED FOR STANDARD OVERHAUL, DUE TO TIME. (TSO) 1982.9.  AFTER PROPELLER DISASSEMBLY, THE FOLLOWING COMPONE	NTS ARE CONDEMNED:  BLADE (PN MV8433-4, SN 36637R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. BLADE (PN MV8433-4, SN C85	096R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. CLAMP (PN 838-1010, SN44) CRACKED THROUGH THE INNER CLAMP ATTACHMENT HO	LE.  CLAMP (PN 838-1010, SN57) CRACKED THROUGH INNER CLAMP ATTACHMENT HOLE.  PILOT INDICATED NO ABNORMAL OP.													5	C	P24EA	 
2001121000120	20011210	00120	CE  	2001	12	10	2001FA0000593    	1	20011121	G	3246		WHEEL           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540*       	41532	EA  					LANDING GEAR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9979C					R18200495				CRACK, 1.25 INCHES IN LENGTH, EMANATING FROM BOLT HOLE.						1	H	7	1 	3O	3	O	RT	3A13    	E295				 
2001121000121	20011210	00121	SO  	2001	12	10	2001FA0000594    	1	20010724	G	2820	1442800	GASCOLATOR      			PIPER 	PA28  	PA28*       	       	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	CRACKED         	G				O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			WP	07										DURING ENGINE START, AN INDUCTION FIRE STARTED WHEN THE CARBURETOR BACKFIRED.  THE FIRE COULD NOT BE EXTINGUISHED AND DE	STROYED THE AIRCRAFT.  DURING AN INVESTIGATION THE GASCOLATOR COVER WAS FOUND CRACKED.  IT APPEARS THE FUEL LEAKING FROM	 THE COVER APPEARS TO HAVE FED THE FIRE THAT DESTROYED THE AIRCRAFT.				1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001121000122	20011210	00122	CE  	2001	12	10	2001FA0000595    	1	20010710	G	3213		BUSHING         	CESSNA      		CESSNA	310   	310J        	2074226	CE  	CONT  	O470  	O470M       	17026	SO  					TORQUE LINK	SEPARATED       	D				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	17										RIGHT MAIN LANDING GEAR UPPER AND LOWER TORQUE LINKS BECAME DISCONNECTED FROM EACH OTHER DURING TAKEOFF ROLL.  IT APPEAR	S THAT A PRESSED IN BUSHING, SEPARATED FROM THE LOWER TORQUE LINK ALLOWING THE BOLT HEAD AND WASHER TO PASS THROUGH THE 	ENLARGED HOLE NORMALLY OCCUPIED BY THE BUSHING.  CATALOG INDICATES THAT A SPECIAL WASHER IS REQUIRED UNDER THE BOLT HEAD	.  THE SPECIAL WASHER HAS A LARGER OUTSIDE DIAMETER THAN THE STANDARD AN WASHER WHICH WAS FOUND INSTALLED.  MM INSTRUCTI	ON DO NOT REQUIRE INSTALLATION OF SPECIAL WASHER.		1	L	7	2 	3O	3	O	 	3A10    	E273				 
2001121000123	20011210	00123	EU  	2001	12	10	2001FA0000597    	1	20011120	G	3230	7733690395	RELAY           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540*      	41532	EA  					LANDING GEAR	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	1871S	336  				1871				LANDING GEAR FAILED TO EXTEND.  CIRCUIT BREAKER FOUND OPEN.  INVESTIGATION FOUND LANDING GEAR UP, RELAY POINTS WELDED CL	OSED.					1	L	7	1 	3O	3	O	RT	A51EU   	1E4				 
2001121000124	20011210	00124	CE  	2001	12	10	2001FA0000598    	1	20010817	G	3260		LENS            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					INSTRUMENT PNL	LOOSE           	D				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			GL	17	339AJ					BB339				PILOT REPORTED THAT UPON SETUP FOR APPROACH AND GEAR DOWN SELECTION WAS MADE WITH GEAR SWITCH.  THAT AN INDICATION FOR B	OTH MAIN GEAR WERE DOWN AND LOCKED, BUT NO INDICATION OF THE NOSE GEAR DOWN AND LOCKED.  AIRCRAFT DIVERTED AND VERIFIED 	WITH ATC THAT NOSE GEAR WAS DOWN.  CAUSE: NOSE GEAR GREEN LAMP SOCKET LENS CAME LOOSE.  AIRCRAFT LANDED INCIDENT FREE.  	PLACED AIRCRAFT ON JACKS, RECHECKED EMERGENCY GEAR EXTENSION OPERATION AND RIGGING PER MM.  PERFORMED NORMAL EXTENSION A	ND RETRACTION.  TIGHTENED NOSE LAMP LENS FUNCTIONAL TEST OF ALL WORK PERFORMED CHECKS, OK.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001121000125	20011210	00125	CE  	2001	12	10	2001FA0000599    	1	20011023	G	5521	043200121	SPAR            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	94584	6515 				15285738				REMOVED ELEVATOR TO REPAIR WORN OUTBOARD HINGE BUSHINGS, AFTER ELEVATOR WAS REMOVED FOUND THE ELEVATOR SPAR CRACKED UNDE	R THE OUTBOARD HINGE WHERE IT ATTACHES TO THE SPAR, REPLACED SPAR WITH NEW.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001121000126	20011210	00126	SO  	2001	12	10	2001FA0000600    	1	20010817	G	3246	16106900	WHEEL           			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540*     	41532	EA  					LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	68SE					273780				DURING ANNUAL INSPECTION, FOUND LEFT INNER MAIN WHEEL HALF CRACKED IN THE BEAD AREA ORIGINATING FROM BRAKE ATTACHMENT PL	ATE RIVETS.					1	L	7	2 	3O	3	O	 	1A10    	E14EA				 
2001121000134	20011210	00134	EA  	2001	12	10	2001FA0000601    	2	20011126	G	7414	IO68256013	GEAR            			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					MAGNETO	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	200HM		481  			32R7680025				DURING INSPECTION FOUND A DISTRIBUTOR GEAR TOOTH BROKEN AND LAYING IN MAG CAP.  THIS IS AN ONGOING PROBLEM.  THIS MAG HA	S PLASTIC GEARS AND HAS BEEN FOUND IN THIS CONDITION ON NUMEROUS MAGNETOS OF THIS TYPE IN THE PAST.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001121000135	20011210	00135	SO  	2001	12	10	2001FA0000602    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	40449	473  				32R7780519				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121000136	20011210	00136	SO  	2001	12	10	2001FA0000603    	1	20011126	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	200HM	481  				32R7680025				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE CRACKED AT REAR ATTACH POINT.  THIS IS A COMMON PROBLEM FOUND ON THIS MODEL 	AIRCRAFT.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002012500039	20020125	00039	SO  	2002	1	25	2001FA0000604    	2	20011205	G	8530	501867	WASHER          			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360GB   	17025	SO  					ENGINE CYLINDER	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	231ND					250207	309202			WHILE TROUBLESHOOTING A FUEL FLOW PROBLEM, AN OIL LEAK MANIFESTED AT NR 6 EXHAUST ROCKER COVER. WHEN COVER REMOVED, THE 	TAB WASHERS WERE FOUND MISSING FROM THE ROCKER SHAFT STUDS. ALL COVERS WERE REMOVED AND THE SAME CONDITION FOUND. A CHEC	K OF MAINTENANCE RECORDS REVALED A "TOP OVERHAUL" WAS ACCOMPLISHED 14.7 HOURS PREVIOUS. SUBMITTER SUSPECTS WASHERS WERE 	LEFT OFF DURING REASSEMBLY. THE TAB WASHERS SERVE TO SAFETY THE ROCKER SHAFT RETAINING NUTS. LOSS OF THE RETAINING NUTS 	COULD RESULT IN CATASTROPHIC ENGINE FAILURE AND UNPLANNED TERMINATION OF FLIGHT. SUBMITTER FAILS TO COMPREHEND OVERLOOKI	NG THIS CRITICAL PART. INSTALLED 501867 WASHERS ON ALL ROCKER SHAFT STUDS AND SECURED.	1	L	7	1 	3O	3	O	 	2A3     	E9CE				 
2002012500040	20020125	00040	SO  	2002	1	25	2001FA0000605    	1	20011205	G	7120	3872902	MOUNT           			PIPER 	PA32  	PA32R301    	7103218	SO  										ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4369M	1877 				32R8413022				ENGINE TRUSS WELD ASSY FOUND CRACKED AT STEERING ARM ATTACH POINT						1	L	7	1 	3O			 	A3SO    					 
2002012500041	20020125	00041	SO  	2002	1	25	2001FA0000606    	1	20011205	G	7120	3872919	MOUNT           			PIPER 	PA32  	PA32R301    	7103218	SO  										ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	395HP	873  				3213085				ENGINE TRUSS WELD ASSEMBY FOUND CRACKED AT STEERING ARM ATTACH POINT.						1	L	7	1 	3O			 	A3SO    					 
2002012500043	20020125	00043	SO  	2002	1	25	2001FA0000607    	2	20011114	G	7414	6310	MAGNETO         			CESSNA	182   	182E        	2072712	CE  	CONT  	O470  	O470R       	17026	SO  					RT & LT	FAILED          	C				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			SO	11	3390Y	231  				18254390				ENGINE RAN A LITTLE ROUGH WHEN STARTED. RAN SMOOTHLY AFTER WARMING UP.  A 45 MIN FLIGHT WAS MADE AND THEN ENGINE WAS SHU	T DOWN.  THE ENGINE STARTED AGAIN WITH NO PROBLEM.  ABOUT 45 MINUTES INTO THE NEXT LEG, THE ENGINE BEGAN RUNNING ROUGH A	ND MISSING.  INITIALLY, CARBURATOR ICE WAS SUSPECTED AND CARB HEAT WAS APPLIED.  AFTER ABOUT 15 MIN OF FULL CARB HEAT, T	HE ENGINE APPEARED TO RUN SMOOTHLY.  RETURNED TO HOME AIPORT (30 MIN) AND LANDED WITH NO PROBLEM.   CARB ICE WAS NOT EXP	ECTED AS THE HUMIDITY WAS LOW (20 PERCENT).  ANOTHER SOURCE FOR THE ENGINE ROUGHNESS WAS LOOKED FOR.  IT WAS DISCOVERED 	THAT ENGINE WOULD NOT START.  IGNITION WAS CHECKED AND IT WAS DISCOVERED THE BOTH MAGNETOS IMPULSE COUPLINGS HAD FAILED 	1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012500046	20020125	00046	EU  	2002	1	25	2001FA0000608    	1	20011206	G	2820	L24266701320000	SUPPORT         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					FUEL SERVO	BROKEN          	B				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	15	147FS	1135 				0735	L2842451A			EYE SCREW, IS A SUPPORT STRUT WHICH ATTACHES TO THE EXHUST STACK AT ONE END AND THE FUEL SERVO TO ENGINE SUMP ATTACHMENT	 STUDS AT THE OTHER END. THE STRUT FELL BETWEEN THE THROTTLE ARM AND SUMP. THIS PREVENTED THE ENGINE FROM BEING ABLE TO 	REDUCE POWER BELOW 1500 RPM. CONDITION REPORTED BY PILOT AND FOUND BY MECHANIC. SUBMITTER REPLACED PART AND SECURED STRU	T AT AN ADDITIONAL POINT IN CASE THE REPLACEMANT PART BREAKS AGAIN. THIS ADJUSTMENT WOULD PREVENT THE STRUT FROM FALLING	 INTO THE CONTROL LINKAGE IF THE PROBLEM REOCCURES.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002012500047	20020125	00047	GL  	2002	1	25	2001FA0000609    	1	20011016	G	3201		BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  										MLG FAIRING	BROKEN          	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	155CD	264  				1058				BOTH LEFT AND RIGHT MAIN LANDING GEAR INBOUARD FAIRING BRACKETS BROKEN, CAUSING FAIRING TO BE VERY LOOSE.  GAUGE OF META	L IS TOO THIN FOR THIS HIGH VIBRATION APPLICATION.					1	L	7	1 	3O			NT	A00009CH					 
2002012500049	20020125	00049	GL  	2002	1	25	2001FA0000610    	1	20011016	G	6120	50597001	BEARING         			CIRRUS	SR    	SR20        	05628AJ	GL  						HARTZL	HCC3Y	PHCC3YF1    	GL  	PROP GOVERNOR	BROKEN          	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	155CD	264  				1058				PROPELLER GOVERNOR CABLE EXTREMELY STIFF WITH POSSIBLE BROKEN WIRE INSIDE OUTER SHROUD.  THIS CAUSED THE THROTTLE LEVER 	BEARING, WHERE THE ROD END FOR THE PROP GOVERNOR CABLE ATTACHES TO THE THROTTLE LEVER, TO BREAK APART.  THE STRENGTH OF 	THE BEARING FOR THIS APPLICATION IS QUESTIONABLE.  THE THROTTLE LEVER PN 10007-001 ALSO HAD TO BE REPLACED.				1	L	7	1 	3O			NT	A00009CH		5	C	P25EA	 
2002012500051	20020125	00051	CE  	2002	1	25	2001FA0000611    	1	20011010	G	2400	S2800275	CONNECTOR       			CESSNA	172   	172R        	2072401	CE  										J BOX	INADEQUATE      	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	109PH	1411 				17280802				CONNECTOR PB017, PN: S2800-275, WHICH ATTACHES SHIP WIRING TO J2 OF  POWER JUCTION BOX MC01-2A, HAD INADEQUATE CRIMPS OF	 BOTH WIRE ENDS ATTACHING WIRES TO SOCKETS.  SOCKET "A" HAD AN OPEN CIRCUIT WHICH CAUSED LOSS OF BUSS NR 2 H1014.  WHEN 	PULLED ON, THE WIRES EASILY CAME OUT OF THE CONNECTOR.  CORRECTIVE ACTION WAS TO CRIMP & SOLDER THE CONNECTOR.				1	H	7	1 	3O			NT	3A12    					 
2002012500056	20020125	00056	CE  	2002	1	25	2001FA0000612    	1	20011123	G	3240		BRAKE ASSY      			CESSNA	188   	A188B       	2073005	CE  										MLG	MALFUNCTIONED   	G				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	01	9541J					18803819T				THE PILOT STARTED THE AIRCRAFT ENGINE, THE AIRCRAFT  STARTED TO ROLL, AT WHICH TIME THE PILOT APPLIED THE BRAKES.  THE L	EFT BRAKE WAS OPERATIONAL BUT THE RIGHT WAS FLAT. THIS CAUSED THE AIRCRAFT TO SWERVE TO THE LEFT HITTING A CESSNA CARAVA	N DAMAGING BOTH AIRCRAFT. THE BRAKE SYSTEM WAS INSPECTED, RESERVOIR FOUND TO BE FULL, NO LEAKS FOUND.  SUSPECT AIR IN TH	E BRAKE SYSTEM.			1	L	7	1 	3O			 	A9CE    					 
2002012500064	20020125	00064		2002	1	25	2001FA0000614    	4	20011124	G	3120	S17111	PRESSURE SWITCH 			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	5444J	5595 				17273798	RL96576T	731908		ON ANNUAL INSPECTION FOUND OIL DRIPPING ON RIGHT SIDE OF AFT FIREWALL IN CABIN.  TRACED TO LEAKING HOUR METER OIL PRESSU	RE SWITCH. SWITCH WAS LEAKING INTERNALLY.  REPLACED SWITCH.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002012500066	20020125	00066	SO  	2002	1	25	2001FA0000615    	1	20011127	G	5750	6270114	CONTROL CABLE   			PIPER 	PA28  	PA28140     	7102802	SO  										TE FLAPS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23						2821855				NEW FLAP CABLE (62701-14) ORDERED TO REPLACE EXISTING FLAP CABLE THAT CORRODED ON MS21260 END FITTING WAS ALSO FOUND TO 	BE PITTED AND CORRODED.					1	L	7	1 	3O			 	2A13    					 
2002012500068	20020125	00068	SO  	2002	1	25	2001FA0000616    	1	20011129	G	5330		PANEL           			GULSTM	G1159 	GIV         	3980115	SO  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	464QS					1264				PANEL (107-CLB-5) LOCATED ON THE LOWER PORTION OF THE FUSELAGE PRESSURE VESSEL AFT OF THE MAIN WHEEL WELL CRACKING AROUN	D A VHF ANTENNA MOUNTING NUTPLATE ATTACHED TO THE PANEL.					2	L	7	2 	4F			RT	A12EA   					 
2002012500069	20020125	00069	CE  	2002	1	25	2001FA0000617    	1	20011130	G	2121	09040022	FAN             			CESSNA	425   	425         	2076018	CE  										COCKPIT FLOOR	FAILED          	B				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	5PP	30   				0198				AIRCRAFT RETURNED FROM FLIGHT WITH CABIN BLOWER OPERATING BUT NOT MOVING ANY AIR.  GAINED ACCESS TO BLOWER ASSEMBLY UNDE	R CO-PILOT FLOOR.  FOUND ALL FAN BLADES TO BE BROKEN OFF.  THIS IS THE SECOND TIME THIS HAS HAPPENED IN LESS THAN TWO MO	NTHS.  CHECKED MOTOR FOR SECURITY AND LOOSENESS, CHECKED GOOD.  CHECKED FAN HUB FOR SECURITY AND LOOSENESS ON MOTOR SHAF	T AND FOUND THAT IT WAS TIGHT.  INSTALLING TECHNICIAN SAID THAT HE SPECIFICALLY CHECKED FOR BLADE CLEARANCE AROUND HOUSI	NG WHEN THIS FAN WAS INSTALLED AND IT WAS FINE.  HIGHLY SUSPECT DEFECTIVE FAN BLADE AT MANUFACTURE.  RECOVERED ALL BROKE	N BLADES AND INSPECTED.  FOUND ONE WITH WHAT APPEARED TO BE A CLEAN BREAK AT BASE.  SUSPECT THAT ONE DEFECTIVE BLADE BRO	1	L	7	2 	3T			RT	A7CE    					 
2002012500072	20020125	00072	CE  	2002	1	25	2001FA0000618    	1	20011130	G	5510	17052	BRACKET         			PIPER 	PA23  	PA23150     	7102303	CE  										HORIZONTAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										AFTER REMOVING THE PAINT FROM THE ELEVATOR HINGE BRACKETS, DISCOVERED THAT BOTH ELEVATOR HINGE BRACKETS ON THE RIGHT SID	E OF THE HORIZONTAL STABILIZER WERE CRACKED THROUGH THE BEARING BORE BOSS, BETWEEN THE BORE AND THE OUTER EDGE OF THE BR	ACKET.  THE CAUSE OF THE CRACK IS UNKNOWN.				1	L	7	2 	3O			RT	1A10    					 
2002012500078	20020125	00078	SO  	2002	1	25	2001FA0000620    	1	20011203	G	3234		CONTROL HANDLE  			EMB   	120   	EMB120      	3260201	SO  										MLG	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										LANDING GEAR CONTROL LEVER FAILURE.						2	L	7	2 	4T			RT	A31SO   					 
2002012500087	20020125	00087		2002	1	25	2001FA0000621    	4	20011203	G	2210	065001790100	ROLL SERVO      			BEECH 	58    	58          	1152740	CE  										AUTO PILOT	MALFUNCTIONED   	C				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SO	05		378  	378  			TH1947				OPERATOR THAT ROLL CONTROL BECAME RESTRICTED AND DIFFICULT DURING FLIGHT. INVESTIGATION REVEALED THAT THE PRIMARY ROLL S	ERVO WAS FOUND TO BE CAUSING RESTRICTION TO CAPSTAN. THIS SERVO WAS REMOVED AND HAS AUDIBLE SOUND OF OBJECTS FLOATING LO	OSE INTERNALLY.				1	L	7	2 	3O			 	3A16    					 
2002012500088	20020125	00088	SW  	2002	1	25	2001FA0000622    	1	20011204	G	2820		LINE            			MOONEY	M20   	M20J        	5870219	SW  										FUEL SYSTEM	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21										MOONEY 201 M20J:   OWNER REPORTED LOW FUEL PRESSURE. FOUND AEROQUIP LINE LEAKING THROUGH BODY OF INNER TUBE STOCK. THIS 	LINE HAS A STAINLESS STEEL BRAID COVERING FULL LENGTH. HOSE HAD A CURE DATE 3RD QUARTER 1995 WITH MANUFACTURED DATE JAN 	1998. HOSE IS CONNECTED TO FUEL INJECTOR AND FUEL PRESSURE SENDER. HOSE WAS LEAKING SUBSTANCIAL AMOUNTS OF FUEL ABOVE EX	HAUST SYSTEM AND ENGINE OPERATION WAS NOT AFFECTED.			1	L	7	1 	3O			 	2A3     					 
2002012500089	20020125	00089		2002	1	25	2001FA0000623    	4	20011203	G	2210	065001790100	ROLL SERVO      			AMTR  	KITFOX	KITFOXIV    	05620EP	GL  										AUTO PILOT	MALFUNCTIONED   	C				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			NM	11	316R	378  								OPEREATOR ENCOUTERED RESTRICTED ROLL AUTHORITY. PRIMARY AP SERVO WAS FOUND TO BE CAUSING RESTICTED CAPSTAN MOVEMENT. SOU	NDS LIKE LOOSE PARTS AR FLOATING AROUND INSIDE SERVO BODY					1	H	7	1 	3I			NC	EXPA    					 
2001121000137	20011210	00137	SO  	2001	12	10	2001FA0000629    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	200HM					32R7680025				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001121000138	20011210	00138	SO  	2001	12	10	2001FA0000630    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	97CR	1075 				32R7780078				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001121000139	20011210	00139	SO  	2001	12	10	2001FA0000631    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	8506F	97   				32R7780107				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121000140	20011210	00140	SO  	2001	12	10	2001FA0000632    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	8506F	297  				32R7780107				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRACE.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121000141	20011210	00141	SO  	2001	12	10	2001FA0000633    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	8506F	93   				32R7780107				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121000142	20011210	00142	SO  	2001	12	10	2001FA0000634    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  										NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4352F	369  				32R7680441				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O			 	A3SO    					 
2001121000143	20011210	00143	SO  	2001	12	10	2001FA0000635    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  										NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4352F	103  				32R7680441				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O			 	A3SO    					 
2001121000144	20011210	00144	SO  	2001	12	10	2001FA0000636    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  										NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4352F	321  				32R7680441				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O			 	A3SO    					 
2001121000145	20011210	00145	SO  	2001	12	10	2001FA0000637    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	40449	153  				32R7780519				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121000146	20011210	00146	SO  	2001	12	10	2001FA0000638    	1	20011116	G	5280	3807601	BRACE           			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG DOOR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	40449	53   				32R7780519				INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT.  ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA	CE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2001121100013	20011211	00013	SO  	2001	12	11	2001FA0000639    	2	20011129	G	7414		DISTRIBUTOR BLK 			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1556A	449  			01040866	CE1318	820455R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M	AGNETO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001121100014	20011211	00014	SO  	2001	12	11	2001FA0000640    	2	20011128	G	7414		DISTRIBUTOR BLK 			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5530A	998  			00050438	CE1342	813779R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M	AGNETO.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001121100015	20011211	00015	SO  	2001	12	11	2001FA0000641    	2	20011128	G	7414		DISTRIBUTOR BLK 	SLICK       		BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5540P				01040863	CE1335	820456R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE	TO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.					1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001121100016	20011211	00016	SO  	2001	12	11	2001FA0000642    	2	20011129	G	7414		DISTRIBUTOR BLK 			BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520B      	17032	SO  					MAGNETO	FAILED          	B			VJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8240T	695  			00070052	CE1542	820387R			MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM.  REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK ASSEMB	LY FROM MAGNETO.  DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION.  NEW DISTRIBUTOR BLOCK ASSEMBLY, INSTALLED IN M	AGNETO.				1	L	7	1 	3O	3	O	 	3A15    	E5CE				 
2001121100017	20011211	00017		2001	12	11	2001FA0000643    	4	20011026	G	2561	FV353500137	LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07										LIFE VEST, TYPE FV-35.  MFG AVG 1986 FAILED THE MFG.  RECOMMENDED 2 PSI CELL TEST IAW MM.																			 
2001121100111	20011211	00111	CE  	2001	12	11	2001FA0000644    	1	20011130	G	6120		PIN             			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520*    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	PROPELLER	BROKEN          	B			FG6R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		NR	NOT REPORTED   	1			NM	11	30EE	5064 	1690 			414A0443		746886		PILOT NOTICED SEVERE VIBRATION IN LEFT ENGINE, SHUTDOWN AND ATTEMPTED FEATHER, WOULD NOT FEATHER, LANDED.  FOUND 1 BLADE	 IN FEATHER AND FREE TO ROTATE.  INSPECTION REVEALED 1 ACTUATING PIN HAD FRACTURED IN THREADS.  PIN HOLE IN FERRULE NOT 	DRILLED AND TAPPED DEEP ENOUGH TO ALLOW PIN TO TIGHTEN ON WASHER.  FATIGUE TO THREADS LED TO FAILURE.(K)				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001121100112	20011211	00112	NE  	2001	12	11	2001FA0000645    	3	20011107	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		28857	6741 					DR61587		PROPELLER RECEIVED FOR ROUTINE OVERHAUL.  AT TEARDOWN, FOUND BLADE (PN 6607132886  SN 2) CRACKED IN OUTER SLEEVE APPROXI	MATELY 2.5 INCHES LONG.  BLADE REJECTED FROM FURTHER SERVICE.															6	C	P30NE	 
2001121100113	20011211	00113	SO  	2001	12	11	2001FA0000646    	2	20011025	G	8530	652956	VALVE           			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470L       	17026	SO  					ENGINE	WORN            	B			CY4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	5670B	153  				33670	069841R			CYLINDER REMOVED DUE TO LOW COMPRESSION.  VALVE STEM WORN TO 0.005.						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001121100115	20011211	00115	NE  	2001	12	11	2001FA0000647    	3	20011129	G	6114	660714200	HUB             													ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27			7522 					DR6178587		PROPELLER RECEIVED FOR OVERHAUL.  AT TEAR DOWN, FOUND HUB ASSEMBLY CRACKED ON BLADE BEARING FACE AT HUB SPLIT LINE NR 4 	BLADE PORT.  HUB ASSEMBLY REJECTED FROM FURTHER SERVICE.															6	C	P30NE	 
2001121100116	20011211	00116	NE  	2001	12	11	2001FA0000648    	3	20011129	G	6111	6607132886	BLADE           													ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		25344	833  					DR694884		PROPELLER WAS REMOVED FROM AIRCRAFT TO CORRECT GREASE LEAK.  AT DISASSEMBLY, BLADE (SN 279) WAS FOUND TO BE CRACKED ON O	UTER SLEEVE AT ROOT END.  BLADE REJECTED FROM FURTHER SERVICE.															6	C	P30NE	 
2001121200091	20011212	00091	SO  	2001	12	12	2001FA0000649    	2	20010717	G	8530	SA52000A20P	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1500 					240860			CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121200092	20011212	00092	SO  	2001	12	12	2001FA0000650    	2	20010717	G	8530	SA52000A20P	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1500 					240860			CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121200093	20011212	00093	SO  	2001	12	12	2001FA0000651    	2	20010717	G	8530	SA52000A20P	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1500 					240860			CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121200094	20011212	00094	SO  	2001	12	12	2001FA0000652    	2	20010717	G	8530	SA52000A20P	CYLINDER        								CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1500 								CRACKED ON INTAKE AND EXHAUST SEATS.											3	O			E5CE				 
2001121200095	20011212	00095	SO  	2001	12	12	2001FA0000653    	2	20010717	G	8530	SA52000A20P	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1500 								CYLINDER CRACKED ON INTAKE AND EXHAUST SEAT.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121200096	20011212	00096	SO  	2001	12	12	2001FA0000654    	2	20010716	G	8530	SA52000A20P	CYLINDER        			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		1648 					240860			CYLINDER CRACKED ALL THE WAY AROUND AT THE VALVE SEAT LINE AND BURNED THROUGH THE EXHAUST PORT SIDE.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121200097	20011212	00097	EA  	2001	12	12	2001FA0000655    	2	20011106	G	8520	77672	LIFTER          			BEECH 	60    	60          	1153602	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					ENGINE	SPALLED         	B			EKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	33LB	132  				P74	L104559			UPON REMOVAL OF PUSH RODS AND PUSH ROD TUBES FOR RESEAL.  THE LIFTERS WERE REMOVED FOR BLEEDING.  THE LIFTERS WERE INSPE	CTED AND WERE FOUND TO HAVE SEVERE SPALLING.  MFG WAS NOTIFIED AND ENGINES ARE TO BE REMOVED AND SENT BACK FOR REPAIR.  	ENGINES HAVE 132.4 HOURS TT.  CAMSHAFT IS ALSO WORN.				1	L	7	2 	3O	3	O	 	A12CE   	E10EA				 
2001121200098	20011212	00098		2001	12	12	2001FA0000656    	4	20011126	G	6122	A21107	IDLER GEAR      	MCAULY      		CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470*       	17026	SO  					PROP GOVERNOR	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	2544R				70647	18258244				RELEVANT INDICATION. (CRACK)						1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2001121300084	20011213	00084	EA  	2001	12	13	2001FA0000657    	2	20011130	G	7414	M3007	IMPULSE COUPLING	SLICK       		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					LT & RT MAGNETOS	WORN            	D			UL9G	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	6436P					15285013	L2223415			INSTALLED NEW M3007 IMPULSE COUPLINGS ON BOTH MAGNETOS.  BOTH COUPLINGS CAME OUT OF BOXES DATED 5/25/01.  INITIAL OPERAT	ION WAS FINE.  IMPULSE COUPLINGS INTERMITTENT SNAPPING. REMOVED MAGNETOS, INSPECTED COUPLINGS PAWLS SHOWED NOTICEABLE WE	AR AT CONTACT POINT WITH STRIKER PIN.  ALSO LOOSENESS AT PIVOT PIN ATTACH.  SUSPECT BAD BATCH OF METAL OR HEAT TREATMENT	.  INSTALLED NEW IMPULSE COUPLING ASSEMBLIES OPERATIONAL CHECK,  FINE. DEFECTIVE IMPULSE COUPLINGS TIME IN SERVICE 93 HO	URS/ 119 HOURS		1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001121400057	20011214	00057	CE  	2001	12	14	2001FA0000658    	1	20011103	G	7160	BA8110	GASKET          			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470U       	17026	SO  					AIR FILTER	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	20379	450  				18053185				THIS AIR FILTER ASSEMBLY HAS THE MANUFACTURING DEFECT DESCRIBED IN AD. WITH THE GASKET COMING LOOSE.  FOUND IT DURING AN	NUAL INSPECTION AND DISCOVERED THAT IT (BA 8110) IS NOT COVERED BY THE AD.					1	H	7	1 	3O	3	O	 	5A6     	E273				 
2001121400058	20011214	00058	SO  	2001	12	14	2001FA0000659    	1	20011204	G	2720	9621200	TORQUE TUBE     			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360*    	17025	SO  					RUDDER	DAMAGED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K	4230 				347970096				WHILE INSPECTING RUDDER ON ANNUAL INSPECTION THE INSPECTOR FOUND LOOSENESS AT THE RUDDER TORQUE TUBE ATTACH BOLTS.  TEAR	DOWN INSPECTION SHOWED BOLT HOLES OVERSIZE AND ELONGATED.  NEW PARTS INSTALLED BECAUSE (AN 174) BOLTS WERE LARGEST SIZE 	BOLTS PERMITTED.  MFG SB REFERS TO THIS PROBLEM.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001121400059	20011214	00059	SO  	2001	12	14	2001FA0000660    	1	20011204	G	5210	47958008	SNUBBER         			PIPER 	PA31T 	PA31T       	7103124	SO  										CABIN DOOR	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	311AC	10   				31T8120016				RECEIVED 2 DIFFERENT SNUBBERS AND INSTALLED.  NEITHER HAD ANY SNUBBING ACTION.  NEW PARTS FROM THE FACTORY.						1	L	7	2 	3T			 	A8EA    					 
2001121400073	20011214	00073	CE  	2001	12	14	2001FA0000661    	1	20011120	G	3710	CH442CW8	COUPLING        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					VACUUM PUMP	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	2741R	230  				340A0922	503320			PNEUMATIC PUMP COUPLING SHEARED AFTER 230.7 HOURS OF OPERATION.						1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001121400074	20011214	00074	CE  	2001	12	14	2001FA0000662    	1	20011011	G	3710	CH442CW8	PUMP            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					PNEUMATIC SYS	SHEARED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	02	2741R	113  				340A0922	519294			PNEUMATIC PUMP SHEARED AFTER 113 HOURS OF OPERATION.  PUMP COULD BE ROTATED WHEN REMOVED. COUPLING SHOWED SIGNS OF HEAT 	(MELTED EDGES).					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001121700078	20011217	00078	SO  	2001	12	17	2001FA0000664    	1	20011118	G	2720	408424	RUDDER PEDAL    			PIPER 	PA18  	PA18135     	7101820	SO  										COCKPIT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	9952Q	3700 				183579				DURING DISASSEMBLY FOR REBUILD ALL AND RUDDER PEDALS WERE FOUND TO BE DAMAGED DUE TO THE RETURN SPRING(40494100) CUTTING	 THROUGH LOWER HINGE SHAFT, WALL.  ALL HAD BEEN WELD REPAIRED BUT WERE AGAIN WORN THROUGH, ALL REPLACED NEW AND APPEAR T	O HAVE SAME WALL THICKNESS.  AS THE WEAR PROGRESSES THE POTENTIAL FOR BINDING EXISTS.				1	H	7	1 	3O			 	1A2     					 
2001121700079	20011217	00079	SO  	2001	12	17	2001FA0000665    	1	20011118	G	2720	404825	RUDDER PEDAL    			PIPER 	PA18  	PA18135     	7101820	SO  										COCKPIT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	9952Q	3700 				183579				DURING DISASSEMBLY FOR REBUILD ALL 4 RUDDER PEDALS WERE FOUND TO BE DAMAGED DUE TO THE RETURN SPRING (40941-00) CUTTING 	THROUGH LOWER HINGE SHAFT WALL.  ALL 4 HAD BEEN WELD REPAIRED BUT WERE AGAIN WORN THROUGH.  ALL REPLACED NEW AND APPEAR 	TO HAVE SAME WALL THICKNESS.  AS THE WEAR PROGRESSES THE POTENTIAL FOR BINDING EXISTS.				1	H	7	1 	3O			 	1A2     					 
2001121700080	20011217	00080	SO  	2001	12	17	2001FA0000666    	1	20011204	G	5343	95554000	BRACKET         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	66BL					347250285				DURING PERFORMANCE OF 100 HOUR INSPECTION AND COMPLIANCE WITH AD.  DURING GEAR RETRACTION NOTICED MOVEMENT OF NOSE GEAR 	SUPPORT CENTER ATTACH BOLT.  AFTER INVESTIGATION AND INSTALLATION OF ACCESS PANEL ON BELLY OF AIRCRAFT FOUND BRACKET PAR	T 95554-000 LOOSE AND WORN EXCESSIVELY INSTALLED NEW FACTORY PARTS.  AIRCRAFT TOTAL TIME 9750.2				1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2001121700081	20011217	00081	SO  	2001	12	17	2001FA0000667    	1	20011204	G	5343	95554000	BRACKET         			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	1056U					347250040				DURING PERFORMANCE OF 100 HOUR INSPECTION AND COMPLIANCE WITH AD.  DURING GEAR, RETRACTION NOTICED MOVEMENT, OF NOSE GEA	R SUPPORT CENTER ATTACH BOLT AFTER INVESTIGATION AND INSTALLATION OF ACCESS PANEL ON BELLY OF AIRCRAFT FOUND BRACKET PAR	T 95554-000 CRACKED AND FITTING PART 95555-000 LOOSE AND WORN EXCESSIVELY.  INSTALLED NEW FACTORY PARTS AIRCRAFT.  TOTAL	 TIME 4793.9			1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2001121700082	20011217	00082	SO  	2001	12	17	2001FA0000668    	2	20011201	G	8530		EXHAUST VALVE   			CESSNA	207   	207A        	2073604	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	STUCK           	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AL	05	17GN					20700693				EXHAUST VALVE APPARENTLY STUCK OPEN, WAS STRUCK BY PISTON AND IN TURN SLIGHTLY BENT AT THE STEM.  THIS INADVERTENTLY CAU	SE THE VALVE TO STICK IN A CLOSED POSITION THERE BY BENDING THE EXHAUST PUSHROD SLIGHTLY.					1	H	7	1 	3O	3	O	 	A16CE   	E5CE				 
2001121700083	20011217	00083	CE  	2001	12	17	2001FA0000669    	1	20011201	G	3060	26700696	RESISTOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6*        	52043	EA  					PROP ANTI-ICE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	715HE					208B0603				PROPELLER ANTI-ICE VARISTOR MELTED PLUGS.  PLUGS SEEM TO OPEN AND WEAR CAUSING INTERMITTENT POWER TO BRUSH BLOCK, DUE MO	ST LIKELY TO VIBRATION.  CHANGING CONNECTORS WOULD FIX PROBLEM.					1	H	7	1 	3T	3	T	 	A37CE   	E2NE				 
2001121900081	20011219	00081	CE  	2001	12	19	2001FA0000670    	1	20011120	G	3211		FRAME           			BEECH 	76    	76          	1153005	CE  										RT MLG	CRACKED         	B			ZM3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	819ER	4724 				ME199				DURING ANNUAL INSPECTION, THE RIGHT MAIN LANDING GEAR A-FRAME WAS FOUND CRACKED HALF WAY AROUND THE CIRCUMFERENCE OF THE	 A FRAME TUBE IN THE AREA WHERE RECURRING INSPECTION WAS REQUIRED BY AD.  THIS A-FRAME DID NOT REQUIRE RECURRING INSPECT	ION BECAUSE IT WAS (PN 105-810023-76) WHICH ELIMINATED THE RECURRING INSPECTION REQUIREMENT.  THE A-FRAME HAD 4724.2 HRS				1	L	7	2 	3O			 	A29CE   					 
2001121900082	20011219	00082	SO  	2001	12	19	2001FA0000671    	1	20011114	G	7820		MUFFLER         			MAULE 	MX7   	MXT7180A    	5460187	SO  	LYC   	O340  	O340*       	41510	EA  					ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	54CH	300  				21028C	3562336A			WELD SHOULD BE INSPECTED EACH 100 HOURS OR EVERY OIL CHANGE.  CRACK COULD BRING EXHAUST GAS INTO CABIN.  POOR DESIGN OF 	MUFFLER AND NOT SUPPORTED PROPERLY.					1	H	7	1 	3O	3	O	NC	3A23    	E277				 
2002012500090	20020125	00090	CE  	2002	1	25	2001FA0000672    	1	20011129	G	5320		EYEBOLT         			CESSNA	170   	170B        	2072306	CE  	LYC   	O340  	O340*       	41510	EA  					FUSELAGE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	01	4669C					25613				FLOAT EQUIPPED, LIFTING EYES WERE INSTALLED IN THE WRONG POSITION.  RESULTING IN DRILLING THROUGH THE MAIN FORWARD WING 	SPAR AND LEAVING APPROXIMATELY EDGE DISTANCE.  BETWEEN THE FORWARD SPAR ATTACH BOLT AND EDGE OF SPAR. (EYES SHOULD BE IN	SIDE CABIN TOP RIVET LINE) (K)				1	H	7	1 	3O	3	O	 	A799    	E277				 
2001121900083	20011219	00083	NM  	2001	12	19	2001FA0000673    	1	20011108	G	2730	401611557	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										FEEL CONTROL	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					335					HOUSING ASSEMBLY HAS HEAVY PITTING AND CORROSION IN THE BOLT HOLES, PORTS, CAP ASSEMBLIES AND ON THE SEALING SURFACES.  	DISSIMILAR METAL CORROSION.					2	L	7	3 	4F			RT	A3WE    					 
2001121900084	20011219	00084	NM  	2001	12	19	2001FA0000674    	1	20011112	G	2730	401611565	HOUSING         	MOOG        		BOEING	727   	727*        	       	NM  										FEEL CONTROL	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					335					ELBOW HOUSING HAS SEVERE CORROSION IN THE BOLT HOLES, CHECK VALVE PORT, PACKING LANDS AND ON THE SEALING SURFACE.  DISSI	MILAR METAL CORROSION.					2	L	7	3 	4F			RT	A3WE    					 
2001121900085	20011219	00085	NM  	2001	12	19	2001FA0000675    	1	20011112	G	2730	4016146202	CAP             	MOOG        		BOEING	727   	727*        	       	NM  										FEEL CONTROL	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					335					CAP ASSEMBLY HAS SEVERE CORROSION IN THE PACKING GROOVE, THE INTERIOR AND EXTERIOR SURFACES.  DISSIMILAR METAL CORROSION	.					2	L	7	3 	4F			RT	A3WE    					 
2001121900086	20011219	00086	NM  	2001	12	19	2001FA0000676    	1	20011112	G	2730	4016146302	CAP             	MOOG        		BOEING	727   	727         	UTILSYS	NM  										FEEL CONTROL	CORRODED        	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					335					CAP ASSEMBLY HAS SEVERE CORROSION IN THE PACKING GROOVE, THE INTERIOR AND EXTERIOR SURFACES.  DISSIMILAR METAL CORROSION	.					2	L	7	3 	4J			RT	A3WE    					 
2002012500091	20020125	00091	NM  	2002	1	25	2001FA0000677    	1	20011108	G	3220	4400612	COIL            	PLESSEY     		BOEING	727   	727*        	       	NM  										MOTOR BRAKE	SHORTED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			901  		21201					BRAKE COILS ARE SHORTED AND BURNED.  UNDER NORMAL OPERATION THE VIBRATION INCURRED HAS BEEN FOUND TO CAUSE ABRADING BETW	EEN THE BRAKE COILS AND STUDS WHICH RESULTS IN A SHORT AND ARCING OF THE BRAKE COILS.  REDUCE THE SIZE OF THE COIL WINDI	NGS OR DIAMETER OF THE STUDS TO ALLOW FOR GREATER CLEARANCE BETWEEN THE TWO.   (NOTE:  THIS MALFUNCTION APPLIES TO BOTH 	NEW AND REWOUND COIL ASSEMBLIES.			2	L	7	3 	4F			RT	A3WE    					 
2002012500092	20020125	00092	NM  	2002	1	25	2001FA0000678    	1	20011108	G	3220	4400613	COIL            	PLESSEY     		BOEING	727   	727*        	       	NM  										MOTOR BRAKE	SHORTED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			901  		21201					BRAKE COILS ARE SHORTED AND BURNED.  UNDER NORMAL OPERATION THE VIBRATION INCURRED HAS BEEN FOUND TO CAUSE ABRADING BETW	EEN THE BRAKE COILS AND STUDS WHICH RESULTS IN A SHORT AND ARCING OF THE BRAKE COILS.  REDUCE THE SIZE OF THE COIL WINDI	NGS OR DIAMETER OF THE STUDS TO ALLOW FOR GREATER CLEARANCE BETWEEN THE TWO.				2	L	7	3 	4F			RT	A3WE    					 
2001123100160	20011231	00160	NM  	2001	12	31	2001FA0000679    	1	20011120	G	3240	511531	HOUSING         			BOEING	737   	737*        	       	NM  										SHUTTLE VALVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING IS CRACKED INSIDE ONE OF THE BOLT MOUNTING HOLES.  FATIGUE, DEFECT IN THE IN THE CASTING OF THE HOUSING AND /OR 	OVERTORQUING OF BOLT ON INSTALLATION.					2	L	7	2 	4F			RT	A16WE   					 
2001123100161	20011231	00161	NM  	2001	12	31	2001FA0000680    	1	20011120	G	2923	654468311	HOUSING         			BOEING	737   	737*        	       	NM  										HYDRAULIC SYS	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING CRACKED IN PORT NR 1 WHILE APPLYING PRESSURE DURING TESTING.  HOUSING HAD LIQUID PENETRANT INSPECTION ACCOMPLISH	ED PRIOR TO TESTING, WITH NO DEFECTS NOTED.  MATERIAL THICKNESS OF PORT NR 1 IS THIN.  FATIGUE AND POSSIBLY THE INSTALLA	TION AND TORQUING OF THE FITTING COULD CONTRIBUTE OVER A PERIOD OF TIME.				2	L	7	2 	4F			RT	A16WE   					 
2001123100162	20011231	00162	CE  	2001	12	31	2001FA0000681    	1	20011126	G	5312	04500391791	BULKHEAD        			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200*       	17020	SO  					FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	6937F	350  				15063537				SINCE MFG. WENT TO PLASTIC BULKHEAD, THEY CRACK ABOUT EVERY 200 HOURS.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002012500093	20020125	00093	SO  	2002	1	25	2001FA0000682    	2	20010614	G	8550	640849	COVER           			SWFTMS	GC1B  	GC1B        	9230104	SO  	CONT  	C125  	C125        	17011	SO  					OIL FILTER	FAILED          	D				A				UNSCHED LANDING         				K	Y	J	FLUID LOSS                	ENGINE STOPPAGE           	WARNING INDICATION        	NR	NOT REPORTED   	1			NM	13	2432B					3732	62791R			WHILE AIRCRAFT WAS IN FLIGHT ALL ENGINE OIL WAS PUMPED OVERBOARD CAUSING CATASTROPHIC ENGINE FAILURE.  LOSS OF ENGINE OI	L WAS DUE TO FAILURE OF THREADS ON MAGNESIUM CRANKCASE COVER ASSEMBLY.  THE THREADS FAILED WHERE THE OIL FILTER ADAPTER 	THREADS INTO THE CRANKCASE COVER ASSEMBLY.  TO PREVENT REOCCURRENCE, REMOVE THREADED TYPE CONTINENTAL OIL FILTER ASSEMBL	Y FROM SERVICE.			1	L	7	1 	3O	3	O	NC	A766    	E236				 
2001123100163	20011231	00163	CE  	2001	12	31	2001FA0000683    	1	20011211	G	5610	NH2401691	WINDOW          			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					COCKPIT	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	910JD	655  				258420				WINDOW DELAMINATED AT THE CENTER HEATING ELEMENT.  POSSIBLE SHORT AT INTERNAL WIRING TO HEATING ELEMENT.  THE DELAMINATI	ON AREA IS IN THE BOTTOM CENTER.  THE UNIT IS BEING SENT TO MFG FOR FURTHER EVALUATION.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001123100164	20011231	00164	SO  	2001	12	31	2001FA0000684    	2	20011204	G	7414	10357586	DISTRIBUTOR GEAR	CONT        		CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					MAGNETO	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			NM	05	402NQ				K099814ER	402C0093				AT FIRST POWER REDUCTION AFTER TAKE OFF RIGHT ENGINE STARTED RUNNING ROUGH.  PILOT SUSPECTED A MAGNETO AND ISOLATED PROB	LEM TO THE RIGHT MAGNETO.  PILOT RETURNED TO THE AIRPORT WITH RIGHT ENGINE RUNNING ON JUST THE LEFT MAGNETO.  UPON REMOV	AL AND DISASSEMBLY OF MAGNETO, THE DISTRIBUTOR GEAR WAS FOUND WITH BROKEN TEETH AND NOT TURNING, RESULTING IN THE MAGNET	O FAILING TO FUNCTION, NO OTHER DEFECTS FOUND.  DISASSEMBLED LEFT MAGNETO AND NO FAULTS FOUND, POINTS CHECKED GOOD AND N	O ADJUSTMENTS NEEDED.  NO REASON FOUND FOR FAILURE OF DISTRIBUTOR GEAR IN RIGHT MAGNETO.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001123100165	20011231	00165	EA  	2001	12	31	2001FA0000685    	2	20011211	G	8530		VALVE SEAT      			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					ENGINE	LOOSE           	G				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	17	123MT					1063				NUMBER 4 CYLINDER HAD AN INTAKE VALVE SEAT COME LOOSE AND THE PISTON HAD BROKEN RINGS.  SUBSEQUENT LOSS OF POWER.						1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2001123100166	20011231	00166	CE  	2001	12	31	2001FA0000686    	1	20011211	G	2510	05142132	CYLINDER        			CESSNA	172   	172R        	2072401	CE  										SEAT	FAILED          	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	181MW	3500 				17280181				SEAT LOCK CYLINDER FAILED TO LOCK IN POSITION WITH NORMAL SEATBACK PRESSURE.  CABLE ADJUSTMENT WITHIN LIMITS.  FAILURE O	CCURRED DURING NORMAL USE.					1	H	7	1 	3O			NT	3A12    					 
2002012500095	20020125	00095	EU  	2002	1	25	2001FA0000687    	1	20010628	G	7830		BRACKET         			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					T/R DOOR	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SO	11	500AF	7225 				170				AFTER LANDING, THE CREW TRIED TO STOW THE THRUST REVERSER HAD A TRANSIT LIGHT ON IN THE COCKPIT.  A VISUAL INSPECTION  R	EVELED THE RIGHT THRUST REVERSER DOOR (PN C41B30212-39 SN 2287) HINGE ARM HAD BROKE BETWEEN THE LOWER HINGE BEARING AND 	THE DOOR.  ALSO DAMAGED WERE A SUPPORT BRACKET (PNF50B583001024) AND THE RIGHT UPPER BUSHING.  A NEW BRACKET WAS INSTALL	ED AND THE BUSHING WAS REPLACED WITH AN OVERSIZED BUSHING.  A ROD BEARING AND ALL HINGE BOLTS FOR BOTH LEFT AND RIGHT DO	ORS WERE REPLACED.  2 OTHER CASES OF CRACKS WERE FOUND IN THE AREA OF OUT THRUST REVERSER HINGE FAILURE.  THE PROBABLE C	AUSE FOR FAILURE WAS FATIGUE.	2	L	7	3 	4F	4	F	 	A46EU   	E6WE				 
2001123100167	20011231	00167	CE  	2001	12	31	2001FA0000688    	2	20010316	G	7314	LW15473	PUMP            								CONT  	IO360 	IO360*      	17025	CE  					ENGINE	FAILED          	C			XBTR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	15							966336A			ON 16 MAR O1 BPA RETURNED TO SERVICE (PN IO360, SN 966336A) AFTER SATISFACTORY TEST AFTER OVERHAUL.  THE ENGINE WAS SUBS	EQUENTLY INSTALLED AT ANOTHER FACILITY.  THE MECHANIC NOTIFIED US BY PHONE THAT FUEL WOULD NOT FLOW THRU THE FUEL PUMP E	VEN WITH THE USE OF THE WOBBLE PUMP, THAT FUEL PRESSURE FROM THE WOBBLE PUMP WAS AVAILABLE AT THE ENGINE NEW AT INSTALLA	TION IN FACILITY AND IS AFFECTED BY SB.  THIS IS IN DIRECT CONFLICT WITH THE FIELD REPORTS OF FAILURE QUOTED ABOVE.  THI	S IS A DEFINITE SAFETY OF FLIGHT ITEM.  COMPLETE STOPPAGE OF THE ENGINE CAN AND IS LIKELY TO OCCUR WITH NO REMEDIAL ACTI	ON AVAILABLE TO THE PILOT.						3	O			E1CE				 
2002011700038	20020117	00038		2002	1	17	2001FA0000689    	4	20011024	G	6122		LINE            			CESSNA	208   	208         	2073702	CE  										ENGINE	CRACKED         	A			HSYA	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			NM	05	903FF					B0003				AIRCRAFT WOULD NOT MAKE TAKEOFF POWER, RESULTED IN RTO.  CRACKED PY LINE BETWEEN FUEL CONTROL AND PROP GOV.  REMOVED AND	 REPLACED PY RIGHT LINE GOING TO PROP AND PERFORMED A SUCCESSFUL OPERATIONAL AND LEAK CHECK.  (M)					1	H	7	1 	3T			NT	A37CE   					 
2002011600149	20020116	00149	SO  	2002	1	16	2001FA0000690    	1	20011113	G	2910		HYDRAULIC LINE  			EMB   	120   	EMB120ER    	3260203	SO  										HYDRAULIC SYS	CHAFED          	A			HSYA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			NM	05	223AS					120021				BLUE HYDRAULIC FLUID LOSS.  BLUE SYSTEM HYDRAULIC LINE CHAFFED THROUGH.  REPAIRED LINE WITH PERMISSIVE IAW EMB-120 MM 20	-10-01 AND A SUCCESSFUL LEAK CHECK WAS PERFORMED.  (M)					2	L	7	2 	4T			RT	A31SO   					 
2001123100168	20011231	00168		2001	12	31	2001FA0000691    	4	20011214	G	3422	6446	FLUX DETECTOR   			PIPER 	PA46  	PA46500TP   	7104622	SO  	PWA   	PT6   	PT6*        	52043	EA  					DIRECTIONAL SYS	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	164ST					4697064				AFTER 10-30 HOURS OF AIRCRAFT OPERATION FLUX VALVE IS FAILING.  SUSPECT THE PROBLEM IS VIBRATION RELATED.  NEED TO REPLA	CE HORIZONTAL STABILIZER IF PROBLEM CANNOT BE ISOLATED.					1	L	7	1 	3O	3	T	RT	A25SO   	E2NE				 
2002020100020	20020201	00020	EA  	2002	2	1	2002F00003       	1	20010911	G	5320	858947	SUPPORT         			CNDAIR	CL604 	CL604       	1900301	EA  										WATER SEP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	TCDHE					5358				THE FLANGE OF THE WATER SEPARATOR SUPPORT ASSEMBLY WAS CRACKED IN TWO PLACES.						2	L	7	2 	4F			RT	A21EA   					 
2002020100021	20020201	00021	NE  	2002	2	1	2002F00036       	3	20011218	G	6111	RFC11M1R6A	BLADE           													HAMSTD	14RF	14RF9       	NE  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			3085 							TWO CRACK INDICATIONS ON THE BLADE SHANK. ONE IN THE FILLET AREA AND THE OTHER IN THE BLADE BUTT AREA.  INDICATIONS WERE	 PARALLEL AND 2 TO 3 INCHES IN LENGTH.															6	C	P11NE	 
2002012500100	20020125	00100	GL  	2002	1	25	2002FA0000000    	3	20011212	G	6114	D4883C55	HUB             													MCAULY	2AF34C	2AF34C55    	GL  	PROPELLER	CRACKED         	B			ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15								815861		DURING INSPECTION HUB WAS FOUND TO BE CRACKED IN THREADS.  HUB HAS BEEN SCRAPPED.																5	C	P5EA	 
2002012500102	20020125	00102	SO  	2002	1	25	2002FA0000001    	2	20011113	G	8530	35967	SEAT            								CONT  	O520  	IO520*      	17032	SO  					ENG CYLINDER	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		116  					818927R			FOUND SEAT CRACKED DURING CLYINDER INSPECTION AT 116.7 HOURS SINCE FACTORY REMANUFACTURE.											3	O			E5CE				 
2002012500103	20020125	00103	SO  	2002	1	25	2002FA0000002    	1	20011129	G	3411		PITOT LINE      			PIPER 	PA28  	PA28181     	7102807	SO  										LEFT WING	DETERIORATED    	B			NS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	35	9290N	481  				2843108				DURING 24 MONTH IFR RECERTIFCATION, STATIC SYSTEM HAD WIDE OPEN LEAK.  DURING TROUBLESHOOTING, PITOT SYSTEM FOUND TO HAV	E WIDE OPEN LEAK ALSO.  FOUND BOTH HOLES SPLIT AND DETERIORATED AT JUNCTION FROM PITOT/STATIC PROBE TO METAL LINES IN LE	FT WING.  NOTE: THIS AIRCRAFT IS LOCATED IN HIGH CORROSION ENVIRONMENT (SALT AIR).  SUGGEST USE OF FUEL LINE, INSTEAD OF	 VACCUM LINE.			1	L	7	1 	3O			 	2A13    					 
2002012500104	20020125	00104	CE  	2002	1	25	2002FA0000003    	1	20011127	G	7714	S25502	CABLE           			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					TACHOMETER	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	917MA	1139 				172S8270				TACHOMETER CABLE BROKE, JUST AFT OF ENGINE.						1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002012500105	20020125	00105	SW  	2002	1	25	2002FA0000004    	1	20011216	G	8011	S8111	CONTACTOR       			BBAVIA	402   	402CHAMP    	2110204	SW  	CONT  	O200  	O200A       	17020	SO  					FIELD COIL	BROKEN          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9957Y	32   				40213				UNABLE TO OPERATE AIRCRAFT.  STARTER CONTACTOR RELAY INOPERATIVE UPON DISASSEMBLY,  FOUND FIELD COIL WIRE WHERE IT ATTAC	HES TO POSITIVE CONNECTOR BROKEN OFF.					1	L	7	2 	3O	3	O	 	A3CE    	E252				 
2002012500106	20020125	00106	CE  	2002	1	25	2002FA0000005    	1	20011220	G	7602	63255536	ARM             			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360GB     	17025	SO  					MIXTURE CONTROL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	1258S					33701894	352804			DURING ANNUAL INSPECTION FOUND MIXTURE ARM ROD END ATTACHING BOLT LOOSE.  ATTEMPTED TO TIGHTEN BOLT BUT FOUND THERE WAS 	STILL PLAY.  DISASSEMBLED ROD END ATTACHING BOLT AND A STEEL SERRATED BEARING INSERT FELL OUT OF THE BRONZE MIXTURE ARM.	  THIS WAS CAUSED BY THE ROD END ATTACHING BOLT BEING TOO LOOSE.  SPHERICAL BALL ROD END ATTACHING BOLTS SHOULD BE TIGHT	 TO ALLOW THE ROD END TO ROTATE AROUND THE BALL.			1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2002012500107	20020125	00107	CE  	2002	1	25	2002FA0000006    	1	20011201	G	3220	22430151	CLAMP           			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540*       	41532	EA  					SHIMMY DAMPER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	737HU					R18200832				THIS CLAMP HOLDS THE SHIMMY DAMPNER IN POSITION ON THE NOSE GEAR BARRELL WITH A PIN WELDED INSIDE THE CLAMP.  PIN WAS FO	UND BROKEN AND THIS ALLOWED THE CLAMP TO SHIFT WHICH CAUSED THE SHIMMY DAMPNER TO HIT THE GEAR WELL AND SOME TIMES LOCK 	THE GEAR IN THE UP POSITION.  A SLIP MARK HELPS TO FIND THIS PROBLEM ON PREFLIGHT INSPECTION AND ANNUALS.  I DO NOT THIN	K THIS PIN GETS BROKEN IN NORMAL USE BUT COULD VERY EASILY BE BROKEN BY USE OF A LARGE TUG.			1	H	7	1 	3O	3	O	 	3A13    	E295				 
2002012500108	20020125	00108	EA  	2002	1	25	2002FA0000007    	2	20011215	G	7322	78A110	LOCK            	PRECISION   		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					CARB BOWL	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			20   							CARBURETOR BOWL SCREWS LOOSE WITH TAB LOCKS IN PLACE.  LOCKS DO NOT HELP SCREWS SECURELY LETTING SCREW LOOSEN SLIGHTLY C	AUSING POOR RUNNING ENGINE AND FUEL LEAK, POTENTIAL FIRE HAZARD.   IMPROVE FIT OF LOCK TO HOUSING.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002012500109	20020125	00109	CE  	2002	1	25	2002FA0000009    	1	20011212	G	3230		GEARBOX         			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					MLG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	5403M	17891				402B0003				DURING GEAR EXTENSION,  PILOT REPORTED A LOUD NOISE.  REPORTED 3 GREEN LIGHTS FOR DOWN AND LOCK GEAR INDICATION, AND EME	RGENCY LANDING ASSISTANCE WAS REQUESTED, AIRCRAFT LANDED SAFELY AND TAXIED TO THE MAINTENANCE FACILITY, UPON INSPECTION 	OF THE LANDING GEAR SYSTEM, THE REDUCTION GEAR UNIT WAS FOUND TO BE WORN AND THE CAUSE OF THE LOUD NOISE.  TOOTHED PART 	OF THE UNIT WAS REPLACED GEAR UP AND DOWN.  CHECKS WERE PERFORMED, IAW MM AND FOUND TO BE IN LIMITS.  AIRCRAFT LOG BOOK 	ENTRY WAS MADE AND RELEASED TO SERVICE.		1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002012500110	20020125	00110	SO  	2002	1	25	2002FA0000010    	2	20011210	G	8530	534398	EXHAUST ROCKER  			CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	02	42862	189  				18259222				THE INSTALLED EXHAUST ROCKERS WERE PN 534398.  THEY EXPLAINED THAT THOSE ROCKERS DID NOT HAVE THE HOLE DRILLED TO SQUIRT	 OIL ON THE EXHAUST VALVE STEM.  THE NEW EXHAUST ROCKER HAS THAT SQUIRTER HOLE TO AID IN LUBRICATION.  THIS WAS CAUSE OF	 FAILURE, PER MFG.  NEW EXHAUST ROCKER IS PN 641682 (2 PIECE BUSHING) OR PN 652130 (1 PIECE BUSHING). SOME REPAIR SHOPS 	MODIFY OLD PART NUMBER ROCKER ARM BY DRILLING THE SQUIRTER HOLE.  OLD ROCKER ARMS (PN 534398) WERE INSTALLED IN THE ENGI	NE FOR AT LEAST THE PREVIOUS 1400 HOURS PRIOR TO THE OVERHAUL AND DID NOT CAUSE PREMATURE VALVE OR GUIDE WEAR.		1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012500111	20020125	00111	SO  	2002	1	25	2002FA0000011    	2	20011210	G	8530	643767	GUIDE           			CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  					CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	42862	189  				18259222				COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS.  REMOVED CYLINDERS AND DIMENSIONALLY  INSPECTING 	VALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012500112	20020125	00112	SO  	2002	1	25	2002FA0000012    	2	20011210	G	8530	652956	VALVE           	CONT        		CESSNA	182   	182L        	2072726	CE  	CONT  	O470  	O470R       	17026	SO  					CYLINDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	42862	189  				18259222				COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS.  REMOVED CYLINDERS AND DIMENSIONALLY INSPECTING V	ALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012500113	20020125	00113	CE  	2002	1	25	2002FA0000013    	1	20011112	G	7120	45A34361005	MOUNT           			BEECH 	MU300 	400A        	1155402	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	712TA	2799 				RK186				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION,  INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT TO BE CRACKED.						2	H	7	2 	4F	4	F	RT	A16SW   	E25EA				 
2002012500114	20020125	00114	EA  	2002	1	25	2002FA0000015    	2	20011024	G	8520	75089	PISTON          								LYC   	O320  	O320D2G     	41508	EA  					ENGINE	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01										DURING INSTALLATION OF NEW PISTON AND RINGS.  IT WAS NOTED THAT ONE OF THE PISTONS WOULD ONLY SLIDE INTO THE BARREL HALF	 WAY.  PISTON SKIRT OD WERE CHECKED, OK AT 5.1175 OD.  THE PROBLEM WAS FOUND TO BE THE OD OF THE PISTON JUST BELOW THE P	ISTON PIN WAS MEASURED TO BE 5.1255 ON THE PISTON THAT DID NOT FIT, THIS IS MUCH LARGER THAN THE SAME OD OF PISTONS THAT	 DID FIT WHICH WAS MEASURED TO BE 5.1025.								3	O			E274				 
2002012500115	20020125	00115	EU  	2002	1	25	2002FA0000016    	1	20011211	G	2910		HOSE            			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					HYD SYSTEM	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	731DL					NA0234				HEAVY CORROSION BUILD UP UNDER OUTER PLASTIC SLEEVE ON EXTERIOR HYDRAULIC SYSTEM FLEX HOSES MOSTLY IN THE LANDING GEAR A	REA DUE TO WATER OR DISSIMILAR METAL.  THIS ONLY NOTED ON 700 SERIES AIRCRAFT.  REC. SB OR SL TO LOOK FOR BULGING AT MET	AL BRAID HOSE WHERE HOSE MEETS THE  (B) NUT FITTING.				2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2002012500118	20020125	00118	EU  	2002	1	25	2002FA0000017    	1	20011214	G	3230	259UM95	TORQUE LINK     			BRAERO	1000  	HAWKER1000  	7450005	EU  										MLG	CRACKED         	B			RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03										DURING OVERHAUL, INSPECTION PROCESSES ARE IDENTIFYING CRACKS IN THE FLANGE / WEBBING AREAS OF THE STEEL TORQUE LINKS (PN	 25-9UM9-5) FOR THE MAIN LANDING GEAR.  CRACKS HAVE BEEN FOUND ON FOUR(4) OF THE LINKS, WHICH HAVE BETWEEN 3967 AND 5603	 CYCLES SINCE REPLACEMENT.				2	L	7	2 	4F			RT	A3EU    					 
2002012500119	20020125	00119	CE  	2002	1	25	2002FA0000018    	1	20011212	G	2421		BOLT            	PRESTOLITE  		CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ALTERNATOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	421PK	44   			A119964	421B0830	22441373H			ALTERNATOR THRU BOLT CAME OUT AND ARCED ON STATOR TERMINAL.  INSPECTED ALTERNATOR AND REINSTALLED ALTERNATOR BOLT.  CHEC	KED TORQUE ON REMAINING BOLTS.  SUGGEST BENDING LOCK TABS OVER PROPERLY AFTER TORQUING BOLTS.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002012500120	20020125	00120	SO  	2002	1	25	2002FA0000019    	1	20011218	G	5530	1610303	BRACKET         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					VERTICAL STAB	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6249Y	3132 				273487	L1981948			VERTICAL STAB BRACKET CRACKED,  OCCURRED DURING NORMAL OPERATING CONDITIONS AND WAS DISCOVERED AT APPROX. 3130 ACTT.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002012500121	20020125	00121	SO  	2002	1	25	2002FA0000020    	1	20011218	G	5530	1610302	BRACKET         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					VERTICAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	6249Y	3132 				273487				VERICAL STAB BRACKET CRACKED,  OCCURRED DURING NORMAL OPERATING CONDITIONS AND WAS DISCOVERED AT APPROX 3130 AC TT.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002012500122	20020125	00122	SO  	2002	1	25	2002FA0000021    	2	20011126	G	8520		CONNECTING ROD  			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					ENGINE	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			EA	23	3910R					17255410				NUMBER THREE CYLINDER CONNECTING ROD AND CAP FAILED AT CRANKSHAFT.  THE CONNECTING ROD THEN FELL DOWN TO THE BOTTOM OF T	HE CYLINDER BORE AND WAS STRUCK REPEATEDLY BY THE CRANKSHAFT UNTIL ENGINE WAS SHUTDOWN.  THE FAILURE OCCURRED AFTER FINA	L POWER REDUCTION DURING A ROUTINE LANDING.  THE PILOT DESCRIBED HEARING A LOUD BANG FOLLOWED BY A LOSS OF POWER.  CAUSE	 OF FAILURE UNDETERMINABLE.			1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002012500124	20020125	00124	EU  	2002	1	25	2002FA0000022    	1	20011012	G	6520	350A33109100	GEAR            			AEROSP	AS355 	AS355*      	       	EU  										T/R GEARBOX	MISALIGNED      	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08										UNABLE TO ESTABLISH ACCEPTABLE GEAR PATTERN ON PINION.						1	G	7	2 	3U			 	H11EU   					 
2002012500125	20020125	00125	SO  	2002	1	25	2002FA0000023    	2	20011113	G	8520		BEARING         			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					LT ENGINE	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	17	3748C	1166 				402B0606	815069R			IN FLIGHT FAILURE OF LT ENGINE NR 2 ROD BEARING FAILED CAUSING CASE DAMAGE.  ROUGH RUNNING AND OIL LOSS.  PILOT SHUT DOW	N ENGINE AND MADE A SUCCESSFUL LANDING TBO IS 1400 HR.  ENGINE HAD 1166.9 SINCE FACTORY REMANUFACTURE.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002012500126	20020125	00126	CE  	2002	1	25	2002FA0000024    	1	20011214	G	6120	C2995060102	CONTROL CABLE   			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  					PROPELLER	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	71398	3695 				18259607	2000529R			PILOT COMPLAINED THAT THE PROPELLER CONTROL WAS HARD TO MOVE.  WHEN TECHNICIAN INVESTIGATED, THE CONTROL CABLE BROKE AND	 CAME OFF IN TECHNICIAN`S HAND.  REMOVED AND REPLACED CONTROL WITH NEW PART.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012500131	20020125	00131	EU  	2002	1	25	2002FA0000026    	1	20011203	G	2435	23091004	STARTER GEN     			ISRAEL	GALAXY	GALAXY      	4500307	EU  										ENGINE	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	35BP					016				STARTER GEN  FAILED.						2	L	7	2 	4F			RT	A53NM   					 
2002012500132	20020125	00132	EU  	2002	1	25	2002FA0000027    	1	20011214	G	4930	FB9682	FUEL BOWL       			HWKSLY	DH125 	HS125600A   	4230158	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					APU	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	800NM					256027				DURING SCHEDULED INSPECTION AND FILTER CHANGE, EXCESSIVE CONTAMINATION FOUND IN FILTER BOWL ASSEMBLY.						2	L	7	2 	4J	4	F	 	A3EU    	E6WE				 
2002012500133	20020125	00133	CE  	2002	1	25	2002FA0000028    	1	20010714	G	2810	41424	FUEL CELL       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520*    	17040	SO  					RT WING	ROTTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	127BC					4140519				RIGHT OUTBOARD WING FUEL CELL (PN 4142-4) REPLACES (PN 5026102-4).  FUEL CELL IS 11 YEARS OLD.  MPG, DATE 2-90.  FUEL CE	LL CAME APART (TOTALLY ROTTEN AND BRITTLE) AT TOP OF FILLER NECK.  FUEL CELL WAS MADE OF DIFFERENT MATERIAL, NOT OF THE 	NORMAL RUBBER.  BAD TANK FOUND.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2002011800031	20020118	00031	SW  	2002	1	18	2002FA0000029    	1	20010730	G	6220	222012104101	PITCH HORN      			BELL  	230   	230         	1182149	SW  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	230LF	2714 				23017				CRACK FOUND ON MAIN ROTOR GRIP AT BOLT HOLE WHERE GRIP ATTACHES TO PITCH HORN.  CRACK EXTENDED FROM BOLT HOLE FOR 1.5 FE	ET TO OUTSIDE OF GRIP.					1	G	7	2 	3U	3	U	NC	H9SW    	E1GL				 
2002012500134	20020125	00134	EU  	2002	1	25	2002FA0000030    	1	20010101	G	5320	4A53360284001	FITTING         			ISRAEL	GALAXY	GALAXY      	4500307	EU  										DOOR STRUT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	83EJ	1100 				009				FITTING HOLDS CABIN ENTRANCE DOOR AIR SPRING.  SPRING GIVES DOOR SUPPORT DURING OPENING.  DOOR SUPPORT DURING OPENING, F	ITTING BROKE ALLOWING DOOR WEIGHT TO HAVE TO BE SUPPORTED BY CREW.  PART TT 1100 HRS					2	L	7	2 	4F			RT	A53NM   					 
2002012500135	20020125	00135	EU  	2002	1	25	2002FA0000031    	1	20010101	G	8011	23091004	STARTER         			ISRAEL	GALAXY	GALAXY      	4500307	EU  										ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	83EJ					009				STARTERS ARE FAILING WITH ONLY 200 TO 300 HOURS.						2	L	7	2 	4F			RT	A53NM   					 
2002012500137	20020125	00137	CE  	2002	1	25	2002FA0000032    	1	20011228	G	3211	513210P24	BUSHING         			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					MLG BRACE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	98692					402B1050	L275471R			BEARING PART OF BUSHING, NOT TAKING GREASE.  DISASSEMBLE AND PHYSICALLY INSPECT BOTH. FOUND CORRODED						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002012500138	20020125	00138	SO  	2002	1	25	2002FA0000035    	1	20011214	G	7714	598881	PICKUP          			PIPER 	PA32  	PA32R301T   	7103220	SO  	LYC   	O540  	TIO540*     	41532	EA  					ENGINE TACH	MISMANUFACTURED 	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	298AT	418  				3257069	L1006661A			REMOVED MAGS FOR 500 HR INSPECTION, NYLON GEARS IN LT MAG DETERORATING, FROSTED APPEARANCE ON BOTH DISTRIB AND CAM GEARS	.  MAG HAS ELECT TACH PICK UP IN PLACE OF NORMAL MAG VENT.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2002012500139	20020125	00139	CE  	2002	1	25	2002FA0000036    	1	20011228	G	3310	0713247200	RHEOSTAT        			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300*       	17022	SO  					CABIN	BURNED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	19	3297L					17256197				SMOKE IN COCKPIT, COMING FROM OVERHEAD.  TURNED OFF RADIO LIGHT RHEOSTAT AND INSTRUMENT LIGHT RHEOSTAT.  SMOKE THEN QUIT	.  INVESTIGATION FOUND RADIO LIGHT RHEOSTAT WAS OVERHEATING AND SMOKING.  RHEOSTAT WAS REMOVED.					1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002012800001	20020128	00001	EU  	2002	1	28	2002FA0000038    	1	20010606	G	2121	M3348A	MOTOR           	DYNAMICAIR  		SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  					FAN	MISREPAIRED     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	15	69LP				217	340AO69				FAN RETURNED TO MFG FOR UPGRADE TO C209-6901) CONFIGURATION.  FAN WAS DISAS AND FOUND TO BE NOT OVERHAULED PER REQUIRED 	MM.  ARMAT AND WINDINGS NOT OF MFG DESIGN.  MM DOES NOT ALLOW FOR REWINDING OF ARMAT FIELD WINDINGS, OR REPLACEMENT OF P	ARTS OTHER THAN LISTED. ARMAT ASSY STACK LENGTH IS TOO SHORT, THE IMPELLER IS  GLUED ON, COMMUTATOR IS UNDERSIZE AND AIR	 GAP BETWEEN IMPELLER AND WINDINGS IS TOO SMALL.  VENT HOLES IN MTR ARE ENLARGED CAUSING REDUC AIR FLOW THROUGH MTR CAUS	ING BRUSH HOLDERS TO OVERHEAT.  END BELL IS MODI NOT TO REQMT.  THREADED BAR WAS USED TO HOLD MOTOR TO HOUSING INSTEAD O	F REQUIRED BOLTS.  FILTER IS REWORKED (UNSERVICABLE PART).  POS STUD IS LOOSE AND NOT MAKING ELECTRIC CONTACT.	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2002012800003	20020128	00003	CE  	2002	1	28	2002FA0000040    	1	20011206	G	3230		PIVOT ASSY      			CESSNA	182   	R182        	2072734	CE  										LT MLG	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	757KP					R18201242				FORWARD BEARING AREA OF LEFT MAIN GEAR PIVOT WAS DETERMINED TO BE CRACKED AND LEAKING BREAK FLUID.  THE PIVOT ASSEMBLY W	AS REPLACED WITH A USED SERVICEABLE PIVOT ASSEMBLY OF THE SAME PART NUMBER.					1	H	7	1 	3O			RT	3A13    					 
2002012800004	20020128	00004	SO  	2002	1	28	2002FA0000041    	1	20010821	G	3220	40336000	DRAG LINK       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  					NLG	BROKEN          	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	114SA	13729				318052053				RIGHT NOSE GEAR DRAB LINK FAILED JUST FORWARD OF WHERE GEAR ACTUATOR ATTACHES.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002012800005	20020128	00005	GL  	2002	1	28	2002FA0000042    	1	20011113	G	5210	6E21	HOOK            	ZENITH      		AMTR  	CH601 	ZODIAC      	       	GL  										CANOPY LOCK	MALFUNCTIONED   	D				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			GL	17	324DZ	18   				63682				NO FLAW FOUND ON LOCK HOOK.  CANOPY SEPARATED FROM FUSELAGE IN STRAIGHT AND LEVEL FLIGHT.						1	L	7	1 	3O			NC	EXPA1L71					 
2002012800006	20020128	00006	EA  	2002	1	28	2002FA0000043    	2	20010418	G	8500		ENGINE          			GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	O540A1D5    	41532	EA  					NACELLE	FAILED          	C				E				ENGINE SHUTDOWN         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			SW	15	280GA	451  				2009825F				ENGINE ACTED AS THOUGH CARBURETOR ICE WAS BEING CLEARED WITH CARBURETOR HEAT ON.  LANDED UNEVENTFULLY.  AT TOUCHDOWN, CO	ULD HEAR A LOUD SQUEAK.  AT ENGINE SHUT DOWN, ENGINE STOPPED AS THOUGH A BRAKE WAS APPLIED.  PROP WAS DIFFICULT TO TURN 	BY HAND.  ALUMINUM AND FERROUS METAL WAS FOUND IN OIL SCREEN, FILTER AND OIL COOLER.				1	L	7	1 	3O	3	O	NC	A00001LA	E295				 
2002011600001	20020116	00001	NE  	2002	1	16	2002FA0000044    	2	20010707	G	7200		TIE ROD         								PWA   	JT8   	JT8D15A     	52051	NE  					SIXTH STAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	GCEAF						686373			CREW REPORTED HIGH VIBRATION IN CRUISE AT FL 330.  GROUND RUNS CARRIED OUT AND VIBRATION CONFIRMED.  ENG HEARD TO BE MAK	ING A METALLIC SCRAPING SOUND WHEN TURNED BACKWARDS.  SIG DAMAGE WAS FOUND WHILE BORESCOPING.  INSP OF 6TH STAGE REVEALE	D THAT REAR TIEROD HAD FAILED AND WAS STUCK IN GASPATH BETWEEN C6 BALDES AND INTERMEDIATE CASE VANES.  ONE TIE ROD FAILE	D IN 4TH STG LAND.  FRNT REMAINED IN PLACE WHILE REAR PART MOVED AFT.  REAR END OF TIEROD MANAGED TO COME OUT OF TIEROD 	HOLE.  BROKEN OFF TIEROD PART CAME OUT OF TIEROD HOLE, THEN PUNCTURED INTERM CASE WHILE TIEROD HEAD STAYED IN CONTACT WI	TH C6 DISK OUTER RIM.  EXTENSIVE SECONDARY DAM CAUSED TO AIRFOILS DOWN STREAM OF C6 BY BROKEN OFF FRAGMENTS OF BLD LOCKS						4	F			E2EA				 
2002012800007	20020128	00007	CE  	2002	1	28	2002FA0000045    	1	20010403	G	3252	0842102	SHIMMY DAMPENER 			CESSNA	310   	310J        	2074226	CE  										NLG	DAMAGED         	G				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	15	63GG	4878 				310J0152				PILOT MADE A HARD LEFT TURN CAUSEING DAMAGE TO THE NOSE GEAR AREA.  BENT ROD ON THE SHIMMY DAMPER CAUSING INTERNAL DAMAG	E TO THE COMPONENT.					1	L	7	2 	3O			 	3A10    					 
2002011800032	20020118	00032	SW  	2002	1	18	2002FA0000048    	1	20010804	G	6420	47LM2505	UNIVERSAL JOINT 			BELL  	47    	47G5        	1181032	SW  	ALLSN 	250C  	250C*       	 	GL  					TAIL ROTOR	FAILED          	C			LPGG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	2251W		559  			7965	CAE801089B			WAS INVOLVED IN AERIAL APPLICATION, ON A SPRAY RUN PILOT NOTICED THAT HE WAS PICKING UP VIBRATION IN TAIL ROTOR CONTROL 	PEDALS AND CEASED SPRAY OPERATIONS.  CAME IN FOR LANDING AND AT HOVER IS WHEN THE U-JOINT FAILED.  HELICOPTER TURNED 180	 DEGREES BEFORE LANDING.  NO DAMAGE TO AIRCRAFT.  PART THAT FAILED INSPECTED DAILY.  LUBRICATED EVERY 10-15 HOURS.  AFTE	R EXAMINING FAILED U-JOINT, FOUND THAT ONLY HALF OF JOINT WAS RECEIVING ANY GREASE.  DONT KNOW HOW LONG THIS CONDITION O	F NO GREASE WAS HAPPENING.		1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2002012800009	20020128	00009	NM  	2002	1	28	2002FA0000049    	1	20010705	G	3240		SHUTTLE VALVE   			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	PW120 	PW123       	 	NE  					MLG BRAKE	MALFUNCTIONED   	D				D				RETURN TO BLOCK         				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			WP	07	347PH	9490 	65   			480				RT OUTBOARD BRAKE LOCKED UP DURING TAXI AND CAUSED BRAKE FIRE.  VALVE WAS PLACED ON TEST STAND AND REPEATEDLY TESTED VIG	OROUSLY FOR 50 MINUTES PER OEMS ATP.  NO PROBLEMS WERE NOTED.  VALVE WAS THEN TORN DOWN AND INSPECTED.  ONLY IRREGULARIT	Y FOUND WAS LOOSE SCREEN IN FILTER FITTING ON INLET PORT.  THIS COULD HAVE CAUSED PROBLEM ON OUTLET PORT.   IT IS INCONC	LUSIVE AS TO THIS VALVE CAUSING THE LOCKUP, BUT FILTER WAS REPLACED AND ONCE AGAIN VALVE TESTED GOOD.  ALL FILTERS ON AL	L VALVES NEED TO BE VERY THOROUGHLY INSPECTED.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2002012800010	20020128	00010	SO  	2002	1	28	2002FA0000051    	1	20011031	G	5520	5161802	BALANCE WEIGHT  			PIPER 	PA31T 	PA31T1      	7103126	SO  										ELEVATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	824VA	4825 				31T8104039				DURING INSPECTION, FOUND RIGHT ELEVATOR BALANCE WEIGHT HAD A CRACK IN TO LEAD WEIGHT BEHIND THE REAR MOUNTING BOLT.  WIT	H WEIGHT REMOVED THE CRACK COULD BE EXPANDED BY HAND. (K)					1	L	7	2 	3T			 	A8EA    					 
2002012800011	20020128	00011	EA  	2002	1	28	2002FA0000052    	2	20011230	G	7322	CF30766	FLOAT           	MARVELSCHEBX		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235*       	41505	EA  					CARBURETOR	FAILED          	G				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		LD	LANDING        	1			NE	03	65463				CR15647	15281566				ON LANDING THE ENGINE QUIT.  FUEL WAS OBSERVED LEAKING FROM THE AIRCRAFT.  DURING DISASSEMBLY OF THE CARBURETOR IT WAS N	OTED BOTH FLOATS WERE FILLED WITH FUEL CAUSING FUEL TO POUR THRU THE VENT.  THE MANUFACTURE DATE OF THE FLOAT WAS 4/92.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002012800012	20020128	00012	CE  	2002	1	28	2002FA0000053    	1	20010122	G	5610	10138402522	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	200WB	140  				FA5				WINDSHIELD DEVELOPED CRACK IN OUTER PLY AT LOWER CENTER CORNER, CRACKING APPEARED CIRCUMFRONTIAL AT  APPROXIMATELY 5 FEE	T 6 INCHES.  WINDSHIELD WAS INSTALLED WITH MFG KIN NR 101-5041-1S.					2	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002012800015	20020128	00015	CE  	2002	1	28	2002FA0000056    	1	20010109	G	2750		PIN             			CESSNA	501   	501         	2076603	CE  	PWA   	JT15  	JT15D1      	52060	NE  					TE FLAP GEARBOX	SHEARED         	B			BGSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	597CS					5010293				THE SHEAR PIN CONNECTING THE FLAP DRIVE MOTOR TO THE FLAP GEARBOX SHEARED OFF AS THE CREW ATTEMPTED TO POSITION FLAPS TO	 2ND POSITION. AFTER INVESTIGATION, THE FLAP GEAR BOX WAS DETERMNED TO BE DEFECTIVE.					1	L	7	2 	4F	4	F	 	A27CE   	E1NE				 
2002011800019	20020118	00019	EU  	2002	1	18	2002FA0000067    	1	20011022	G	7810	0292808700	EXHAUST STACK   			SNIAS 	350   	AS350BA     	8680817	EU  										ENGINE	CRACKED         	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	270SH	958  				1864				ENGINE EXHAUST IS CRACKED.  INSTALLED SERVICEABLE EXHAUST STACK.  (M)						1	G	7	1 	3U			NC	H9EU    					 
2002011800020	20020118	00020	EU  	2002	1	18	2002FA0000068    	1	20011018	G	6410	350A33215300	BEARING         			SNIAS 	350   	AS350*      	       	EU  										TAIL ROTOR	CUT             	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	115SH	640  				3141				BEARING HAS DEEP CUT, DELAMINATION.  REPLACED WITH NEW BEARING.  (M)						1	G	7	1 	3U			 	H9EU    					 
2002011800021	20020118	00021		2002	1	18	2002FA0000069    	4	20011017	G	3422	RCA15BR1	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT	INOPERATIVE     	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	230SH	11   				2337				DIRECTIONAL GYRO INOPERATIVE.  REPLACED WITH SERVICEABLE UNIT.  (M)						1	G	7	1 	3U			NC	H9EU    					 
2002011800022	20020118	00022		2002	1	18	2002FA0000070    	4	20011011	G	3422	RCA15BK1	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT	PRECESSES       	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	230SH	319  				2337				DIRECTIONAL GYRO PRECESSES CONTINUOUSLY.  REPLACED WITH SERVICABLE UNIT.  (M)						1	G	7	1 	3U			NC	H9EU    					 
2002011800023	20020118	00023	EU  	2002	1	18	2002FA0000071    	1	20011016	G	3110	704A47270101	INDICATOR       			SNIAS 	350   	AS350BA     	8680817	EU  										COCKPIT	INTERMITTENT    	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	37SH	1221 				2300				FUEL PSI READING INTERMITTENT.  FURTHER TROUBLESHOOTING FOUND BAD GROUND WIRE, THIS UNIT IS TO BE RESTOCKED.  INSTALLED 	SERVICEABLE INSTRUMENT CLUSTER.  (M)					1	G	7	1 	3U			NC	H9EU    					 
2002011800024	20020118	00024	SW  	2002	1	18	2002FA0000072    	1	20010828	G	6510	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404AL					53479				BEARING SHOWING SIGNS OF WEAR AND BEGINNING SIGNS OF OVERTEMP.  SCRAPPED BEARING.  (M)						1	G	7	1 	3U			O	H2SW    					 
2002011800025	20020118	00025	NE  	2002	1	18	2002FA0000073    	2	20010807	G	7250	23053299	TURBINE WHEEL   			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	707AL	1110 				760189				TURBINE CAME IN FOR SHOP VISIT FOR LOW POWER.  BEGAN DISASSEMBLY OF TURBINE, REMOVED OUTER COMBUSTION CASE AND FOUND SUL	FIDATION ON 1ST STAGE WHEEL.  HAD ONE BLADE MISSING AND SEVERAL BROKEN BLADES.  THIS TURBINE HAD A ROLLS ROYCE LINER.  H	AVE WHEELS TESTED FOR PROPER COATING.  (M)				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002011800026	20020118	00026	SW  	2002	1	18	2002FA0000074    	1	20011002	G	5330	206010200133	SKIN            			BELL  	206   	206B        	1181511	SW  										FUSELAGE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5743B	3310 				3056				DISCOVERED DURING ROUTINE AIRFRAME INSPECTION, LOWER SKIN CORRODED AND SEPARATED BENEATH OUTBOARD GRIP FINGER DOUBLER.  	(M)					1	G	7	1 	3U			 	H2SW    					 
2002011800027	20020118	00027	GL  	2002	1	18	2002FA0000075    	2	20010822	G	7250	6895801	TURBINE WHEEL   			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	CORRODED        	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2025G	987  				45690				WHEN TURBINE CAME IN FOR NR 3 AND NR 4 WHEEL CHANGE AND VISUAL INSPECTION ON TURBINE HOT END.  NR 1 WHEEL SHOWED EARLY A	TTACH OF SULFIDATION.  HAVE WHEEL TESTED FOR PROPER COATING.  (M)					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002011800028	20020118	00028	EU  	2002	1	18	2002FA0000076    	1	20010808	G	6320	4649010006	CASE            			UROCOP	EC135 	EC135T1     	5620026	EU  										M/R GEARBOX	DAMAGED         	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	511ME	547  				0143				FOUND HOLE IN MAIN GEARBOX CASING.  (M)						1	G	7	2 	3U			 	H88EU   					 
2002012800017	20020128	00017		2002	1	28	2002FA0000078    	4	20010918	G	3197	PQ876SW	RING            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					WIRE	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	1368U	317  				17267039				PART WAS INSTALLED AROUND TACH AND CONNECTED TO REOSTATE FOR THE INSTRUMENT LIGHTS.  IT SHORTED OUT THE SYSTEM AND BURNE	D OUT REOSTATE-S2091-5 AND POWER TRANSISTER 2N3055.  THIS CAUSED NO INSTRUMENT LIGHTS IN AIRCRAFT.  OWNER NOTICED NO LIG	HTS AND NOTIFIED TECHNICIAN.  TROUBLESHOOTING THE SYSTEM TECH FOUND THAT WIRES ON TOP OF RING WAS TOUCHING ONE ANOTHER, 	CAUSING A DIRECT SHORT.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002012800018	20020128	00018	EA  	2002	1	28	2002FA0000079    	2	20010930	G	7414	M3635	IMPULSE COUPLING	SLICK       		PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540B2C5    	41532	EA  					MAGNETO	SEPARATED       	D				E				ENGINE SHUTDOWN         				D	K		INFLIGHT SEPARATION       	FLUID LOSS                		TX	TAXI/GRND HDL  	1			EA	33	8903L	230  				255364	L121180			DURING GROUND RUN, OPERATOR NOTED A LOUD BANG AND SUDDEN OIL LEAKAGE.  AFTER SHUT DOWN FOUND THAT LT MAGNETO CAME OFF TH	E ACCESSORY HOUSING,  CAUSING OIL LEAK. BANG WAS CAUSED BY MAG HOUSING WHICH CAME APART AT UPPER ATTACHMENT AREA (ATACHM	ENT LUG).				1	L	7	1 	3O	3	O	 	2A10    	E295				 
2002012800019	20020128	00019	WP  	2002	1	28	2002FA0000083    	1	20011016	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	8353K	797  				0348	L2507840A			HIGH OIL TEMPERATURES, AT RED LINE 245 DEGREES, VERIFIED BY DECREASE IN OIL PRESSURE.  FOUND VALVE STUCK, NOT EXTENDING.	  REMOVED AND REPLACED WITH NEW PART.  OPS CHECKED GOOD.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002012800022	20020128	00022	CE  	2002	1	28	2002FA0000088    	1	20011211	G	5210	07110271	HANDLE          			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470*       	17026	SO  					CREW DOOR	STRIPPED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	9109X					18253509				WHILE INVESTIGATING A COMPLAINT OF A DEFECTIVE DOOR LATCH IT WAS DISCOVERED THAT THE INTERNAL SPLINES OF THE DOOR HANDLE	 WERE STRIPPED.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002012800023	20020128	00023	CE  	2002	1	28	2002FA0000089    	1	20011119	G	5260		STRUT           			CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470*      	17026	SO  					AIRSTAIR	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	8TC					310Q0264				MAINTENANCE PERSONNEL ATTEMPTED TO BOARD AIRCRAFT WHEN MOUNTING STEP STRUT ASSEMBLY BROKE AWAY.  WELD ASSEMBLY (PN 08119	46-23) FAILED COMPLETELY AT UPPER STEP.  INDICATIONS OF A PRE EXISTING CRACK AROUND ONE THIRD OF THE CIRCUMFERENCE OF TH	E TUBE.  NO SIGNS OF RUST BLEED THROUGH AT THE EXTERIOR PAINT.  STEP MOUNTING SCREW SPACERS MISSING AT UPPER STEP.				1	L	7	2 	3O	3	O	 	3A10    	E1CE				 
2002012800031	20020128	00031	NM  	2002	1	28	2002FA0000091    	1	20010627	G	2612	088131007	SWITCH          			BOEING	737   	737*        	       	NM  										FIRE DETECTION	SHORTED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	XAAEX	6    				32774				SWITCHES SHORTED INTERNALLY.  SHOULD RETURN TO N/O CONDITION.  LOOKS LIKE MICROSWITCH FAILED INTERNALLY IN ASSY.  REMOVE	D AND REPLACED SWITCHES, RETESTED NO MALFUNCTION OR DEFECTS NOTED.  FIRE BELL CUTOUT SWITCHES AND SYSTEM OPS CHECKED GOO	D.  (M)				2	L	7	2 	4F			RT	A16WE   					 
2002012800033	20020128	00033	CE  	2002	1	28	2002FA0000092    	1	20011219	G	2730	676033215	TIE ROD         			CESSNA	750   	750         	2076810	CE  										RT ELEVATOR	STIFF           	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	551AM	262  	262  			7500155				DURING INSPECTION AND PERFORMANCE,  BEARING ROD END LUBRICATION, P/N 676033215 TIE ROD, INTERCONNECTING THE TWO OUTBOARD	 ELEVATOR BELLCRANKS, WAS FOUND TIGHT AND NOT ABLE TO ROTATE SLIGHTLY ABOUT ITS LONGITUDINAL AXIS. IT WAS DISCOVERED THA	T THE ROD  ENDS, WHICH ARE RIVETED TO THE MAIN TUBE AND NOT ADJUSTABLE, WERE MISALIGNED WITH EACH OTHER---NOT IN THE SAM	E PLANE. WHEN ATTACHED TO THE BELLCRANKS, THE ROD ENDS WERE PINCHED AGAINST THE BELLCRANK EARS INSTEAD OF JUST THE SPHER	ICAL BEARING. NO DAMAGE WAS NOTED ON THE BELLCRANK EARS, HOWEVER, FUTURE PROBLEMS MIGHT ARISE AS THE TIE ROD AND OTHER P	USHROD AND BUNGEE ROD ENDS IN THIS SYSTEM ARE SUBJECT TO ROD END BEARING CORROSION. TIE ROD WAS REPLACED WITH NEW PART W	2	L	7	2 	4J			RT	T00007WI					 
2002012400033	20020124	00033	GL  	2002	1	24	2002FA0000095    	1	20011210	G	3213	3525151004	FORK            			AMTR  	GLASAR	GLASAIRIISTD	05602E5	GL  										MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	07	225S	918  	40   							DURING LANDING THE AIRCRAFT VEERED OFF TO THE RIGHT SIDE OF THE RUNWAY. AN INSPECTION REVELED A RIGHT HALF FORK WAS BROK	EN. THE WHEEL ATTACHES TO THIS HALF FORK WHICH ATTACHES TO THE MAIN STRUT. PER A GLASAIR REPRESENATIVE, MFG. OF THE GLAS	AIR KITS FOR AMATUERBUILDERS, THIS PART IS NOW MADE OF STEEL. THE CAST ALUMINUM HALF FORK, SUCH AS THE BROKEN PART, WAS 	REPLACED BY THE STEEL HALF FORK ABOUT 8-10 YEARS AGO.  AN UPGRADE WAS MADE AVAILABLE TO ALL THE PREVIOUS KITS FROM GLASA	IR.		1	L	7	1 	3O			RT	EXPA1L71					 
2002012800037	20020128	00037	EA  	2002	1	28	2002FA0000096    	2	20011210	G	8550		ENGINE          			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	O360A4K     	41514	EA  	SNSNCH	76E	76EM8       	EA  	NACELLE	LEAKING         	F				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	09	999TE	68   				10201	L3776336A			ENGINE DEVELOPED OIL LEAK AT THE TOP OF THE CASE NEAR THE ACCESSORY CASE.  LEAK BEGAN DURING INITIAL ENGINE RUN.  LEAK I	S APPX 1/8 QT PER 6 HRS.  LEAK COULD NOT BE FIXED WITHOUT REMOVING ENGINE.					1	L	7	1 	3O	3	O	NT	1L71    	E286	5	N	P4EA	 
2002012400038	20020124	00038	SO  	2002	1	24	2002FA0000100    	2	20010921	G	7414	K3823	DISTRIBUTOR     	SLICK       	6310        	CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					MAGNETO	BURNED          	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	99	PK-MP	9    			00111980	U20606987				MAGNETO FAILED - WOULD NOT RUN AT ALL.  THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED FROM SPARKS GOING FROM	 THE THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT.  SUPPORT IS BADLY MELTED.  M3215 CARBON 	BRUSH IS BURNED ALSO.  DISTRIBUTOR BLOCK AND GEAR ARE COATED WITH A WHITE DEPOSIT MATERIAL WHICH IS ALSO SEEN SPATTERED 	INSIDE THE MAGNETO HOUSING AND ON THE COIL.			1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2002012400039	20020124	00039	SO  	2002	1	24	2002FA0000101    	2	20010925	G	7414	K3823	DISTRIBUTOR     	SLICK       	6310        	CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					MAGNETO	BURNED          	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	99	PKMPT	12   			00111983	U20606987				MAGNETO FAILED - WOULD NOT RUN AT ALL.  THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED SHOWING DEEP TRACKING 	FROM SPARKS GOING FROM THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT.  SUPPORT HAS A DEEP TR	ACK BURNED ACROSS IT.  DISTRIBUTOR BLOCK AND GEAR ARE COATED WITH A WHITE DEPOSIT MATERIAL WHICH IS ALSO SEEN SPATTERED 	INSIDE THE MAGNETO HOUSING AND ON THE COIL.  MAGNETO WAS SUPPLIED AS PART OF A FACTORY REBUILT ENGINE.			1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2002012400040	20020124	00040		2002	1	24	2002FA0000103    	4	20010809	G	2564	R0097104	LIFE RAFT       																	CABIN	DAMAGED         	B				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03										DURING 1ST 8 MONTH INSPECTION, LIFE RAFT HAS TOO MUCH POROSITY.  RECOMMENDATION BETTER COATING OF FABRIC AND MORE INTENS	IVE INSPECTION AFTER MANUFACTURING OF RAFT.  (M)																		 
2002012400041	20020124	00041	SO  	2002	1	24	2002FA0000105    	2	20010810	G	8550	6420B5415R	HOUSING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520*    	17040	SO  					SCAV PUMP	FRACTURED       	D				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			AP	APPROACH       	1			SW	99	121PB	1482 				402C0507				ON FINAL APPROACH, CREW NOTICED OIL LEAKING FROM LEFT ENGINE COWL.  OIL PRESSURE AND TEMPERATURE WERE INDICATING NORMAL.	  CREW SHUT DOWN LEFT ENGINE AS A PRECAUTION AND LANDED WITHOUT INCIDENT.  MAINTENANCE FOUND SCAVENGE PUMP HOUSING FRACT	URED AND LEAKING.  TEAR DOWN REVEALED SCAVENGE PUMP DRIVEN GEAR FAILED, CAUSING THE HOUSING TO CRACK.  MAINTENANCE REMOV	ED AND REPLACED STARTER ADAPER OIL FILER AND CHANGED OIL.  AIRCRAFT RETURNED TO SERVICE.  (M)			1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002012400042	20020124	00042	EA  	2002	1	24	2002FA0000106    	2	20010801	G	7414		BEARING         			AMRGEN	AG5B  	AG5B        	3990100	SO  	LYC   	O360  	VO360*      	41514	EA  					MAGNETO	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	1194T					10083				MAGNETO FORWARD BEARING SEIZED BENDING SHAFT AND DRIVE GEAR ROAD OVER ENGINE ACCESSORY DRIVE GEAR CHIPPING DRIVE GEAR AN	D PUTTING ENGINE OUT OF TIME SHUTTING ENGINE DOWN WHEN TAXIING AND ENGINE WOULD NOT RESTART.  (M)					1	L	7	1 	3O	3	O	NT	1L71    	1E1				 
2002012400044	20020124	00044	CE  	2002	1	24	2002FA0000107    	1	20011212	G	3710	H67402A3	SHUTTLE VALVE   			CESSNA	401   	401         	207590C	CE  										VACUUM SYSTEM	FAILED          	B				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SW	99	3264Q	1577 				4010064				AFTER STARTING THE RT ENGINE & THE LT ENGINE IS OFF. THE RT VACUUM SYSTEM PULLED BOTH LT & RT ORANGE INDICATOR BULLETS O	N THE VACUUM GAUGE INDICATING THAT THE LT VACUUM SYSTEM IS WORKING, BUT THE LT ENGINE IS SHUT DOWN. CAUSE: THE LT SHUTTL	E/CHECK VALVE FOR THE WING DEICE BOOTS STUCK OPEN ALLOWING THE RT VACUUM PUMP TO SUCK DOWN THE LT SYSTEM THROUGH THE LT 	VACUUM PUMP GIVING A FALSE OPERATIONAL INDICATION.			1	L	7	2 	3O			 	A7CE    					 
2002012400049	20020124	00049	SO  	2002	1	24	2002FA0000109    	2	20011207	G	7414	K3823	DISTRIBUTOR     	SLICK       	6310        	CESSNA	206   	U206F       	2073333	CE  	CONT  	O550  	IO550F      	17042	SO  					MAGNETO	BURNED          	C				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	99	PKMPR	2    			00111980	U20603398	284921			MAGNETO HAD FAILED 9.3 HOURS AFTER BEING SUPPLIED AS A PART OF A FACTORY REBUILT ENGINE.  IT WAS DISASSEMBLED AND THE DI	STRIBUTOR, COIL, CAPACITOR AND BREAKER WERE REPLACED.  MAGNETO WAS CHECKED OK.  2.5 HOURS AFTER THIS REPAIR THE MAGNETO 	FAILED AGAIN.  THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED SHOWING DEEP TRACKING FROM APARKS GOING FROM TH	E SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT.  SUPPORT HAS A DEEP TRACK BURNED ACROSS IT AND 	IS PARTLY BURNED AWAY.		1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2002012400050	20020124	00050	SO  	2002	1	24	2002FA0000110    	2	20011207	G	7414	K3823	DISTRIBUTOR     	SLICK       	6230        	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					MAGNETO	BURNED          	D				D				RETURN TO BLOCK         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	99	PKMPY	449  			00091743	U20606904	818183R			MAGNETO WAS SUPPLIED AS PART OF A TCM FACTORY REBUILT ENGINE.  IT FAILED AND UPON INSPECTION IT WAS DISCOVERED THAT THE 	DISTRIBUTOR GEAR SUPPORT WAS BADLY BURNED BY SPARKS GOING FROM THE COIL TERMINAL TO GROUND ON THE M3485 BEARING CAP BY A	RCING ACROSS THE SHELF OF THE SUPPORT.  SUPPORT HAS A DEEP TRACK BURNED ACROSS IT.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE				 
2002012400052	20020124	00052	SO  	2002	1	24	2002FA0000111    	1	20011221	G	3230	7954302	BOLT            			PIPER 	PA28  	PA28151     	7102805	SO  										DRAG LINK	FAILED          	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SW	99	43125	4395 	6    			287415430				JUST AFTER TAKEOFF, THE GREASE BOLT (P/N 79543-02) FAILED AND ALLOWED THE UPPER AND LOWER TORQUE LINKS TO SEPARATE.  THI	S ALLOWED THE STUB AXLE, OLEO TUBE, AND RIGHT WHEEL AND BRAKE ASSEMBLY TO FALL OFF THE AIRCRAFT.  THE BRAKE LINE BROKE A	LLOWING EVERYTHING TO FALL FREE.   THE ASSEMBLY WAS RECOVERED AND THE TORQUE LINKS FOUND TO BE INTACT.  THE GREASE BOLT 	WAS NOT RECOVERED, SO THE EXACT LOCATION OF THE FAILURE IS UNKNOWN.  THIS AIRCRAFT HAS BEEN USED FOR TRAINING EXTENSIVEL	Y, SO STRESSES ON THE GEAR ARE HIGHER THAN IN NORMAL USE.  ANY SIDE LOAD ON THE GEAR STRESSES THE GREASE BOLT, SO PERHAP	S A LANDING WHILE YAWED CRACKED THE BOLT, CAUSING A FAILURE ON THE NEXT FLIGHT.	1	L	7	1 	3O			 	2A13    					 
2002012400062	20020124	00062	CE  	2002	1	24	2002FA0000112    	1	20011227	G	3340	W31X100010	SWITCH          			CESSNA	172   	172S        	2072439	CE  										INSTRUMENT PANEL	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			NM	03		1429 				172S8135				PRE-RUN FOR MAINTENANCE FOUND TAXI LIGHT ON WITH SWITCH IN THE OFF POSITION.  MAINTENANCE FOUND TAXI LIGHT SWITCH FAILED	 IN THE ON POSITION.  REPLACED SWITCH AND FUNCTIONAL CHECKED SAT.					1	H	7	1 	3O			NT	3A12    					 
2002012400063	20020124	00063	EU  	2002	1	24	2002FA0000113    	1	20011108	G	2613		OVERHEAT LOOP   			BRAERO	DH125 	BAE125800A  	1500285	EU  										AFT E/E BAY	FAILED          	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	07	12F					258182				DURING A 5 YEAR FUNCTIONAL TEST OF THE REAR EQUIPMENT BAY OVERHEAT DETECT SYSTEM, THE FUNCTIONAL TEST FAILED. FOUND FUSE	 F36(3AMP) ON THE ZK PANEL BLOWN. THE FLIGHT CREW HAS NO WAY OF KNOWING THEIR OVERHEAT DETECT SYSTEM IS INOP, BECAUSE TH	E COCKPIT TEST CIRCUIT, WHICH TESTED OK, IS NOT WIRED THROUGH THIS FUSE. THIS COULD BE A POTENTIALLY DANGEROUS SITUATION	.			2	L	7	2 	4F			RT	A3EU    					 
2002012400082	20020124	00082	CE  	2002	1	24	2002FA0000124    	1	20011219	G	2120		ODOR            			RAYTHN	DH125 	HAWKER800XP 	7150012	CE  	GARRTT	TFE731	TFE7315BR   	 	WP  					COCKPIT	DETECTED        	B				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	07	833QS					258433	107407			DURING CLIMB AT FL240, PILOTS NOTICED "BURNING" SMELL FOLLOWED BY A HUMMING SOUND FROM THE LEFT-HAND SIDE OF AIRCRAFT. P	ILOT ELECTED TO SHUTDOWN ENGINE.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2002012800046	20020128	00046	EU  	2002	1	28	2002FA0000136    	1	20010116	G	2435	150SG10095	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	200  			1618	1102	34117			DEFECT FOUND DURING SCHEDULED MAINTENANCE,  100 HOUR INSPECTION.  LARGE QUANTITY OF CARBON DUST NOTICED AROUND STARTER G	ENERATOR.  FURTHER INSPECTION FOUND BRUSHES WORN BEYOND LIMITS.					1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2002013000008	20020130	00008	SW  	2002	1	30	2002FA0000143    	1	20011231	G	5302	206033004045	SUPPORT         			BELL  	206   	206L        	1181522	SW  										TAILBOOM	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM.  RADIUS BEND IS TOO WIDE.  BETTER QUALITY CONTROL AT MFG.						1	G	7	1 	3U			 	H2SW    					 
2002013000009	20020130	00009	SW  	2002	1	30	2002FA0000144    	1	20011231	G	5302	206033004045	SUPPORT         			BELL  	206   	206L        	1181522	SW  										TAILBOOM	MISMANUFACTURED 	C			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM.  RADIUS BEND IS TOO WIDE.  BETTER QUALITY CONTROL AT MFG.						1	G	7	1 	3U			 	H2SW    					 
2002013000010	20020130	00010	SW  	2002	1	30	2002FA0000145    	1	20011231	G	5302	206033004045	SUPPORT         			BELL  	206   	206L        	1181522	SW  										TAILBOOM	MISMANUFACTURED 	C			ALGR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03										TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM.  RADIUS BEND IS TOO WIDE.  BETER QUALITY CONTROL AT MFG.						1	G	7	1 	3U			 	H2SW    					 
2002013000093	20020130	00093	NM  	2002	1	30	2002FA0000149    	1	20011218	G	5346		SUPPORT         			PIPER 	PA60  	PA60601     	7106010	NM  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	700US	14000				610652796214				DURING ROUTINE MAINTENANCE TO REPLACE MAIN TIRES, THE AIRCRAFT WAS JACKED.  THE NOSE LANDING GEAR HAD EXCESSIVE MOVEMENT	.  THE NOSE LANDING GEAR ACTUATOR SUPPORT STRUCTURE WAS FOUND CRACKED IN NUMEROUS MEMBERS OF THE SUPPORT STRUCTURE AND C	RACKED THROUGH PREVIOUS REPAIRS.				1	M	7	2 	3O			RT	A17WE   					 
2002013000094	20020130	00094	NM  	2002	1	30	2002FA0000150    	1	20011218	G	5531	22000000	RIB             			PIPER 	PA60  	PA60601     	7106010	NM  										VERTICAL STAB	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	700US					610652796214				DURING ANNUAL INSPECTION THE VERTICAL STABILIZER LOWER FORWARD RIB WAS FOUND CRACKED AT THE 90 DEGREE BEND ADJACENT TO T	HE FORWARD SPAR.  THIS AREA NEEDS CLOSE INSPECTION.  10X MAGNIFYING GLASS SHOULD HELP.					1	M	7	2 	3O			RT	A17WE   					 
2002020500043	20020205	00043	SO  	2002	2	5	2002FA0000154    	2	20011231	G	8530	641320	CYLINDER HEAD   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					LT ENGINE	SEPARATED       	B			DYTR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	15	2931L	105  				347970387				DURING LEVEL FLIGHT THE LEFT ENGINE STARTED RUNNING VERY ROUGH.  ENGINE FEATHERED AND AIRCRAFT RETURNED TO AIRPORT.  ENG	INE UNCOWLED AND NR 5 CYLINDER HEAD WAS FOUND SEPARATED FROM BARREL.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2002031200004	20020312	00004	SO  	2002	3	12	2002FA0000160    	1	20010116	G	2710	62701123	WIRE ROPE       			PIPER 	PA32  	PA32300     	7103212	SO  	PWA   	PT6   	PT6A67B     	52043	NE  					LT AILERON	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145R	2227 				3240495				LEFT AILERON BALANCE CABLE,  DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE WAS FOUND WORN WHERE THE CABLE 	PASSES OVER THE CENTER PULLEY IN THE MIDDLE OF THE FUSELAGE.					1	L	7	1 	3O	4	T	 	A3SO    	E26NE				 
2002031200034	20020312	00034	GL  	2002	3	12	2002FA0000210    	3	20011201	G	6111	R10115255	BLADE           													HARTZL	HCB3R	HCB3R304    	GL  	PROPELLER	BROKEN          	B			F3PR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	15		1015 						EMA1094		BLADE LOST APPROXIMATELY 11 INCHES INBOARD FROM TIP.  HAD PREVIOUS KNOWN GROUND STRIKE ALL BLADES.  REMOVED SUBJECT BLAD	ES AND HUB FROM SERVICE.  REPLACED WITH NEW.  2 OTHER BLADES SHOW SIGNS OF STRAIGHTING 02-01-2002															5	C	P28EA	 
2002031200036	20020312	00036	CE  	2002	3	12	2002FA0000212    	1	20011226	G	5751	0322709	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON HINGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195CN					16062	R7557			BOTH BRACKETS CRACKED ALL THE WAY ACROSS BEARING BOSS, SEVERELY CORRODED AND MOUNTING LEG OF ONE BRACKET BROKEN OFF.  TH	E PROBLEM WITH THESE BRACKETS IS THE HIGHLY REAACTIVE MAGNESIUM WHICH THEY ARE MADE OF.  THIS IS A HIGHLY CRITICAL COMPO	NENET AND SHOULD BE INSPECTED CLOSELY OR REPLACED.				1	H	7	1 	3R	3	R	 	A790    	TC121				 
2002031200037	20020312	00037	CE  	2002	3	12	2002FA0000213    	1	20011226	G	5751	03227091	BRACKET         			CESSNA	195   	195A        	2073110	CE  	JACOBS	R755  	L4*         	35003	EA  					AILERON HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195CN					16062	R7557			BOTH BRACKETS CRACKED ALL THE WAY ACROSS BEARING BOSS, SEVERLY CORRODED AND MOUNTING LEG OF ONE BRACKET BROKEN OFF.  THE	 PROBLEM WITH THESE BRACKETS IS THE HIGHLY REACTIVE MAGNESIUM WHICH THEY ARE MADE OF.  THIS IS A HIGHLY CRITICAL COMPONE	NT AND SHOULD BE INSPECTED CLOSELY OR REPLACED.				1	H	7	1 	3R	3	R	 	A790    	TC121				 
2002031200045	20020312	00045	EA  	2002	3	12	2002FA0000221    	2	20010125	G	8530	LS32000WA21P	CYLINDER        			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320*       	41508	EA  					ENGINE	CRACKED         	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	7477L	665  				187509060	L4155427A			ENGINE INSTALLED IN FEBRUARY 1997.  AT APPROXIMATELY 665 HOURS, TWO CYLINDERS WERE CRACKED THROUGH THE FINS OUTSIDE THE 	EXHAUST PORT, ADJACENT TOTHE EXHAUSE SEAT.					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2002031200053	20020312	00053	CE  	2002	3	12	2002FA0000229    	1	20010401	G	3222	35825005	BOLT            			BEECH 	35    	N35         	1151528	CE  	CONT  	O470  	IO470*      	17026	SO  					NLG	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	1228Z	5040 				D6688				DURING ANNUAL INSPECTION,  CHECKING NOSE GEAR BOLT.  BOLT WAS BENT.						1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2002031200055	20020312	00055	CE  	2002	3	12	2002FA0000231    	1	20010530	G	5320		PLATE           			BBAVIA	11    	11AC        	0191102	CE  	CONT  	A65   	A65*        	17003	SO  					RT SPAR	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9540E	1685 				11AC1178				FWD REINFORCING PLATE ON RIGHT REAR SPAR AT STRUT ATTACH FITTING WAS FOUND DELAMINATING AND SEPARATING FROM SPAR AT BOND	 AREA.  PROBABLE CAUSE IS ATTACK BY MOISTURE AND THIN OR POOR QUALITY WOOD SURFACE FINISH.  RECOMMEND MORE PRECAUTION WH	EN FINISHING WOOD STRUCTURES.  PART TOTAL 1685 HOURS.				1	H	7	1 	3O	3	O	 	A761    	E205				 
2002031200056	20020312	00056	SW  	2002	3	12	2002FA0000232    	1	20010815	G	5720		FLANGE          			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O290  	O290*       	41506	EA  					WING RIB	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	57679	1515 				99974				FOUND LOOSE NAILS LESS THAN .1250 OUT ON SECOND RIB OUTBOARD OF STRUT AFT SPAR.  FIRST AND SECOND RIB INBOARD OF STRUT A	ND FIRST RIB OUTBOARD OF STRUT AND FRONT SPAR ALL ON RIGHT WING.  LEFT WING, FOUND LOOSE NAILS MORE THAN .1250 OR MISSIN	G ON 1ST AND 2ND RIB OUTBOARD OF STRUT ON FRONT SPAR.  ONE NAIL MISSING ON 1ST RIB INBOARD OF STRUT ON FRONT SPAR.  ONE 	LOOSE LESS THAN .1250 ON SECOND RIB INBOARD OF STRUT ON FRONT SPAR.  NO CRACKS FOUND IN EITHER WING.			1	H	7	1 	3O	3	O	 	A759    	E229				 
2002022500016	20020225	00016	CE  	2002	2	25	2002FA0000233    	1	20010828	G	2530		DRAIN VALVE     			RKWELL	NA265 	NA26565     	7630107	CE  	GARRTT	TFE731	TFE7313R1D  	01518	WP  					GALLEY	CRACKED         	C				O				OTHER                   				K	F		FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			GL	07	45H	7367 				4652				AIL TRIM LIGHT ILLUM DURING CRUISE FLIGHT. PILOT ATTEMPTED TO FREE FROZEN CONTROLS BY SLAMMING CONTROL WHEEL TO LEFT. CO	NTROLS WERE FREE BUT BINDING. CONTROLS FROZE WHEN PIC SLAMMED CONTROL WHEEL LEFT, CONTROL WHEEL STUCK IN LEFT POSITION. 	CAUSING AN CONTINUOUS TURN OF A/C. DIVERTED TO ENROUTE AIRPORT. AT LOW ALTITUDE CONTROLS WARMED UP AND AILERONS WERE REL	EASED.  MECHANIC LOOKED AT A/C AND NO PROBLEM NOTED WITH CONTROLS. TRIP WAS CONTINUED WITH NO PROBLEMS. UPON RETURN TO H	OME BASE A/C WAS REINSPECTED. A CRACKED DRAIN FITTING IN THE GALLEY WAS ALLOWING WATER FROM ICE BIN DRAIN TO LEAK INTO A	P SERVO AND FREEZE. FITTING WAS REPLACED. NO PROBLEMS NOTED SINCE FITTING REPLACED.	2	L	7	2 	4J	4	F	 	A2WE    	E6WE				 
2002031200058	20020312	00058	CE  	2002	3	12	2002FA0000235    	1	20010925	G	5711	5271	SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	8615V	2230 				50475				WING MAIN SPAR, TOP OF SPAR OUTBOARD OF STRUT FITTING.						1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002031200059	20020312	00059	SW  	2002	3	12	2002FA0000236    	1	20011017	G	5711	5271	SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	8807	1632 				47373				FOUND A CRACK AT THE SPAR BUTT ON THE RIGHT FORWARD SPAR WHILE COMPLYING WITH AD.  THE CRACK WAS CLOSE TO THE WING ATTAC	H FITTING WHICH LIMITED THE ABILITY TO FULLY INSPECT THE CRACK WITHOUT MAJOR DISASSEMBLY.  A PIECE OF .020 INCH SAFETY W	IRE WAS ABLE TO GO INTO THE CRACK .5000 INCH.  ( A FEELER GUAGE COULD NOT BE USED DUE TO THE LOCATION IN REFERENCE TOTHE	 ATTACHMENT BARCKET).  THE CRACK APPEARED TO START FROM JUST BELOW THE WING ATTACHMENT BOLT AND GO TOWARD THE LOWER ATTA	CHMENT BOLT.		1	H	7	1 	3O	3	O	NC	A759    	E274				 
2002031200060	20020312	00060	SW  	2002	3	12	2002FA0000237    	1	20010813	G	1400		FASTENER        			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					RT WING	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	38WK	3617 				113379				RIGHT WING: 16 LOOSE NAILS, 3 VERY LOOSE, 1 MISSING  LEFT WING:  9 LOOSE NAILS, 0 VERY LOOSE, 0 MISSING.						1	H	7	1 	3O	3	O	NC	A759    	E274				 
2002031200061	20020312	00061	SW  	2002	3	12	2002FA0000238    	1	20010507	G	5711	5263	SPAR            			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2D     	41508	EA  					WING	CRACKED         	D			VE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	5038A					37679	L4862927A			INSPECTED AIRCRAFT AS PER AD, FOUND LEFT AFT SPAR HAS COMPRESSION CRACK AT OUTBOARD END OF DOUBLER PLATES FOR STRUT ATTA	CH FITTING.					1	H	7	1 	3O	3	O	 	A759    	E274				 
2002031200062	20020312	00062	SW  	2002	3	12	2002FA0000239    	1	20010627	G	5711	5262	SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					WINGS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	2763G	1762 				459				DURING ANNUAL INSPECTION, WING SPAR INSPECTION IAW AD., FOUND LONGITUDINAL CRACKS IN THE AREA OF WING STRUT ATTACH POINT	S.  RIGHT FORWARD SPAR LONGITUDINAL CRACK OBSERVED FROM MISSING CENTER RIB NAIL, INBOARD FROM THE STRUT ATTACH DOUBLER A	PPROXIMATELY 2 INCH LONG, ANOTHER OUTBOARD FROM STRUT ATTACH DOUBLER UPPER BOLT HOLE APPROXIMATELY 3 INCHES LONG.  LEFT 	FORWARD SPAR, OUTBOARD RIB FROM STRUT ATTACH DOUBLER, A RIB NAIL WAS PREVIOUSLY REPLACED AND LONGITUDINAL CRACK IN BOTH 	DIRECTIONS FROM NAIL POSITION (CENTER NAIL) APPROXIMATELY 2 INCHES LONG.  THIS IS WHERE THE INSPECTION WAS TERMINATED.  	DID NOT CUT ANY HOLES OR INSPECT THE REST OF THE SPAR DUE TO REJECTION OF THE WING SPARS.	1	H	7	1 	3O	3	O	 	A759    	E223				 
2002031200063	20020312	00063	SW  	2002	3	12	2002FA0000240    	1	20010103	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4221E					7AC7151				1) RIGHT WING FRONT SPAR BETWEEN 3RD AND 4TH RIB ON FORWARD FACE OF SPAR A CRACK CROSSING 3 ANNUAL RINGS APPROXIMATELY 4	 INCHES IN LENGTH.  2) LEFT WING LOOSE OR MISSING NAILS IN FRONT SPAR AS 3RD AND 4TH RIBS LOOSE OR MISSING NAILS IN FRON	T AND REAR SPARS ADJACENT TO STRUT ATTACH FITTING AND OUTBOARD OF SAME.				1	H	7	1 	3O	3	O	 	A759    	E205				 
2002031200064	20020312	00064	SW  	2002	3	12	2002FA0000241    	1	20010103	G	5711		SPAR            			BBAVIA	7     	7AC         	2110102	SW  	CONT  	A65   	A65*        	17003	SO  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	83946					7AC2628				1) RIGHT WING/ CRACKS PROPAGATING FROM BOLT HOLES ADJACENT TO FUSELAGE ATTACHMENT FROM AND REAR.  2) CRACK OUTBOARD OF R	EAR LIFT STRUT REAR SPAR (RIGHT WING) 3) LEFT WING REAR SPAR (ORIGINAL FACTORY SPAR)  EDGE GLUED JOINT DELAMINATED FROM 	ATTACH FITTING OUT TO AILERON 1ST INBOARD RIB.				1	H	7	1 	3O	3	O	 	A759    	E205				 
2002031200065	20020312	00065	SW  	2002	3	12	2002FA0000242    	1	20010615	G	5711	SAR5263L	SPAR            			BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2B     	41508	EA  					LT WING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	7591F	5025 				21070	L3018827A			CRACK IN REAR SPAR OF LEFT WING OUTBOARD OF DOUBLER AT SPAR ATTACH FITTING.  WING HAS HIT GROUND BEFORE WHEN INBOARD LAN	DING GEAR BOLT FAILED.  TIP OF FORWARD SPAR HAS REPAIR AND DOUBLER.					1	H	7	1 	3O	3	O	 	A759    	E274				 
2002031200066	20020312	00066	SW  	2002	3	12	2002FA0000243    	1	20010517	G	1400		FASTENER        			BBAVIA	7     	7ECA        	21101NN	SW  	CONT  	O200  	O200*       	17020	SO  					SPAR	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	9510S	2572 				7ECA275				APPROXIMATELY 8 RIB ATTACH NAILS WERE FOUND MISSING ON EACH WING.  (BOTH SPARS)  SCRATCHES AND GOUGES WERE FOUND ON LEFT	 REAR SPAR MID AREA.  THESE WERE APPARENTLY MADE BY REPAIRMAN SLIDING RIBS DOWN SPAR, DURING THE LAST REPAIR OF WING.  B	OTH WINGS WILL HAVE COVER REMOVED FOR FURTHER INSPECTION AND REPAIR.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2002031200067	20020312	00067	CE  	2002	3	12	2002FA0000244    	1	20010517	G	1400		FASTENER        			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360*    	 	EA  					RIB	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	2561Z	1290 				35377				APPROXIMATELY 10 RIB NAILS WERE MISSING ON EACH WING.  NAIL HOLES WERE NOT ELONGATED.  NO OTHER DAMAGE WAS FOUND.  THE G	ENERAL LOCATION OF MISSING NAILS WERE AT STRUT ATTACH AREAS.					1	H	7	1 	3O	3	O	 	A21CE   	1E10				 
2002031200068	20020312	00068	CE  	2002	3	12	2002FA0000245    	1	20010630	G	5711	SA5263R	SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	8643	3161 				35473	L495755A			AIRFRAME TOTAL TIME 3161 DURING THE ANNUAL INSPECTION AND WHILE COMPLYING WITH AD INSTRUCTIONS.  IT WAS DISCOVERED THAT 	THE RIGHT WING REAR SPAR HAD AN 8 INCHES LONG LONGITUDINAL CRACK AT THE REAR STRUT ATTACH POINT.  ITS SUSPECTED THAT THE	 AIRFRAME HIGH TIME COULD BE THE CAUSE.				1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002031200069	20020312	00069	SW  	2002	3	12	2002FA0000246    	1	20010718	G	5711		SPAR            			BBAVIA	7     	7FC         	2110124	SW  	CONT  	C90   	C90*        	17009	SO  					RT WING	DEFECTIVE       	D			FYUG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9898B					218				CRACK VISIBLE MIDWAY FROM TOP TO BOTTOM OF RIGHT WING FRONT SPAR FROM 44 INCHES INBOARD ALONG SPAR TO APPROXIMATELY 130 	INCHES FROM INBOARD.  WOOD APPEARS TO BE IN GOOD CONDITION OTHER WISE.  DEFECT DISCOVERED DURING SPAR INSPECTION IN COMP	LIANCE WITH AD.  AIRCRAFT WAS NOT DAMAGED OR UNAIRWORTHY IN ANY OTHER WAY.				1	H	7	1 	3O	3	O	 	A759    	E252				 
2002031200070	20020312	00070	CE  	2002	3	12	2002FA0000247    	1	20011226	G	5751		BRACKET         			CESSNA	195   	195B        	2073112	CE  	JACOBS	R755  	R7557       	35003	EA  					IB AILERON	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195BA					16069				BOTH BRACKETS CRACKED COMPLETELY ACROSS BEARING BOSSES.  THIS IS A RECURRING AND EXTENSIVE PROBLEM THAT IS POTENTIALLY V	ERY CRITICAL FOR CONTROLLABILITY OF THE AIRCRAFT.  WE WERE ABLE TO BREAK THE INBOARD END OF AN AILERON LOOSE FROM THE AI	RCRAFT WITH APPROXIMATELY 40 LBS OF FORCE EXERTED BY HAND ON THE AILERON WITH A BEARING BOSS CRACKED ON THE HINGE BRACKE	T.			1	H	7	1 	3R	3	R	 	A790    	5E11				 
2002031200071	20020312	00071	CE  	2002	3	12	2002FA0000248    	1	20011226	G	5751	03227091	BRACKET         			CESSNA	195   	195B        	2073112	CE  	JACOBS	R755  	R7557       	35003	EA  					AILERON HINGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	195BA					16069				BOTH BRACKETS CRACKED COMPLETELY ACROSS BEARING BOSSES.  THIS IS A RECURRING AND EXTENSIVE PROBLEM THAT IS POTENTIALLY V	ERY CRITICAL FOR CONTROLLABILITY OF THE AIRCRAFT.  WE WERE ABLE TO BREAK THE INBOARD END OF AN AILERON LOOSE FROM THE AI	RCRAFT WITH APPROXIMATELY 40 LBS OF FORCE EXERTED BY HAND ON THE AILERON WITH A BEARING BOSS CRACKED ON THE HINGE BRACKE	T.			1	H	7	1 	3R	3	R	 	A790    	5E11				 
2002031200073	20020312	00073	CE  	2002	3	12	2002FA0000250    	1	20010125	G	5711		SPAR            			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320*      	41508	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	6369N	2881 				44				WOODEN SPARS, NAILS OUT OF LEADING EDGE RIBS, WOODEN SPACERS WERE LEFT OUT OF FIRST FOUR INBOARD LEADING EDGE RIBS.  LEA	DING EDGE LOOSE, NAILS LOOSE.   HAD BEEN PATCHED BEFORE, HAD PUT SCREWS INSTEAD OF NAILS ON LEADING EDGE SPARS AND RIBS.	  SOME RIBS CRACKED, INNER RIB LACING CORDS BROKEN, HAVE SCRAPPED WINGS AND REPLACING WITH NEW METAL SPAR WINGS.				1	H	7	1 	3O	3	O	 	A759    	1E12				 
2002031200074	20020312	00074	SW  	2002	3	12	2002FA0000251    	1	20010717	G	5711	5270	SPAR            			BBAVIA	7     	7GCBC       	1220601	SW  	LYC   	O320  	O320*       	41508	EA  					WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2546Z	979  				99877				DETECTED COMPRESSION CRACK AT TOP OF AFT SPAR  ON THE OUTBOARD END OF LIFT STRUT DOUBLER PLATE.  CRACK PROGRESSED DOWN A	FT SIDE ABOUT 1 INCH.  LONGITUDINAL CRACK WAS ALSO FOUND IN AFT SPAR LAST 12 INCHES NEAR TIP.  CRACK WAS IN CENTER OF SP	AR.  WHEN THE WING WAS DISASSEMBLED FOR SPAR REPLACEMENT, LONGITUDINAL CRACKS WERE FOUND ON FRONT SPAR UNDER THE DOUBLER	 PLATES FOR THE FUSELAGE TO WING ATTACH FITTINGS.  THESE CRACKS WERE NOT DETECTED UNTIL THE PLATE WAS REMOVED.  CRACKS W	ERE BETWEEN THE BOLT HOLES FOR THE DOUBLER PLATE.  THIS WING SUSTAINED A TIP STRIKE, AND WAS REPAIRED.  SUBMITTER SPECUL	ATES THAT COMPRESSION CRACK AND OTHER DAMAGE OCCURRED AT THIS TIME.	1	H	7	1 	3O	3	O	NC	A759    	E274				 
2002031200076	20020312	00076	SW  	2002	3	12	2002FA0000253    	1	20010403	G	5711		SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					RT WING	CRACKED         	D			TVMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6309N	2214 				233				WHILE COMPLYING WITH AD, A LONGITUDINAL CRACK IN THE RIGHT FOREWARD WOODEN WING SPAR APPROXIMATELY 30 INCHES LONG.						1	H	7	1 	3O	3	O	 	A759    	E223				 
2002031200078	20020312	00078	SW  	2002	3	12	2002FA0000255    	1	20010801	G	1400		FASTENER        			BBAVIA	7     	7ECA        	21101NN	SW  	LYC   	O235  	O235*       	41505	EA  					FWD & REAR SPARS	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	86983	3566 				103174				NUMEROUS RIB NAILS MISSING OR BACKED OUT FARTHER THAN .1250 ON FORWARD AND AFT WING SPARS, LEFT AND RIGHT WINGS.  INSPEC	TED SPARS AND REPLACED SUCH NAILS.					1	H	7	1 	3O	3	O	 	A759    	E223				 
2002031200079	20020312	00079	SW  	2002	3	12	2002FA0000256    	1	20010626	G	5711		SPAR            			BBAVIA	7     	7GCB        	2110130	SW  	LYC   	O320  	O320*       	41508	EA  					RT WING	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	9866Y					64				LONGITUDINAL CRACK LOCATED AT ROOT END OF FRONT WING SPAR IN RIGHT WING.  CRACK RUNS FROM BUTT END OF SPAR THROUGH THE T	WO TOP BOLT HOLES OF THE SPAR TO FUSELAGE ATTACHMENT BRACKET.  CRACK COULD BE SEEN IN THE BUTT END GRAIN AND BY REMOVING	 THE FUSELAGE ATTACHMENT BRACKET AND THE BUSHINGS FROM THE BOLT HOLES.				1	H	7	1 	3O	3	O	 	A759    	E274				 
2002031200082	20020312	00082	SW  	2002	3	12	2002FA0000258    	1	20010718	G	5711		SPAR            			BBAVIA	7     	7EC         	2110120	SW  										RT WING	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9898B					218				WING SPAR, CRACK VISIBLE MIDWAY FROM TOP TO BOTTOM OF NIGHT WING FRONT SPAR FROM 44 INCHES INBOARD ALONG SPAR TO APPROXI	MATELY 1130 INCHES FORM INBOARD.  WOOD APPEARS TO BE IN GOOD CONDITION OTHERWISE.  DEFECT DISCOVERED DURING SPAR INSPECT	ION IN COMPLIANCE WITH AD.  AIRCRAFT WAS NOT DAMAGED OR UNAIRWORTHY IN ANY OTHER WAY.				1	H	7	1 	3O			 	A759    					 
2002031200086	20020312	00086	SW  	2002	3	12	2002FA0000263    	1	20010129	G	5711		SPAR            			BBAVIA	7     	7GCAA       	21101N8	SW  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	CGFJD					92				WINGS REMOVED FROM AC, THE REPAIR ON THE LT REAR SPAR STRUT ATTACH POINT.  ALL FABRIC COVERING REMOVED, LT REAR SPAR HAD	 A 1 INCH X 16 INCHES LONG .1250 PLYWOOD STRIP GLUED TO THE TOP OF THE SPAR WHICH HID THE CRACK TO BUSHING HOLE.  IT WOU	LD APPEAR THAT CRACK,  4 .7500 AND ADDING THE 1 INCH X 16 INCH STRIP ON TOP.  GLUING WAS LESS THAN ACCEPTABLE.   2 INCH 	CRACK ON THE LT SPAR REMOVED FROM THE RIB FLANGE AND THE RIB MOVED, DETECTION OF THE CRACK IS NEXT TO IMPOSSIBLE.  THE 1	 INCH COMPRESSION FAILURE ON THE RIGHT SPAR IS BESIDE EDGE OF THE .1250 PLYWOOD REINFORCEMENT.  CRACK IS VISIBLE WITH GO	OD LIGHT, CRACK DOES NOT GO COMPLETELY ACROSS THE .7500 INCH THICKNESS AND NO LINE VISIBLE ON THE OPPOSITE SIDE.	1	H	7	1 	3O			 	A759    					 
2002031200087	20020312	00087	CE  	2002	3	12	2002FA0000264    	1	20010313	G	2760	26270522	SOLENOID        			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE731*     	01518	WP  					SPOILER MANIFOLD	INTERMITTENT    	B			WIBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	10AH					657				SPOILER OPERATION INTERMITTENT.  MAINIFOLD ASSEMBLY HAS TWO SOLENOIDS, APPEARS THAT ONE MAY BE STICKING OR HAVE AN ELECT	RICAL PROBLEM.					2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002031200089	20020312	00089	SO  	2002	3	12	2002FA0000267    	2	20011201	G	8520	SA640518	PISTON          			CESSNA	182   	182M        	2072728	CE  	CONT  	O470  	O470R       	17026	SO  					NR 5 CYL	FAILED          	G				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CL	CLIMB          	1			WP	19	71298	280  				18259567				CASTROSPHOIC ENGINE FAILURE AFTER TAKEOFF.  EMERGENCY LANDING WAS EXECUTED WITHOUT INCIDENT.  ENGINE WAS DISASSEMBLED, R	EVEALING NR 5 PISTON DISINTEGRATED.  ENGINE HAD BEEN OVERHAULED APPROXIMATELY 280 HOURS AND 3.5 YEARS PRIOR TO FAILURE. 	 ALL PISTONS HAD BEEN REPLACED WITH NEW AT OVERHAUL.  PARTS WERE SUBMITTED TO THE MANUFACTURER FOR ANALYSIS.				1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002031300009	20020313	00009	GL  	2002	3	13	2002FA0000294    	1	20010722	G	2821		FUEL FILTER     			AMTR  	GLASAR	GLASAIR     	05618GT	GL  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE FUEL	CLOGGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	14WQ					2172				IN LINE FUEL FILTER INSTALLED BETWEEN FUEL SELECTOR VALVE AND BOOST PUMP.  CLOGGED WITH RUST DEBRIS, AND RESTRICTED FLOW	 TO ENGINES.					1	L	7	1 	3O	3	O	RT	EXPA1L71	1E10				 
2002031300014	20020313	00014	GL  	2002	3	13	2002FA0000299    	2	20011220	G	7323	23065125	GOVERNOR        								ALLSN 	250C  	250C30      	03013	GL  					ENGINE	INOPERATIVE     	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		11056					890384			VERY SENSITIVE, COULD NOT MATCH TORQUES AND SHAFT IS RACHETY.  REPLACED WITH SERVICEABLE PART.											3	U			E1GL				 
2002031300017	20020313	00017	EA  	2002	3	13	2002FA0000304    	2	20011126	G	7414	1068256013	MAGNETO         			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540*      	41532	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	200HM					32R7680025				DURING INSPECTION FOUND A DISTRIBUTOR GEAR TOOTH BROKEN AND LAYING IN MAGNETO CAP.  THIS MAGNETO HAS PLASTIC GEARS AND H	AS BEEN FOUND IN THIS CONDITION ON NUMEROUS MAGNETOS OF THIS TYPE.					1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002031300121	20020313	00121	CE  	2002	3	13	2002FA0000338    	1	20010918	G	3310	PQ876SW	LIGHT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320*       	41508	EA  					COCKPIT	SHORTED         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	13	1368U					17267039				THE PART WAS INSTALLED AROUND THE TACH AND CONNECTED TO THE RHEOSTAT FOR THE INSTRUMENT LIGHTS.  AFTER A COUPLE OF YEARS	 IT SHORTED OUT THE SYSTEM.  IT BURNED OUT THE RHEOSTAT S2091-5 AND THE POWER TRANSISTOR 2N3055.  THIS CAUSED NO INSTRUM	ENT LIGHT IN THE AIRCRAFT.  THIS HAPPENED IN THE DAY TIME AND NOT AT NIGHT IFR.  THE OWNER NOTICED NO LIGHTS AND NOTIFIE	D HIS TECHNICIAN.  AFTER TROUBLESHOOTING THE SYSTEM HE FOUND THAT THE WIRES ON THE TOP OF THE LITE RING WERE TOUCHING ON	E ANOTHER, CAUSING A DIRECT SHORT.  CALLED MFG, THEY INQUIRED,  WHEN THIS RING WAS INSTALLED.  THEY SAID TO REMOVE IT FR	OM THE AIRCRAFT AND SEND IT BACK TO THEM, THEY WOULD REPLACE IT FREE OF CHARGE, BECAUSE THIS IS AN OLD STYLE RING.	1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002032700076	20020327	00076	CE  	2002	3	27	2002FA0000345    	1	20010402	G	2810	051600918	FUEL TANK       			CESSNA	172   	172S        	2072439	CE  	LYC   	O360  	IO360A1A    	41514	EA  					FUSELAGE	CRACKED         	D				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SO	05	272RP	613  				172S8405				DURING GROUND RUN, DETECTED FUEL SMELL IN COCKPIT.  REMOVED FORWARD FLOOR PANS AND OBSERVED FUEL PUDDLE AND STAIN.  INSP	ECTION REVEALED STAINING ON RESERVOIR TANK.  DEFUELED AIRCRAFT AND REMOVED RESERVOIR TANK.  STRIPPED PAINT FROM SUSPECTE	D CRACK AREA.  DYE PEN INSPECTION REVEALED 1 INCH CRACK ON LOWER AFT WELD BEAD.  REPLACED WITH NEW PART, SUSPECTED CAUSE	:  STRESS DUE TO UPPER MOUNT HOLE NOT ALIGNED WITH NUT PLATE.			1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2002032700094	20020327	00094	SW  	2002	3	27	2002FA0000347    	1	20010625	G	5711		SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	CONT  	O200  	O200*       	17020	SO  					RT WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	CFQYQ	1905 				128				TROUBLE AREA IN THE REGION OF LIFT STRUT ATTACHMENT POINT,  REMOVED VARNISH AND SMALL AMOUNT OF WOOD, COULD IDENTIFY SMA	LL CRACK IN THE GLUE JOINT ON REAR FACE OF RT REAR WING SPAR.  ALSO DETECTED ON UPPER EDGE OF RT REAR SPAR A TOTAL OF 5 	COMPRESSION TYPE CRACKS.  TWO ACTUAL SPLITS WERE REVEALED STARTING AT THE REINFORCING PLYWOOD PLATE.  FOLLOWED EDGE GRAI	N OF WOOD FRO ABOUT 2 AND 3 INCHES.  TWO OF THESE CRACKS EXTENDED DOWN THROUGH SPAR, AT  PLYWOOD PLATE EDGE, A DISTANCE 	OF ABOUT 40-50 PER CENT OF THE WING SPAR.  SUGGEST: ALL PLYWOOD REINFORCING PLATES HAVE THEIR VERTICAL EDGES CHAMFERED(T	APERED) AT LEAST .7500 INCH, HELP IN REDUCING STRESS RISER CRATED AT VERTICAL EDGE OF REINFORCING PLATE.	1	H	7	1 	3O	3	O	 	A759    	E252				 
2002040500007	20020405	00007	CE  	2002	4	5	2002FA0000443    	1	20011203	G	3110	04131267	RHEOSTAT        			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470*       	17026	SO  					INSTRUMENT PANEL	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	05	5379B	3026 				33379				FLYING LOW THRU MOUNTAIN PASS, TRIED TO TURN ON INSTRUMENT LIGHTS.  MUCH SMOKE IN CABIN, TURNED OFF MASTER.   FOUND RESI	STOR WINDINGS FAILED, CONTACT ARM BURNED THRU TO CASE,  ALSO CIRCUT BREAKER DID NOT OPEN. FOUND PLASTIC TRIM PANEL HOLE 	HAD EGG SHAPE, BUTTON COULD NOT POP OUT.  REMOVE BACK OF SWITCH AND INSPECT.  BETTER TO REPLACE WITH PUSH-PULL SWITCH AN	D CHECK CIRCUIT BREAKERS.			1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2002042500054	20020425	00054	GL  	2002	4	25	2002FA0000524    	1	20011119	G	7120		MOUNT           			CIRRUS	SR    	SR22        	2130001	GL  	CONT  	O550  	IO550*      	 	SO  					ENGINE	CHAFED          	B			MNGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	730CD	101  				0053				DURING THE 100 HOUR INSPECTION, A FUEL LINE CLAMP WAS FOUND CHAFING ON THE ENGINE MOUNT.  THE CLAMP HAD CHAFED APPROXIMA	TELY .006 INTO ONE OF THE ENGINE MOUNT TUBES.  THE CLAMP FOR THIS LINE APPEARS TO BE TOO LONG, ALLOWING IT TO CONTACT TH	E MOUNT TUBE.  THE ENGINE MOUNT WAS REPLACED AND THE CLAMP ATTACH BRACKET WAS SHORTENED SO AS TO PREVENT A REOCCURANCE O	F THIS CONDITION.  THIS AREA SHOULD BE GIVEN A CLOSE INSPECTION FOR CHAFING AND THE CLAMP REPOSITIONED OR THE BRACKET SH	ORTENED.		1	L	7	1 	3O	3	O	NT	A00009CH	E3SO				 
2002050600134	20020506	00134	CE  	2002	5	6	2002FA0000560    	1	20010117	G	2140	FR13E55IEL4500	COMBUST CHAMBER 			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520*   	17032	SO  					HEATER	CRACKED         	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	13	6798V	531  				421C1254				OWNER REQUESTED PRESSURE DECAY TEST IAW AD.  PRESSURE COULD NOT BE MAINTAINED.  REMOVED HEATER,  DISCOVERED LARGE CRACK 	AT AFT,  LOWER WALL OF COMBUSTION CHAMBER,   ALONG WELD LINE.  THIS HEATER WAS INSTALLED 11/1/99 WITH ONLY 531.3 TT HEAT	ER HOURS ON PART.  FACTORY REBUILT UNIT INSTALLED WITH NEW CERAMIC COATED LINER TO PREVENT CRACKING.  HEATER WAS REPLACE	D WITH FACTORY WARRANTY UNIT,  AND SENT BACK TO FACTORY FOR EXCHANGE.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002051400039	20020514	00039	WP  	2002	5	14	2002FA0000582    	1	20010420	G	6310	369D25146	BEARING RACE    			HUGHES	369   	369D        	4470706	WP  										M/R TRANSMISSION	CRACKED         	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	C6PHC					180257D				REMOVED MAIN ROTOR TRANSMISSION FOR AN OIL LEAK.  FOUND FORWARD TAIN ROTOR O/P ASSEMBLY PINION BEARING INNER RACE.  CRAC	KED.  REPLACED BEARING ASSEMBLY.					1	G	7	1 	3U			 	H3WE    					 
2002052300105	20020523	00105	CE  	2002	5	23	2002FA0000665    	1	20011120	G	5410		STRUCTURE       			CESSNA	411   	411A        	2075904	CE  	CONT  	O520  	GTSIO520C   	17032	SO  					NACELLE	CORRODED        	B			A5OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	333SF	3788 				4110260				DURING INSPECTION OF THE WING NACELLE BAGGAGE COMPARTMENT STRUCTURE CORROSION WAS DISCOVERED UNDER THE TRIM AND CARPETS.	  UPON REMOVAL OF THE NACELLE BAGGAGE COMPARTMENT TRIM AND CARPETS SEVER SURFACE CORROSION WAS DISCOVERED.  MAJOR SECTIO	N OF THE NACELLE STRUCTURE IN BOTH WINGS WAS DAMAGED BY CORROSION.  THE PROBABLE CAUSE OF THIS CORROSION WAS THE USE OF 	TRIM ADHESIVE DIRECTLY ON THE AIRCRAFT STRUCTURE.  THE TRIM ADHESIVE ACTED LIKE AN ACID ON THE SKINS, RIBS, ANGELS AND B	ULKHEADS OF THE NACELLE.  RECOMMEND ONLY APPROVED ADHESIVES BE USED TO INSTALL TRIM AND CARPETS.		1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2002072900009	20020729	00009	EA  	2002	7	29	2002FA0000860    	2	20010925	G	7414	BL68256013	MAGNETO         			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					ENGINE	CRACKED         	G				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			GL	25	39945	17   				32R7887172				AIRCRAFT ON CLIMBOUT FROM AIRPORT, LOST ENGINE POWER AND CRASHED.  INVESTIGATION CONCLUDED MAGNETO FAILED DUE TO FATIGUE	 CRACK IN HOUSING CAUSING MAGNETO HOUSING TO SEPARATE FROM ENGINE.					1	L	7	1 	3O	3	O	 	A3SO    	E14EA				 
2002082600057	20020826	00057	CE  	2002	8	26	2002FA0000987    	1	20010801	G	3213	9530489	AXLE            			HELIO 	H295  	H295        	4300802	CE  	LYC   	O480  	GO480*      	41527	EA  					MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	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				 
2002091900002	20020919	00002	CE  	2002	9	19	2002FA0001052    	1	20011203	G	3110	04131267	RHEOSTAT        			CESSNA	182   	182         	2072702	CE  	CONT  	O470  	O470*       	17026	SO  					INTERNAL	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	05	5379B	3026 				33379				FLYING LOW THROUGH A  MOUNTAIN PASS TRIED TO TURN ON INSTRUMENTS LIGHTS.  SMOKE IN CABIN.  TURNED OFF MASTER.  FOUND RES	ISTOR WINDINGS FAILED.  CONTACT ARM BURNED THRU TO CASE.  ALSO CIRCUIT BREAKER DID NOT OPEN.					1	H	7	1 	3O	3	O	NT	3A13    	E273				 
2003010600012	20030106	00012	CE  	2003	1	6	2002FA0001387    	1	20010701	G	2720	12600211	BELLCRANK       			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470J       	17026	SO  					RUDDER PEDALS	BENT            	D				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NM	02	64426	2067 				18052897				AIRCRAFT WAS INVOLVED IN AN ACCIDENT ON LANDING DUE TO LOSS OF CONTROL.  CFI WAS FLYING FROM THE RT SEAT.  AIRCRAFT LEFT	 THE RUNWAY TO THE RT EVEN THOUGH PILOT APPLIED FULL LT RUDDER.  DURING INSPECTION.   DISCOVERED THAT THE LT RUDDER PEDA	L WOULD UNLOCK (STOWABLE PEDALS)  WHEN FIRM PRESSURE WAS APPLIED, DUE TO BENT BELLCRANK.				1	H	7	1 	3O	3	O	 	5A6     	E273				 
2003021800083	20030218	00083		2003	2	18	2003FA0000125    	4	20010711	G	6113	055032111	BULKHEAD        			CESSNA	172   	172S        	2072439	CE  										SPINNER	CRACKED         	B			IBIR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	27	740SP	126  				172S8671				SPINNER AFT BULKHEAD, CRACKED.						1	H	7	1 	3O			NT	3A12    					 
2003031200048	20030312	00048	NM  	2003	3	12	2003FA0000184    	1	20010623	G	6320	900D1400005101	TRANSMISSION    			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      	 	NE  					MAIN ROTOR	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	56   				90000085				MAIN TRANSMISSION PRODUCING METAL CHIPS.  CHIP SIZE EXCEED MAINTENANCE MANUAL LIMITS.						1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2003031300001	20030313	00001	NM  	2003	3	13	2003FA0000186    	1	20010724	G	6220	900C2010186101	DRIVE LINK      			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      	 	NE  					MAIN ROTOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD	107  				90000085				MAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS.						1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2003031300002	20030313	00002	NM  	2003	3	13	2003FA0000187    	1	20010726	G	6220	900C2010186101	DRIVE LINK      			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      	 	NE  					MAIN ROTOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD					90000084				MAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS.						1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2003031300003	20030313	00003	NM  	2003	3	13	2003FA0000188    	1	20010906	G	2910	071142258	INDICATOR       			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      	 	NE  					FILTER BYPASS	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3PD					90000085				AFTER INSTALLING NEW HYDRAULIC FILTER, THE RETURN SIDE BYPASS INDICATOR POPPED WITH NO PRESSURE APPLIED.  AFTER RESETTIN	G THE INDICATOR, INDICATOR POPPED AGAIN.  REPLACED IMPENDING BY-PASS INDICATOR PN 071142-258.  OPS CHECK GOOD.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2003031300004	20030313	00004	NM  	2003	3	13	2003FA0000190    	1	20010917	G	2910	AC3676F1	FILTER          			DOUG  	MD900 	MD900       	3027375	NM  	PWC   	PW207 	PW207E      	 	NE  					HYD SYSTEM	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	902PD					90000084				BYPASS PIN POPPED ON NR 1 HYDRAULIC RETURN FILTER.  REMOVED FILTER AND INSPECTED FOR CONTAMINATION.  REPLACED FILTER.  O	PS AND LEAK CHECK GOOD.					1	G	7	2 	3U	3	U	NC	H19NM   	E42NE				 
2003031300012	20030313	00012	GL  	2003	3	13	2003FA0000218    	1	20010905	G	4900	427CK1	BATTERY         			BOMBDR	BD700 	BD7001A10   	1390006	GL  	RROYCE	BR700 	BR700710A220	09500	NE  					APU	FAULTY          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	226HD	168  				9022	12201			AIRCRAFT WAS CONNECTED TO EXTERNAL AIRCRAFT POWER CART, AND POWERED UP.  A LOUD POP WAS HEARD COMING FROM AFT EQUIPMENT 	BAY OF AIRCRAFT.  DURING INVESTIGATION, ANOTHER POP WAS HEARD.  ACCESSED APU BATTERY.  FOUND IT TO BE DAMAGED AND SMOKIN	G.  FOUND SEVERAL CELLS BURNED AND HEAT BLANKET BURNED, ALSO.   SUSPECT BATTERY CHARGER TO BE FAULTY.  BOTH COMPONENTS R	EPLACED. REMOVED ITEMS, SENT FOR EVALUATION.  NO DAMAGE TO AIRCRAFT.  THE COCKPIT INDICATION AT TIME OF INCIDENT SHOWED 	(APU BATT FAIL) TEMPERATURE AND VOLTAGE WERE NORMAL.		2	L	7	2 	4F	4	F	RT	T00003NY	E00061EN				 
2003040900063	20030409	00063	SO  	2003	4	9	2003FA0000324    	2	20011116	G	8520	SA639193	BUSHING         								CONT  	A50   	A502        	17002	SO  					CRANK C/WEIGHT	MISMANUFACTURED 	B			JZYR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			NM	09										WHILE CHECKING THE SIZE OF THE NEW MFG SA639193 BUSHINGS PRIOR TO INSTALLATION IN THE COUNTERWEIGHTS I FOUND TWO NEW STA	NDARD SIZE BUSHINGS THAT WERE APPROXIMATELY .002 SMALL IN THE OUTER DIAMETER.										3	O			E190				 
2003050700158	20030507	00158	CE  	2003	5	7	2003FA0000400    	1	20010816	G	3230	12416308	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	136  				P21000417				LT AND RT MAIN LANDING GEAR SHELL BUMPER DEBONDS.  THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FUL	L DOWN TRAVEL.  THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, 	THEREFORE, 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				 
2003091700006	20030917	00006	CE  	2003	9	17	2003FA0000755    	1	20011229	G	2701	05117821	CONTROL COLUMN  			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520*      	17032	SO  					COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	185AF	2126 				18502236				A CRACK WAS FOUND ON THE AFT SIDE, ASCENDING UP FROM THE BASE OF THE CONTROL COLUMN (CONTROL U ASSY).  THE CRACK MEASURE	D APPROXIMATELY 6 INCHES AND HAD SPREAD APART APPROXIMATELY .5000 INCH JUST ABOVE THE ELEVATOR PUSH-PULL TUBE BEARING AN	D EXTENDED UP THROUGH THE PIVOT BEARING.  SIGNIFICANT AMOUNTS OF RUST WERE NOTED INSIDE THE COLUMN AT THE BASE OF THE CR	ACK.  IT SHOULD BE NOTED THE AIRCRAFT IS INSTALLED ON AMPHIBIAN FLOATS.  POSSIBLE CAUSE OF CRACK COULD BE CONTRIBUTED TO	 WATER COLLECTING IN THE BOTTOM OF THE COLUMN AND FREEZING.		1	H	7	1 	3O	3	O	 	3A24    	E5CE				 
2003111400050	20031114	00050	EA  	2003	11	14	2003FA0001091    	2	20010601	G	8520		FLANGE          			PITTS 	S2B   	S2B         	2210006	SO  	LYC   	O540  	AEIO540D4A5 	41532	EA  	HARTZL	HCC2Y	HCC2YR4     	GL  	CRANKSHAFT	CRACKED         	B			R6AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	260MM					5186				FOUND CRACKED CRANKSHAFT FLANGE.  INSTALLED 3 BLADE PROP TO DECREASE STRESS ON CRANKSHAFT.						1	Q	7	1 	3O	3	O	NC	A8SO    	1E4	5	C	P920	 
2003111400045	20031114	00045	EA  	2003	11	14	2003FA0001092    	2	20010701	G	8520		FLANGE          			PITTS 	S2B   	S2B         	2210006	SO  	LYC   	O540  	AEIO540D4A5 	41532	EA  	HARTZL	HCC2Y	HCC2YR4     	GL  	CRANKSHAFT	CRACKED         	B			R6AR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	260GR					5059				FOUND CRACKED CRANKSHAFT FLANGE.  INSTALLED 3 BLADE MT PROP TO DECREASE STRESS ON CRANKSHAFT.(K)						1	Q	7	1 	3O	3	O	NC	A8SO    	1E4	5	C	P920	 
2004100400096	20041004	00096	CE  	2004	10	4	2004FA0000742    	1	20010109	G	1430		NUT             			BEECH 	35    	V35B        	1151548	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	RUDDER	CRACKED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	4572A	3452 				D9150				ON ANNUAL INSPECTION OF RUDDERS AT THE CENTER ATTACH FITTING AFT SPAR MOUNT, SLIGHT RUST WAS NOTED.  FURTHER INSPECTION 	REVEALED 5 OUT OF THE 8 ATTACH NUTS ON THE SPAR ATTACH WERE CRACKED THROUGH TO THE BOLT THREADS.  THESE NUTS ARE CRACKED	 ONLY O THE BOTTOM AREA OF NUT.  LOOKING DOWN AT THE ATTACH NUTS WILL NOT SHOW CRACKS.  TELL TALE RUST ON THE BOLT THREA	DS IS THE ONLY TOP SIDE INDICATOR.  RECOMMEND THAT NAS679A NUT BE INSPECTED OR REPLACED WITH MS21042 OR MS21083N.  THESE	 NUTS ARE USED IN OTHER LOCATIONS ON THE PLANE.  EXPOSED NUTS ARE MORE SUSCEPTIBLE TO CRACKING.		1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P21EA	 
2002012800051	20020128	00051		2002	1	28	223527605        	4	20011203	G	2562	BP1010	BATTERY         	NARCO       	10          	CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100*      	GL  	ELT	LEAKING         	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	60830	10   	10   		19503	15070606	250894	G1018		ON DOING A PRE FLIGHT INSPECTION I FOUND THAT ACID WAS LEAKING FROM THE ELT BATTERY. FURTHER INSPECTION SHOWS THAT ACID 	LEAKING FROM THE PACK HAD DESTROYED THE ELT ELECTRONICS MODULE, THE MOUNTING BASE WAS EATEN THROUGH AS WAS THE CARPET AN	D THE ACID WAS ATTACKING THE FLOOR OF THE BAGGAGE COMPARTMENT.				1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002012800054	20020128	00054	SO  	2002	1	28	3372             	1	20011203	G	5102		WEB             	BALWKS      	F11B        	BALWKS	FIREFY	FIREFLY11B  	1050140	SO  										UPPER ENVELOPE	DAMAGED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	7244W	171  	30   		003	F11B003				HOT AIR BALLOON ENVELOPE TOP GIRDLE 1INCH WEBBING STRETCHED.  TOP ENVELOPE FABRIC PANELS DO NOT STRETCH, CAUSING SEVERE 	STITCH-HOLE ELONGATION DAMAGE TO FABRIC ALONG ALL TOP PANEL VERTICAL SEAMS, EXTENDING FROM TOP GIRDLE DOWNWARD 6-12 INCH	ES.				1	B	0	0 	  			 	A14SO   					 
2001050200067	20010502	00067	SO  	2001	5	2	58392816R        	1	20010319	G	5712		RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										LT WING	CRACKED         	P				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2816R					28R35297				INSPECTION OF AIRCRAFT IN MAINT HANGAR REVEALED TWO INCH CRACK ON LT WING AT APPROX WS 49.25, AROUND SINGLE RIVET, SKIN 	HAD BULGED AROUND RIVET AND CRACKED FORE AND AFT. INSPECTION IN WHEEL WELL SHOWED THAT RIVETS ATTACHING FLANGE TO FALSE 	REAR SPAR AND RIB TO FALSE REAR SPAR HAD SHEARED, HEADS GONE, SOME PORTION OF RIVETS LEFT, LEAVING NO STRENGTH BELOW ARE	A OF SKIN. INSPECTION INSIDE INSPECTION PANEL IMMEDIATELY AFT OF THAT AREA REVEALED CRACKED RIB AT JOIN WITH FALSE REAR 	SPAR. CLOSE INSPECTION SHOWS EVIDENCE THAT THERE WAS DAMAGE SOME TIME AGO WHICH HAD BEEN WORKING ITSELF DURING FLIGHT OP	S (ALUM. DUST AROUND FAILURE AND SEAMS, DIRT AND GREASE AT PLACES WHERE RIVET HEADS WERE GONE).	1	L	7	1 	3O			 	2A13    					 
2001050300237	20010503	00237		2001	5	3	65BA046A         	4	20010413	G	2300		RHEOSTAT        			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					RADIO	FAILED          	H			GSBA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	76RL	15481				327540024	L1737448A			RETURNING FROM A FLIGHT,  PILOT SHUT DOWN ENGINE, RADIO MASTER, THE A/C MASTER.  WHEN MASTER WAS SHUT OFF, PILOT HEARD A	 POP FROM THE RIGHT SIDE OF PANEL.  HE CHECKED BREAKERS, NOTICED NONE BLOWN, BUT SMELLED;  NOTICE SMOKE COMING FROM BEHI	ND PANEL TO LEFT OF CIRCUIT BREAKERS.  WHEN INVESTIGATED, FOUND RHEOSTAT ASSEMBLY WIRING AND COMPONENTS BURNT FOR CABIN 	LIGHT CONTROLS.  PART WAS REPLACED WITH SERVICABLE ASSEMBLY.			1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2001050200055	20010502	00055	CE  	2001	5	2	951141           	1	20010314	G	2910	124F0016CL0532	HOSE            			CESSNA	500   	550         	2076604	CE  										HYD PUMP	BURST           	B			R8RR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	07	3262M	2572 				5500652				DURING FLIGHT BOTH THE HYDRAULIC FLOW LIGHTS AND THE HYDRAULIC RESERVEOIR LOW LEVEL LIGHT ILLUMNINATED. FOUND THE PRESSU	RE LINE FROM THE NR 1 HYDRAULIC PUMP BURST APPROX. 18 INCHES FROM THE PUMP. THERE WERE NO CHAFF MARKS ON THE HOSE, SUSPE	CT INTERNAL FAILURE OF THE HOSE. THE INCIDENT IS STILL UNDER INVESTIGATION.				1	L	7	2 	4F			 	A22CE   					 
2001092400010	20010924	00010	NE  	2001	9	24	A244583          	2	20010826	G	7310	430137601C	TUBE            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					FUEL MANIFOLD	CRACKED         	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	15	911WJ					7050	L45178			MINUTE CRACK DEVELOPED IN MANIFOLD RIGID TRANSFER TUBE, CAUSING INFLIGHT FUEL LEAK.  ALLOW USE OF FLEXIBLE TRANSFER TUBE	 FUEL MANIFOLDS ON LTS101650B1.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001050700572	20010507	00572	GL  	2001	5	7	AC2A072773       	2	20010110	G	7250	6898683	NOZZLE          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30S     	03013	GL  					4TH STAGE	DEBONDED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238					51492				MAIN ROTOR BLADES FAILED TO TURN BY SPECIFIED N1 SPEED UPON STARTING ENGINE. IT WAS DETERMINED THAT SOMETHING INSIDE OF 	TURBINE WAS RUBBING DUE TO SOUND COMING FROM TURBINE WHEN ROTOR WAS TURNED BACKWARDS. TURBINE WAS REMOVED AND DISASSEMBL	ED. IT WAS FOUND THAT THE 4TH STAGE NOZZLE #4 BLADE PATH HAD DISBONDED AND WAS RUBBING THE #4 TURBINE WHEEL OUTER DIAMET	ER KNIFE EDGES CREATING DRAG THAT WAS CAUSING  PROBLEM WITH MAIN ROTOR NOT TURNING ON START. DISBONDING WAS IN APPROXIMA	TELY 25 SEPARATE SPOTS SPACED AROUND CIRCUMFRENCE OF BLADE PATH, WITH THE LARGEST SPOT BEING AROUND ONE QUARTER INCH IN 	DIAMETER, ROUGHLY ROUND IN SHAPE AND RAISED ENOUGH TO CONTACT THE WHEEL OUTER DIAMETER. THIS CONDITION WOULD APPEAR TO B	1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050700573	20010507	00573	SW  	2001	5	7	AC2A072774       	1	20010110	G	2432	RG222	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	7159H	676  				51397				PART IS WEAK. REPLACED BATTERY						1	G	7	1 	3U			 	H2SW    					 
2001050700574	20010507	00574	SW  	2001	5	7	AC2A072775       	1	20010111	G	2432	RG222	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	17238	807  				51492				PART IS WEAK. REPLACED BATTERY						1	G	7	1 	3U			 	H2SW    					 
2001050700575	20010507	00575	NE  	2001	5	7	AC2A072776       	1	20010112	G	2430	A1077B	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										BATTERY	SHORTED         	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	7266K					760283				PART CIRCUIT-SHORTED. REPLACED RELAY						1	G	7	2 	3U			 	H1NE    					 
2001050700576	20010507	00576	NE  	2001	5	7	AC2A072777       	1	20010122	G	6320	7635109082105	CHIP DETECTOR   			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	5403C					760141				PART LEAKS AT CONNECTOR. REPLACED CHIP DETECTOR						1	G	7	2 	3U			 	H1NE    					 
2001050700577	20010507	00577	EU  	2001	5	7	AC2A072778       	1	20010125	G	2435	230321825	STATOR          			BOLKMS	105   	BO105S      	5626006	EU  										STARTER GEN	GROUNDED        	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	8775	8034 				775				PART IS CIRCUIT-GROUNDED. REPLACED STATOR.						1	G	7	2 	3U			 	H3EU    					 
2001050700578	20010507	00578	EU  	2001	5	7	AC2A072779       	1	20010125	G	2435	230322111	ARMATURE        			BOLKMS	105   	BO105S      	5626006	EU  										STARTER GEN	GROUNDED        	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	8776					776				PART IS CIRCUIT-GROUNDED. REPLACED ARMATURE						1	G	7	2 	3U			 	H3EU    					 
2001050700579	20010507	00579	EU  	2001	5	7	AC2A072780       	1	20010125	G	2435	230322111	ARMATURE        			BOLKMS	105   	BO105S      	5626006	EU  										STARTER GEN	GROUNDED        	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	8775					775				PART IS CIRCUIT-GROUNDED. REPLACED ARMATURE.						1	G	7	2 	3U			 	H3EU    					 
2001050700580	20010507	00580	GL  	2001	5	7	AC2A072781       	2	20010130	G	7230	23039791	SPLINE ADAPTER  		6890550     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C*       	 	GL  					COMPRESSOR	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	21460	1562 			41256	4075				COMPRESSOR WAS REMOVED TO FACILITATE GEARBOX MAINTENANCE. SPLINE ADAPTER WEAR WAS CHECKED WITH GO-NO-GO GAUGE AND WAS FO	UND TO BE WORN. SPLINE ADAPTER WAS REMOVED AND WAS FOUND TO HAVE A RING OF CORROSION PITTING AROUND OUTSIDE CIRCUMFRENCE	 OF ADAPTER .650 INCH FORWARD OF AFT END OF ADAPTER. LOCATION OF CORROSION IS AT THE POINT WHERE THE ADAPTER SEATS INTO 	THE IMPELLER AT THE JUNCTION OF THE AFT END OF THE IMPELLER AND THE ADAPTER. CORROSION IS AT THE SAME LOCATION WHERE A P	REVIOUS SPLINE ADAPTER FAILED HERE AT CHEVRON RESULTING IN AN IN FLIGHT ENGINE FAILURE AND UNSCHEDULED LANDING. SPLINE A	DAPTER FIT AND INSTALLATION WAS IN ACCORDANCE WITH MAINTENANCE INSTRUCTIONS.   SPLINE ADAPTER WAS REPLACED. COMPRESSOR I	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050700581	20010507	00581	GL  	2001	5	7	AC2A072782       	2	20010130	G	7230	23039791	SPLINE ADAPTER  		6890550     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	59588	756  			41394	780				COMPRESSOR WAS REMOVED DUE TO F.O.D. SPLINE ADAPTER WAS REMOVED IN ORDER TO DISASSEMBLE COMPRESSOR ROTOR FOR REPAIR. SPL	INE ADAPTER WAS FOUND TO HAVE A RING OF CORROSION AROUND OUTSIDE CIRCUMFRENCE OF ADAPTER .650 INCH FROM REAR END OF ADAP	TER. CORROSION IS AT THE POINT WHERE THE ADAPTER SEATS INTO THE IMPELLER AT THE JUNCTION OF THE ADAPTER AND THE REAR END	 OF THE IMPELLER. CORROSION IS AT THE SAME LOCATION WHERE CHEVRON PREVIOUSLY HAD AN ADAPTER FAIL THAT RESULTED IN AN IN 	FLIGHT ENGINE FAILURE AND UNSCHEDULED LANDING. SPLINE ADAPTER FIT AND INSTALLATION WERE IN ACCORDANCE WITH MAINTENANCE I	NSTRUCTIONS. SPLINE ADAPTER WAS REPLACED. COMPRESSOR IS STILL IN SPARES AT THIS TIME AND HAS NOT BEEN RETURNED TO SERVIC	1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001050700582	20010507	00582	GL  	2001	5	7	AC2A072783       	2	20010213	G	7210	23063371	SEAL            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250B  	250B*       	 	GL  					GEARBOX	LEAKING         	H			AC2A	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			FS	01	7159J					51408				AIRCRAFT WAS GROUND RUN AND LEAK CHECKED FOLLOWING ENGINE CHANGE.  NO LEAKS FOUND.  AIRCRAFT RETURNED AFTER 20 MINUTE TE	ST FLIGHT.  OIL WAS FOUND IN THE ENGINE PAN.  OIL LEAKING FROM STARTER-GENERATOR SEAL ON ENGINE GEARBOX. REPLACED SEAL. 	 UPON INSPECTION OF SEAL, IT WAS FOUND TO HAVE A TEAR OR CUT HALF WAY AROUND THE INSIDE CIRCUMFERENCE OF THE SEAL.				1	G	7	1 	3U	3	T	 	H2SW    	E10CE				 
2001050700583	20010507	00583	NE  	2001	5	7	AC2A072784       	2	20010311	G	7532	23005366	BLEED VALVE     			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	LOOSE           	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	46   				49037	844154			BLEED VALVE HOUSING WAS LOOSE. REPLACED DIAPHRAGM. REASSAMBLED AND PERFORMED TEST.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001051500109	20010515	00109	CE  	2001	5	15	AC2A072785       	1	20010311	G	7810	12502642	EXHAUST PIPE    			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		5357 								EXHAUST COLLECTOR FOUND CRACKED REPLACED WITH NEW COLLECTOR						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001050700584	20010507	00584	NE  	2001	5	7	AC2A072786       	2	20010327	G	7320	AN8378J	ELBOW           			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072	844154			FUEL LEAK ON LINE FROM CEFA TO HMU. FOUND ELBOW ON CEFA HAD A MILLING MARK ON FACE OF FLANGE. REPLACED ELBOW.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001050700585	20010507	00585	NE  	2001	5	7	AC2A072787       	2	20010327	G	7261	6871937	LINE            			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072	844154			OIL LEAK ON INBOARD SIDE OF NR 1 ENGINE. FOUND TUBE ASSY FROM CHECK VALVE TO GEAR BOX HOUSING WOULD NOT SEAT PROPERLY. R	EPLACED TUBE ASSY.					1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001050700586	20010507	00586	SW  	2001	5	7	AC2A072788       	1	20010331	G	2432	RG222	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	WEAK            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	319  				51408				PART IS WEAK. REPLACED BATTERY WITH A NEW PART						1	G	7	1 	3U			 	H2SW    					 
2001050700587	20010507	00587		2001	5	7	AC2A072789       	4	20010402	G	3416	1042011968E	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	OUT OF TOLERANCE	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	5403C					760141				VIBRATOR INOP,AUTOPILOT CORRECTION POTENTIOMETER OUT OF TOLERANCE AND OFF FLAG STICKS. REPLACED INST.						1	G	7	2 	3U			 	H1NE    					 
2001050700588	20010507	00588	NE  	2001	5	7	AC2A072790       	1	20010405	G	2435	03600923	BEARING         		23081018    	SKRSKY	S76   	S76A        	8143006	NE  										DRIVE END	DETERIORATED    	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	5401G	907  			3361	760137				PART IS DETERIORATED. BEARING CAGE FAILED ALLOWING ALL BALLS TO GROUP TOGETHER. NO BALLS WERE LOST OR DETERIORATED OVERH	AULED STARTER - GENERATOR AND REPLACED BEARINGS.					1	G	7	2 	3U			 	H1NE    					 
2001050700589	20010507	00589		2001	5	7	AC2A072791       	4	20010416	G	2210	065001580211	COMPUTER        			BELL  	430   	430         	1182150	SW  										COCKPIT	FAILED          	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	430CV	105  				49072				AFCS PIT CAUTION LIGHT DURING AP2 TEST.  AP2 & SAS2 CAUTION LIGHT REMAINS ON AFTER COMPLETION OF TEST.  AFCS PIT CAUTION	 LIGHT ILLUMINATES WHEN IN AP2. REPLACED WITH NEW PART.					1	G	7	2 	3U			RT	H9SW    					 
2001051000139	20010510	00139	SW  	2001	5	10	AC2A072803       	1	20010101	G	6220	430010101101	YOKE            			BELL  	430   	430         	1182150	SW  										ROTOR HEAD	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				SPAN-WISE CRACK ON TOP APPROX 12 INCHES FROM CENTER. REPLACED.						1	G	7	2 	3U			RT	H9SW    					 
2001051000140	20010510	00140	SW  	2001	5	10	AC2A072804       	1	20010101	G	6220	430010101101	YOKE            			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				SPAN-WISE CRACK 12 INCHES FROM CENTER. REPLACED.						1	G	7	2 	3U			RT	H9SW    					 
2001051000141	20010510	00141	SW  	2001	5	10	AC2A072805       	1	20010101	G	6410	222016001131	BLADE           			BELL  	430   	430         	1182150	SW  										TAIL ROTOR	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	1742 				49037				FEATHERING BEARINGS CRACKED.   FEATHERING BEARINGS WERE REPLACED BEFORE THIS AT TIME 589.4. THE BLADE HAS 1152.8 SINCE R	EPLACEMENT OF BEARINGS. REPLACED BLADE					1	G	7	2 	3U			RT	H9SW    					 
2001051000142	20010510	00142	SW  	2001	5	10	AC2A072806       	1	20010101	G	6510	430044100101	DRIVE SHAFT     			BELL  	430   	430         	1182150	SW  										TAIL ROTOR	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				CORROSION AROUND FLANGE AREA.  DRIVE SHAFTS WERE NR 2 & 3 AND AREA OF CORROSION WAS NEAR WHERE OILCOOLER COWLING AND TAI	L DRIVE SHAFT COWLING MEET. REPLACED DRIVE SHAFTS.					1	G	7	2 	3U			RT	H9SW    					 
2001051000143	20010510	00143	SW  	2001	5	10	AC2A072807       	1	20010101	G	6220	430310101105	SHEAR RESTRAINT 			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	DELAMINATED     	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				DELAMINATING FROM SHAFT REPLACED SHEAR RESTRAINT.						1	G	7	2 	3U			RT	H9SW    					 
2001051000144	20010510	00144	SW  	2001	5	10	AC2A072808       	1	20010101	G	6300	430010212101	RESTRAINT       			BELL  	430   	430         	1182150	SW  										MAIN ROTOR DRIVE	DEBONDED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				ELASTOMERIC DEBONDING REPLACED RESTRAINT						1	G	7	2 	3U			RT	H9SW    					 
2001051000145	20010510	00145	SW  	2001	5	10	AC2A072809       	1	20010101	G	6710	222382001107	ACTUATOR        			BELL  	430   	430         	1182150	SW  										FLIGHT CONTROL	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				LEAKING, REPLACED ACTUATOR.						1	G	7	2 	3U			RT	H9SW    					 
2001051000146	20010510	00146	SW  	2001	5	10	AC2A072810       	1	20010101	G	7120	430360051101	MOUNT           			BELL  	430   	430         	1182150	SW  										ENGINE	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2862 				49037				REAR ENGINE MOUNT BEARING AT DECK WORN.  BALL (P/N 230-360-101-103) NOT WORN. ROD END BODY (P/N 230-360-101-105) WAS WOR	N. REPLACED MOUNT					1	G	7	2 	3U			RT	H9SW    					 
2001051000147	20010510	00147	SW  	2001	5	10	AC2A072811       	1	20010101	G	6210	430015001123	BLADE           			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	1370 				49037				CRACKED INBOARD TRIM TAB REPLACED TRIM TAB						1	G	7	2 	3U			RT	H9SW    					 
2001051000148	20010510	00148	SW  	2001	5	10	AC2A072812       	1	20010129	G	7921	230365001101	BLOWER          			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					OIL COOLER	DEFECTIVE       	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	693  				49037				BEARING MAKES CLICKING SOUND AND CORROSION NEAR REAR NUT.  PART WAS NEVER INSTALLED ON AIRCRAFT DUE TO THIS.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001051000149	20010510	00149	SW  	2001	5	10	AC2A072813       	1	20010202	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	31079	296  				51526				CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001051000150	20010510	00150	SW  	2001	5	10	AC2A072814       	1	20010205	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	53702	90   				51249				CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001051000151	20010510	00151	SW  	2001	5	10	AC2A072815       	1	20010220	G	2910	70053H000A100A	HOSE            			BELL  	206   	206L3       	1182108	SW  										HYD SYSTEM	LEAKING         	H			AC2A	B	A			EMER. DESCENT           	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			FS	01	17592					51535				AT CRUISE TO LEEVILLE (LA)  HELIPORT, THE PILOT HEARD A LOUD GRINDING NOISE FOLLOWED BY COMPLETE HYDRAULIC FAILURE.  THE	 PILOT PERFORMED THE EMERGENCY PROCEDURE THEN CONFIRMED IT WITH THE BOOK WITH NO CORRECTION TO THE EMERGENCY.  PILOT PER	FORMED A SHALLOW APPROACH WITH A SLIGHT RUN ON LANDING, AND SHUT DOWN THE AIRCRAFT. REPLACED HYDRAULIC LINE P/N 70-053H0	00A100A.			1	G	7	1 	3U			 	H2SW    					 
2001051000152	20010510	00152	SW  	2001	5	10	AC2A072817       	1	20010223	G	3340	AN33201	RELAY           			BELL  	206   	206B3       	1181506	SW  										LANDING LIGHT	FAILED          	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	7131U	9    				4111				RELAY FAILED AFTER 41 DAYS ON THE AIRCRAFT.  THE LANDING LIGHT WAS INOPERABLE.						1	G	7	1 	3U			 	H2SW    					 
2001051000153	20010510	00153	SW  	2001	5	10	AC2A072818       	1	20010306	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159H	441  				51397				CRACKED. REPLACED PART.						1	G	7	1 	3U			 	H2SW    					 
2001051000154	20010510	00154	SW  	2001	5	10	AC2A072819       	1	20010311	G	6210	4300150037101	EROSION SHIELD  		430015001123	BELL  	430   	430         	1182150	SW  										MAIN ROTOR BLADE	DAMAGED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV				A1118	49072				EROSION TAPE FOR MAIN ROTOR BLADE WAS FOUND BUBBLED. FUTHER INSPECTION FOUND BUBBLE WAS FULL OF WATER. THERE WAS NO SIGN	 OF AREA OF ENTRY. REPLACED EROSION TAPE.					1	G	7	2 	3U			RT	H9SW    					 
2001051500110	20010515	00110	SW  	2001	5	15	AC2A072820       	1	20010311	G	6230	430010105105	PLATE           		430010100113	BELL  	430   	430         	1182150	SW  										MAIN ROTOR	LOOSE           	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		46   			A166					CLAMP PLATE WAS NOT SHIMED PROPERLY ON SHEAR RESTRAINT. RESHIMED CLAMP PLATE.						1	G	7	2 	3U			RT	H9SW    					 
2001051000155	20010510	00155	SW  	2001	5	10	AC2A072821       	1	20010311	G	5210		LATCH           			BELL  	430   	430         	1182150	SW  										CREW DOOR	OUT OF ADJ      	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072				CABIN DOOR WAS EXTREMELY HARD TO OPEN AND WOULD NOT CLOSE PROPERLY. AJUSTED DOOR LATCHES.						1	G	7	2 	3U			RT	H9SW    					 
2001051000156	20010510	00156	SW  	2001	5	10	AC2A072822       	1	20010311	G	7500	230025203101	TUBE            			BELL  	430   	430         	1182150	SW  										ENGINE BLEED AIR	CHAFED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072				CUSTOMER BLEED AIR TUBE HAD A WORN SPOT FROM THE UPPER ENGINE COWLING(PN 230-061-803-104). REPLACED TUBE ASSY AND REPAIR	ED COWLING.					1	G	7	2 	3U			RT	H9SW    					 
2001051000157	20010510	00157	SW  	2001	5	10	AC2A072823       	1	20010311	G	5320	222035165164	CLIP            			BELL  	430   	430         	1182150	SW  										FUSELAGE	MISINSTALLED    	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072				TAIL ROTOR DRIVE SHAFT COVER (PN 222-035-165-179) WAS RUBBING TAIL ROTOR DRIVE SHAFT SUPPORT BEARING SUPPORT (PN 430-035	-164-105). CAUSE OF RUBBING WAS FORWARD TAIL ROTOR DRIVE SHAFT COWLING CLIP (PN 222-025-165-164) WAS INSTALLED TO CLOSE 	TOGETHER AND DID NOT GIVE SUFFICIENT CLEARENCE FOR SUPPORT. ADDED SPACER PAD BETWEEN DRIVE SHAFT COVER AND CLIP.				1	G	7	2 	3U			RT	H9SW    					 
2001051000158	20010510	00158	SW  	2001	5	10	AC2A072824       	1	20010311	G	6200	2006508083	BOLT            			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	46   				49072				WHILE REMOVING MAIN ROTOR YOKES WATER CAME OUT OF AREA OF MAIN ROTOR DRIVE BUSHINGS AND MAIN ROTOR BOLTS. DRIVE PLATE WA	S FOUND NOT TO BE SEALED PROPERLY AND 2 MAIN ROTOR BOLTS WERE FOUND TO HAVE CORROSION PITTING. REPLACED BOLTS AND SEALED	 PROPERLY.				1	G	7	2 	3U			RT	H9SW    					 
2001051000159	20010510	00159	SW  	2001	5	10	AC2A072825       	1	20010325	G	6520	222342402101	SEAL            		222042001103	BELL  	430   	430         	1182150	SW  										TAIL ROTOR G/B	LEAKING         	H			AC2A	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	430CV	46   			A270	49072				TAIL ROTOR GEAR BOX WAS LEAKING FROM OUT PUT SEAL. WHEN SEAL WAS RENOVED IT WAS DISCOVERED THAT THE SEAL LIP HAD SEALENT	 MIL-S-8784 ON IT. THIS SEALENT IS USED ON THE OUTER SURFACE OF THE SEAL WHEN INSTALLING.  REPLACED SEAL.					1	G	7	2 	3U			RT	H9SW    					 
2001051000160	20010510	00160	SW  	2001	5	10	AC2A072826       	1	20010403	G	3213	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										LANDING GEAR	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	31079	602  				51526				PART HAS INTERGRANULAR CORROSION SEVERAL PLACES ON TUBE.  THIS FORWARD CROSSTUBE HAD ONLY 602 HOURS SINCE INSTALLATION, 	THE CORROSION WAS EXTENSIVE AND BEYOND LIMITS. REPLACED CROSSTUBE WITH NEW PART.					1	G	7	1 	3U			 	H2SW    					 
2001051000161	20010510	00161		2001	5	10	AC2A072827       	4	20010416	G	3425	430375002107	DISPLAY         			BELL  	430   	430         	1182150	SW  										EFIS	FAILED          	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	430CV	105  				49072				SCREEN WENT BLANK IN FLIGHT. REPLACED PART.						1	G	7	2 	3U			RT	H9SW    					 
2001051000162	20010510	00162	SW  	2001	5	10	AC2A072828       	1	20010416	G	2436	222375060115	VOLT REGULATOR  			BELL  	430   	430         	1182150	SW  										ELECTRICAL	DEFECTIVE       	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH					49037				REGULATOR WAS INOPERATIVE WHEN WE RECEIVED IT FROM BELL. EXCHANGING THIS PART FOR A NEW ONE.						1	G	7	2 	3U			RT	H9SW    					 
2001051000163	20010510	00163	SW  	2001	5	10	AC2A072829       	1	20010419	G	2910	70012H000Y264	HOSE            			BELL  	430   	430         	1182150	SW  										TRANSMISSION	CHAFED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	122  				49072				PART IS CHAFED.  LINE CHAFED ON TRANSMISSION COWLING. INSTALLED NEW LINE.  REPOSITIONED ELBOW FOR NEW LINE TO CLEAR TRAN	SMISSION COWLING.					1	G	7	2 	3U			RT	H9SW    					 
2001051000164	20010510	00164	SW  	2001	5	10	AC2A072830       	1	20010426	G	2622	40000MODLE11211	EXTINGUISHER    			BELL  	206   	206L3       	1182108	SW  										CABIN	DISCHARGED      	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	301  				51478				FIRE EXTINGUISHER HAD LOW WEIGHT. REPLACED WITH NEW FIRE EXTINGUISHER.						1	G	7	1 	3U			 	H2SW    					 
2001051000165	20010510	00165	SW  	2001	5	10	AC2A072831       	1	20010426	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	187  				51439				PART IS CRACKED. REPLACED WITH NEW EXHAUST.						1	G	7	1 	3U			 	H2SW    					 
2001051000166	20010510	00166	SW  	2001	5	10	AC2A072832       	1	20010426	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17592	815  				51535				CRACKED. REPLACED EXHAUST ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001051000179	20010510	00179	GL  	2001	5	10	AC2A072834       	2	20010306	G	7323	23065123	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	DEBONDED        	H			AC2A	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			FS	01	5366Y	8130 				782				PILOT REPORTED N2 OVERSPEED UNCONTROLLABLE WITH RPM TRIM MOTOR.  NR 1 ENGINE RETURNED TO FLIGHT IDLE.  FUEL JETTISONED, 	AND PILOT PERFORMED RUN-ON LANDING. REMOVED GOVERNOR AND FOUND DRIVE SPLINE DISENGAGED FROM GOVERNOR SHAFT. GOVERNOR REP	LACEMENT FIXED PROBLEM.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001051000180	20010510	00180	GL  	2001	5	10	AC2A072835       	2	20010319	G	7323	23004831	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEBONDED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5366Y	1888 				782				UNBONDED SHAFT.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001051000181	20010510	00181	GL  	2001	5	10	AC2A072836       	2	20010319	G	7323	23065123	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	8776	11601				776				CHECKED DRIVE COUPLING AND FOUND DEFECTIVE.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001051000182	20010510	00182	GL  	2001	5	10	AC2A072837       	2	20010319	G	7323	23065123	GOVERNOR        			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEBONDED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7131U	9381 				4111				DRIVE COUPLING DEBONDED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001051000183	20010510	00183	GL  	2001	5	10	AC2A072838       	2	20010425	G	7323	23065123	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 2 ENGINE	BROKEN          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	8775	7744 				775				POTTING ON END OF DRIVE GEAR IS BROKEN LOOSE. REMOVED GOVERNOR.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001091900004	20010919	00004	SW  	2001	9	19	AC2A075785       	1	20010502	G	6310	206040272101	SEAL            			BELL  	206   	206L3       	1182108	SW  										INPUT SHAFT	LEAKING         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	614  				51478				PARTS ARE LEAKING GREASE. REPLACED SEALS.						1	G	7	1 	3U			 	H2SW    					 
2001091900005	20010919	00005	EU  	2001	9	19	AC2A075786       	1	20010502	G	7810	59528AELPSW3	CLAMP           			BOLKMS	105   	BO105S      	5626006	EU  										EXHAUST STACK	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	59588	286  				780				PART WAS FOUND CRACKED WHILE WHILE PERFORMONG NDT INSPECTION AS PER ASB BO-105-60-107. REPLACED CLAMP.						1	G	7	2 	3U			 	H3EU    					 
2001091900006	20010919	00006	GL  	2001	9	19	AC2A075787       	2	20010502	G	7323	23065123	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 1 ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5366Y	7199 				782	836103			EPOXY DEBONDED ON GOVERNOR DRIVE SHAFT. REMOVED FROM SERVICE AND SENT IN FOR WARRANTY REPAIR.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001091900007	20010919	00007	EU  	2001	9	19	AC2A075788       	1	20010507	G	6340	32005007	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										TRANSMISSION	DEFECTIVE       	H			AC2A	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			FS	01	826MB	18   				771				PART IS DEFECTIVE. ROTOR INDICATIONS WERE ZERO ON CRANK-UP REPLACED TACH/GEN						1	G	7	2 	3U			 	H3EU    					 
2001091900008	20010919	00008	EU  	2001	9	19	AC2A075789       	1	20010507	G	6240	32005007	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DEFECTIVE       	H			AC2A	A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			FS	01	826MB	2    				771				PART IS DEFECTIVE.CAUSED HIGH RPM AUDIO TO SOUND DURING NORMAL OPERATION. REPLACED TACH/GEN						1	G	7	2 	3U			 	H3EU    					 
2001091900009	20010919	00009	EU  	2001	9	19	AC2A075790       	1	20010507	G	7714	32005023	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										NR 1 ENGINE	ERRATIC         	H			AC2A	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			FS	01	826MB					771				PART IS INDICATIONS.N1 INDICATIONS WERE IRRATIC.  REPLACED TACH/GEN.						1	G	7	2 	3U			 	H3EU    					 
2001091900010	20010919	00010	EU  	2001	9	19	AC2A075791       	1	20010507	G	6340	KDW021A	WARNING SYSTEM  			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	H			AC2A	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			FS	01	826MB					771				PART IS INDICATIONS. PILOT EXPERIENCED "HI RPM" LIGHT AND AUDIO DURING NORMAL OPERATION. REPLACED RPM WARNING BOX.						1	G	7	2 	3U			 	H3EU    					 
2001091900011	20010919	00011	EU  	2001	9	19	AC2A075792       	1	20010507	G	6240	22021002	WARNING SYSTEM  			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	H			AC2A	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			FS	01	826MB					771				PART IS INDICATIONS.LOUD STATIC IN HEAD SET AND "HI AUDIO" INDICATIONS DURING NORMAL OPERATION. REPLACED RPM WARNING BOX						1	G	7	2 	3U			 	H3EU    					 
2001091900012	20010919	00012	SW  	2001	9	19	AC2A075793       	1	20010507	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	597  				51478				FOUND CRACKED AT REAR SEAM. REMOVED AND REPLACED STACK.						1	G	7	1 	3U			 	H2SW    					 
2001091900013	20010919	00013	SW  	2001	9	19	AC2A075795       	1	20010512	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238	1199 				51492				PART IS CORRODED. REMOVED,REPLACED FORWARD CROSS TUBE						1	G	7	1 	3U			 	H2SW    					 
2001091900014	20010919	00014	SW  	2001	9	19	AC2A075796       	1	20010514	G	6410	222312753103	BEARING         		222016001131	BELL  	430   	430         	1182150	SW  										T/R BLADE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	501  			A1712	49037				BEARINGS ARE CRACKED. REPLACED BEARINGS WITH NEW.						1	G	7	2 	3U			RT	H9SW    					 
2001091900015	20010919	00015	SW  	2001	9	19	AC2A075797       	1	20010518	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	53702	434  				51249				FOUNDED CRACKED AT REAR SEAM. REMOVED AND REPLACED STACK.						1	G	7	1 	3U			 	H2SW    					 
2001091900016	20010919	00016	NE  	2001	9	19	AC2A075798       	1	20010518	G	2435	230811011	ARMATURE        		23081002    	SKRSKY	S76   	S76A        	8143006	NE  											SHORTED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					643					PART IS CIRCUIT-SHORTED. REMOVED DEFECTIVE PART AND INSTALLED A SERVICABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001091900017	20010919	00017	SW  	2001	9	19	AC2A075799       	1	20010529	G	7430	1064BH1436	SWITCH          			BELL  	430   	430         	1182150	SW  										IGNITION	SHORTED         	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	430CV	263  				49072				MICRO SWITCH FAILED TO ENGAGE ENGINE STARTER OR HOLDING COIL. REPLACED SWITCH.						1	G	7	2 	3U			RT	H9SW    					 
2001091900019	20010919	00019	SW  	2001	9	19	AC2A075800       	1	20010529	G	5210	NAS5623R7A	CAM FOLLOWER    			BELL  	430   	430         	1182150	SW  										DOOR	CRACKED         	H			AC2A	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	430CV	258  				49072				BEARING RACE CRACKED. INSIDE OF BEARING FALLING APART.. REPLACED CAMFOLLOWER.						1	G	7	2 	3U			RT	H9SW    					 
2001091900020	20010919	00020	SW  	2001	9	19	AC2A075801       	1	20010607	G	6510	430010124103	BUSHING         			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	2268 				49037				PART IS WORN EXCESSIVELY.  ALL EIGHT M/R DRIVE BUSHINGS ARE WORN BEYOND LIMITS ALLOWED IN BHT-430-CR&O-2.						1	G	7	2 	3U			RT	H9SW    					 
2001091900021	20010919	00021	SW  	2001	9	19	AC2A075803       	1	20010612	G	6230	430310461101	BEARING         			BELL  	430   	430         	1182150	SW  										SWASHPLATE	RATCHETING      	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH					49037				WITH SWASHPLATE INSTALLED ON ACFT. BEARING FELT RATCHETY.  BEARING WAS THE NEW UPDATED STLYE. REMOVED AND REPLACED BEARI	NG.					1	G	7	2 	3U			RT	H9SW    					 
2001091900022	20010919	00022	SW  	2001	9	19	AC2A075804       	1	20010612	G	6220	MS1652245	PIN             			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	BROKEN          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	3447 				49037				FOUND SHEAR RESTRAINT LOOSE AND UPON DISASSEMBLY FOR INSP. FOUND PIN BROKEN. REPLACED BROKEN PIN AND WORN RESTRAINT.						1	G	7	2 	3U			RT	H9SW    					 
2001091900023	20010919	00023	SW  	2001	9	19	AC2A075805       	1	20010612	G	6220	430310101107	RESTRAINT       		430010100113	BELL  	430   	430         	1182150	SW  										MAIN ROTOR	LOOSE           	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	585  			A123	49037				FOUND LOOSE ON INSP. AND UPON DISASSEMBLY FOUND ROLL PIN BROKEN WHICH ALLOWED MOVEMENT IN CLAMP-UP. REPLACED RESTRAINT A	ND PIN.					1	G	7	2 	3U			RT	H9SW    					 
2001091900025	20010919	00025	NE  	2001	9	19	AC2A075810       	1	20010625	G	6320	7635109082105	CHIP DETECTOR   			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	SHORTED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7266F					760273				PART IS CIRCUIT-SHORTED. REPLACED WITH SERVICEABLE PART						1	G	7	2 	3U			 	H1NE    					 
2001091900026	20010919	00026	SW  	2001	9	19	AC2A075812       	1	20010626	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	1539 				51380				EXHAUST IS CRACKED. REPLACED WITH NEW.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001091900027	20010919	00027	GL  	2001	9	19	AC2A075813       	2	20010628	G	7261	6870032	FILTER          								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE OIL	DETERIORATED    	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01										PART IS DETERIORATED. THE OUTSIDE SCREEN IS EATEN AWAY EXPOSING THE MORE COARSE SCREEN. REPLACED FILTER ASSY.											3	U			E4CE				 
2001091900030	20010919	00030	NE  	2001	9	19	AC2A075814       	2	20010702	G	7532	23005366	BLEED VALVE     			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	LOOSE           	H			AC2A	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			FS	01	430CV	374  				49072				POWER ASSURANCE LOW NR 1 ENGINE.  FOUND NR 1 ENGINE BLEED VALVE BODY BOLTS LOOSE. REPLACED WITH REPAIRED BLEED VALVE.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL				 
2001091900031	20010919	00031	EU  	2001	9	19	AC2A075815       	1	20010709	G	6320	4638304001	SUN GEAR        			BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	FLAKING         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	8775	673  				775				DRIVE SIDE TOP CORNER OF TOOTH FLAKING. REPAIRED.						1	G	7	2 	3U			 	H3EU    					 
2001091900035	20010919	00035	GL  	2001	9	19	AC2A075817       	2	20010712	G	7230	23056634	GEARSHAFT       			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5403C	702  				760141				EXCESSIVE SPLINE WEAR ON AFT END. REPLACED WITH NEW.						1	G	7	2 	3U	3	U	 	H1NE    	E4CE				 
2001091900037	20010919	00037	GL  	2001	9	19	AC2A075818       	2	20010712	G	7230	23031922	GEARSHAFT       			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C*       	 	GL  					SPUR GEAR	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7131U	962  				4111				EXCESSIVELY WORN SPLINES. REPLACED WITH NEW.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001091900038	20010919	00038	SW  	2001	9	19	AC2A075819       	1	20010728	G	2435	230321827	STATOR          		23081018    	BELL  	206   	206L3       	1182108	SW  										STARTER GEN	SHORTED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238				3794	51492				PART IS CIRCUIT-GROUNDED. REPLACED DEFECTIVE PART						1	G	7	1 	3U			 	H2SW    					 
2001091900039	20010919	00039	SW  	2001	9	19	AC2A075820       	1	20010728	G	2435	230811011	ARMATURE        			BELL  	206   	206L3       	1182108	SW  										STARTER GEN	SHORTED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238					51492				PART IS CIRCUIT-GROUNDED.						1	G	7	1 	3U			 	H2SW    					 
2001091900050	20010919	00050	NE  	2001	9	19	AC2A075821       	1	20010729	G	2435	23081002	STARTER GEN     			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	LOOSE           	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7266K	9962 				760283				PART IS LOOSE. DRIVE SHAFT BECAME LOOSE WHEN FRICTION RING DISINTAGRATED. REPLACED STARTER GENERATOR.						1	G	7	2 	3U			 	H1NE    					 
2001091900064	20010919	00064	SW  	2001	9	19	AC2A075822       	1	20010808	G	7931	222375077113	TRANSMITTER     			BELL  	430   	430         	1182150	SW  										ENGINE OIL	MALFUNCTIONED   	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	535  				49072				INDICATOR READS 12 PSI WITHOUT ENGINE WARNING. REPLACED WITH NEW TRANSMITTER.						1	G	7	2 	3U			RT	H9SW    					 
2001091900085	20010919	00085	SW  	2001	9	19	AC2A075823       	1	20010811	G	5311	206033107121	FRAME           			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159H	9831 				51397				FRAME IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900087	20010919	00087	SW  	2001	9	19	AC2A075824       	1	20010811	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159H	9831 				51397				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900088	20010919	00088	SW  	2001	9	19	AC2A075825       	1	20010811	G	5320	206033107051	CLIP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159H	9831 				51397				CLIP IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900089	20010919	00089	SW  	2001	9	19	AC2A075826       	1	20010811	G	5311	206033107121	FRAME           			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	10161				51408				FRAME IS CRACKED. REPLACED WITH NEW PART						1	G	7	1 	3U			 	H2SW    					 
2001091900090	20010919	00090	SW  	2001	9	19	AC2A075827       	1	20010811	G	5320	206033107051	CLIP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	10161				51408				CLIP IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900091	20010919	00091	SW  	2001	9	19	AC2A075828       	1	20010811	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	10161				51408				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900092	20010919	00092	SW  	2001	9	19	AC2A075829       	1	20010811	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	31079	8884 				51526				PART IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900093	20010919	00093	SW  	2001	9	19	AC2A075830       	1	20010811	G	5320	206033107053	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	31079	8884 				51526				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900094	20010919	00094	SW  	2001	9	19	AC2A075831       	1	20010811	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	31079	8884 				51526				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900095	20010919	00095	SW  	2001	9	19	AC2A075832       	1	20010811	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	8707 				51478				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900096	20010919	00096	SW  	2001	9	19	AC2A075833       	1	20010811	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	8707 				51478				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900097	20010919	00097	SW  	2001	9	19	AC2A075834       	1	20010811	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17592	8963 				51535				STIFFENER IS CRACKED. REPAIRED WITH DER APPROVAL.						1	G	7	1 	3U			 	H2SW    					 
2001091900098	20010919	00098	SW  	2001	9	19	AC2A075835       	1	20010811	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17592	8964 				51535				STIFFENER IS CRACKED. REPAIRED WITH DER APPROVAL.						1	G	7	1 	3U			 	H2SW    					 
2001091900099	20010919	00099	SW  	2001	9	19	AC2A075836       	1	20010813	G	7931	222375077113	TRANSMITTER     			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE OIL	MALFUNCTIONED   	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	534  				49072				INDICATOR READS 10 PSI STACTICLY. REPLACED WITH NEW PART.						1	G	7	2 	3U	3	U	RT	H9SW    	E4CE				 
2001091900100	20010919	00100	SW  	2001	9	19	AC2A075837       	1	20010814	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238	8992 				51492				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900101	20010919	00101	SW  	2001	9	19	AC2A075838       	1	20010814	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238	8992 				51492				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900102	20010919	00102	SW  	2001	9	19	AC2A075839       	1	20010814	G	5320	206033107052	CLIP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17238	8992 				51492				CLIP IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900103	20010919	00103	GL  	2001	9	19	AC2A075840       	2	20010821	G	7200		ENGINE          			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C*       	 	GL  					NR 2	DAMAGED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV					49072				DURING A DAILY SERVICEABILITY CHECK THE NR 2 ENGINE WAS FOUND TO BE DAMAGED.  SUSPECT CAUSE OF DAMAGE WAS THE FAILURE OF	 CAMLOC BLADE ASSY  P/N:  40G2-1.  THE ENGINE WAS DISASSEMBLED .  THE COMPRESSOR WAS REMOVED AND DISASSEMBLED, THE TURBI	NE ASSY REMOVED.  THE COMPRESSOR SCROLL WAS REMOVED AND SENT OUT FOR REPAIR.				1	G	7	2 	3U	3	U	RT	H9SW    	E4CE				 
2001091900124	20010919	00124	SW  	2001	9	19	AC2A075841       	1	20010827	G	2150	2730502	VALVE           			BELL  	430   	430         	1182150	SW  										A/C PACK	FAILED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	573  				49072				VALVE POPS CIRCUIT BREAKER. REPLACED WITH NEW PART.						1	G	7	2 	3U			RT	H9SW    					 
2001091900125	20010919	00125	SW  	2001	9	19	AC2A075842       	1	20010828	G	2150	5861653	TURBINE         			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	FROZEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	569  				49072				COOLING TURBINE FROZEN.   IT WOULD NOT TURN. REPLACED WITH NEW PART.						1	G	7	2 	3U	3	U	RT	H9SW    	E4CE				 
2001091900126	20010919	00126	SW  	2001	9	19	AC2A075845       	1	20010904	G	6720		BEARING         			BELL  	430   	430         	1182150	SW  										P/C LINK	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				OUTBOARD BEARINGS WORN. REPLACED WITH NEW LINKS.						1	G	7	2 	3U			RT	H9SW    					 
2001091900127	20010919	00127	SW  	2001	9	19	AC2A075846       	1	20010904	G	2150	2730502	VALVE           			BELL  	430   	430         	1182150	SW  										A/C PACK	FAILED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				ECU BREAKER POPPED. REPLACED WITH NEW VALVE.						1	G	7	2 	3U			RT	H9SW    					 
2001091900128	20010919	00128	SW  	2001	9	19	AC2A075847       	1	20010904	G	7170	6854255	DRAIN VALVE     			BELL  	430   	430         	1182150	SW  										ENGINE	LEAKING         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				VALVE IS EXCESSIVELY LEAKING.						1	G	7	2 	3U			RT	H9SW    					 
2001091900129	20010919	00129	SW  	2001	9	19	AC2A075848       	1	20010904	G	2913	222380009105	PUMP            			BELL  	430   	430         	1182150	SW  										HYD SYSTEM	LEAKING         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	478  				49072				LEAKING AT INPUT SEAL. REPLACED PUMP.						1	G	7	2 	3U			RT	H9SW    					 
2001091900132	20010919	00132	SW  	2001	9	19	AC2A075849       	1	20010905	G	6520	222012714001	BEARING         			BELL  	430   	430         	1182150	SW  										TAIL ROTOR	BRINELLED       	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				INNER RACE WORN.  IT WAS BRINNELING. REPLACED WITH NEW.						1	G	7	2 	3U			RT	H9SW    					 
2001091900136	20010919	00136	SW  	2001	9	19	AC2A075852       	1	20010905	G	6420	222312753103	BEARING         		222012701125	BELL  	430   	430         	1182150	SW  										T/R BLADE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  			A649	49072				CRACKED BEARINGS. REPLACED THE FOUR BEARINGS.						1	G	7	2 	3U			RT	H9SW    					 
2001091900139	20010919	00139	SW  	2001	9	19	AC2A075853       	1	20010905	G	6310	214040812001	SEAL            		222044002101	BELL  	430   	430         	1182150	SW  											DEFORMED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  			A218	49072				DURING 600 HOUR INSPECTION, DISASSY. COUPLING FOUND SEAL DEFORMED. REPLACED SEAL.						1	G	7	2 	3U			RT	H9SW    					 
2001091900142	20010919	00142	GL  	2001	9	19	AC2A075854       	2	20010905	G	7320	23065147	FUEL CONTROL    			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 1 ENGINE	MALFUNCTIONED   	H			AC2A	O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			FS	01	5402T	12214				760140				ENGINE WENT TO 40.6 PERCENT N1 UPON LANDING. REPLACED FUEL CONTROL.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001091900144	20010919	00144	SW  	2001	9	19	AC2A075855       	1	20010908	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	53702	12265				51249				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900146	20010919	00146	SW  	2001	9	19	AC2A075856       	1	20010908	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	53702	12265				51249				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900147	20010919	00147	SW  	2001	9	19	AC2A075857       	1	20010908	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	9821 				51439				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900152	20010919	00152	SW  	2001	9	19	AC2A075858       	1	20010908	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	9821 				51439				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900153	20010919	00153	SW  	2001	9	19	AC2A075859       	1	20010908	G	5312	206033107107B	BULKHEAD        			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	9821 				51439				BULKHEAD IS CORRODED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900154	20010919	00154	SW  	2001	9	19	AC2A075860       	1	20010913	G	5311	206032308003	FRAME           			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	9821 				51439				FRAME IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900155	20010919	00155	SW  	2001	9	19	AC2A075861       	1	20010913	G	5340	206031329003	FITTING         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	6533U	9821 				51439				FITTING IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2001091900159	20010919	00159	SW  	2001	9	19	AC2A075862       	1	20010914	G	6220	430310101105	SHEAR RESTRAINT 			BELL  	430   	430         	1182150	SW  										ROTOR SYSTEM	DELAMINATED     	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CH	3732 				49037				SHEAR RESTRAINT DELAMINATED FROM CENTER PIN AND CAUSED DAMAGE TO CLAMP PLATE P/N 430-010-105-105.						1	G	7	2 	3U			RT	H9SW    					 
2001091900161	20010919	00161	SW  	2001	9	19	AC2A075863       	1	20010918	G	2432	RG222	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN BATTERY	WILL NOT TEST   	H			AC2A	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			FS	01	17237	153  				51478				BATTERY FAILED TEST. REPLACED BATTERY. CHARGED BATTERY. PERFORMED CAPACITY CHECK. BATTERY FAILED CAPACITY						1	G	7	1 	3U			 	H2SW    					 
2001101500096	20011015	00096	SW  	2001	10	15	AC2A076110       	1	20010917	G	6320	40621	CLIP            		430061829101	BELL  	430   	430         	1182150	SW  										XMSN COWL	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				PART IS CRACKED. SOME REMOVED TO REDUCE RISK OF ENG. F.O.D. R & R CLIPS						1	G	7	2 	3U			RT	H9SW    					 
2001101500098	20011015	00098	SW  	2001	10	15	AC2A076111       	1	20010917	G	1400	214165	RECEPTACLE      			BELL  	430   	430         	1182150	SW  										UPPER FAIRING	WORN            	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				PREMATURE WEAR R&R RECEPTICLE						1	G	7	2 	3U			RT	H9SW    					 
2001101500100	20011015	00100	SW  	2001	10	15	AC2A076112       	1	20010918	G	1400	430031517135	STRAP           			BELL  	430   	430         	1182150	SW  										LT FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				CRACKED IN BENT RADIUS. REMOVED AND REPLACED						1	G	7	2 	3U			RT	H9SW    					 
2001101500102	20011015	00102	SW  	2001	10	15	AC2A076113       	1	20010918	G	5411	230069900150	FRAME           			BELL  	430   	430         	1182150	SW  										FIREWALL	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				CRACKS IN FRAME. REMOVED AND REPLACED FRAME ASSY.						1	G	7	2 	3U			RT	H9SW    					 
2001101500103	20011015	00103	SW  	2001	10	15	AC2A076114       	1	20010919	G	2510	222320823121	SEAT BELT       			BELL  	430   	430         	1182150	SW  										COCKPIT	DAMAGED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				SEAT BELT WAS UNTHREADING. REPLACED WITH NEW SEAT BELT.						1	G	7	2 	3U			RT	H9SW    					 
2001101500105	20011015	00105	SW  	2001	10	15	AC2A076115       	1	20010919	G	6310	222060084101	PRESSURE SWITCH 			BELL  	430   	430         	1182150	SW  										M/R GEARBOX	INOPERATIVE     	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	600  				49072				PRESSURE SWITCH IS INOPERABLE. REPLACED WITH NEW SWITCH.						1	G	7	2 	3U			RT	H9SW    					 
2001101500106	20011015	00106	SW  	2001	10	15	AC2A076116       	1	20010924	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	306  				51380				CRACKED. REPLACED WITH NEW EXHAUST STACK.						1	G	7	1 	3U			 	H2SW    					 
2001101500107	20011015	00107	SW  	2001	10	15	AC2A076117       	1	20011001	G	2520	222020742133	CUSHION         			BELL  	430   	430         	1182150	SW  										CABIN SEAT	DAMAGED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	670  				49072				FOAM WAS BUSTED AND SEPARATED FROM FRAME. REPLACED SEAT CUSHION.						1	G	7	2 	3U			RT	H9SW    					 
2002012300020	20020123	00020	SW  	2002	1	23	AC2A077049       	1	20011013	G	3213	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159H	10143				51397				THE MANUFACTURED DATE IS JAN. 2001 WITH 619 HOURS. TWO SPOTS OF CORROSION WERE FOUND UNDER THE SUPPORT CLAMPS. THE CROSS	TUBE WAS REPLACED.					1	G	7	1 	3U			 	H2SW    					 
2002012300021	20020123	00021	SW  	2002	1	23	AC2A077050       	1	20011015	G	2120	3136171	SOLENOID        			BELL  	430   	430         	1182150	SW  										DIVERTER VALVE	STUCK           	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	694  				49072				DIVERTER VALVE NOT OPENING OR CLOSING.  TOO MUCH COLD AIR COMING OUT OF LOWER VENTS. REPLACED WITH NEW SOLENOID.  IT FIX	ED PROBLEM.					1	G	7	2 	3U			RT	H9SW    					 
2002012300022	20020123	00022	SW  	2002	1	23	AC2A077051       	1	20011022	G	5320	206033107055	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	10225				51380				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2002012300023	20020123	00023	SW  	2002	1	23	AC2A077052       	1	20011022	G	5320	206033107053	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	10225				51380				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2002012300024	20020123	00024	SW  	2002	1	23	AC2A077053       	1	20011022	G	5320	206033107056	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	10225				51380				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2002012300025	20020123	00025	SW  	2002	1	23	AC2A077054       	1	20011022	G	5320	206033107054	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	10225				51380				STIFFENER IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2002012300026	20020123	00026	SW  	2002	1	23	AC2A077055       	1	20011022	G	5320	206033107052	CLIP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	10225				51380				CLIP IS CRACKED. REPLACED WITH NEW PART.						1	G	7	1 	3U			 	H2SW    					 
2002012300027	20020123	00027	SW  	2002	1	23	AC2A077056       	1	20011024	G	3212	206073926103	VALVE           			BELL  	206   	206L3       	1182108	SW  										MLG	FAILED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	17237	234  				51478				VAVLE FAILING AFTER ONLY 234 HOURS.						1	G	7	1 	3U			 	H2SW    					 
2002012300028	20020123	00028	SW  	2002	1	23	AC2A077057       	1	20011024	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7159J	712  				51408				EXHAUST STACK CRACKED. REPLACED WITH NEW .						1	G	7	1 	3U			 	H2SW    					 
2002012300029	20020123	00029	SW  	2002	1	23	AC2A077058       	1	20011024	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	53702	312  				51249				EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE.						1	G	7	1 	3U			 	H2SW    					 
2002012300035	20020123	00035	SW  	2002	1	23	AC2A077536       	1	20011205	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	715CC	205  				51380				EXHAUST STACK CRACKED. REPLACED WITH NEW.						1	G	7	1 	3U			 	H2SW    					 
2002012300036	20020123	00036	SW  	2002	1	23	AC2A077537       	1	20011205	G	3040	222325001027	ARM             			BELL  	430   	430         	1182150	SW  										WINDSHILD WIPER	BROKEN          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	804  				49072				WINDSHIELD WIPER GUIDE ARM IS BROKEN. REPLACED WITH NEW PART.						1	G	7	2 	3U			RT	H9SW    					 
2002012300039	20020123	00039	SW  	2002	1	23	AC2A077539       	1	20011211	G	7500	23056648	TUBE            			BELL  	430   	430         	1182150	SW  										BLEED AIR	CHAFED          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	205  				49072				ENGINE COWL ASSY P/N: 430-061-804-101 FORWARD HINGE P/N: 230-061-808-101 IS RUBBING ON BLEED AIR TUBE P/N: 23056648 WHEN	 COWLING IS OPENED. REPLACED TUBE.  PROBLEM WILL CONTINUE DUE TO DESIGN OF COWLING HINGE.					1	G	7	2 	3U			RT	H9SW    					 
2002012300040	20020123	00040	SW  	2002	1	23	AC2A077540       	1	20011211	G	6730	065001620200	SERVO           			BELL  	430   	430         	1182150	SW  										MAIN ROTOR YAW	MALFUNCTIONED   	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	943  				49072				WHEN FD IS COUPLED IN HDG & ALT THE A/C GOES INTO A CLIMBING RIGHT TURN WITH FULL LEFT PEDAL APPLIED. REPLACED WITH NEW 	YAW SERVO.					1	G	7	2 	3U			RT	H9SW    					 
2002012300042	20020123	00042	SW  	2002	1	23	AC2A077541       	1	20011226	G	3040	222325001028	ARM             			BELL  	430   	430         	1182150	SW  										WINDSHIED WIPER	BROKEN          	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	953  				49072				LOWER MOUNTING POINT BROKEN. THE MATERIAL THAT THIS PART IS MADE OF IS VERY SUSEPTIBLE TO CORROSION.  CORROSION CAUSED T	HIS PART TO FAIL.  UPPER ROD END CORRODED VERY EASILY ALSO. REPLACED WITH NEW PART.					1	G	7	2 	3U			RT	H9SW    					 
2002012300043	20020123	00043	SW  	2002	1	23	AC2A077542       	1	20011226	G	6410	222312753103	BEARING         		222016001131	BELL  	430   	430         	1182150	SW  										T/R BLADE	CRACKED         	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	430CV	281  			A1901	49072				TAIL ROTOR BLADE BEARINGS WERE CRACKED. REPLACED TWO BEARINGS.						1	G	7	2 	3U			RT	H9SW    					 
2002012300044	20020123	00044	NE  	2002	1	23	AC2A077543       	1	20011226	G	7600	23065125	GOVERNOR        			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	H			AC2A	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		11057					890384			GOVERNOR VERY SENSITIVE, COULD NOT MATCH TORQUES & SHAFT IS RACHETY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002012300045	20020123	00045	NE  	2002	1	23	AC2A077544       	1	20011227	G	7921	28E252	THERMOSTAT      			SKRSKY	S76   	S76A        	8143006	NE  										OIL COOLER	INACCURATE      	H			AC2A	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			FS	01	5401G					760137				HIGH ENGINE OIL TEMPERATURE IN FLIGHT.  REPLACED THERMOSTAT.  CURED PROBLEM.						1	G	7	2 	3U			 	H1NE    					 
2001082300084	20010823	00084	CE  	2001	8	23	AMB20011         	1	20010814	G	3244	22X80010	TIRE            			CESSNA	500   	550         	2076604	CE  										MLG	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	753CC					5500109				DURING A DAILY INSPECTION THE SIDE WALL WAS FOUND TORN OUT WHERE THE SIDE WALL AND TIRE TRED ARE BONDED TOGOTHER. THERE 	IS ANOTHER AREA APROX. 6 INCHES AWAY FROM THIS TEAR, WHERE YOU CAN SEE THAT THE RUBBER IS ALSO STARTING TO SEPERATE. THE	 INNER AREA OF THE TEAR HAS SOFT RUBBBER COMMING OUT IT HAS THE CONTIENCY AND FEEL OF RUBBER THAT HAS NOT FULLY CURED. T	HIS TIRE WAS PULLED FROM SERVICE AND A REPLACEMENT INSTALLED. WE ARE GOING TO SUBMIT THIS TO GOOD YEAR FOR THEM TO EVALU	ATE.		1	L	7	2 	4F			 	A22CE   					 
2001011105977	20010111	05977	NM  	2001	1	11	ANCF200100004    	1	20010107	G	2751		CONNECTOR       			BOEING	767   	767259      	1385136	NM  	PWA   	4056  	PW4056      	 	NE  					TE FLAPS	DIRTY           	W			ANCF	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	99	986AN					24835				AFTER T/O BOTH FLAP POINTERS WERE ON 1 WITH THE FLAP LEVER IN UP POSITION, AIRCRAFT RETURNED TO MEX. CLEANED CONNECTORS	 AT FSEU PERFORMED BITE TEST AND OPERATIONAL TEST IAW AMM 27-58-05 TEST OK, COULD NOT DUPLICATED FAULT, FLAP/SLAT VISUAL	 CHECK OK.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001072600248	20010726	00248	NM  	2001	7	26	ANCF200100010    	1	20010609	G	2824		VALVE           			BOEING	767   	767259      	1385136	NM  										FUEL SYSTEM	FAILED          	W			ANCF	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	23	986AN					24835				DURING CRUISE 1:30 HOURS AFTER T/O FUEL CROSSFEED VALVE LIGHT REMAINED ILLUMINATED WHEN VALVE SELECTED OPEN.  EICAS MESS	AGE FUEL CROSSFEED DISPLAYED.  AIRCRAFT RETURNED TO MAD.  PERFORMED PROCEDURE IAW FIM 28-22-00/101 FIG 108 BLOCKS 1, 2 A	ND 14.  REPLACED FUEL CROSSFEED VALVE, PERFORMED TEST WITH SATISFACTORY RESULTS.  AIRCRAFT WAS RETURNED TO SERVICE. 				2	L	7	2 	4F			RT	A1NM    					 
2001080200270	20010802	00270	NE  	2001	8	2	AO1R200100001    	2	20010717	G	7230	794909	COMPRESSOR WHEEL								PWA   	JT9   	JT9D*       	 	NE  					ENGINE	FRETTED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99		16393					695739			EXCESSIVE FRETTING DAMAGE ON BLADE SLOT PRESSURE FACES BEYOND LIMITS IN ACCORDANCE WITH JT9D OHM P/N 646028 SECTION 72-3	5-04 REV 109 FRETTING CHECKS 0.0024". REPAIR ORDER RECEIVED FROM P&W SMMO REQUESTED INSPECT TO THE LATEST REVISION OF E/	M 646028 DIMENSIONAL INSPECT PART AND REPORT FINDINGS TO JEFF FISCUS. PART WAS RECEIVED IN OVERHAUL CONDITION.									4	F			E20EA				 
2001080200271	20010802	00271	NE  	2001	8	2	AO1R200100002    	2	20010717	G	7230	500110801	COMPRESSOR WHEEL								PWA   	JT9   	JT9D*       	 	NE  					ENGINE	FRETTED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99		31003					715441			EXCESSIVE FRETTING DAMAGE ON BLADE SLOT PRESSURE FACES BEYOND LIMITS IN ACCORDANCE WITH JT9D OHM P/N 646028 SECTION 72-3	5-04 REV 109 FRETTING CHECKS 0.0024". FRONT SNAP AND SHOULDER ARE OVERSIZE 0.002", REAR SNAP AND SHOULDER ARE OVERSIZE 0	.002" AND OUT OF ROUND 0.004". REPAIR ORDER RECEIVED FROM P&W SMMO REQUESTED INSPECT TO THE LATEST REVISION OF E/M 64602	8 DIMENSIONAL INSPECT PART AND REPORT FINDINGS TO JEFF FISCUS. PART WAS RECEIVED IN OVERHAUL CONDITION.								4	F			E20EA				 
2001040200081	20010402	00081	NE  	2001	4	2	AU010001         	2	20010102	G	7310	226311001	PIPE            			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE FUEL	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FUEL PIPE FROM FLOW DIVIDED TO FUEL MANIFOLD CHAFED ON COMBUSTOR HOUSING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200082	20010402	00082	CE  	2001	4	2	AU010002         	1	20010103	G	3221	5842000211	TRUNNION        			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION PINS CRACKED. FOUND DURING INSPECTION IAW CESSNA SB MEB88-5R2.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200083	20010402	00083	CE  	2001	4	2	AU010003         	1	20010102	G	3231	08411066	ARM             			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG DOOR	CRACKED         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR INNER DOOR BELLCRANK IDLER ARM CRACKED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001040200084	20010402	00084		2001	4	2	AU010004         	4	20010104	G	2211	065006401	COMPUTER        			REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AUTOPILOT	FAULTY          	W				O	 	 	 	OTHER                   				B	J	 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			3823 							(AUS) AUTOPILOT COMPUTER SUSPECT FAULTY.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001040200269	20010402	00269	EA  	2001	4	2	AU010005         	1	20010107	G	5230		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					CARGO DOOR	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) CARGO DOOR MASTER CAUTION LIGHT ILLUMINATED. INVESTIGATION FOUNDTHE CARGO DOOR HANDLE PARTIALLY RELEASED. A FUNCTI	ONAL CHECK OF THE DOOR LATCHING SYSTEM COULD FIND NO FAULT. SUSPECT THAT THEHANDLE WAS INCORRECTLY STOWED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040200085	20010402	00085	CE  	2001	4	2	AU010006         	1	20010103	G	5540	10164001419	FITTING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	RUDDER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CENTER HINGE ASSEMBLY ATTACHMENT FITTING CORRODED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2001040200086	20010402	00086	SO  	2001	4	2	AU010007         	1	20010106	G	3230		DOWNLOCK        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	CONTAMINATED    	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK ARM JAMMED BY A STONE PREVENTING LANDING GEAR FROM CORRECTLY LOCKING IN THE DOWN POS	ITION.					1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2001040200087	20010402	00087	SO  	2001	4	2	AU010008         	2	20010103	G	8530	631996	RETAINER        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360HB     	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE CYLINDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 CYLINDER ROCKER HAT REMOVED TO REPAIR OIL LEAK. THE ROCKER PIN RETAINER WAS FOUND TO CRACKED. ON FURTHER INSP	ECTION OTHER ROCKER PIN RETAINERS SHOWED SIGNS OF INCIPIENT FAILURE.					1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2001040200088	20010402	00088	EU  	2001	4	2	AU010009         	2	20010104	G	7321	0164168190	FUEL CONTROL    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					NR 1 ENGINE	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND THE PPNG OF THE FCU  INTERNAL CIRCUIT TO BE OPEN CIRCUIT	ED.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001040200089	20010402	00089	WP  	2001	4	2	AU010010         	2	20010110	G	7261	31080801	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	RT ENGINE OIL	CHAFED          	W				K	 	 	 	NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE OIL PIPE LEAKING DUE TO CONTINUED CHAFING WITH ANOTHERPIPE.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001040200270	20010402	00270	CE  	2001	4	2	AU010011         	1	20010110	G	2897	4410174	WIRE            	CESSNA      	C441        	CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	BOOST PUMP	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4410174					(AUS) LT FUEL TANK BOOST PUMP WIRING CHAFED THROUGH TO BARE WIRE.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2001040200090	20010402	00090		2001	4	2	AU010012         	4	20010103	G	2565	7A146723	SLIDE           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					PAX DOOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			12456							(AUS) NR 4 LT MAIN DOOR ESCAPE SLIDE TORN.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040200091	20010402	00091	NM  	2001	4	2	AU010013         	1	20010109	G	2510		SEAT BACK       			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					COCKPIT	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OBSERVERS SEAT BACK REST SEPARATED FROM SEAT BASE DUE TO A BROKEN BRACKET.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200092	20010402	00092	NM  	2001	4	2	AU010014         	1	20010109	G	7830	1275084	ARM             	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	DAMAGED         	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			AU	S 			31016							(AUS) NR 2 ENGINE THRUST REVERSER COWL POSITION (TRCP) RESOLVER ARM DISCONNECTED AT ADJUSTMENT TURNBUCKLE AND ATTACHED B	Y ONLY ONE THREAD AT THE RESOLVER. SAFETY WASHER LOCKTABS PARTIALLY BENT AND RESOLVER APPEARS TO HAVE SUFFERED CONTACT D	AMAGE.				2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040200093	20010402	00093	NM  	2001	4	2	AU010015         	1	20010109	G	2823	737M28500011	VALVE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL SELECTOR	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 			3161 							(AUS) NR 1 ENGINE FUEL SHUTOFF VALVE FAILED IN THE CLOSED POSITION.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200094	20010402	00094	NM  	2001	4	2	AU010016         	1	20010110	G	3260	841005	PSEU            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) PROXIMITY SENSE ELECTRICAL UNIT (PSEU) FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200095	20010402	00095	SO  	2001	4	2	AU010017         	1	20010109	G	7920	2W127984S190	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL	DETERIORATED    	W				O	 	 	 	OTHER                   				K	B	J	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	LD	LANDING        	1			AU	S 										(AUS) RT ENGINE TURBOCHARGER OIL RETURN HOSE DETERIORATED AND LEAKING.HOSE FAILED PRESSURE TESTING. THE HOSE HAD BEEN AF	FECTED BY THE HEAT FROM THE TURBOCHARGER.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040200097	20010402	00097	EU  	2001	4	2	AU010018         	1	20010111	G	2760		BUSHING         			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DRAG CONTROL	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SPEED BRAKE CABLE INPUT QUADRANT CORRODED. THE FOLLOWING ITEMSWERE FOUND DETERIORATED: GROOVE OF PULLEY ASSEMBLY. 	WEB ADJACENT TO STOP PIN HOLE OF BRACKET. INTERNAL SPLINE OF LEVER. EXTERNAL SPLINE ON  SHAFT AND BUSHING. BEARING AND F	OUND CORRODED AND ROUGH TO ROTATE				2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200098	20010402	00098	CE  	2001	4	2	AU010019         	1	20010104	G	3230	51420025	DRAG BRACE      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE CRACKED IN AREA ADJACENT TO THE ACTUATOR ATTACHMENT LUG.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040200099	20010402	00099	CE  	2001	4	2	AU010020         	1	20010112	G	3221	5842000211	PIN             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG TRUNNION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION PIN CRACKED. FOUND DURING INSPECTION IAW CESSNA SB CQB00-3.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001040200100	20010402	00100	CE  	2001	4	2	AU010021         	1	20010103	G	5210	1313232C12	PIN             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PAX DOOR	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DOOR HOOK CLEVIS PIN SHEARED. DOOR DIFFICULT TO OPEN.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001040200101	20010402	00101	EU  	2001	4	2	AU010022         	1	20010112	G	2910	24Q2395	HOSE            			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5322L   	54509	EU  					HYDRAULIC SYS	CRACKED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT GEARBOX MOUNTED HYDRAULIC PUMP OUTLET HOSE END FITTING CRACKED ON FLARED OLIVE.						2	L	7	2 	3T	4	T	 	A24EU   	E297				 
2001040200102	20010402	00102	SO  	2001	4	2	AU010023         	1	20010115	G	3230	40336000	DRAG BRACE      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE ACTUATOR ATTACHMENT LUGS CRACKED. FOUND USING VISUAL AND CONFIRMED USING NDI.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040200103	20010402	00103	EU  	2001	4	2	AU010024         	1	20010116	G	3213	200877682	PIN             			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					RT MLG	FRACTURED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR WHEEL LEVER TO OLEO ATTACHMENT PIN FRACTURED AND MIGRATED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200104	20010402	00104	GL  	2001	4	2	AU010025         	2	20010112	G	7230	9380M28P05	TURBINE WHEEL   	GE          							GE    	CF6   	CF680C2*    	 	GL  					ENGINE	OUT OF TOLERANCE	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			6513 							(AUS) HIGH PRESSURE COMPRESSOR ROTOR SPOOL NR 3 STAGE TO NR 9 STAGE OUTSIDE OF LIMITS AS PER AD/CF6/41, AD/CF6-43, FAA A	D FAD 99-24-15 AND FAA AD FAD 2000-16-12.										4	F			E23EA				 
2001040200105	20010402	00105	NM  	2001	4	2	AU010026         	1	20010112	G	8011	9702038	CLAMP           	GE          	CF680C2     	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					STARTER	FAILED          	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 			4159 		9702038					(AUS) RT ENGINE STARTER CLAMP BROKEN AND STARTER LOOSE. SEAL CUT.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200106	20010402	00106	NM  	2001	4	2	AU010027         	1	20010111	G	2910	AV13J5147	VALVE           			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYS	SEIZED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			25973							(AUS) HYDRAULIC STANDBY MODULE SHUTOFF VALVE SEIZED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200107	20010402	00107	NE  	2001	4	2	AU010028         	2	20010103	G	8500		ENGINE          			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NACELLE	SEIZED          	W				A	 	 	 	UNSCHED LANDING         				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		CL	CLIMB          	1			AU	S 										(AUS) ENGINE RAN ROUGH AND THEN SEIZED. LIMITED INFORMATION PROVIDED.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001040200108	20010402	00108	EA  	2001	4	2	AU010029         	2	20010116	G	7310	25765311	FLOW DIVIDER    			CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	FUEL DIST	CORRODED        	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 			92   							(AUS) ENGINE FUEL FLOW DIVIDED CORRODED. PARTICLES OF CORROSION BLOCKING FUEL INJECTORS. AIRCRAFT HAD BEEN CONTAMINATED 	WITH EDAAND DECONTAMINATED IAW AD/GEN/80 AND MANUFACTURERS INSTRUCTIONS.					1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2001040200109	20010402	00109	SO  	2001	4	2	AU010030         	1	20010113	G	2150	MS21346221	SWITCH          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	AIR CONDITIONING	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) AIR CONDITIONING SYSTEM CROSS BLEED VALVE SWITCH FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040200110	20010402	00110	NM  	2001	4	2	AU010031         	1	20010104	G	2530	CA16371	CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GALLEY	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIQUID HEATER CONNECTORS DAMAGED DUE TO OVERHEATING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200111	20010402	00111	NM  	2001	4	2	AU010032         	1	20010104	G	2530	CA16731	CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GALLEY	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIQUID HEATER CONNECTORS DAMAGED DUE TO OVERHEATING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200112	20010402	00112	NM  	2001	4	2	AU010033         	1	20010114	G	7830		DOOR            	RROYCE      	RB211524D4  	BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					THRUST REVERSER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE BLOCKER PARTIALLY MISSING. DAMAGE TO CORONA AND COLD STREAM DUCT AT 10 OCLOCK POSITION.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001040200113	20010402	00113		2001	4	2	AU010034         	4	20010115	G	2330	311038	CONTROL BOX     			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENTERTAIN SYS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					311038					(AUS) SEAT 5A HARNESS PLUG TO SEAT ELECTRONICS BOX ARCING. ARCING CONTINUED WITH PLUG DISCONNECTED. NO CIRCUIT BREAKERS 	POPPED.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040200114	20010402	00114	NM  	2001	4	2	AU010035         	1	20010116	G	7830		DOOR            	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE THRUST REVERSER NR 9 BLOCKER DOOR PARTLY MISSING. DAMAGE TO CORONA WITH A 76.2MM BY 25.4MM (3IN BY 1IN	) HOLE ADJACENT TO BLOCKER DOOR POSITION. DAMAGE ALSO TO LT COMBUSTION FAIRING AND INTEGRATED NOZZLE ASSEMBLY.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040200141	20010402	00141	SO  	2001	4	2	AU010036         	1	20010116	G	2752	1202001	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	TE FLAP	WORN            	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) FLAP MOTOR BRUSHES AND COMMUTATOR WORN. MOTOR INOPERATIVE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040400001	20010404	00001	NE  	2001	4	4	AU010038         	3	20010111	G	6111	7922141	TAPE            	HAMSTD      	SFA13MIOA   	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER BLADE	LOOSE           	W				O	 	 	 	OTHER                   				O		 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT PROPELLER BLADE LEADING EDGE TAPE LOOSE ON ONE BLADE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200121	20010402	00121	EU  	2001	4	2	AU010039         	1	20010116	G	2770	A78300401	LOCK            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR GUSTLOCK HOUSING MOUNTING LUGS CRACKED. FOUND DURING INSPECTION IAW AD/F28/72 AMDT1. SUSPECT CAUSED BY LO	OSE MOUNT.BOLTS.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040200122	20010402	00122	CE  	2001	4	2	AU010040         	1	20010116	G	3221	5842000211	PIN             			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG TRUNNION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION PIN CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001040200123	20010402	00123	NE  	2001	4	2	AU010041         	2	20010107	G	7310	21631001	PIPE            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUEL DIST	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE LT PRIMARY FUEL PIPE CHAFING ON COMBUSTOR CASE IN AREA OF THE FORWARD FLANGE OF THE CUSTOMER BLEED FLA	NGE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200124	20010402	00124	EU  	2001	4	2	AU010042         	1	20010104	G	7603		CABLE           	LYC         	IO540K1B5   	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	POWER LEVER	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THROTTLE CABLE OUTER CONDUIT DISCONNECTED AT FIREWALL. THE NUT SECURING THE CONDUIT HAD NO LOCKWIRE.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040200125	20010402	00125	EU  	2001	4	2	AU010043         	1	20010105	G	7602		CABLE           	LYC         	IO540K1B5   	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MIXTURE CONTROL	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MIXTURE CONTROL INNER CABLE ONLY ENGAGED IN THE ENGINE CONTROL END BY APPROXIMATELY 1.5 TURNS.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040200126	20010402	00126	EU  	2001	4	2	AU010044         	1	20010110	G	6120		CONTROL CABLE   	HARTZL      	HCC2YK2     	BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROP CONTROL	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT PROPELLER CSU CONTROL CABLE OUTER CONDUIT WORN THROUGH WITHTHE INNER CABLE CATCHING ON THE WORN AREA. CONTROL S	EIZED.					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040200127	20010402	00127	NE  	2001	4	2	AU010045         	2	20010117	G	7260	3022375	SEAL            			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 ACCESSORY DRIVE SEAL MIGRATED OUT OF SEAL CARRIER PNO 3007737 ALLOWING APPROXIMATELY 3.5 LITRES OF OIL TO LEA	K FROM THE ENGINE DRIVEN LOW PRESSURE FUEL PUMP DRIVE SPLINE DRAIN.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001040200128	20010402	00128	SW  	2001	4	2	AU010046         	1	20010122	G	3233	MS28775116	SEAL            		EA1568      	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	MLG ACTUATOR	WORN            	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			DE	DESCENT        	1			AU	S 			2020 							(AUS) MAIN LANDING GEAR RETRACTION ACTUATOR SEAL WORN.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2001040200129	20010402	00129	SO  	2001	4	2	AU010047         	2	20010111	G	7314		SEAL            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					FUEL PUMP	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE DRIVEN FUEL PUMP SEAL FAILED. FUEL LEAKING FROM VENT.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001040200130	20010402	00130	EU  	2001	4	2	AU010048         	1	20010108	G	5711		SPAR            			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT & RT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPARS CONTAINED PITTING CORROSIONIN AREAS OUTBOARD OF RIB NR 13. HEAVY STAINING FOU	ND IN WING TANKS SUSPECTED FROM CLADOSPORIUM RESINAE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200131	20010402	00131	NM  	2001	4	2	AU010049         	1	20010122	G	3242	26056623	BRAKE           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					LT WING MLG	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			7020 							(AUS) LT FORWARD WING LANDING GEAR NR 2 POSITION BRAKE FAILED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001040200132	20010402	00132	NM  	2001	4	2	AU010050         	1	20010119	G	2432	401767	BATTERY         			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					BATTERY BAY	DISCHARGED      	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			4    							(AUS) MAIN AIRCRAFT BATTERY DISCHARGED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040200133	20010402	00133	EU  	2001	4	2	AU010051         	1	20010118	G	7722	897476	COMPENSATOR     			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	EGT/TIT INDICATO	OUT OF TOLERANCE	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE EGT COMPENSATOR OUT OF TOLERANCE.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001040200134	20010402	00134	NM  	2001	4	2	AU010052         	1	20010123	G	2400	S010488308	RELAY           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ELECTRICAL	SEPARATED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RELAY BASE SEPARATED AT PRODUCTION BREAK ALLOWING THE RELAY CONTACTS TO COME AWAY FROM THE RELAY. BASE MANUFACTURE	R CLOVER. THE RELAYS ARE USED IN NUMEROUS AREAS.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040200135	20010402	00135	NE  	2001	4	2	AU010053         	2	20010118	G	7321	8063023	FUEL CONTROL    			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	RT ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) RT ENGINE FUEL CONTROL UNIT FAULTY.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001040200136	20010402	00136	WP  	2001	4	2	AU010054         	1	20010121	G	3234	630294W	PISTON          			LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  	HAMSTD	43E	43E60       	NE  	MLG STRUT	BROKEN          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE PISTONS (2OFF4) BROKEN ACROSS SHANK IN AN O-RING SEAL GROOVE. BROKEN PISTON JAMMED IN 	PORT.					2	L	7	4 	4R	4	R	 	6A5     	E272	6	C	P871	 
2001040200137	20010402	00137	SO  	2001	4	2	AU010055         	2	20010125	G	8520	632043	CONNECTING ROD  			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3AF34C	3AF34C74    	GL  	ENGINE	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			847  							(AUS) LT ENGINE NR 5 CYLINDER CONNECTING ROD SEPARATED FROM CRANKSHAFT AND PENETRATED THE CRANKCASE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P22EA	 
2001040200138	20010402	00138	EU  	2001	4	2	AU010056         	1	20010128	G	5753	7257830022	FITTING         		7257800504  	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	TE FLAP	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					1114					(AUS) RT FLAP ASSEMBLY OUTBOARD FITTING AFT ATTACHMENT LUG CRACKED. CRACK APPEARS TO HAVE EMANATED FROM THE BOLT/BUSHING	 HOLE AND PROGRESSED THROUGH ONE SIDE OF THE LUG. FOUND DURING VISUAL INSPECTION IAW SB-340-57-037.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001040200139	20010402	00139	EA  	2001	4	2	AU010057         	2	20010119	G	8530	17C21191	KEY             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 5 CYLINDER EXHAUST VALVE KEY BROKEN WITH DAMAGE TO TAPPET AND SOCKET. SUSPECT TAPPET DAMAGED AT MANUFACTURE CAU	SING INCORRECT VALVE CLEARANCE.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001040200140	20010402	00140	SW  	2001	4	2	AU010058         	1	20010127	G	2133	A6009	ADAPTER         			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	PRESSURE REG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE SUCTION FITTING FAILED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001040200271	20010402	00271	SW  	2001	4	2	AU010059         	1	20010123	G	6510	2006505008	BOLT            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TAIL ROTOR DRIVE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVESHAFT TO TAIL ROTOR GEARBOX INPUT COUPLING BOLT SEPARATED. MARKS ON BOLT INDICATE THAT IT HAD BEEN	 LOOSE FOR SOME TIME.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001040200272	20010402	00272	SW  	2001	4	2	AU010060         	1	20010113	G	7334	42D218	PRESSURE SWITCH 			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL PRESSURE	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE FUEL PRESSURE SWITCH LEAKING FUEL FROM SOLDERED JOINT AT BASE OF CONNECTOR PLUG CONNECTOR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001040200273	20010402	00273	SW  	2001	4	2	AU010061         	1	20010113	G	7334	42D218	PRESSURE SWITCH 			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL PRESSURE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PRESSURE SWITCH LEAKING FROM SOLDERED JOINT AT BASE OF CONNECTOR PLUG FITTING.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001040200274	20010402	00274		2001	4	2	AU010063         	4	20010101	G	2565	B732560135	CABLE           			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L2 DOOR SLIDE ATTACHMENT CABLE FRAYED IN LOOP AREA.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040200275	20010402	00275	NM  	2001	4	2	AU010064         	1	20010109	G	2897	6130024	WIRE            			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) KAPTON WIRES LOCATED IN REFUEL PANEL HAVE DAMAGED INSULATION ALLOWING THE WIRES TO BE EXPOSED.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040200276	20010402	00276	EU  	2001	4	2	AU010065         	1	20010123	G	5343		FITTING         			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR ACTUATOR FITTING AND CONNECTING STRIP CRACKED IN TWO PLACES. CRACK LENGTHS 20MM (0.78IN)	 IN FORWARD FLANGE AND 28MM (1.102IN) IN AFT FLANGE. CONNECTION STRAP CRACKED FROM FASTENER HOLE. CRACK LENGTH 5MM (0.19	6IN). FOUND DURING NDI INSPECTION IAW SB A320-53A1135 AND AN ENGINEERING RELEASE A32-53-40-9B.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001040200277	20010402	00277	CE  	2001	4	2	AU010066         	1	20010120	G	5511	07326022	SPAR            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER REAR SPAR CRACKED IN AREA BEHIND THERE INFORCED HINGE BRACKET CRACK LENGTH 50MM (1.96IN). CA	USED BY SEVERE CORROSION ON THE DOUBLER BRACKET SECURING THE ATTACHMENT HINGE PNO 0732101-11.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2001040200278	20010402	00278	CE  	2001	4	2	AU010067         	1	20010131	G	3213	10581002375NLH	FRAME           			BEECH 	76    	76          	1153005	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR A FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040200279	20010402	00279	CE  	2001	4	2	AU010068         	1	20010131	G	3213	10581002376RH	FRAME           			BEECH 	76    	76          	1153005	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR A FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040200280	20010402	00280	SO  	2001	4	2	AU010069         	1	20010128	G	3250		PIN             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	NLG STEERING	LOOSE           	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NOSE WHEEL STEERING RELAY BOX CONNECTOR PIN LOOSE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040200281	20010402	00281		2001	4	2	AU010070         	4	20010124	G	2565	7A126130	SLIDE           			BOEING	747   	747SP38     	       	NM  										PAX DOOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			12818							(AUS) RT MAIN ENTRY DOOR SLIDE FAILED TO CORRECTLY DEPLOY DURING TEST. THE SLIDE CAUGHT ON THE DOOR STRUCTURE SUSTAINING	 A SMALL PUNCTURE AND DAMAGING THE LOWER BUSTLE.					2	L	7	4 	4F			RT	A20WE   					 
2001040200282	20010402	00282	EU  	2001	4	2	AU010071         	1	20010202	G	7931	PDCR3301028	TRANSMITTER     			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					OIL PRESSURE	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 			3153 							(AUS) NR 3 ENGINE OIL PRESSURE TRANSMITTER FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040200283	20010402	00283	NE  	2001	4	2	AU010072         	2	20010203	G	7321	8061963	FMU             			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					FUEL CONTROL	FAULTY          	W				O		 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) NR 2 ENGINE FUEL METERING UNIT (FMU) AND ELECTRONIC ENGINE CONTROLLER (EEC) FAULTY.						2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2001040200284	20010402	00284	NE  	2001	4	2	AU010073         	2	20010203	G	7321	114E6112G117	EEC             			BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					FUEL CONTROL	FAULTY          	W				O		 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) NR 2 ENGINE ELECTRONIC ENGINE CONTROLLER (EEC) FAULTY. SEE ALSO MDR 01/0072.						2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2001040200285	20010402	00285	NE  	2001	4	2	AU010074         	3	20010129	G	6111	RFC11U1R6A	BLADE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PROPELLER BLADE DAMAGED BY MISSING SPINNER ATTACHMENT SCREW. THREE SCREWS MISSING FROM SPINNER. ONE SCREW WAS F	OUND EMBEDDED IN THE PROPELLER BLADE. MAINTENANCE HAD BEEN CARRIED OUT ON THE PROPELLER PRIOR TO THE FLIGHT.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001040200286	20010402	00286	EA  	2001	4	2	AU010075         	1	20010203	G	3213		BLOCK           			DHAV  	DHC6  	DHC6300     	2802606	EA  										MLG	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR COMPRESSION BLOCKS FAILED WITH RESULTANT DAMAGE TO THE FUSELAGE. BLOCKS FAILED DUE TO RT MLG 	CONTACTING A RIDGE ON THE AIRSTRIP.					1	H	7	2 	3T			RT	A9EA    					 
2001040200287	20010402	00287	EA  	2001	4	2	AU010076         	2	20010112	G	7414	K3984	CAPACITOR       	SLICK       	4381        	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	LT MAGNETO	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			2068 		97020839					(AUS) LT MAGNETO CAPACITOR CONNECTING WIRE BROKEN DUE TO LOOSE BEARING CAP. FURTHER INVESTIGATION FOUND THE BEARINGS TO 	BE DRY AND AN UNKNOWN SUBSTANCE UNDER THE BEARING CAP HOLD-DOWN PLATES WHICH PREVENTED THE CAP BEING PROPERLY SECURED.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001040200288	20010402	00288	SO  	2001	4	2	AU010077         	2	20010206	G	8550		GEAR            								CONT  	O520  	TSIO520K    	17040	SO  					SCAV PUMP	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL SCAVENGE PUMP GEAR FAULTY. ROCKWELL HARDNESS TEST GAVE A READING OF 34 WHICH IS BELOW SPECIFICATION.											3	O			E8CE				 
2001040200289	20010402	00289	NM  	2001	4	2	AU010078         	1	20010112	G	5330		SKIN            			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED AT TWO FASTENER HOLES IMMEDIATELY FORWARD OF THE FRAME AT STN 980.						2	L	7	4 	4F			 	A20WE   					 
2001040200290	20010402	00290	GL  	2001	4	2	AU010079         	3	20010128	G	6114	737568	HUB             								LYC   	O360  	O360A2A     	41514	EA  	MCAULY	2D36C	2D36C14     	GL  	PROPELLER	DAMAGED         	W				C	 	 	 	ABORTED TAKEOFF         				D	 	 	INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) PROPELLER HUB FAILED DUE TO CRACK ORIGINATING IN THE ROOT OF THEBLADE RETAINING THREAD. PROPELLER BLADE SEPARATED 	FROM HUB.										3	O			E286	5	C	P901	 
2001040200291	20010402	00291	NM  	2001	4	2	AU010080         	1	20010127	G	7110		PANEL           	RROYCE      	RB211524D4  	BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					COWLING	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			15288							(AUS) NR 1 ENGINE NR 1 AND NR 3 & 4 ACOUSTIC PANELS MISSING.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001040200292	20010402	00292	NM  	2001	4	2	AU010081         	1	20010127	G	2910	13206001	SWITCH          			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					HYDRAULIC SYS	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) LT HYDRAULIC TAIL SHUTOFF VALVE SWITCH MODULE FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001040200293	20010402	00293	CE  	2001	4	2	AU010082         	1	20010205	G	3213	10581002376RH	FRAME           			BEECH 	76    	76          	1153005	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR A FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040200294	20010402	00294	CE  	2001	4	2	AU010083         	1	20010205	G	3213	10581002375LH	FRAME           			BEECH 	76    	76          	1153005	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR A FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040200295	20010402	00295	NM  	2001	4	2	AU010084         	1	20010130	G	2741		WIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					STABILIZER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT STABILISER POSITION ROTARY VARIABLE DISPLACEMENT TRANSDUCER(RVDT) PLUG DM7884 HAD CHAFED WIRING ADJACENT TO PLU	G.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040200296	20010402	00296	NM  	2001	4	2	AU010085         	1	20010131	G	2120		UNKNOWN         			BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					AIR CONDITIONING	ODOR            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) FUMES IN CABIN. INVESTIGATION CONTINUING INTO CAUSE.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001040300151	20010403	00151	NM  	2001	4	3	AU010086         	1	20010130	G	5730	113T161331	PANEL           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT WING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PANEL 551VB LOCATED ON LT WING LOWER SURFACE AFT OF THE LT  MAIN LANDING GEAR MISSING A CENTRE SECTION APPROXIMATE	LY 6 FEET LONG.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040300152	20010403	00152	NM  	2001	4	3	AU010087         	1	20010128	G	2910	65C268393152	PIPE            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYS	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM A ENGINE DRIVEN PUMP HYDRAULIC LINE CHAFED BY  LOWER AILERON PCU.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040300153	20010403	00153	CE  	2001	4	3	AU010088         	1	20010202	G	5510	10562000025	HINGE           			BEECH 	76    	76          	1153005	CE  										HORIZONTAL STAB	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CENTER BEARING SUPPORT BLOCK MOVING IN CLAMPING FLANGES DUE TO APPROXIMATELY 0.127MM TO 0.254MM (0.005IN 	TO 0.010IN) ELONGATION OF THE RIVET HOLES.					1	L	7	2 	3O			 	A29CE   					 
2001040300154	20010403	00154	SO  	2001	4	3	AU010089         	1	20010205	G	2910	D100366	FITTING         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	HYDRAULIC SYS	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC FITTING LOCATED IN LT OUTBOARD NACELLE LEAKING UNDERPRESSURE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001040300155	20010403	00155	EU  	2001	4	3	AU010090         	1	20010119	G	3610		LOOP            			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					PNEUMATIC DIST	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) WING LOOP A PNEUMATIC SYSTEM INOPERATIVE.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040300156	20010403	00156	EU  	2001	4	3	AU010091         	1	20010202	G	3610		DUCT            			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					PNEUMATIC DIST	LEAKING         	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 BLEED AIR SYSTEM LEAKING.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040300157	20010403	00157	EU  	2001	4	3	AU010092         	1	20010202	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	CONTAMINATED    	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) FORWARD CARGO DOOR MICROSWITCH CONTAMINATED WITH DIRT AND PAINT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300158	20010403	00158	EU  	2001	4	3	AU010094         	1	20010131	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	OUT OF ADJ      	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300159	20010403	00159	EU  	2001	4	3	AU010095         	1	20010130	G	3610		DUCT            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PNEUMATIC DIST	LEAKING         	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) TAIL SECTION PNEUMATIC DUCT LEAK WARNING. INVESTIGATION COULD FIND NO LEAKS.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300163	20010403	00163	EU  	2001	4	3	AU010096         	1	20010129	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) SERVICE DOOR WARNING LIGHT ILLUMINATED. SUSPECT MICROSWITCHES OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300164	20010403	00164	EU  	2001	4	3	AU010097         	1	20010128	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	STUCK           	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) CARGO DOOR MICROSWITCHES STICKING INTERMITTENTLY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300165	20010403	00165	EU  	2001	4	3	AU010098         	1	20010128	G	2432	23531	BATTERY         			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					BATTERY BAY	OVERHEATED      	W				A	 	 	 	UNSCHED LANDING         				M	J	 	OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) FORWARD BATTERY OVERTEMPERATURE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300166	20010403	00166	EU  	2001	4	3	AU010099         	1	20010126	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) FORWARD SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300167	20010403	00167	EU  	2001	4	3	AU010100         	1	20010125	G	5312		BULKHEAD        			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR PRESSURE BULKHEAD CRACKED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300168	20010403	00168	EU  	2001	4	3	AU010101         	1	20010120	G	3230		UPLOCK          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RT MLG	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR UPLOCK HOOK LOOSE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300169	20010403	00169	EU  	2001	4	3	AU010102         	1	20010105	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	STUCK           	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) CARGO DOOR MICROSWITCHES STICKING INTERMITTENTLY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300170	20010403	00170	SO  	2001	4	3	AU010103         	1	20010202	G	2731	41734078	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR TAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM CABLE SEVERELY WORN IN THE AREA AROUND THE TRIM SERVO. ALL WIRE STRANDS BROKEN EXCEPT FOR TWO.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040300171	20010403	00171	EA  	2001	4	3	AU010104         	2	20010202	G	8550	LW13383	BAFFLE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE SUMP	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			691  							(AUS) ENGINE SUMP BAFFLE RIVET MISSING. THREE REMAINING RIVETS LOOSE. METAL IN OIL SYSTEM CAME FROM WORKING RIVETS.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040300172	20010403	00172	EU  	2001	4	3	AU010105         	2	20010205	G	7261	9584	ENGINE          			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					OIL PRESSURE	LOW             	W				O	 	 	 	OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 										(AUS) NO2 ENGINE LOW OIL PRESSURE. ENGINE REMOVED AND AWAITING STRIPREPORT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040300173	20010403	00173	NM  	2001	4	3	AU010106         	1	20010105	G	5310		STRUCTURE       			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NUMEROUS AREAS OF CORROSION FOUND DURING CPCP INSPECTION IAWAD/B727/128.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001040300174	20010403	00174	NM  	2001	4	3	AU010107         	1	20010130	G	2520	11	BOLT            			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					SEAT BELT	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			4006 							(AUS) SEAT BELT ATTACHMENT BOLT LOOSE AT SEAT 11E. FOUND DURING INSPECTION IAW ER B73-25-20-246.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001040300175	20010403	00175	NE  	2001	4	3	AU010108         	2	20010207	G	7200	0292005250	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 1	SEIZED          	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1738 							(AUS) NR 1 ENGINE INTERNAL FAILURE. INSPECTION FOUND COMPRESSOR SEIZED AND SEVERAL TURBINE BLADES MISSING/BROKEN.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001040300176	20010403	00176	NM  	2001	4	3	AU010109         	1	20010123	G	3230	113T1110	FITTING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					MLG	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR SIDE STRUT SWIVEL ASSEMBLY FITTINGS COORODED IN AREA BENEATH BUSHING FLANGE.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001040300177	20010403	00177	CE  	2001	4	3	AU010110         	1	20010214	G	5330	101120108604	SKIN            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FUSELAGE	DEBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP SKIN DISBONDED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001040300178	20010403	00178	EU  	2001	4	3	AU010111         	1	20010211	G	5102	GATES	HOSE            			COLT  	160   	160A        	8970104	EU  										BALLOON REPORTS	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTER SKIN OF THE LPG HOSE RUPTURED.						1	B		0 	  			 	3BEU    					 
2001040300179	20010403	00179	EA  	2001	4	3	AU010112         	1	20010122	G	5553	C6TFM102227	FITTING         			DHAV  	DHC6  	DHC6300     	2802606	EA  										VERTICAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER FORWARD ADAPTER FITTING RIGHT HAND ATTACHMENT LUG CRACKED.						1	H	7	2 	3T			RT	A9EA    					 
2001040300180	20010403	00180	SO  	2001	4	3	AU010113         	1	20010208	G	2823	480700	PIN             			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	FUEL SELECTOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUEL SELECTOR ROLL PINS (2OFF) BROKEN.						1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2001040300181	20010403	00181	CE  	2001	4	3	AU010114         	1	20010206	G	2731		BOLT            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	FLIGHT CONTROL	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXCESSIVE TRIM TAB FREE-PLAY DUE TO WORN AFT PUSHROD BOLT.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040300182	20010403	00182	EU  	2001	4	3	AU010115         	1	20010129	G	7933	J03040C	CONNECTOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					OIL TEMP	CONTAMINATED    	W				O	 	 	 	OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE OIL TEMPERATURE PROBE CONNECTOR PLUG LOOSE AND CONTAMINATED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001040300183	20010403	00183	NM  	2001	4	3	AU010116         	1	20010122	G	2910	82910010113	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	FRACTURED       	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC PIPE FRACTURED ON RADIUS AT STA. 110.0. LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040300184	20010403	00184	WP  	2001	4	3	AU010117         	1	20010130	G	5720	157	FITTING         			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					LT WING	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					157					(AUS) LT WING FRONT LOWER INTERPLANE STRUT ATTACHMENT FITTING BROKEN AWAY DUE TO WOOD ROT.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001040300185	20010403	00185	NM  	2001	4	3	AU010118         	1	20010120	G	3260		UPLOCK SENSOR   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK SENSOR OUT OF ADJ.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040300186	20010403	00186	CE  	2001	4	3	AU010119         	1	20010206	G	8011	PM2407	STARTER         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	LT ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE STARTER MOTOR FAULTY. ONE NEGATIVE BRUSH MISSING WITH THE OTHER NEGATIVE BRUSH LOOSE IN THE BRUSH HOLDER	 AND EVIDENCE OF SEVERE ARCING AROUND THE BRUSH/PIGTAIL SECURING SCREW. BOTHPOSITIVE BRUSHES WERE LOOSE AND THE BRUSH HO	LDERS WITHSEVERE ARCING AROUND THE SECURING SCREW.				1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001040300187	20010403	00187	NE  	2001	4	3	AU010120         	2	20010216	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE BAY	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			4811 							(AUS) ENGINE CHIP DETECTOR CONTAMINATED BY METAL CHIP. SUSPECT CHIP WAS A PART OF A TAB WASHER.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001040300188	20010403	00188	CE  	2001	4	3	AU010121         	1	20010115	G	5511	04320016	RIB             			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER FORWARD ATTACHMENT RIBS CRACKED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001040300189	20010403	00189	CE  	2001	4	3	AU010122         	1	20010115	G	5511	043200146	RIB             			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER FORWARD ATTACHMENT RIBS CRACKED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001040300190	20010403	00190	EU  	2001	4	3	AU010124         	2	20010206	G	7321	0164168200	FUEL CONTROL    			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					NR 2 ENGINE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			258  							(AUS) NR 2 ENGINE FUEL CONTROL UNIT FAULTY.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001040300193	20010403	00193	SO  	2001	4	3	AU010126         	1	20010206	G	5243	12007993614	DOOR            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	HYDRAULIC BAY	SEPARATED       	W				O	 	 	 	OTHER                   				D		 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) RT HYDRAULIC BAY DOOR FAILED AND SEPARATED DURING FLIGHT. DOORHAD BEEN OPENED FOR MAINTENANCE BEFORE FLIGHT AND IT	 IS SUSPECTED THAT IT WAS NOT PROPERLY CLOSED AND LATCHED.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001040300194	20010403	00194	NM  	2001	4	3	AU010127         	1	20010204	G	7603		CABLE           	RROYCE      	RB211524D4  	BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					POWER LEVER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST CONTROL SYSTEM CABLES, PULLEYS AND FITTINGS DAMAGED. FOUND DURING INSPECTION IAW AD/B747/229 AND FAA	AD/2000-05-30 AMDT39-11640.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001040300195	20010403	00195	CE  	2001	4	3	AU010128         	1	20010201	G	2701	05131679	WHEEL           			CESSNA	182   	182C        	2072708	CE  	CONT  	O470  	O470L       	17026	SO  	HARTZL	HCA2X	BHCA2XF1    	GL  	CONTROL COLUMN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH CONTROL WHEELS CRACKED FROM BOTTOM RIVET HOLE.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P908	 
2001040300196	20010403	00196	NM  	2001	4	3	AU010129         	1	20010202	G	2612	51291001	FIRE LOOP       			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					APU BAY	MALFUNCTIONED   	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) APU LOWER DOOR FIRE DETECTOR LOOP HAD HIGH RESISTANCE. FALSE WARNING INDICATION RESULTED IN DISCHARGE OF FIRE BOTT	LE.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001040300197	20010403	00197	NM  	2001	4	3	AU010130         	1	20010202	G	2910		HOSE            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYS	FAILED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK HYDRAULIC HOSE SPLIT. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040300198	20010403	00198	NM  	2001	4	3	AU010131         	1	20010110	G	3260	841005	PSEU            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR PROXIMITY SWITCH ELECTRONIC UNIT (PSEU) FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040300200	20010403	00200	SO  	2001	4	3	AU010132         	2	20010202	G	8530		EXHAUST VALVE   			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST VALVE LEAKING.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001040300201	20010403	00201	SO  	2001	4	3	AU010133         	1	20010207	G	5320	12043522001LH	BEAM            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	CABIN	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT ATTENDANT SEAT SUPPORT FRAMES CORRODED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040300202	20010403	00202	SO  	2001	4	3	AU010134         	1	20010207	G	5320	12025916001RH	BEAM            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	CABIN	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT ATTENDANTS SEAT SUPPORT FRAMES CORRODED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040300203	20010403	00203	EU  	2001	4	3	AU010135         	1	20010203	G	7712	P66230C	ENGINE          			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	LEFT	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE RPM ROLLBACK. SUSPECT CAUSED BY NR 1 TORQUE BRIDGE PIT OUT OF ADJUSTMENT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001040300204	20010403	00204	SO  	2001	4	3	AU010136         	1	20010206	G	2133	2091G010800	OUTFLOW VALVE   			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	CABIN PRESSURE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 			4884 							(AUS) PRESSURISATION SYSTEM OUTFLOW VALVE FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040300205	20010403	00205	SO  	2001	4	3	AU010137         	1	20010126	G	2751	487927	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT WING TE FLAPS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING FLAP UPLIMIT MICROSWITCH FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040300206	20010403	00206	CE  	2001	4	3	AU010138         	1	20010220	G	3510	1013800491	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	CREW OXYGEN	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COPILOTS OXYGEN HOSE FAILED. HOSE HAD BEEN INCORRECTLY FITTED WITH A TIGHT RADIUS.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001040300207	20010403	00207	GL  	2001	4	3	AU010139         	2	20010123	G	7210	6877180	GEARBOX         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) ENGINE GEARBOX OUT OF LIMITS. CHIP DETECTORS CONTAMINATED WITHMETAL PARTICLES.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001040300208	20010403	00208	EU  	2001	4	3	AU010140         	1	20010119	G	5302	332A2400200001	STRUCTURE       			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					TAIL BOOM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL BOOM CRACKED IN AREA OF PYLON DECK.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001040300209	20010403	00209	SO  	2001	4	3	AU010141         	1	20010213	G	7112		BAFFLE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE AIR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE BAFFLES DAMAGED. FOUND DURING INSPECTION IAW AD/PA31/96REQ1.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040300210	20010403	00210	EA  	2001	4	3	AU010142         	2	20010119	G	8530	LW16740	EXHAUST VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1146 							(AUS) LH ENGINE EXHAUST VALVES (2OFF) ERODED. RT ENGINE EXHAUST VALVES(4OFF) ERODED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040300211	20010403	00211	NE  	2001	4	3	AU010143         	2	20010215	G	7200	RB211524G	ENGINE          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 4	FIRE            	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			16202							(AUS) NR 4 ENGINE FIRE. INVESTIGATION FOUND FIRE/HEAT DAMAGE TO WIRING AND CLAMPS IN AREA OF COMBUSTION CHAMBER COWLING.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040300212	20010403	00212	NM  	2001	4	3	AU010144         	1	20010216	G	2741		WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HORIZONTAL STAB	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) HORIZONTAL STABILISER SURFACE POSITION INDICATOR WIRE CHAFED ANDSHORT CIRCUITING INSIDE CONDUIT LOCATED BETWEEN TH	E FORWARD SPAROF THE HORIZONTAL STABILISER AND THE RT ELEVATOR SYNCHRO.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040300213	20010403	00213	NE  	2001	4	3	AU010146         	2	20010208	G	7321	CPW3111697503B	EEC             			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	LT ENGINE	OUT OF ADJ      	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE ELECTRONIC UNIT AUTO-FEATHER OPERATION FUNCTION OUT OF ADJUSTMENT. UNIT HAD BEEN ADJUSTED ON THE PREVIOU	S NIGHT WITHOUTCHECKING THE AUTO-FEATHER FUNCTION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040300214	20010403	00214	CE  	2001	4	3	AU010147         	1	20010221	G	3213	10581002376	FRAME           			BEECH 	76    	76          	1153005	CE  										MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR A FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001032600495	20010326	00495	NM  	2001	3	26	AU010148         	1	20010217	G	2910	DSC252A40230	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC, MAIN	LEAKING         	W				K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LINE LOCATED IN RH WHEEL BAY CONTAINED A PINHOLE LEAK.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001032600012	20010326	00012	SO  	2001	3	26	AU010149         	2	20010123	G	8520	652560	CRANKCASE       	CONT        	IO520L      	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RECIPROCATING EN	CRACKED         	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			415  		567731					(AUS) CRANKCASE CRACKED IN NUMEROUS PLACES. INSPECTION FOUND EXCESSIVE FRETTING ON THE SECOND AND THIRD MAIN BEARING SAD	DLE FACES WHEN VIEWED FROM THE REAR. LOCTITE OR SIMILAR WAS FOUND ON THE BEARING SADDLE FACES. THE MAIN THROUGH BOLTS WE	RE OF THE OLDER SIX POINTNUTS. THE HYDRAULIC LIFTERS FITTED IN THE EXHAUST POSITIONS WERE PNO 646288 INSTEAD OF PNO 6462	77. THE OIL PICKUP SCREEN SUCTION SCREEN WAS THE INCORRECT TYPE AS REQUIRED BY SB M87-11 REV2. NO OVERHAUL HISTORY COULD	 BE FOUND FOR THE FUEL PUMP OR THE FCU. PERSONNEL/MAINTENANCE ERROR. WRONG PART.		1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2001032600013	20010326	00013	EA  	2001	3	26	AU010150         	2	20010213	G	8530	LW16703	CYLINDER        	LYC         	O235L2C     	PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	RECIPROCATING EN	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			810  		L1609315					(AUS) ENGINE NO2 CYLINDER CRACKED AT BASE. OIL LEAKING FROM CRACK.						1	L	7	1 	3O	3	O	 	A18SO   	E223	5	N	P9045	 
2001032700417	20010327	00417	NM  	2001	3	27	AU010151         	1	20010109	G	5280	28489	DOOR            	BOEING      	737400      	BOEING	757   	757*        	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					LANDING GEAR DOO	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			10341		28489					(AUS) RT MAIN LANDING GEAR STRUT DOOR CRACKED THROUGH LOWER ATTACHMENT BOLT HOLDER.						2	L	7	2 	4F	4	F	RT	A2NM    	E21EU				 
2001032700418	20010327	00418	SO  	2001	3	27	AU010152         	1	20010213	G	3242	RFS1015	DISK            	BFGOODRICH  	214791      	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	BRAKE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					0671					(AUS) BRAKE ROTATING DISC (CARRIER AND LINING ASSEMBLY) BROKEN.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001032700419	20010327	00419	SO  	2001	3	27	AU010153         	1	20010213	G	5330	120056	SKIN            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SKIN SURROUNDING THE COPILOTS WINDOW FRAME CRACKED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001032700420	20010327	00420	NM  	2001	3	27	AU010154         	1	20010202	G	5753	6546435274SP	SKIN            			BOEING	737   	7374Q8      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TE FLAPS	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT AFT OUTER FLAP TRAILING EDGE DELAMINATING AT INBOARD AFT CORNER.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040300001	20010403	00001	EA  	2001	4	3	AU010155         	2	20010219	G	7310	420218	SWITCH          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL BYPASS	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL FILTER BYPASS SWITCH  LEAKING FROM SWITCH BODY IN THE AREA WHERE THE ELECTRICAL CONNECTOR IS SOLDERED TO THE 	SWITCH. FUEL WAS SEEN RUNNING INTO THE ENGINE INTAKE PLENUM. A REPLACEMENT SWITCH HAD POOR SOLDERING OF THE CONNECTOR IN	 THE SAME AREA ASTHE FAILED ITEM.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001040300002	20010403	00002	EU  	2001	4	3	AU010156         	1	20010211	G	7714	2454401	SENSOR          			AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OVERSPEED SENSOR FAULTY.						1	G	7	2 	3U	3	U	 	H10EU   	E19EU				 
2001032700421	20010327	00421	CE  	2001	3	27	AU010157         	1	20010202	G	2410	646655	GEAR            	CESSNA      	ALTERNATOR  	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC GENERATOR-ALT	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			185  		EO030305377					(AUS) LH ENGINE ALTERNATOR DRIVE GEAR DAMAGED AND OUTER SHELL DISTORTED. EVIDENCE OF VICE MARKS ON OUTSIDE OF SHELL. FUR	THERDAMAGE FOUND:-1. OIL SEAL INSTALLED BACKWARDS.2. SUPPRESSOR CAPACITOR LOOSE INSIDE OF ALTERNATOR AND SCREW LOOSE. 3.	 PITTING IN CASE HARDENING ON THE SLIP RING END OF THE ROTOR SHAFT. 4. STATOR CORE LAMINATIONS BADLY DISTORTED RENDERING	 CORE  UNSERVICEABLE. THE ROTOR IN ALTERNATOR AT TIME OF STRIP DOWN INSPECTION SHOWED NO SIGNS OF CONTACT WITH STATOR PO	LES.PERSONNEL/MAINTENANCE  ERROR.		1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001032700422	20010327	00422	CE  	2001	3	27	AU010158         	1	20010222	G	5280	08411066	BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR DR	BROKEN          	W				K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		LD	LANDING        	1			AU	S 			5203 							(AUS) LH MAIN LANDING GEAR DOOR BRACKET FAILED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001040300003	20010403	00003	EU  	2001	4	3	AU010159         	1	20010212	G	7722	21186009	COMPUTER        			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	ENGINE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE SINGLE RED LINE COMPUTER FAULTY.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001040300004	20010403	00004	EU  	2001	4	3	AU010160         	1	20010223	G	7160	TU195MM660MMCC	HOSE            			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENG AIR INTAKE	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE INTAKE HOSE LOCATED BETWEEN THE AIR FILTER AND THE FCU COLLAPSED DUE TO LOOSE INNER SUPPORT WIRE.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040500255	20010405	00255	NE  	2001	4	5	AU010161         	2	20010222	G	7530	216035037	ACTUATOR        	LYC         	ALF502R5    	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COMPRESSOR BLEED	FAULTY          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			AP	APPROACH       	1			AU	S 					XRC8122					(AUS) NR 3 ENGINE BLEED BAND ACTUATOR FOLLOWUP ARM RETAINING CLIP AND PIN MISSING ALLOWING THE FOLLOWUP ARM AND THE OPER	ATING LEVER TO FOUL EACH OTHER WHICH RESULTED IN THE BLEED BAND REMAINING CLOSED.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040500256	20010405	00256	EU  	2001	4	5	AU010162         	1	20010221	G	2450	A2043C	POWER UNIT      			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	AC POWER DIST	FAULTY          	W				O	 	 	 	OTHER                   				H	B	J	ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 										(AUS) RT POWER DISTRIBUTION UNIT (PDU) FAULTY. STARTER-GENERATOR WOULDNOT DISENGAGE AND AN OVERTEMPERATURE WAS OBSERVED 	WITH SMOKE COMING FROM THE COWLS. THE FIRE BOTTLE WAS DISCHARGED AS APRECAUTION.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001040500257	20010405	00257	WP  	2001	4	5	AU010163         	2	20010228	G	7210	851	GEARBOX         			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	LEFT ENGINE	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE REMOVED DUE TO SUSPECT DISTRESS IN THE GEARBOX AND VIBRATION. OIL ANALYSIS FOUND METAL CONTAMINATION.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001040500258	20010405	00258	CE  	2001	4	5	AU010164         	1	20010222	G	2710	50452133	TUBE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	AILERON CONTROL	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTBOARD PUSH-PULL TUBE LOCATED IN RT WHEEL WELL CORRODED INTERNALLY.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001040500259	20010405	00259	SW  	2001	4	5	AU010165         	1	20010226	G	5712	273102336	RIB             			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) RT WING RIB CRACKED IN BEND RADIUS. RIB FORMS THE INNER WALL OF THE BATTERY BOX. CRACK LENGTH 203.2MM (8IN).						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001040500260	20010405	00260	SW  	2001	4	5	AU010166         	1	20010226	G	5712	273102336	RIB             			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING RIB CRACKED IN BEND RADIUS. RIB FORMS THE INNER WALL OF THE BATTERY BOX. CRACK LENGTH 76.2MM (3IN).						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001040500261	20010405	00261	EU  	2001	4	5	AU010167         	1	20010223	G	7714	AG34	TACH GENERATOR  			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				P		 	NO WARNING INDICATION     			CL	CLIMB          	1			AU	S 										(AUS) TACHO-GENERATOR ZERO OUTPUT. INVESTIGATION ALSO FOUND BROKENWIRE STRANDS AT THE ENGINE WIRING DISCONNECT SPLICE.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001040500262	20010405	00262	EU  	2001	4	5	AU010168         	2	20010219	G	7230		COMPRESSOR      			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 1 ENGINE	DAMAGED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NO1 ENGINE VIBRATION. BORESCOPE INSPECTION FOUND DAMAGE TO THESEVENTH STAGE HPC.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500263	20010405	00263	EU  	2001	4	5	AU010169         	1	20010218	G	2133	566920	OUTFLOW VALVE   			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					CABIN COOLING SY	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 					4585					(AUS) AVIONICS COOLING SYSTEM OUTFLOW VALVE FAILED.						2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001040500264	20010405	00264	CE  	2001	4	5	AU010170         	1	20010201	G	3260	JE1	SWITCH          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	WORN            	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR MICROSWITCH ARM WORN. ARM BROKE OFF DURING FLIGHT.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001040500265	20010405	00265		2001	4	5	AU010172         	4	20010305	G	3423		COMPASS         			CESSNA	150   	150B        	2071806	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	COCKPIT	OUT OF ADJ      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COMPASS SWING OUT OF DATE. NO COMPASS CORRECTION CARD FITTED.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001040500266	20010405	00266	SO  	2001	4	5	AU010173         	1	20010228	G	5511	40122002	SPAR            	PIPER       	PA31350     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					311274					(AUS) HORIZONTAL STABILISER SPAR CRACKED. FOUND DURING INSPECTION IAW PIPER MSB 1007. WHEN INSPECTED IAW AD/PA31/97 AMDT	2 NO CRACKS WERE FOUND DUE TO CRACKS BEING HIDDEN BY THE ELEVATOR OUTBOARD HINGE ATTACHMENT FITTING.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040500267	20010405	00267	SO  	2001	4	5	AU010174         	1	20010228	G	5511	40122003	SPAR            	PIPER       	PA31350     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 					311274					(AUS) HORIZONTAL STABILISER SPAR CRACKED. FOUND DURING INSPECTION IAW PIPER MSB 1007. WHEN INSPECTED IAW AD/PA31/97 AMDT	2 NO CRACKS WERE FOUND DUE TO CRACKS BEING HIDDEN BY THE ELEVATOR OUTBOARD HINGE ATTACHMENT FITTING.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040500268	20010405	00268	CE  	2001	4	5	AU010175         	1	20010223	G	2752	08615582	GEAR            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					TE FLAP ACTUATOR	WORN            	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP ACTUATOR TRANSFER GEAR STRIPPED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001040500269	20010405	00269	EA  	2001	4	5	AU010176         	2	20010225	G	7414	4370	SHAFT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAGNETO	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO SHAFT BROKEN IN AREA WHERE THE POINTS CAM ATTACHES.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2001040500270	20010405	00270	SO  	2001	4	5	AU010177         	2	20010308	G	8500	IO470L	ENGINE          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	RIGHT	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 			1450 				20139971L			(AUS) RT ENGINE CATASTROPHIC FAILURE.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2001040500271	20010405	00271	WP  	2001	4	5	AU010178         	1	20010204	G	2436	15891A	VOLT REGULATOR  			DOUG  	DC4   	C54E        	3021530	WP  	PWA   	R2000 	R2000*      	52023	NE  	HAMSTD	23E	23E50       	NE  	DC SYSTEM	OVERHEATED      	W				A	 	 	 	UNSCHED LANDING         				B	J	 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					R704					(AUS) NR 2 GENERATOR VOLTAGE REGULATOR FAULTY.						2	L	7	4 	4R	4	R	 	A762    	5E5	6	C	P603	 
2001040500272	20010405	00272	SO  	2001	4	5	AU010179         	2	20010219	G	8530	649166	CYLINDER        			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			397  				270089R			(AUS) NR 1 AND NR 3 CYLINDERS CRACKED FROM UPPER SPARK PLUG HOLE. CRACK LENGTHS APPROXIMATELY 25.4MM (1IN). BOTH CYLINDE	RS ARE P0.015IN.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2001040500273	20010405	00273	SO  	2001	4	5	AU010180         	2	20010220	G	8520		CRANKCASE       			CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE IN AN EXTREMELY POOR CONDITION. DEFECTS INCLUDE CRACKED CRANKCASE, WORN CRANKSHAFT, WORN GEARS, WORN CYLIND	ERS AND VALVES.					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2001040500274	20010405	00274	NE  	2001	4	5	AU010181         	3	20010227	G	6111	RFC11U16A	BLADE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT PROPELLER NR 1 BLADE DAMAGED BY FOD. LEADING EDGE SHEATH HAD APIECE MISSING APPROXIMATELY 10MM (0.393IN) IN DIA	METER. THE LEFT FRONT PASSENGER WINDOW BEHIND THE GALLEY HAD A LARGE IMPACT MARK APPROXIMATELY 12MM (0.472IN) IN DIAMETE	R.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001040500275	20010405	00275	EA  	2001	4	5	AU010182         	2	20010307	G	8520	68606	CRANKSHAFT      			FUJI  	FA200 	FA200160    	3730101	WP  	LYC   	O320  	O320D2A     	41508	EA  	MCAULY	1C172	1C172MGM    	GL  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 							L639239A			(AUS) CRANKSHAFT INTERNAL BORE CORRODED. FOUND DURING INSPECTION IAWAD/LYC/102 AMDT2 PART 1 AND PART 2.						1	L	7	1 	3O	3	O	 	A4PC    	E274	5	N	P910	 
2001040500276	20010405	00276	SW  	2001	4	5	AU010183         	1	20010307	G	6230	206040002109	MAST            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DAMAGED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN ROTOR MAST SUBJECTED TO TORSIONAL DAMAGE DURING N2 LOCKUP ON START.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001040500277	20010405	00277	EA  	2001	4	5	AU010184         	2	20010307	G	8520	L639239A	PUSHROD         			FUJI  	FA200 	FA200160    	3730101	WP  	LYC   	O320  	O320D2A     	41508	EA  	MCAULY	1C172	1C172MGM    	GL  	ENGINE	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L639239A			(AUS) ENGINE PUSHRODS AND TAPPETS INCORRECTLY FITTED DURING ASSEMBLY FOLLOWING A BULK STRIP FOLLOWING A PROPELLER STRIKE	. METAL CONTAMINATION OF ENGINE.					1	L	7	1 	3O	3	O	 	A4PC    	E274	5	N	P910	 
2001040500278	20010405	00278	SO  	2001	4	5	AU010185         	1	20010308	G	8120	4091709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			1    							(AUS) RT ENGINE TURBOCHARGER FAULTY. LOSS OF ENGINE OIL (4LITRES).						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040500279	20010405	00279	NE  	2001	4	5	AU010186         	3	20010305	G	6111	RFC11MIRGADE	BLADE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	PROPELLER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			4860 							(AUS) PROPELLER BLADE NICKEL SHEATH CRACKED. CRACK LENGTH APPROXIMATELY 50.8MM (2IN) LOCATED ON THE FACE APPROXIMATELY 5	0.8MM (2IN) FROMTHE BLADE HEATER.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001040500280	20010405	00280	EA  	2001	4	5	AU010188         	1	20010311	G	5610	NP1393225	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					9910H4795					(AUS) CAPTAINS SIDE WINDOW OUTER PANE SHATTERED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500281	20010405	00281	CE  	2001	4	5	AU010189         	1	20010225	G	2750		WIRE            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP PRESELECT MICROSWITCH WIRE BROKEN.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001040500282	20010405	00282	SO  	2001	4	5	AU010190         	1	20010312	G	5210	41420002	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PAX DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP CABIN DOOR FORWARD HINGE FAILED DUE TO CORROSION INDUCED CRACKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001040500283	20010405	00283	EA  	2001	4	5	AU010191         	2	20010110	G	7250		ENGINE          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SKI JUMP SEVERELY CRACKED AND DISTORTED IN AREA AROUND NR 3 BEARING COVER. SOME PIECES OF THE EXHAUST CASIN	G HAVE COMPLETELY BROKEN AWAY CAUSING DAMAGE TO THE POWER TURBINE DISC AND BLADES. POWER TURBINE STATOR CRACKED THROUGH 	THE INNER BAND.				1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001040500284	20010405	00284		2001	4	5	AU010192         	4	20010312	G	3497		WIRE            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NAVIGATION UNIT	LOOSE           	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) NR 2 COMPASS SYSTEM FAULTY. INVESTIGATION FOUND A LOOSE WIRE TERMINAL AND NUT ON THE RT FLUX VALVE TERMINAL BLOCK 	LOCATED AT THE RH OUTER WING TRAILING EDGE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040500285	20010405	00285	SO  	2001	4	5	AU010193         	2	20010306	G	7314		PUMP            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	ENGINE	CONTAMINATED    	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE DRIVEN FUEL PUMP ADJUSTABLE ORIFICE CONTAMINATED WITH A SMALL PARTICLE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001040500286	20010405	00286	NE  	2001	4	5	AU010194         	2	20010310	G	7323	430121204	DRIVE SHAFT     			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					GOVERNOR	SHEARED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			2238 							(AUS) NR 1 ENGINE POWER TURBINE GOVERNOR DRIVE COUPLING SHEARED.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001040500287	20010405	00287	CE  	2001	4	5	AU010195         	1	20010314	G	2820	5892000017	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	FUEL DIST	LOOSE           	W				O	 	 	 	OTHER                   				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	LD	LANDING        	1			AU	S 			7522 							(AUS) RT ENGINE MAIN FUEL LINE FLARE NUT DISCONNECTED ON AFT SIDE OFFIREWALL. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001040500288	20010405	00288	NE  	2001	4	5	AU010196         	2	20010312	G	7323	8210161E	GOVERNOR        	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 ENGINE	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 					2248689					(AUS) NR 1 ENGINE OVERSPEED GOVERNOR FAULTY. THE GOVERNOR WAS A NEWLY FITTED ITEM WITH NO HOURS SINCE OVERHAUL.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040500289	20010405	00289	NM  	2001	4	5	AU010197         	1	20010226	G	4900	211734219	GCU             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					APU	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			18690							(AUS) APU GENERATOR CONTROL UNIT (GCU) FAULTY. INVESTIGATION FOUND THETOP COVER COOLING HOLES BLOCKED WITH DUST.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040500290	20010405	00290	NM  	2001	4	5	AU010198         	1	20010222	G	2840	BACJ40A204	JUMPER          			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL WIRING	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CROSSFEED MANIFOLDS IN CENTER WING TANK HAD MISSING BONDINGJUMPERS.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040500291	20010405	00291	NM  	2001	4	5	AU010199         	1	20010227	G	2910	65C268393061	LINE            			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYDRAULIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC B SYSTEM RESERVOIR TO STANDBY SYSTEM SUPPLY LINE  LEAKING. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040500292	20010405	00292	NM  	2001	4	5	AU010200         	1	20010223	G	2782	1267625	ACTUATOR        			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					SLATS	JAMMED          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			41940							(AUS) RH OUTBOARD LEADING EDGE FLAP DRIVE ACTUATOR JAMMED.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040500293	20010405	00293	NM  	2001	4	5	AU010201         	1	20010224	G	2530	GENM2585013	OVEN            			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					GALLEY	BURNED          	W				D	 	 	 	RETURN TO BLOCK         				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 			221  							(AUS) REAR GALLEY OVEN FAN MOTOR BURNT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040500294	20010405	00294	NM  	2001	4	5	AU010202         	1	20010223	G	3250		NUT             			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NLG STEERING	UNLOCKED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT NOSE GEAR STEERING CABLES DID NOT HAVE SPLIT PINS FITTED THROUGH CASTELLATED NUTS. BOTH NUTS WERE ONLY F	INGER TIGHT AND THE LT NUT WAS HELD BY ONLY TWO THREADS.PERSONNEL/MAINTENANCE ERROR.					2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001040500295	20010405	00295	NM  	2001	4	5	AU010203         	1	20010220	G	3320		LIGHT           			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					CABIN	CONTAMINATED    	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) CROSSOVER CEILING LIGHT LOCATED AT DOOR NR 5 RT HAD SEVERAL PIECES OF TISSUE STUFFED INTO THE LIGHT. THE TISSUE HA	D BEGUN TO SMOULDER. THE CROSSOVER LIGHT LENS AND ASSOCIATED METAL GRILL ASSEMBLY WAS MISSING.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040500296	20010405	00296		2001	4	5	AU010204         	4	20010220	G	2565	7A146913	RESERVOIR       			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ESCAPE SLIDE	DISCHARGED      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			5336 		GJ1033					(AUS) NO5 LH MAIN ENTRY DOOR EMERGENCY ESCAPE SLIDE INFLATION RESERVOIR PRESSURE BELOW LIMITS.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040500297	20010405	00297	NM  	2001	4	5	AU010205         	1	20010217	G	3320		SOCKET          			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					LIGHT	BURNED          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) SIDEWALL WASH LIGHT SOCKET LOCATED AT SEAT 25 HJK BURNED OUT AND ARCING DUE TO WATER CONTAMINATION. AREA AROUND SE	ATS FOUND TO BE SOAKING WET DUE TO BLOCKAGE OF RT SIDE UPPER DECK DOOR DRAINBLOCKAGE ALLOWING WATER LEAKAGE. AIRCRAFT HA	D BEEN ON THE GROUNDDURING A SEVERE RAIN STORM.				2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001040500298	20010405	00298	NM  	2001	4	5	AU010206         	1	20010219	G	2823	737M28500011	SHUTOFF VALVE   		737M2850001X	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL SELECTOR	FAILED          	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE FUEL SHUTOFF VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040500299	20010405	00299	NM  	2001	4	5	AU010207         	1	20010207	G	3244	B2700	TIRE            			BOEING	747   	747238B     	1384828	NM  										LT MLG	SEPARATED       	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 			2096 							(AUS) LT BODY MAIN LANDING GEAR FRONT INBOARD WHEEL TIRE (4F) HAD TREAD MISSING.						2	L	7	4 	4F			 	A20WE   					 
2001040500300	20010405	00300	NM  	2001	4	5	AU010208         	1	20010309	G	2910	AS11506K0264	HOSE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC SYSTEM	FAILED          	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 BRAKE HYDRAULIC HOSE FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040500301	20010405	00301	NM  	2001	4	5	AU010209         	1	20010305	G	2610		CONNECTOR       			BOEING	747   	747238B     	1384828	NM  										DETECTION SYSTEM	LOOSE           	W				K	 	 	 	NONE                    				P		 	NO WARNING INDICATION     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRE WARNING SYSTEM CARD A8 NOT SEATING CORRECTLY DUE TO REAR CONNECTOR ADRIFT FROM HOUSING.						2	L	7	4 	4F			 	A20WE   					 
2001040500302	20010405	00302		2001	4	5	AU010210         	4	20010306	G	2565	D31591475	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PAX DOOR	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			AU	S 			5661 							(AUS) NR 1 RT MAIN ENTRY DOOR ESCAPE SLIDE FAILED TO FULLY DEPLOY. INVESTIGATION FOUND THAT THE SLIDE EXHAUST VALVE WAS 	STUCK OPEN AND THE VALVE ELEMENT HAD BROKEN AWAY FROM THE VALVE BODY.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001040500303	20010405	00303	NM  	2001	4	5	AU010211         	1	20010304	G	2610		WARNING HORN    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DETECTION SYSTEM	INOPERATIVE     	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			AU	S 										(AUS) FIRE TEST WARNING BELL INOPERATIVE.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040500304	20010405	00304	EU  	2001	4	5	AU010213         	1	20010320	G	7712	SELOC29EC	INDICATOR       			FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  					ENGINE TORQUE	MALFUNCTIONED   	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 			3921 							(AUS) LT ENGINE TORQUE INDICATOR SUSPECT FAULTY.						2	H	7	2 	4T	4	T	RT	A817    	E20NE				 
2001040500305	20010405	00305		2001	4	5	AU010214         	4	20010223	G	6113	C19042	SPINNER         			GROB  	G115  	G115        	       	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	PROPELLER	DEBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNERS (7OFF) FOUND TO HAVE DISBONDED OR POOR BONDING BETWEEN THE INTERNAL FORWARD SUPPORT BULKHEAD AN	D THE SPINNER WALL. THE SPINNERS WERE NEW ASSEMBLIES BEING INSPECTED ON RECEIPT FROM THE MANUFACTURER.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2001040500306	20010405	00306	NE  	2001	4	5	AU010215         	2	20010316	G	8530	114650	CYLINDER        			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	SEPARATED       	W				O	 	 	 	OTHER                   				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			381  							(AUS) RT ENGINE NNR 1 CYLINDER UPPER BARREL AND HEAD SEPARATED. DAMAGE TO PISTON, RINGS, BARREL, INDUCTION TUBE AND PUSH	ROD TUBE. OIL FILTER METAL CONTAMINATION.					2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001040500307	20010405	00307	EU  	2001	4	5	AU010216         	1	20010312	G	7921		PLUG            	GARRTT      	7997        	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	ROTOL	R333	R333482F12  	GL  	DOOR ACTUATOR	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				E	N	 	VIBRATION/BUFFET          	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 	7921									(AUS) LT ENGINE OIL COOLER DOOR ACTUATOR PLUG CONTAMINATED.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	P61GL	 
2001040500308	20010405	00308	CE  	2001	4	5	AU010217         	1	20010313	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 			6006 							(AUS) RT MAIN LANDING GEAR ACTUATOR BODY CRACKED. FOUND FOLLOWING INSPECTION IAW SEB01-2.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001040500309	20010405	00309	NE  	2001	4	5	AU010218         	2	20010307	G	7321		CONNECTOR       	PWA         	7397        	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	EEC	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE TORQUE SIGNAL CONDITIONER AND ENGINE ELECTRONIC CONTROL (EEC) ELECTRICAL CONNECTORS CONTAMINATED WITH OI	L.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001040500310	20010405	00310	GL  	2001	4	5	AU010219         	3	20010306	G	6111	A22173QTY2	BLOCK           	HARTZL      	HCM2YR1BF   	BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	PROPELLER BLADE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1240 		EN273					(AUS) PROPELLER PITCH CHANGE BLOCKS CRACKED. PITCH CONTROL FORK WORNEXCESSIVELY. HUB PRELOAD PLATE DAMAGED DUE TO PREVIO	US FOREIGN OBJECT STRIKE.					1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P43GL	 
2001040500311	20010405	00311	SO  	2001	4	5	AU010220         	2	20010223	G	8520	629680	COLLAR          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	MISMANUFACTURED 	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT ENGINE CRANKSHAFT OIL TRANSFER COLLAR HAD INCORRECT CLEARANCE. THE MEASURED CLEARANCE WAS 0.0254MM (0.001IN) WI	TH THE CORRECTMANUFACTURERS LIMITS BEING 0.127MM TO 0.4572MM (0.005IN TO0.0018IN).					1	L	7	2 	3O	3	O	 	3A10    	E5CE				 
2001040500312	20010405	00312	CE  	2001	4	5	AU010221         	1	20010225	G	3260	ICH16	DOWNLOCK SWITCH 			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG	FAULTY          	W				O	 	 	 	OTHER                   				P		 	NO WARNING INDICATION     			DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001040500313	20010405	00313	EU  	2001	4	5	AU010222         	1	20010112	G	5330	11207	PLATE           			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER LT FUSELAGE PANEL 95B REBATE PLATE CONTAINED SEVERE EXFOLIATION CORROSION (LEVEL2).						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500314	20010405	00314		2001	4	5	AU010223         	4	20010304	G	6122	PCE21275	GOVERNOR        	PWA         	PT6A20      	PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 					PCE21275					(AUS) PROPELLER REVERSE GOVERNOR IDLER GEAR BEARING COLLAPSED. METALCONTAMINATION OF ENGINE.						1	H	7	1 	3O	3	T	 	7A15    	E4EA	6	C	P15EA	 
2001040500315	20010405	00315	EA  	2001	4	5	AU010224         	2	20010202	G	7261		RELIEF VALVE    			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE OIL PRESSURE RELIEF VALVE CONTAMINATED BY A PIECE OF O-RING SEAL.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001040500316	20010405	00316	EU  	2001	4	5	AU010226         	2	20010113	G	7250	2425	STATOR          			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					TURBINE SECTION	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FIRST STAGE TURBINE NOZZLE GUIDE VANE INNER RING CRACKED.CRACK RAN FOR APPROXIMATELY 270 DEGREES OF CIRCUMF	ERENCE.					2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001040500317	20010405	00317	CE  	2001	4	5	AU010227         	1	20010312	G	5321		SCREW           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C512   	GL  	FLOOR PANEL	UNAPPROVED PART 	W				K	 	 	 	NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT LENGTH SCREW FITTED TO PILOTS FLOOR PANEL. LONG SCREW CUT A GROOVE IN PIPE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001040500318	20010405	00318	EA  	2001	4	5	AU010228         	2	20010313	G	7314	AN9296J	CAP             	LYC         	O360A1F6    	GROB  	G115  	G115        	       	EU  	LYC   	O360  	O360A1F6    	41514	EA  					ENGINE FUEL PUMP	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRIC FUEL PUMP OUTLET T FITTING BLANKING CAP CONTAMINATED WITH SWARF. THE BLANKING CAPS ARE FITTED DURING MODI	FICATION IAW  EO E121-01 REV1.					1	L	7	1 	3O	3	O	NT	A57EU   	E286				 
2001040500319	20010405	00319	CE  	2001	4	5	AU010229         	1	20010320	G	3211	10581002376	FRAME           			BEECH 	76    	76          	1153005	CE  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR A FRAMES CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040500320	20010405	00320	WP  	2001	4	5	AU010230         	1	20010315	G	6420	C1281	HUB             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					TAIL ROTOR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR HUB CONTAINED STRESS CORROSION AND CRACKING FROM THE TEETER BEARING RACES.						1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001040500321	20010405	00321	CE  	2001	4	5	AU010232         	1	20010320	G	3211	10581002375	FRAME           			BEECH 	76    	76          	1153005	CE  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR A-FRAMES CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040500322	20010405	00322	CE  	2001	4	5	AU010233         	1	20010319	G	7810		EXHAUST PIPE    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST DUCT FAILED IN AREA AROUND NR 3 BEARING COVER SUPPORT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2001040500323	20010405	00323	CE  	2001	4	5	AU010234         	1	20010320	G	3211	10581002376	FRAME           			BEECH 	76    	76          	1153005	CE  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR A-FRAME CRACKED.						1	L	7	2 	3O			 	A29CE   					 
2001040500324	20010405	00324	NM  	2001	4	5	AU010235         	1	20010316	G	2752	734374D	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  										TE FLAPS	LACK OF LUBE    	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RH FLAP INBOARD ACTUATOR BALLSCREW NUT BADLY WORN. INVESTIGATION FOUND MISSING BALLS IN JACKSCREW AND SEVERE DAMAG	E TO THE FORCE LIMITER. SUSPECT CAUSED BY LACK OF LUBRICATION.					2	H	7	2 	4T			RT	A13NM   					 
2001040500325	20010405	00325	EU  	2001	4	5	AU010237         	1	20010303	G	2432		BATTERY         			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					E/E BAY	OVERHEATED      	W				O	 	 	 	OTHER                   				M	J	 	OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) AFT BATTERY OVERHEATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500326	20010405	00326	EU  	2001	4	5	AU010238         	1	20010223	G	2910		PIPE            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYDRAULIC SYSTEM	CHAFED          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC PIPES LOCATED IN LT WHEEL WELL RUBBING ON LANDING GEARDOOR PREVENTING REAR UPLOCK SWITCH FROM ACTIVATING	.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500327	20010405	00327	EU  	2001	4	5	AU010239         	1	20010222	G	2910		HYDRAULIC SYSTEM			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2	LOW             	W				K	 	 	 	NONE                    				K	J	 	FLUID LOSS                	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM LOW QUANTITY. INVESTIGATION COULD FIND NOEVIDENCE OF LEAKS. SUSPECT SYSTEM NOT REPLENISHED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500328	20010405	00328	EU  	2001	4	5	AU010240         	1	20010119	G	2612		FIRE LOOP       			AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					LT ENGINE	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LT ENGINE FIRE LOOP A FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001040500329	20010405	00329	EU  	2001	4	5	AU010241         	1	20010206	G	2131		CONTROLLER      			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					CABIN PRESSURE	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) CABIN PRESSURISATION SYSTEM FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500330	20010405	00330	EU  	2001	4	5	AU010242         	1	20010306	G	2913		PUMP            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYDRAULIC SYS	LEAKING         	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM ENGINE DRIVEN PUMP SILENCER LEAKING INTERNALLY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500331	20010405	00331	EU  	2001	4	5	AU010243         	1	20010226	G	5610		WINDOW          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					COCKPIT	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CAPTAINS SLIDING WINDOW STUCK OPEN. INVESTIGATION FOUND WORN TRACK AND UPPER ROLLER.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040900389	20010409	00389	SO  	2001	4	9	AU010245         	2	20010216	G	8530	682995	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O550  	IO550B      	 	SO  					ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			243  							(AUS) ENGINE CYLINDERS PNO 649358, LIFTERS PNO 646277 AND CAMSHAFT PNO649322A1 CONTAINED PITTING CORROSION. ENGINE HAS O	NLY 242.6 HOURS TOTAL TIME SINCE NEW.					1	L	7	1 	3O	3	O	 	3A15    	E3SO				 
2001040900390	20010409	00390	SO  	2001	4	9	AU010246         	2	20010301	G	8520		CONNECTING ROD  			CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	SEPARATED       	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			85   							(AUS) RT ENGINE NR 2 AND NR 4 CONNECTING ROD BIG ENDS FAILED. CRANKCASE HOLES AND MAGNETOS SEPARATED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001040900391	20010409	00391	CE  	2001	4	9	AU010247         	1	20010115	G	8120	C1650040604	SEAL            	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					TURBOCHARGER	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			183  							(AUS) LT ENGINE VAPC LEAKING OIL PAST PISTON DUE TO INTERNAL SEAL FAILURE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001040900392	20010409	00392	SW  	2001	4	9	AU010248         	1	20010321	G	5540	304566	STRUCTURE       			AIRTRC	AT802 	AT802A      	       	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	RUDDER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CRACKED AND SKIN DEFORMED IN UPPER AREA WHERE THE BALANCEHORN ATTACHES TO THE RUDDER STRUCTURE.						1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
2001040900393	20010409	00393	SW  	2001	4	9	AU010249         	1	20010319	G	7120	9388013	MOUNT           			AIRTRC	AT802 	AT802A      	       	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT SIDE ENGINE MOUNT RUBBER ISOLATION MOUNTS FAILED. ENGINE LOW ON LT SIDE CAUSING CHAFING OF THE FIRE SEALS ON TH	E BEARER.					1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL	 
2001040900394	20010409	00394	EA  	2001	4	9	AU010250         	2	20010323	G	8530	G4299	COLLET          	LYC         		BEECH 	65    	A658200     	1152805	CE  	LYC   	O480  	GSO480B1A6  	41529	EA  	HARTZL	HCB3Z	HCB3Z202    	GL  	LT ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 			20   							(AUS) LT ENGINE NR 6 CYLINDER VALVE COLLETS FAILED. INLET VALVE DROPPED. METAL CONTAMINATION OF OIL SYSTEM. OTHER COLLET	S INSPECTED HADSIGNS OF ABNORMAL WEAR. SUSPECT UNAPPROVED PARTS.					1	L	7	2 	3O	3	O	 	3A20    	E284	5	C	P907	 
2001040500332	20010405	00332	CE  	2001	4	5	AU010251         	1	20010322	G	2701	05600144	CONTROL COLUMN  			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	COCKPIT	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONTROL YOKE CONTAMINATED INTERNALLY WITH WATER. FOUND DURING INSPECTION IAW CESSNA SEB 01-3						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001040500333	20010405	00333	EA  	2001	4	5	AU010252         	2	20010312	G	7414		PIN             			BNORM 	BN2   	BN2A21      	1520221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	IMPULSE COUPLING	FAILED          	W				O	 	 	 	OTHER                   				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	LD	LANDING        	1			AU	S 										(AUS) RT ENGINE MAGNETO IMPULSE COUPLING PIN MIGRATED OUT, ALLOWING THE FLANGE SECURING PIN AND FLANGE  TO FAIL. LOSS OF	 ENGINE OIL.					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040500334	20010405	00334		2001	4	5	AU010253         	4	20010319	G	3416	28702501	ALTIMETER       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O		 	OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) ALTIMETER INTERNAL FAILURE.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001040500335	20010405	00335	NE  	2001	4	5	AU010254         	2	20010326	G	7321	6068T72P09	HMU             			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	FUEL CONTROL	FAULTY          	W				O	 	 	 	OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001040500336	20010405	00336	EA  	2001	4	5	AU010255         	2	20010313	G	7414	4370	MAGNETO         			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					RIGHT	FAILED          	W				O	 	 	 	OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAGNETO FAILED.						1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001040500337	20010405	00337	CE  	2001	4	5	AU010256         	1	20010313	G	5512		SKIN            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZONTAL STAB	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT HORIZONTAL STABILIZER LOWER SKINS CHAFED BY THE GAP SEAL STRIP / ANGLE AT THE FUSELAGE TO STABILISER JUN	CTION.REDUCTION IN SKIN THICKNESS FROM 0.635MM (0.025IN) TO 0.33MM(0.013IN).					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2001040500338	20010405	00338	EU  	2001	4	5	AU010257         	1	20010213	G	5711		SPAR            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT & RT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040500339	20010405	00339	EU  	2001	4	5	AU010258         	1	20010212	G	5711		SPAR            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					LT & RT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT LOWER SPAR CAPS CRACKED IN AREABETWEEN RIBS NR 13 AND NR 18. CORROSION ALSO FOUND O	N LOWER SKINS AT RIB BAYS NR 13 TO NR 18.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040500340	20010405	00340	EU  	2001	4	5	AU010259         	1	20010212	G	5730		SKIN            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SKIN CORRODED AT RIB BAYS NR 14 TO NR 16. RT WING LOWER SKIN CORRODED AT RIB BAYS NR 14 AND NR 15.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040500341	20010405	00341	NM  	2001	4	5	AU010260         	1	20010318	G	2897	W60000818R	WIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL SYSTEM	SHORTED         	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) FUEL SYSTEM CONTROL VALVE WIRE PNO W6400-008-18R LOCATED IN NR 4 STRUT KNEE CAP DISCONNECT PLUG D14300P CHAFED AND	 SHORT CIRCUITING TO GROUND.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001040500342	20010405	00342	NM  	2001	4	5	AU010261         	1	20010309	G	3242	26088127	BRAKE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					RT MLG	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			15104							(AUS) RT MAIN LANDING GEAR NR 7 BRAKE STATORS DELAMINATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040500343	20010405	00343	NM  	2001	4	5	AU010262         	1	20010318	G	3242	26088127	BRAKE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LT MLG	FAILED          	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			13318							(AUS) LT NR 4 MAIN WHEEL BRAKE ASSEMBLY ROTORS DISINTEGRATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001040500344	20010405	00344	EU  	2001	4	5	AU010263         	1	20010325	G	2160	7828602	CONTROL VALVE   			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	CABIN TEMP	SEIZED          	W				C	 	 	 	ABORTED TAKEOFF         				B	J	 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			16660							(AUS) DUAL TEMPERATURE CONTROL VALVE SEIZED IN OPEN POSITION.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001040500345	20010405	00345	NE  	2001	4	5	AU010264         	2	20010323	G	7321	6078T55P18	FUEL CONTROL    	GE          		CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE FUEL CONTROL UNIT LEAKING FROM THE AREA OF THE THROTTLE CONTROL INPUT ARM.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500346	20010405	00346	GL  	2001	4	5	AU010265         	3	20010325	G	6111	660715698	EROSION SHIELD  	ROTOL       	6607152727  	FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	PROPELLER BLADE	SEPARATED       	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 			1779 		F50470					(AUS) PROPELLER BLADE EROSION SHIELD SEPARATED.						2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG	 
2001040500347	20010405	00347	EU  	2001	4	5	AU010266         	2	20010324	G	7321	B12597	AMPLIFIER       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUEL CONTROL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			7419 							(AUS) NR 1 ENGINE POWER FLUCTUATIONS. ENGINE CONTROL AMPLIFIER AND TEMPERATURE CONTROL ACTUATOR CHANGED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500348	20010405	00348	EU  	2001	4	5	AU010267         	1	20010324	G	2913		COUPLING        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYDRAULIC PUMP	CRACKED         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 HYDRAULIC SYSTEM HYDRAULIC PUMP PRESSURE LINE ELBOW COUPLING THREADED SECTION CRACKED AND LEAKING. LOSS OF HY	DRAULIC FLUID.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500349	20010405	00349	SW  	2001	4	5	AU010268         	1	20010320	G	6210	206015001117AS	BLADE           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE CORRODED IN AREA BETWEEN PAINT AND LEADING EDGESTRIP ON UNDERSIDE OF BLADE. CORROSION DEPTH APPRO	XIMATELY 1.52MM (0.060IN). FOUND BEFORE FITMENT.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001040500350	20010405	00350	EU  	2001	4	5	AU010269         	1	20010309	G	5270		WARNING SYSTEM  			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PAX DOOR	INTERMITTENT    	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) PASSENGER DOOR WARNING LIGHT INTERMITTENT IN OPERATION. INVESTIGATION COULD FIND NO FAULT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500351	20010405	00351		2001	4	5	AU010270         	4	20010310	G	3442	20412170413	RADAR           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					WEATHER	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 			780  		2673					(AUS) RADAR RECEIVE/TRANSMIT UNIT FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500352	20010405	00352		2001	4	5	AU010271         	4	20010312	G	2212	637SUE1	WARNING SYSTEM  			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ALTITUDE CONTROL	FAILED          	W				A	 	 	 	UNSCHED LANDING         				P	 	 	NO WARNING INDICATION     			CR	CRUISE         	1			AU	S 										(AUS) ALTITUDE ALERT SYSTEM FAILED. ALTITUDE PRESELECT COUPLER CHANGED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500353	20010405	00353	EU  	2001	4	5	AU010272         	2	20010314	G	7200	RB18355515H	ENGINE          			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 1	VIBRATES        	W				C	 	 	 	ABORTED TAKEOFF         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE VIBRATION AND NOISE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001040500354	20010405	00354	CE  	2001	4	5	AU010273         	1	20010316	G	3260		FASTENER        			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	MLG UPLOCK	FAILED          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR UPLOCK ASSEMBLY HI-LOK FASTENERS FAILED. BRACKETS TORN AWAY FROM SPAR BOX.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001040500355	20010405	00355	EU  	2001	4	5	AU010274         	1	20010321	G	2720	NB45961	LEVER           			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RUDDER CONTROL S	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CONTROL RT IDLER LEVER LOOSE AND CATCHING ON FUSELAGE FRAME OPENING.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001040500356	20010405	00356		2001	4	5	AU010276         	4	20010317	G	6122	1680640	PICKUP          	WOODWARD    	89741016    	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	PROP GOVERNOR	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 					2330240					(AUS) LT ENGINE GOVERNOR MAGNETIC PICKUP (MONOPOLE) OUTPUT VOLTAGEUNSTABLE.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001040500357	20010405	00357	GL  	2001	4	5	AU010277         	3	20010320	G	6110	991996	SPACER          	MCAULY      	B3DF36C527  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	MCAULY	3DF36C	B3DF36C526  	GL  	PROPELLER ASSY	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			597  		991996					(AUS) RT PROPELLER SPACER INCORRECTLY FITTED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	 	 
2001050700400	20010507	00400	EU  	2001	5	7	AU010278         	1	20010303	G	2550	A25LT	CARGO HOOK      			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					CARGO AREA	FAULTY          	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 										(AUS) CARGO HOOK FAILED AND RELEASED LOAD. INVESTIGATION FOUND SCREWLOCATED ON THE LOWER LH SIDE OF THE COVER WAS INTERF	ERING WITHTHE RETURN OF THE LEVER AND LATCH ASSEMBLY RESULTING IN INTERMITTENT OPERATION OF THE LATCH. EXCESSIVE PLAY IN	 LINK AND PINS CONTRIBUTED TO THE PROBLEM.				1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001051000071	20010510	00071	EA  	2001	5	10	AU010279         	2	20010326	G	8520	LW12596	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	BROKEN          	W				O	 	 	 	OTHER                   				E	F	K	VIBRATION/BUFFET          	FLT CONT AFFECTED         	FLUID LOSS                	DE	DESCENT        	1			AU	S 										(AUS) LT ENGINE CONNECTING ROD BOLT FAILED. ENGINE SUMP HOLED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001050700401	20010507	00401	SW  	2001	5	7	AU010281         	1	20010322	G	6220	471202527	GRIP            			BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  					MAIN ROTOR HEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			577  		NC5779					(AUS) MAIN ROTOR GRIP CRACKED IN SECOND, THIRD AND FOURTH THREADS. FOUND DURING EDDY CURRENT INSPECTION. X-RAY INSPECTIO	N RESULTSWERE INCONCLUSIVE.					1	G	7	1 	3O	3	O	 	2H3     	E279				 
2001051000072	20010510	00072	SW  	2001	5	10	AU010282         	1	20010128	G	7931	2719153003	TRANSDUCER      			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENGINE OIL PRESS	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL PRESSURE TRANSDUCER FAILED FOLLOWING FITMENT.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001051000073	20010510	00073	SW  	2001	5	10	AU010284         	1	20010314	G	2121	071040370001	COOLING FAN     			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	AIR DISTRIBUTION	FAILED          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) AVIONICS COOLING FAN FAILED. CIRCUIT BREAKER POPPED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001051100004	20010511	00004	EU  	2001	5	11	AU010285         	1	20010329	G	2910	AE7064588	HOSE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HYDRAULIC SYSTEM	RUPTURED        	W				C	 	 	 	ABORTED TAKEOFF         				K	J	 	FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR FLEXIBLE DOWN LINE RUPTURED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001051100005	20010511	00005	SO  	2001	5	11	AU010286         	1	20010205	G	2436	VSF7203S	REGULATOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  					DC SYSTEM	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) REGULATOR OVERVOLTAGE. CHARGING SYSTEM TRIPPED.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001051100006	20010511	00006		2001	5	11	AU010287         	4	20010325	G	6122	8210004	GOVERNOR        	HARTZL      	HCB3TN3     	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP GOVERNOR	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 					103231ST					(AUS) RT PROPELLER GOVERNOR FAULTY.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001051100007	20010511	00007	SO  	2001	5	11	AU010288         	1	20010325	G	2750		CONTROLLER      			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	TE FLAPS	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) OUTBOARD FLAP DISAGREEMENT WARNING. INSPECTION COULD FIND NOFAULTS.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001051100008	20010511	00008	NE  	2001	5	11	AU010289         	2	20010312	G	7250	3053556220	BEARING         	GE          	CFM565A1    	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					TURBINE SECTION	SPALLED         	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NR 2 ENGINE NR 4 BEARING OUTER RACE SEVERELY SPALLED.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001051100009	20010511	00009	EU  	2001	5	11	AU010290         	1	20010328	G	6123	HTE123542A	PRESSURE SWITCH 	HARTZL      	HCA6A3      	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	PROP FEATHER	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				J		 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) LH PROPELLER AUTOFEATHER SYSTEM PRESSURE SWITCH FAULTY.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001051100010	20010511	00010	CE  	2001	5	11	AU010291         	1	20010323	G	5740	0811351	FITTING         	CESSNA      	402C        	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 					4020625					(AUS) WING SPAR CAP FITTING CONTAINED SEVERE EXFOLIATION CORROSION ON THE FORWARD FACE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001051100011	20010511	00011	NE  	2001	5	11	AU010292         	2	20010403	G	7310	230350901	PIPE            	LYC         	ALF502R3A   	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					ENGINE FUEL DIST	FRACTURED       	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FUEL PIPE FRACTURED. FUEL LEAKING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001051100012	20010511	00012	NM  	2001	5	11	AU010293         	1	20010331	G	3244	A21580664	TIRE            		161U00011   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211*      	54555	NE  					MLG	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 					A21580664					(AUS) RH BODY LANDING GEAR OUTBOARD REAR NR 6R TIRE SHREDDED. DAMAGE CAUSED TO BODY FAIRING PANELS 194BR, 194CR, 194GR, 	RT WING LANDING GEAR DOOR AND HINGE, NR 5R WHEEL, RH BODY LANDING GEAR TRUCK POSITIONING ACTUATOR HYDRAULIC LINE, NR 13 	AND NR 14 BRAKELINES. NUMEROUS FUSELAGE DENTS ALSO EVIDENT.				2	L	7	4 	4F	4	F	RT	A20WE   	A12EU				 
2001051100013	20010511	00013	NM  	2001	5	11	AU010294         	1	20010401	G	2434	727810C	GENERATOR       			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					APU	FAILED          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			52   							(AUS) APU GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001051100014	20010511	00014	NM  	2001	5	11	AU010295         	1	20010403	G	5410		FAIRING         			BOEING	747   	747400      	       	NM  	GE    	CF6   	CF680C2*    	 	GL  					NACELLE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE RT COLD STREAM C DUCT MISSING UPPER INBOARD DUCT TO  STRUT FILLET FAIRING.						2	L	7	4 	4F	4	F	RT	A20WE   	E23EA				 
2001051100015	20010511	00015	EU  	2001	5	11	AU010296         	1	20010318	G	7712	1090729245	TRANSMITTER     			AGUSTA	A109  	A109A       	0260109	EU  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) ENGINE TORQUE TRANSMITTER FAULTY.						1	G	7	2 	3U	3	U	 	H7EU    	E4CE				 
2001051100016	20010511	00016	NM  	2001	5	11	AU010297         	1	20010406	G	5742		FITTING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING PYLON ATTACHMENT FITTING OUTBOARD LUG CRACKED. CRACK PENETRATES THE FULL THICKNESS OF THE LUG AND EXTENDSA	PPROXIMATELY 25.4MM (1IN) ALONG THE INBOARD FACE AND APPROXIMATELY 12.7MM (0.5IN) ALONG THE OUTBOARD FACE. FOUND USING E	DDY CURRENT INSPECTION IAW BSB 767-57A0070 AND ERB76-57-40-18.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051100017	20010511	00017	NM  	2001	5	11	AU010298         	1	20010409	G	5742		FITTING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING PYLON ATTACHMENT FITTING OUTBOARD LUG CRACKED. FOUND DURING VISUAL INSPECTION IAW ER B76-57-40-19.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051100018	20010511	00018	GL  	2001	5	11	AU010299         	3	20010320	G	6111	C4451	FERRULE         	MCAULY      	3AF32C75    	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	3AF32C	3AF32C75    	GL  	PROPELLER BLADE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1500 							(AUS) PROPELLER BLADE FERRULE CRACKED AROUND BEARING SHELF ORIGINATINGFROM A PREVIOUSLY DRILLED ACTUATING PIN HOLE. CRAC	K LENGTH 50.8MM (2IN).					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P22EA	 
2001051100019	20010511	00019	SO  	2001	5	11	AU010300         	1	20010326	G	2752	3203001007	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	TE FLAPS	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) LT OUTBOARD FLAP ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001051100020	20010511	00020	NM  	2001	5	11	AU010302         	1	20010326	G	5511		SPAR            			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					HORIZONTAL STAB	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT HORIZONTAL STABILIZER REAR SPAR UPPER CHORD CORRODED AT STN 267.50. LT HORIZONTAL STABILISER REAR SPAR UPPER CH	ORD CORRODED AT STN 258.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051100021	20010511	00021	CE  	2001	5	11	AU010303         	1	20010331	G	3260	JE6	ACTUATOR        			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR	BROKEN          	W				O	 	 	 	OTHER                   				N		 	FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR MICROSWITCH ACTUATOR FAILED.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2001051100022	20010511	00022	CE  	2001	5	11	AU010304         	1	20010330	G	2434	ALT9422	ALTERNATOR      			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC SYSTEM	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			46   							(AUS) ENGINE DRIVEN ALTERNATOR SUSPECT REAR BEARING FAILED. DAMAGE TO ENGINE CRANKSHAFT DRIVE GEAR.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001051100023	20010511	00023	NM  	2001	5	11	AU010305         	1	20010403	G	1100	ASM321032A	PLACARD         			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					MLG	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TIRE INFLATION PLACARD MISSING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051100024	20010511	00024	NM  	2001	5	11	AU010306         	1	20010404	G	7997		WIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					NR 3 ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE OIL PRESSURE INDICATION FAILED. INVESTIGATION FOUNDA SHORT CIRCUIT IN THE WING ROOT/ENGINE DISCONNECT 	DUE TO WIRECHAFING AT ACCESS PANEL 611BB.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001051100025	20010511	00025	NM  	2001	5	11	AU010308         	1	20010404	G	2910	BACF8A06EN0700B	HOSE            			BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					HYDRAULIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR TILT ACTUATOR HYDRAULIC HOSE LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001051100026	20010511	00026	NM  	2001	5	11	AU010309         	1	20010404	G	2910	AS11506K0280	HOSE            			BOEING	767   	767330      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR FLEXIBLE BRAIDED BRAKE HOSE HOLED ANDLEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001051100027	20010511	00027	EU  	2001	5	11	AU010310         	1	20010314	G	2920	MS24142D1	RELAY           			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HYDRAULIC SYSTEM	FAULTY          	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) AUXILIARY HYDRAULIC CONTROL RELAY FAULTY.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001051100028	20010511	00028	NM  	2001	5	11	AU010311         	1	20010324	G	5230	6941730	BUNGEE CORD     			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					CARGO DOOR	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) AFT CARGO DOOR RELEASE LANYARD HANDLE JAMMED UNDER DOOR SEAL. INVESTIGATION FOUND THE LANYARD BUNGEE CORD BROKEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051100029	20010511	00029	SO  	2001	5	11	AU010312         	1	20010330	G	5740	4511500	FITTING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT UPPER MAIN SPAR ATTACHMENT FITTINGS CORRODED ANDPARTIALLY EXFOLIATED. WHEN THE FITTINGS WERE REMOVED THE	 ATTACHMENT RIVETS WERE FOUND TO BE SHEARED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051100030	20010511	00030	SO  	2001	5	11	AU010313         	1	20010330	G	5740	4511500	FITTING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT UPPER MAIN SPAR ATTACHMENT FITTINGS CORRODED ANDPARTIALLY EXFOLIATED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051100031	20010511	00031	SO  	2001	5	11	AU010314         	1	20010330	G	5720		BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD SPAR ATTACHMENT BRACKET LOCATED AT STN 104.6 CRACKED ONFORWARD AND REAR SIDES.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051100032	20010511	00032	SO  	2001	5	11	AU010315         	1	20010330	G	5720		BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	WING SPAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD SPAR ATTACHMENT BRACKET LOCATED AT STN104.6 CRACKED ONFORWARD AND REAR SIDES.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051100033	20010511	00033	CE  	2001	5	11	AU010316         	1	20010319	G	2434	902015	BEARING         	PRESTOLITE  	ALU9405     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC GENERATOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					4E000070					(AUS) RT ENGINE ALTERNATOR BEARING FAILED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001051100034	20010511	00034	SO  	2001	5	11	AU010317         	1	20010314	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR INBOARD DOOR FORWARD HINGE CRACKED. FOUNDDURING INSPECTION IAW AD/PA31/93 AMDT1.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051100035	20010511	00035	SO  	2001	5	11	AU010319         	2	20010330	G	8530		VALVE GUIDE     			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 AND NR 6 CYLINDER EXHAUST VALVE GUIDES WORN.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001051100036	20010511	00036	NM  	2001	5	11	AU010320         	1	20010409	G	7910		OIL SYSTEM      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE	LOW             	W				C	 	 	 	ABORTED TAKEOFF         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NO1 ENGINE OIL LEVEL LOW. SUSPECT OIL LEVEL HAD NOT BEEN TOPPED UP DURING PREFLIGHT INSPECTION. PERSONNEL/MAINTENA	NCE ERROR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051100037	20010511	00037	NE  	2001	5	11	AU010321         	2	20010410	G	7320	226332003	PIPE            	LYC         	ALF502R3A   	BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					FUEL CONTROL	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) NO3 ENGINE P3 SENSE LINE TO FCU LOOSE. THE AIRCRAFT HAD A NO3 ENGINE AND FCU CHANGED THE PREVIOUS DAY. PERSONNEL/M	AINTENANCEERROR.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001051100038	20010511	00038	NM  	2001	5	11	AU010322         	1	20010410	G	5742		MOUNT           			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING FITTING OUTBOARD LUG CRACKED DIAGONALLY ACROSS THE UPPERFLANGE FACE THROUGH THE LUG FILLET RADIUS. THE CRA	CK WAS FOUNDVISUALLY AND CONFIRMED USING NDI. FOUND DURING INSPECTION IAW ERB76-57-40-19.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051100039	20010511	00039	NM  	2001	5	11	AU010323         	1	20010409	G	5742		FITTING         			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING FITTING OUTBOARD LUG CRACKED AROUND THE INBOARD AFT CORNER OF THE LUG APPROXIMATELY 10MM (0.393IN) FORWARD	AND 5MM (0.196IN) OUTBOARD. CRACK CONFIRMED USING NDI. FOUND DURING INSPECTION IAW ER B76-57-40-18.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051100040	20010511	00040	SO  	2001	5	11	AU010324         	1	20010317	G	5280		DOOR            			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR	DISCONNECTED    	W				C	 	 	 	ABORTED TAKEOFF         				D	 	 	INFLIGHT SEPARATION       			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR DOORS DISCONNECTED ON TAKEOFF PREVENTING NOSE LANDING GEAR FROM RETRACTING. SUSPECT DOORS INCORR	ECTLY ATTACHED. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001051100041	20010511	00041	CE  	2001	5	11	AU010325         	1	20010326	G	3230	57412026	UPLOCK          			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LANDING GEAR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR UPLOCK HOOK BROKEN. HOOK WAS AN OLD TYPE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001051100042	20010511	00042	CE  	2001	5	11	AU010326         	1	20010410	G	3230	45825080	DRAG BRACE      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LANDING GEAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR AFT DRAG BRACE CRACKED FROM SEALING RIVET.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001051500001	20010515	00001	GL  	2001	5	15	AU010327         	1	20010320	G	2701	LS52RS	BEARING         			PAC   	CT4   	CT4A        	05623UC	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	CONTROL COLUMN	WORN            	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RT CONTROL COLUMN TORQUE TUBE BEARING WORN.						1	Q	7	1 	3I	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001051500002	20010515	00002	CE  	2001	5	15	AU010328         	1	20010329	G	2434	ALT9422	ALTERNATOR      			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	DC SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RT ALTERNATOR DISINTEGRATED. SEVERE INTERNAL DAMAGE. SUSPECTCAUSED BY BEARING FAILURE.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001051500003	20010515	00003	NM  	2001	5	15	AU010329         	1	20010407	G	5710		DRAIN VALVE     			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					WING	CLOGGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DRAINS LOCATED IN WING CENTRE SECTION AFT CAVITY AT BS 1241 WERE BLOCKED BY FOREIGN MATERIALS WITH EIGHT TO TEN LI	TRES OF WATER PRESENT. TIDE MARKS ALSO PRESENT ON SURROUNDING STRUCTURE INDICATING EVIDENCE OF GREATER QUANTITIES OF WAT	ER RETENTION.				2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001051500004	20010515	00004	NM  	2001	5	15	AU010331         	1	20010413	G	3520	S417T40127	GENERATOR       			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					PAX OXYGEN	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OXYGEN GENERATORS LOCATED ABOVE SEATS 9LT, 11LT, 13LT, 15LT AND 17LT HAD THE RELEASE PIN LOCATED IN THE SAFETY PIN	 HOLE.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051500005	20010515	00005	NM  	2001	5	15	AU010332         	1	20010407	G	2424	734284F	GCU             			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					AC REGULATOR	FAULTY          	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			AU	S 			21473							(AUS) RH GENERATOR CONTROL UNIT (GCU) FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001051500006	20010515	00006	SO  	2001	5	15	AU010333         	2	20010406	G	8530	539647	PISTON PIN      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			343  							(AUS) DURING PRE-PURCHASE INSPECTION IT WAS FOUND THAT THE LOG BOOK ENTRY INDICATED THAT ONLY ONE NEW PISTON PIN HAD BEE	N FITTED ANDTHAT THE OTHER FIVE HAD BEEN INSPECTED BY MAGNETIC PARTICLE INSPECTION AND REFITTED. AD/CON/62 AND TCM SB M8	7-11 REV 2STATES THAT NEW PISTON PINS BE FITTED. OVERHAUL FACILITY STATES THAT ALL OF THE PISTON PINS WERE REPLACED. AN 	ANOMALY EXISTS BETWEEN THE LOG BOOK AND THE OVERHAUL FACILITY.			1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001051500007	20010515	00007	NM  	2001	5	15	AU010334         	1	20010315	G	5230	1U1168	ACTUATOR        			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					CARGO DOOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			495  							(AUS) MAIN CARGO DOOR REAR ACTUATOR EYE END BEARING MIGRATED RESULTING IN DISTORTION OF THE EYE END. MINOR DAMAGE TO RET	RACTION ARM.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001051500008	20010515	00008	NM  	2001	5	15	AU010335         	1	20010405	G	2910	BACH30B01H326R	HOSE            			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					HYDRAULIC SYSTEM	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT WING MAIN LANDING GEAR DOOR ACTUATOR FLEXIBLE HOSE LEAKING.LOSS OF HYDRAULIC FLUID. NR 4 ENGINE DRIVEN HYDRAULI	C PUMP CHANGED DUE TO OPERATION WITH LOW HYDRAULIC QUANTITY.					2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001051500009	20010515	00009	NM  	2001	5	15	AU010336         	1	20010409	G	2750		CONTROLLER      			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					TE FLAPS	FAULTY          	W				O	 	 	 	OTHER                   				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			AU	S 										(AUS) DURING APPROACH FLAPS RAN TO 20 DEGREES ON SELECTION OF 25DEGREES. SELECTION TO 30 DEGREES SAW NO FURTHER MOVEMENT	. INVESTIGATION COULD FIND NO FAULTS. SUSPECT CAUSED BY MOISTURE IN FLAP DRIVES.					2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051500010	20010515	00010	WP  	2001	5	15	AU010337         	1	20010108	G	5730	3787	SKIN            		DH82A       	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					WINGS	PEELING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			73   							(AUS) FABRIC COVERING ON WINGS AND TAIL SURFACES HAD PAINT PEELING DUETO PROOFING NOT PENETRATING FABRIC. ALL RIB STITCH	ING TAPES LOOSE AND NOT ATTACHED TO FABRIC.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001051500011	20010515	00011	WP  	2001	5	15	AU010338         	1	20010108	G	5711	H347377	SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			73   							(AUS) LT UPPER WING MAIN SPAR CRACKED IN SEVERAL PLACES. FURTHER INSPECTION FOLLOWING FABRIC REMOVAL FOUND THAT THE SPAR	 HAD BEEN DRESSED WITH FILLER AND PAINT UNDER WHICH MORE CRACKS WERE FOUND.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001051500012	20010515	00012	WP  	2001	5	15	AU010339         	1	20010108	G	5521		SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			73   							(AUS) LT ELEVATOR SPAR CRACKED. FOLLOWING FABRIC REMOVAL THE SPAR WAS FOUND TO BE CRACKED IN SEVERAL PLACES INCLUDING AR	EAS WHICH HAD BEEN BOUND WITH FABRIC.					1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001051500013	20010515	00013	EU  	2001	5	15	AU010340         	1	20010406	G	2400		SPLICE          			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ELECTRICAL POWER	BURNED          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) APU GENERATOR IN LINE SPLICE LOCATED IN THE FORWARD CARGO COMPARTMENT ROOF LINING OVERHEATED AND BURNED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001051500014	20010515	00014	NM  	2001	5	15	AU010341         	1	20010409	G	3230	65B0154020	ACTUATOR        			BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					MLG	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			8931 							(AUS) RT WING LANDING GEAR DOWNLOCK ACTUATOR SUFFERED A CATASTROPHIC FAILURE. THE FAILURE OCCURRED DURING THE FIRST OPER	ATION OF THE ACTUATOR WHICH HAD JUST BEEN FITTED FOLLOWING MAINTENANCE.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001051500015	20010515	00015	NE  	2001	5	15	AU010342         	2	20010407	G	7200		ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4	FLAMED OUT      	W				O	 	 	 	OTHER                   				E	X	 	VIBRATION/BUFFET          	ENGINE FLAMEOUT           		DE	DESCENT        	1			AU	S 										(AUS) NR 4 ENGINE FLAMEOUT. LIMITED INFORMATION PROVIDED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001051500016	20010515	00016	NE  	2001	5	15	AU010343         	2	20010416	G	7261	ST307607	KEY             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 1 ENGINE	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE AC GENERATOR OIL SYSTEM SCAVENGE PUMP WOODRUFF KEY NOT FITTED. KEY WAS FOUND LOOSE IN THE BOTTOM OF TH	E PUMP HOUSING.SUSPECT KEY FELL OUT DURING ASSEMBLY WITHOUT BEING NOTICED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500017	20010515	00017	EU  	2001	5	15	AU010344         	1	20010410	G	3234		MOTOR           			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR MOTOR FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001051500018	20010515	00018	EU  	2001	5	15	AU010345         	1	20010416	G	2421		IDG             			BAG   	BAE146	BAE146200A  	1500266	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					AC GENERATOR	FAILED          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) INTEGRATED DRIVE GENERATOR (IDG) FAILED.						2	H	7	4 	4F	4	F	RT	A49EU   	E29NE				 
2001051500019	20010515	00019	NM  	2001	5	15	AU010346         	1	20010412	G	2133		MOTOR           			BOEING	737   	737377      	       	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					OUTFLOW VALVE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) AIRCRAFT PRESSURISATION SYSTEM OUTFLOW VALVE ELECTRIC MOTOR FAILED. OUTFLOW VALVE FAILED TO OPEN.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2001051500020	20010515	00020	SO  	2001	5	15	AU010347         	2	20010407	G	8530		ROCKER BOSS     			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ENGINE	CRACKED         	W				C	 	 	 	ABORTED TAKEOFF         				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE CYLINDER ROCKER HATS (2OFF) CRACKED AT PUSHROD END. EVIDENCE OF ROCKER HAT CONTACT ON THREE OTHER CYLINDERS	.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P25EA	 
2001051500021	20010515	00021	NM  	2001	5	15	AU010348         	1	20010417	G	2910	AS4624J0300SS	HOSE            			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					HYDRAULIC SYSTEM	LEAKING         	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR CENTER SYSTEM TILT RETURN HOSE LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001051500022	20010515	00022	NM  	2001	5	15	AU010349         	1	20010414	G	2910		HOSE            			BOEING	767   	767330      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYSTEM	SPLIT           	W				K	 	 	 	NONE                    				K		 	FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLINE PRESSURE HOSE SPLIT.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001051500023	20010515	00023	NE  	2001	5	15	AU010350         	2	20010318	G	7397		WIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL CONTROL	WORN            	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) NR 4 ENGINE FUEL SYSTEM WIRE CHAFED AND SHORT CIRCUITING. WIRE W6400-008-18R WAS LOCATED IN NR 4 STRUT KNEECAP DIS	CONNECT PLUGD14300P.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001051500024	20010515	00024		2001	5	15	AU010351         	4	20010409	G	2565	101651303	SLIDE           			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					ESCAPE SLIDE	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ESCAPE SLIDE FITTED TO DOOR LT 1 INCORRECTLY FITTED FOLLOWINGHEAVY MAINTENANCE. INSPECTION FOUND THAT THE SLIDE BA	R WAS IN THE STOWED (TRANSPORT) POSITION AND WAS NOT CONNECTED TO THE GIRT BAR. FURTHER INVESTIGATION FOUND THAT THE ESC	APE SLIDES ONTHE  OTHER THREE DORS (LH2, RH1 AND RH2) WERE SIMILARLY INCORRECTLY  FITTED. PERSONNEL/MAINTENANCE ERROR.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051500025	20010515	00025	CE  	2001	5	15	AU010352         	1	20010409	G	2710	35521189	CONTROL CABLE   			BEECH 	35    	S35         	1151532	CE  	CONT  	O520  	IO520B      	17032	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	AILERON CONTROL	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) AILERON THREADED CABLE AND FITTING SEPARATED APPROXIMATELY MIDWAY BETWEEN THE THREADED END AND THE SWAGED NUT.						1	L	7	1 	3O	3	O	 	3A15    	E5CE	5	C	P25EA	 
2001051500026	20010515	00026	EA  	2001	5	15	AU010353         	2	20010413	G	8520	L2363440A	GEAR            			BNORM 	BN2   	BN2A8       	1520209	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE CRANK	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E		 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) CRANKSHAFT DRIVE GEAR FAILED.						1	H	7	2 	3O	3	O	 	A17EU   	E295	5	C	P920	 
2001051500027	20010515	00027	NM  	2001	5	15	AU010354         	1	20010405	G	5320		WEB             			BOEING	747   	747338      	       	NM  										FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT VERTICAL BEAM WEB OF NOSE WHEEL STRUCTURE CRACKED FROM INSULATION BLANKET STUD HOLE AT BS 320. FOUND DURING INS	PECTION IAW EI 747-053-0041 REV5.					2	L	7	2 	4F			RT	A20WE   					 
2001051500028	20010515	00028		2001	5	15	AU010355         	4	20010417	G	2565	61621469	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PAX DOOR	MISINSTALLED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			875  							(AUS) MAIN ENTRY DOOR ESCAPE SLIDE SAFETY PIN INSTALLED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001051500029	20010515	00029	NM  	2001	5	15	AU010356         	1	20010417	G	2752	734374D	ACTUATOR        			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP ACTUATORS (3OFF) HAD EXCESSIVE BACKLASH.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500030	20010515	00030	NM  	2001	5	15	AU010357         	1	20010417	G	2752	734374D	ACTUATOR        			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP ACTUATORS (2OFF) HAD EXCESSIVE BACKLASH.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500031	20010515	00031	NM  	2001	5	15	AU010358         	1	20010417	G	2752	734374D	ACTUATOR        			DHAV  	DHC8  	DHC8315     	2809010	NM  										TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP ACTUATORS (6OFF) HAD EXCESSIVE BACKLASH.						2	H	7	2 	4T			RT	A13NM   					 
2001051500032	20010515	00032	NM  	2001	5	15	AU010359         	1	20010417	G	2752	734374D	ACTUATOR        			DHAV  	DHC8  	DHC8*       	       	NM  										TE FLAPS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TRAILING EDGE FLAP ACTUATORS (6OFF) HAD EXCESSIVE BACKLASH.						2	H	7	2 	4T			RT	A13NM   					 
2001051500033	20010515	00033	SO  	2001	5	15	AU010360         	1	20010419	G	5280	4752932	HINGE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR INBOARD DOOR FORWARD HINGE ARM CRACKED ONINNER RADIUS. FOUND DURING DYE PENETRANT INSPECTION 	IAW PIPER MSB 682.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051500034	20010515	00034		2001	5	15	AU010361         	4	20010417	G	2565	D31591475	SLIDE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					PAX DOOR	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			8870 							(AUS) MAIN ENTRY DOOR ESCAPE SLIDE FAILED TO INFLATE DUE TO DAMAGE TO THE ASPIRATOR FLAPPER VALVE SUPPORT BRIDGE. INVEST	IGATION FOUND THE BRIDGE TO BE LOOSE AND TWISTED PREVENTING THE FLAPPER VALVE HALVES FROM SEATING.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001051500035	20010515	00035	EU  	2001	5	15	AU010362         	1	20010331	G	2130	K1813	RELAY           			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					PRESSURE CONTROL	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) PRESSURISATION SYSTEM FAULTY. SUSPECT CAUSED BY HIGH RESISTANCE ACROSS CONTACTS IN RELAYS K1813, K1261, K1819 AND 	K1821 IN THEGROUND/FLIGHT RELAY BOX.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001051500036	20010515	00036	CE  	2001	5	15	AU010363         	1	20010412	G	3244	22X775X10X10	TIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT MLG	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			119  							(AUS) LT MAIN WHEEL TYRE CONTAINED A SLOW LEAK FROM ONE OF THE SIDEWALL VENT HOLES.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001051500037	20010515	00037	SO  	2001	5	15	AU010364         	2	20010410	G	8520	632043	CONNECTING ROD  	CONT        	GTSIO510M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			1598 		272103R					(AUS) NR6 CONNECTING ROD RUBBING ON COUNTERWEIGHT. ROD WAS OUT OF ALIGNMENT WITH THE BIG END AND SMALL END AXIS. INSPECT	ION FOUND THAT THREE COUNTERWEIGHTS HAD MATERIAL GROUND FROM THE BOTTOM SURFACE. THE CRANKCASE WAS ALSO UNSERVICEABLE DU	E TO THE BREAKUP  OF THE SECOND REAR LT SIDE BEARING SADDLE.				1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001051500038	20010515	00038	EU  	2001	5	15	AU010365         	1	20010327	G	7933		INDICATOR       			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  					ENGINE OIL	FAULTY          	W				C	 	 	 	ABORTED TAKEOFF         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE OIL TEMPERATURE INDICATION SYSTEM FAULTY. WIRING AND INSULATION CHECKED WITH NO FURTHER PROBLEMS. CONN	ECTORS CLEANED AND INSPECTED. PROBLEM HAS NOT REOCCURRED.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001051500039	20010515	00039	SO  	2001	5	15	AU010366         	1	20010403	G	6123		CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AUTOFEATHER SYS	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) AUTOFEATHER SYSTEM FAULTY. INSPECTION OF THE SYSTEM AND CLEANING OF CONNECTOR PLUGS CARRIED OUT. NO DEFECTS EVIDEN	T.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P7NE	 
2001051500040	20010515	00040	SO  	2001	5	15	AU010367         	1	20010223	G	3221	6705403	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	FRACTURED       	W				O	 	 	 	OTHER                   				P		 	NO WARNING INDICATION     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION FRACTURED THROUGH THE DRAG LINKATTACHMENT BOLT HOLE.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001051500041	20010515	00041	NE  	2001	5	15	AU010368         	2	20010330	G	8530	L2144448A	CYLINDER        			PIPER 	PA60  	PA60602P    	7106015	NM  	LYC   	O540  	IO540AA1A   	41532	NE  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE CYLINDERS AND PISTONS DAMAGED BY DETONATION.						1	M	7	2 	3O	3	O	RT	A17WE   	1EA	5	C	P25EA	 
2001050700402	20010507	00402	NE  	2001	5	7	AU010369         	1	20010420	G	5531	7620105501101	SPAR CAP        			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					VERTICAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILISER FORWARD RH SPAR CAP ANGLE LOCATED AT VS117.25 CRACKED IN THE AREA WHERE THE RIVETS ATTACH THE 	TOP RIB TO THEANGLE.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001051500042	20010515	00042	NM  	2001	5	15	AU010370         	1	20010422	G	5610	8SC00430780205	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 										(AUS) CAPTAINS WINDSHIELD OUTER PANE CRACKED. CRACK ORIGINATED AT THE HEATER ELEMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500043	20010515	00043	EA  	2001	5	15	AU010371         	2	20010418	G	8550	LW13388	SEAL            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DETERIORATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL FILTER CONVERTER PLATE SEAL DETERIORATED. REFER TO AD/LYC105.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001051500044	20010515	00044	NM  	2001	5	15	AU010372         	1	20010421	G	3260	11300105	UPLOCK          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT MLG	FAULTY          	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK LATCHING SPRINGS FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500045	20010515	00045	NM  	2001	5	15	AU010373         	1	20010420	G	2910	9741735	HOSE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					HYDRAULIC SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			AP	APPROACH       	1			AU	S 										(AUS) NR 1 HYDRAULIC PUMP PRESSURE HOSE FAILED. LOSS OF HYDRAULIC FLUID.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001051500046	20010515	00046	NM  	2001	5	15	AU010374         	1	20010422	G	7160	12788	PANEL           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					AIR INTAKE	DELAMINATED     	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			1749 							(AUS) NR 1 ENGINE ICE IMPACT PANEL DELAMINATED FROM THE 5 OCLOCK POSITION THROUGH TO THE 11 OCLOCK POSITION. DELAMINATED	 MATERIAL WAS CAUGHT IN THE INLET GUIDE VANES. BOROSCOPE INSPECTION FOUND NIL INTERNAL DAMAGE.					2	L	7	2 	4F	4	F	RT	A20WE   	E30NE				 
2001051500047	20010515	00047	NM  	2001	5	15	AU010375         	1	20010420	G	2910		HYDRAULIC SYSTEM			BOEING	737   	737377      	       	NM  										A SYSTEM	LOW             	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC A SYSTEM QUANTITY AND PRESSURE LOST.						2	L	7	2 	4F			RT	A16WE   					 
2001051500048	20010515	00048	NM  	2001	5	15	AU010376         	1	20010420	G	2750		CONTROLLER      			BOEING	737   	737377      	       	NM  										TE FLAPS	FAULTY          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAPS FAILED TO MOVE PAST 15 DEGREES.						2	L	7	2 	4F			RT	A16WE   					 
2001051500049	20010515	00049		2001	5	15	AU010377         	4	20010420	G	2565	7A13946	SLIDE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PAX DOOR	MISINSTALLED    	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			10430		GV198					(AUS) NR 1 LH MAIN ENTRY DOOR ESCAPE SLIDE SAFETY PIN INSTALLED. PERSONNEL/MAINTENANCE ERROR.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001051500050	20010515	00050	WP  	2001	5	15	AU010378         	1	20010418	G	5511		SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					HORIZONTAL STAB	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER REAR SPAR DAMAGED.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2001051500051	20010515	00051	EU  	2001	5	15	AU010379         	1	20010406	G	2760	P308450070	SWITCH          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					DRAG CONTROL	FAULTY          	W				O	 	 	 	OTHER                   				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LT AND RT OUTBOARD SPOILER MICROSWITCHES FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001051500052	20010515	00052		2001	5	15	AU010380         	4	20010422	G	3423		COMPASS         			BOEING	737   	737377      	       	NM  										COCKPIT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BUBBLE IN COMPASS FLUID. FOUND DURING INSPECTION IAW AD/INST/9.						2	L	7	2 	4F			RT	A16WE   					 
2001051500053	20010515	00053		2001	5	15	AU010381         	4	20010423	G	3423		COMPASS         			BOEING	737   	737377      	       	NM  										COCKPIT	FAULTY          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIR BUBBLE IN STANDBY COMPASS. FOUND DURING INSPECTION IAWAD/INST/9.						2	L	7	2 	4F			RT	A16WE   					 
2001050700403	20010507	00403	GL  	2001	5	7	AU010382         	2	20010426	G	7250	6898785	SHAFT           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					TURBINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 			3464 				CAG90756			(AUS) ENGINE GEARBOX POWER TAKEOFF SHAFT CRACKED. SUSPECT CAUSED BY OVERTIGHTENING OF THE POWER OUTPUT ADAPTER.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001051500054	20010515	00054	NM  	2001	5	15	AU010383         	1	20010424	G	5313		STRINGER        			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STRINGER 32L LOCATED AT STN 1085 CRACKED. CRACK LENGTH 114.3MM(4.5IN).						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001051500055	20010515	00055		2001	5	15	AU010385         	4	20010423	G	2312		RADIO           			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					VHF SYSTEM	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) VHF SYSTEM FAULTY.						2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001051500056	20010515	00056	SO  	2001	5	15	AU010386         	1	20010402	G	2750	487377	SPRING          			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	TE FLAPS	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP RETURN SPRING FAILED AT ATTACHMENT HOOK.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001051500057	20010515	00057	NM  	2001	5	15	AU010387         	1	20010426	G	2751	2061141	INDICATOR       			BOEING	737   	73733A      	1384673	NM  										TE FLAPS	FAULTY          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			AU	S 										(AUS) FLAP POSITION INDICATOR FAULTY.						2	L	7	2 	4F			RT	A16WE   					 
2001051500058	20010515	00058	CE  	2001	5	15	AU010388         	1	20010412	G	3260	7401CGE	SWITCH          			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	INTERMITTENT    	W				K	 	 	 	NONE                    				N		 	FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR WARNING LIGHT DIMMER SWITCH INTERMITTENT IN OPERATION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001051500059	20010515	00059	NE  	2001	5	15	AU010389         	2	20010423	G	7320	78639010	HMU             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	RT ENGIEN	FAULTY          	W				O	 	 	 	OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001080700080	20010807	00080	NM  	2001	8	7	AUS20010391      	1	20010430	G	5313		STRINGER        	            	            	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		FUSELAGE MAIN, L	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) STRINGER 39L LOCATED BELOW THE FLOOR IN THE AFT CARGO AREACORRODED BETWEEN BS 1285 AND BS 1307.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080800001	20010808	00001	EU  	2001	8	8	AUS20010392      	1	20010425	G	2430		GENERATOR       			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					DC GENERATING SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DC GENERATION SYSTEM FAULTY.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800002	20010808	00002	NM  	2001	8	8	AUS20010393      	1	20010426	G	2720		PCU             			BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					RUDDER CONTROL	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) RUDDER CONTROL SYSTEM FAULTY. NUMEROUS ITEMS IN THE CONTROL SYSTEM WERE REPLACED TO CORRECT THE PROBLEM. INVESTIGA	TION IS CONTINUING INTO THE REPLACED ITEMS. ITEMS REPLACED WERE DFDR PNO 2100-4043-00, RUDDER PCU PNO 65C37053-9, STANDB	Y RUDDERPCU PNO 1U1150-3 AND YAW DAMPER  COUPLER PNO 4030952-906.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800003	20010808	00003	NM  	2001	8	8	AUS20010394      	1	20010424	G	7110	UL26237	FAIRING         	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ENGINE COWLING	SEPARATED       	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			13461		13043					(AUS) NR 3 ENGINE LT AND RT GAS GENERATOR FAIRINGS PNO UL26237 AND PNO UL23239 SEPARATED FROM ENGINE. DAMAGE TO NR 3 ENG	INE INTEGRATEDNOZZLE AREA AND RT C' FLAP.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080700081	20010807	00081	SO  	2001	8	7	AUS20010395      	1	20010426	G	2430	460620	FILTER          	PIPER       	460620      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	DC GENERATING SY	INTERMITTENT    	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 									(AUS) LH NOISE FILTER INTERMITTENT IN OPERATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800007	20010808	00007	NM  	2001	8	8	AUS20010396      	1	20010428	G	3260		SENSOR          			BOEING	737   	737377      	       	NM  										LANDING GEAR	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) AIR SENSING TEST CARD FAILED.						2	L	7	2 	4F			RT	A16WE   					 
2001080800016	20010808	00016	NM  	2001	8	8	AUS20010398      	1	20010429	G	3520	S417T40127	GENERATOR       			BOEING	737   	737377      	       	NM  										PASSENGER OXYGEN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) OXYGEN GENERATORS LOCATED IN THE FLIGHT ATTENDANT SERVICE UNITADJACENT TO CABIN DOORS L1 AND L2 HAD THE RELASE PIN	S LOCATED INTHE SAFETY PIN HOLES. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F			RT	A16WE   					 
2001080700082	20010807	00082	NM  	2001	8	7	AUS20010399      	1	20010502	G	3230	EO3600491750S	SPRING          	ROTOL       	ACTUATOR    	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR RET	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				DCL30093					(AUS) UPLOCK ACTUATOR SPRING (1OFF2) BROKEN AT THE BASE OF THE UPPERATTACHMENT HOOK.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800018	20010808	00018	NM  	2001	8	8	AUS20010400      	1	20010501	G	7110	13453	PANEL           	RROYCE      	RB211524H36 	BOEING	767   	767338      	1385151	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE COWLING	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			11290		13453					(AUS) NR 1 ENGINE ACOUSTIC PANEL TRAILING EDGE SECTION SEPARATED FROMTHE AIRCRAFT. NR 5 BLOCKER DOOR REPLACED DUE TO DAM	AGE. NR 7, NR 8 AND NR 9 BLOCKER DOORS HAD MINOR SKIN DAMAGE. NR 7 DEFLECTOR BOX CASCADE VANE DAMAGED.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001080800020	20010808	00020	EU  	2001	8	8	AUS20010401      	1	20010416	G	2450		SPLICE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC POWER DIST	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GENERATOR FEEDER INLINE SPLICE OVERHEATING. FOUND DURINGINSPECTION IAW TSI 146-24-003.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700083	20010807	00083	NM  	2001	8	7	AUS20010402      	1	20010503	G	3230	EO3600491750S	SPRING          	ROTOL       	ACTUATOR    	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				DCL30293DCL2					(AUS) LH AND RH MAIN LANDING GEAR UPLOCK ACTUATOR SPRINGS BROKEN.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800021	20010808	00021	NM  	2001	8	8	AUS20010403      	1	20010502	G	5730		SKIN            			BOEING	737   	73733A      	1384673	NM  										WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING UPPER SKIN LOWER SURFACES AND TOP STRINGERS IN AREA BETWEEN WS557 AND WS583. CORROSION ALSO EVIDENT	 ON RH REAR SPAR LOWER FLANGE IN AREA BETWEEN WS576 AND WS580.					2	L	7	2 	4F			RT	A16WE   					 
2001080800022	20010808	00022	EU  	2001	8	8	AUS20010404      	1	20010420	G	5320	D5337061320200	FITTING         			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (KEEL BEAM) CRACKED. CRACKS FOUND IN LH AFT FITTING PNO D5337061320200 RH	 AFT AND LH FORWARD FITTINGS PNO D5337961320300. CRACKS EMANATE FROM THE TOPTWO FASTENER HOLES IN THE VERTICAL FLANGE. F	OUND DURING INSPECTION IAW ER A32-53-40-9C (SB A320-53-1135).				2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080700084	20010807	00084	WP  	2001	8	7	AUS20010405      	1	20010421	G	7920	R14	FILTER          	LYC         	O320B2C     	ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  	 		            		ENGINE OIL DISTR	LEAKING         	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 	 									(AUS) ENGINE OIL FILTER O' RING SEAL POPPED OUT ALLOWING OIL TO BE PUMPED OVERBOARD. THE RYCO R14 OIL FILTER IS FITTED T	O SOME R22 AIRCRAFT BY AN ENGINEERING ORDER.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080700085	20010807	00085	NM  	2001	8	7	AUS20010406      	1	20010430	G	7110	LK73708	PANEL           	RROYCE      	RB211524D419	BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  	 		            		ENGINE COWLING S	SEPARATED       	W			    	K	 	 	 	NONE                    				O	D	 	OTHER                     	INFLIGHT SEPARATION       		IN	INSP/MAINT     	1			AU	S 	 		7466 		12679					(AUS) NO4 ENGINE VIGV CONTROLLER ACCESS PANEL SEPARATED. DAMAGE CAUSEDTO THE REAR FAN CASE ACOUSTIC LINER.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001080800023	20010808	00023	EA  	2001	8	8	AUS20010407      	2	20010430	G	7310	689	LINE            			PILATS	PC6   	PC6         	7090102	EU  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL DIST	CONTAMINATED    	W				O				OTHER                   				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		LD	LANDING        	1			AU	S 										(AUS) ENGINE FAILED DUE TO LACK OF FUEL. INVESTIGATION FOUND AIR IN THE FUEL LINE BETWEEN THE FUEL HEATER AND THE FCU. S	USPECT CAUSED BYPOOR VENTING OF THE FUEL HEADER TANK. AD/PC6/42 (PC-6-SB-171) ISENTERED INTO THE LOG BOOK AS HAVING BEEN	 COMPLIED WITH BUT HASNOT BEEN CARRIED OUT. THE AD AND SB INTRODUCES A VENTING SYSTEM TO THE HEADER TANK. PERSONNEL/MAIN	TENANCE ERROR.			1	H	7	1 	3O	3	T	 	7A15    	E4EA	6	C	P15EA	 
2001080700086	20010807	00086	SO  	2001	8	7	AUS20010408      	2	20010510	G	8550	CH48109	FILTER          	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RECIPROCATING EN	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL FILTER ELEMENT END CAP MISSING.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080800024	20010808	00024	NE  	2001	8	8	AUS20010409      	3	20010503	G	6110		PROPELLER       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RIGHT	OUT OF BALANCE  	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) RT PROPELLER OUT OF BALANCE. PROPELLER HAD BEEN RECENTLY REPLACED BUT HAD NOT BEEN BALANCE CHECKED FOLLOWING FITME	NT.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001080700087	20010807	00087		2001	8	7	AUS20010410      	4	20010513	G	3416	WL1107AMMS4	ALTIMETER       	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		ALTIMETER, BAROM	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			CL	CLIMB          	1			AU	S 	 		24008		AF756					(AUS) CAPTAINS ALTIMETER FAILED.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080800025	20010808	00025	SO  	2001	8	8	AUS20010411      	1	20010507	G	3260		SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	OUT OF ADJ      	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR UP LIMIT SWITCH OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800026	20010808	00026	CE  	2001	8	8	AUS20010412      	1	20010423	G	5320	MS21047L3	NUT             			CESSNA	303   	T303        	2073820	CE  	CONT  	O520  	TSIO520AE   	17040	SO  	MCAULY	3AF32C	3AF32C506   	GL  	FUEL CELL	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING FUEL TANK LEAKING. INVESTIGATION FOUND THAT THE FUEL TANK PANEL ANCHOR NUTS WERE THE INCORRECT TYPE. THE C	ORRECT NUTS PNO NAS1473A3 ANCHOR NUTS ARE SEALED BUT THE FITTED ANCHOR NUTS PNO MS21047L3 ARE UNSEALED. MANUFACTURING ER	ROR. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O	 	A34CE   	E8CE	5	C	P57GL	 
2001080700088	20010807	00088	NM  	2001	8	7	AUS20010413      	1	20010511	G	6322	A1851	BRACKET         	            	            	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		ROTORCRAFT COOLI	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) COOLING FAN SCROLL BRACKET CRACKED. CRACK ORIGINATED AT A SIDESCREWDRIVER NOTCH. FOUND DURING INSPECTION IAW AD/R2	2/24.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080800027	20010808	00027	CE  	2001	8	8	AUS20010414      	1	20010504	G	5720		RIVET           			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					WING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING STRUT ATTACHMENT RIB TO OUTBOARD TIP RIVETS LOOSE AND MISSING. LEADING EDGE HAD BEEN REPLACED IN 1972.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800029	20010808	00029	CE  	2001	8	8	AUS20010415      	1	20010504	G	3246		WHEEL           			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE AND MAIN WHEEL HALVES (5OFF6) CORRODED WITH BEARINGS SPINNING IN THE WHEEL HALVES. CORROSION ALSO FOUND IN AR	EA OF THE FELT SEALS.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800030	20010808	00030	SO  	2001	8	8	AUS20010416      	2	20010504	G	8550		FILTER          			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) METAL CONTAMINATION OF THE REAR ENGINE OIL FILTER. SUSPECT MAIN BEARING FAILURE.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800032	20010808	00032	CE  	2001	8	8	AUS20010417      	1	20010504	G	5311		FRAME           			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ROOF SUPPORT FORMER LOWER EDGE CONTAINED INTERGRANNULARCORROSION.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800033	20010808	00033	CE  	2001	8	8	AUS20010418      	1	20010504	G	5310		RIVET           			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL PAN/FIREWALL STRUCTURE RIVETS PULLED. FAILED RIVETS LOCATED IN THE AFT LT TOP CORNER.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800034	20010808	00034	CE  	2001	8	8	AUS20010419      	1	20010504	G	2720		TORQUE TUBE     			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					RUDDER CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PEDAL TORQUE TUBE CLAMP SUPPORT STRUCTURE CRACKED ANDWORKING. LOOSE RIVETS AND DAMAGE CAUSED BY BELLCRANK.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800057	20010808	00057	CE  	2001	8	8	AUS20010420      	1	20010504	G	2823		SELECTOR VALVE  			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360D      	17025	SO  					FUEL SYSTEM	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FRONT AND REAR FUEL SELECTORS FAULTY. FUEL CAN'T BE TURNED OFF. SUSPECT FAULTY SEALS.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001080800067	20010808	00067	EU  	2001	8	8	AUS20010421      	1	20010514	G	2621	57333012	FIRE BOTTLE     			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE FIRE BOTTLE FIRING SWITCH WIRING CONTAINED TWO INLINESPLICES FITTED WITH SMALLER GAUGE WIRES. UNAPPROV	ED MODIFICATION. PERSONNEL/MAINTENANCE ERROR.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700089	20010807	00089	CE  	2001	8	7	AUS20010422      	1	20010515	G	2701	07606331	BEARING         	            	            	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	CONTROL COLUMN S	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 		3847 							(AUS) COPILOTS CONTROL COLUMN BEARING BLOCK NEEDLE ROLLER BEARING WORNOUT AND THE ROLLERS DISLODGED DUE TO LACK OF LUBRI	CATION. THE ROLLER BEARING SHAFT GROOVED FROM VIBRATION INDUCED WEAR.					1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2001080800080	20010808	00080		2001	8	8	AUS20010423      	4	20010507	G	3425	7003360941	INDICATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	AHRS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) NR 1 ATTITUDE HEADING REFERENCE SYSTEM (AHRS) FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800081	20010808	00081		2001	8	8	AUS20010424      	4	20010503	G	3416	6223890002	TRANSCEIVER     			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ALTIMETER	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RADIO ALTIMETER TRANSCEIVER INTERMITTENT OPERATION. INVESTIGATION FOUND THE FAULT WAS DUE TO A STRAY VOLTAGE ON A 	SPARE PIN IN THETRANSCEIVER DUE TO A WIRE FITTED BY A PREVIOUS OPERATOR. THEMODIFICATION WAS NOT NOTIFIED TO THE MANUFAC	TURER AND THE WIRINGDIAGRAMS WERE NOT AMENDED. PERSONNEL/MAINTENANCE ERROR.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800083	20010808	00083	SO  	2001	8	8	AUS20010425      	1	20010507	G	5510	717002	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HORIZONTAL STAB	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT HORIZONTAL STABILISER OUTBOARD HINGES FITTED WITH ONLYTWO RIVETS ON THE TOP AND BOTTOM WHEN THE PIPER MO	DIFICATION KITPNO 766-646 WHEN THE CORRECT NUMBER SHOULD BE FOUR RIVETS.PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800084	20010808	00084	CE  	2001	8	8	AUS20010426      	1	20010507	G	5551	12326231	FITTING         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AFT TAILPLANE ATTACHMENT REINFORCEMENT CRACKED.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080700090	20010807	00090	EU  	2001	8	7	AUS20010427      	1	20010506	G	5553	13708F2	HINGE           	            	            	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	VERTICAL STABILI	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER CENTRE HINGE BRACKET CENTRE LUG FAILED DUE TO CORROSION.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001080700091	20010807	00091	EU  	2001	8	7	AUS20010428      	1	20010506	G	5554	1379036F403	HINGE           	            	            	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RUDDER/TAB, ATTA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER CENTRE HINGE CRACKED. SUSPECT CAUSED BY EXTRA LOADS DUE TO FAILURE OF THE FIN MOUNTED HALF OF THE HINGE. SE	E MDR 01/0427.					2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001080700092	20010807	00092	NM  	2001	8	7	AUS20010429      	1	20010424	G	6310	A1843	BEARING         	            	            	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		ENGINE/TRANSMISS	SPALLED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) UPPER BEARING ROUGH. ONE BALL BADLY SPALLED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080700093	20010807	00093	EU  	2001	8	7	AUS20010430      	1	20010504	G	5711	D53	FLANGE          	PARTEN      	P68B        	PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	WING SPAR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				D53					(AUS) AFT WING SPAR WEB FLANGE CRACKED ON THE LH SIDE IN THE AREA OUTBOARD OF THE ATTACHMENT FITTING. FOUND DURING INSPE	CTION IAW AD/P68/22, AD/P68/45 AND SB 65.					1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2001080700094	20010807	00094	CE  	2001	8	7	AUS20010431      	1	20010115	G	5347	121040821	SEAT TRACK      	            	            	CESSNA	206   	U206F       	2073333	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 TRACKS CRACKED THROUGH STOP PIN HOLES.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080700095	20010807	00095	CE  	2001	8	7	AUS20010432      	1	20010115	G	5312	12121365	BULKHEAD        	            	            	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE MAIN, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HORIZONTAL STABILISER ATTACHMENT BULKHEAD CRACKED THROUGH TOP RIVET HOLE. CRACK LENGTH 19.05MM (0.75IN).						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080700096	20010807	00096	CE  	2001	8	7	AUS20010433      	1	20010115	G	5753	12210107	FLAP TRACK      	            	            	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	TRAILING EDGE FL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FLAP TRACKS CONTAINED EXFOLIATION AND INTERGRANNULAR CORROSIONLOCATED IN THE FORWARD END OF THE LOWER SLOT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080800086	20010808	00086	NE  	2001	8	8	AUS20010434      	2	20010103	G	8520	3592	LINK ROD        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 9 CYLINDER LINKROD BROKEN. SEVERE INTERNAL DAMAGE PREVENTED ESTABLISHING THE CAUSE OF THE FAILURE.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001080700097	20010807	00097	EA  	2001	8	7	AUS20010435      	2	20010503	G	7310	L142368A	HOSE            	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL DIST	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				L142368A					(AUS) FUEL HOSES LOCATED BETWEEN THE FCU AND THE FLOW DIVIDER DID NOT HAVE FIRESLEEVES FITTED. PERSONNEL/MAINTENANCE ERR	OR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080700098	20010807	00098	EU  	2001	8	7	AUS20010437      	1	20010506	G	5553	13708F1	BRACKET         	            	            	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	VERTICAL STABILI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER HINGE BRACKET CONTAINED EXFOLIATION CORROSION IN THE AREAOF THE BONDING LEAD ATTACHMENT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001080800087	20010808	00087	SO  	2001	8	8	AUS20010438      	1	20010401	G	3220		LANDING GEAR    			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	COLLAPSED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR COLLAPSED. INSPECTION COULD FIND NO DEFECTS WITH THE SYSTEM. SUSPECT INCORRECT TECHNIQUE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800089	20010808	00089	EU  	2001	8	8	AUS20010439      	1	20010504	G	7920	70009K000V332A	HOSE            			AGUSTA	206AGS	206AAGUSTA  	0260301	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE OIL	LEAKING         	W				A				UNSCHED LANDING         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE OIL HOSE LEAKING IN AN AREA APPROXIMATELY 100MM (4IN) FROM THE FORWARD UNION END.						1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2001080700099	20010807	00099	SO  	2001	8	7	AUS20010440      	1	20010427	G	7170	CCA1550	DRAIN VALVE     	LYC         	O320D3G     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE DRAINS	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) AIRCRAFT RETURNED TO AIRSTRIP AFTER TAKEOFF FOR A FORCED LANDING. FUEL STAINS FOUND DOWN THE SIDE OF THE AIRCRAFT 	EMANATING FROMTHE DRAIN VALVE. INSPECTION OF THE VALVE COULD FIND NO DEFECTSAND THE VALVE WAS CLOSED. ENGINE DRAIN VALVE	 SUSPECT LEFT PARTIALLY OPEN ALLOWING FUEL LEAKAGE AND THEN CLOSED ON LANDING.				1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2001080800091	20010808	00091	EU  	2001	8	8	AUS20010441      	1	20010420	G	5343	D5337061320300	FITTING         			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (3OFF4) CRACKED FROM THE TOP TWO FASTENER HOLES IN THE VERTICAL FLANGE. F	ITTINGS CRACKED ARE PNO D5337061320200 (LH AFT) AND PNO D5337061320300 (RH AFTAND LH FORWARD). FOUND DURING INSPECTION I	AW ER A32-53-40-9C(SB A320-53-1135).				2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080700100	20010807	00100	SO  	2001	8	7	AUS20010442      	1	20010321	G	3397		WIRE            		BA08006281  	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	PASSENGER COMPAR	WORN            	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN LIGHTING SYSTEM INVERTER OUTPUT WIRING CHAFING AGAINST GASPER AIR DUCT CAUSING THE WIRING LOOM AND DUCT INSU	LATION TO BURN.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001080800093	20010808	00093	NM  	2001	8	8	AUS20010443      	1	20010417	G	3520		DOOR            			BOEING	737   	737377      	       	NM  										PASSENGER OXYGEN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD TOILET OXYGEN SYSTEM DROP-DOWN DOOR HAD WHITE SILASTICMATERIAL ACROSS THE FORWARD OUTBOARD CORNER PREVENTI	NG IT FORM OPENING. THE SILASTIC HAD BEEN USED ON THE TOILET CEILING PANEL AND HAD BEEN SMEARED ACROSS THE OXYGEN PANEL 	DOOR.				2	L	7	2 	4F			RT	A16WE   					 
2001080700101	20010807	00101	EU  	2001	8	7	AUS20010444      	1	20010407	G	2822		PUMP            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		FUEL BOOST PUMP	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) AFT BOOST PUMP FAILED. CIRCUIT BREAKER RESET AND PUMP OPERATEDNORMALLY SINCE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800095	20010808	00095	NM  	2001	8	8	AUS20010445      	1	20010430	G	3230	658005118	DRAG BRACE      			BOEING	737   	73733A      	1384673	NM  										LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			21713							(AUS) NOSE LANDING GEAR UPPER DRAG BRACE CRACKED AT RETRACTION ACTUATOR ATTACHMENT. CRACK WAS DETECTED VISUALLY.						2	L	7	2 	4F			RT	A16WE   					 
2001080700102	20010807	00102	EU  	2001	8	7	AUS20010446      	1	20010417	G	7830	22100009519	CABLE           	PWA         	PW4152      	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		THRUST REVERSER	DISTORTED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) NO1 ENGINE THRUST REVERSER MASTER ACTUATOR FLEXIBLE CABLE DRIVE TO SPLITTER GEARBOX KINKED AND TWISTED.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001080700103	20010807	00103	EU  	2001	8	7	AUS20010447      	1	20010430	G	3260		DOOR            	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR POS	FALSE INDICATION	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		NR	NOT REPORTED   	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR DOOR INDICATIONS INCORRECT. INVESTIGATIONCOULD FIND NO FAULT WITH THE SYSTEM. DEFECT NOT CONF	IRMED.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700104	20010807	00104	EU  	2001	8	7	AUS20010448      	1	20010430	G	3242	50002685	BRAKE           	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BRAKE	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 		58   		DEC6976					(AUS) NO2 BRAKE UNIT LEAKING FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800096	20010808	00096	EA  	2001	8	8	AUS20010450      	2	20010501	G	8530	LW12993	CYLINDER        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			145  							(AUS) ENGINE CYLINDERS IN POOR CONDITION. OIL LEAKING PAST VALVE STEMS.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001080700105	20010807	00105	EA  	2001	8	7	AUS20010451      	2	20010420	G	8520	71907	WASHER          	LYC         	IO540E1B5   	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				L1111148					(AUS) RH ENGINE COUNTERWEIGHT RETAINING WASHER PNO 71907 HAD FAILED ALLOWING THE COUNTERWEIGHT ROLLER PNO 72797 TO MIGRA	TE ANDCONTACT NO5 CYLINDER CONNECTING ROD AND CAUSING IT TO FAIL WHICHCAUSED SEVERE DAMAGE TO THE CRANKCASE. THE RETAINI	NG CIRCLIPPNO  LW14820 REMAINED IN POSITION.				1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2001080800098	20010808	00098	EU  	2001	8	8	AUS20010452      	1	20010430	G	3241	95427193	SENSOR          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					WHEEL SPEED	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			351  		JUL74569					(AUS) NR 2 WHEEL SPEED GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700106	20010807	00106	EA  	2001	8	7	AUS20010453      	1	20010417	G	2432		CONNECTOR       	            	            	DHAV  	DHC6  	DHC6        	2802606	EA  	      		            			 		            		BATTERY/CHARGER	MELTED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 	 									(AUS) BATTERY SHUNT GROUND CONNECTION MELTED.						1	H	7	2 	3T			RT	A9EA    					 
2001080700107	20010807	00107	EU  	2001	8	7	AUS20010455      	1	20010505	G	3260	GC1016	RELAY           	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) RH GROUND/FLIGHT RELAY FAULTY. LH AND RH MLG GROUND FLIGHTSWITCHES CONTAMINATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700108	20010807	00108	CE  	2001	8	7	AUS20010456      	1	20010406	G	5343	07900065	BRACKET         	            	            	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	LANDING GEAR ATT	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR ATTACHMENT BRACKET SEVERELY CORRODED.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2001080700109	20010807	00109	CE  	2001	8	7	AUS20010457      	1	20010406	G	5343	07900066	BRACKET         	            	            	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	LANDING GEAR ATT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR ATTACHMENT BRACKET CRACKED. MLG LEG LOOSE ATWEDGES.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2001080700110	20010807	00110	NM  	2001	8	7	AUS20010458      	1	20010405	G	6510	A0413	ARM             	ROBSIN      	TAILCONE    	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		TAIL ROTOR DRIVE	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 	 				1057					(AUS) TAIL ROTOR DRIVESHAFT DAMPENER ARM FAILED ALLOWING TAIL ROTOR DRIVESHAFT TO WHIP AND BREAK AND CAUSING DESTRUCTION	 OF THE TAILCONE ASSEMBLY PNO A023-20.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080800100	20010808	00100	EU  	2001	8	8	AUS20010459      	1	20010505	G	3260		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LANDING GEAR	STUCK           	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) MAIN LANDING GEAR GROUND/FLIGHT SWITCHES STICKY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800102	20010808	00102	EU  	2001	8	8	AUS20010461      	2	20010508	G	7200		ENGINE          			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NACELLE	MALFUNCTIONED   	W				C				ABORTED TAKEOFF         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) INCORRECT TAKEOFF THRUST SET BY PILOT. PERSONNEL ERROR.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800106	20010808	00106	NM  	2001	8	8	AUS20010463      	1	20010505	G	7331	AS21515	BOLT            	RROYCE      	R211524D419 	BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FLOW INDICATOR	WRONG PART      	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			6100 		12647					(AUS) NR 2 ENGINE FUEL FLOW TRANSMITTER INLET GASKET LEAKING. LOOSEBOLTS RETIGHTENED BUT THE LEAK CONTINUED. FURTHER INV	ESTIGATION FOUND THAT THE MOUNTING BOLTS WERE PNO AS21515 INSTEAD OF THE CORRECT PNO AS21514. FITMENT OF THE INCORRECT B	OLTS HAD DAMAGED THE THREADS IN THE TRANSMITTER REQUIRING REPLACEMENT. UNAPPROVEDPART. PERSONNEL/MAINTENANCE ERROR.				2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080700111	20010807	00111	EU  	2001	8	7	AUS20010464      	1	20010505	G	3230		LANDING GEAR    	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) LANDING GEAR WOULD NOT RETRACT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700112	20010807	00112	EU  	2001	8	7	AUS20010465      	1	20010511	G	2752		BOLT            	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		TRAILING EDGE FL	SHEARED         	W			    	K	 	 	 	NONE                    				F	K	 	FLT CONT AFFECTED         	FLUID LOSS                		CL	CLIMB          	1			AU	S 	 									(AUS) FLAP MOTOR ASSEMBLY BODY BOLT SHEARED AND BODY HALVES SEPARATED AT JOINT. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700113	20010807	00113	EU  	2001	8	7	AUS20010466      	1	20010505	G	3220	200725209LOWER	TORQUE LINK     	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		NOSE/TAIL LANDIN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				DCS6809LOWER					(AUS) NOSE LANDING GEAR LOWER TORQUE LINK CRACKED IN GREASE NIPPLEHOLE. FOUND USING VISUAL INSPECTION AND CONFIRMED USIN	G EDDYCURRENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700114	20010807	00114	EU  	2001	8	7	AUS20010468      	1	20010507	G	2760		CONNECTOR       	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		DRAG CONTROL SYS	LOOSE           	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) RH OUTBOARD LIFT DUMPER BELLCRANK INLOCK CONNECTOR LOOSE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700115	20010807	00115	EU  	2001	8	7	AUS20010469      	1	20010505	G	3220	200725209UPPER	TORQUE LINK     	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		NOSE/TAIL LANDIN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				DCS6808UPPER					(AUS) NOSE LANDING GEAR UPPER TORQUE LINK CRACKED IN GREASE NIPPLEHOLE. FOUND USING VISUAL INSPECTION AND CONFIRMED USIN	G EDDYCURRENT INSPECTION.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700116	20010807	00116	CE  	2001	8	7	AUS20010470      	1	20010407	G	3222	998200005	SHOCK ABSORBER  	BEECH       	9782000061  	BEECH 	200   	200BEECH    	1152920	CE  	      		            			 		            		NOSE/TAIL LANDIN	FAULTY          	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE LANDING GEAR SHOCK ABSORBER INNER O' RING SEAT OVERSIZE ALLOWING THE O' RING TO MOVE ON THE HOUSING AND LEAK.						1	L	7	2 	4T			 	A24CE   					 
2001080800107	20010808	00107	EA  	2001	8	8	AUS20010471      	1	20010511	G	3220		LANDING GEAR    			DHAV  	DHC6  	DHC6        	2802606	EA  										NLG	FOD             	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR FAILED WHEN THE NOSE WHEEL CONTACTED A ROCK ONLANDING. TYRE DEFLATED AND NOSE WHEEL SHATTERED. N	LG FORK FAILEDAT THE OLEO AND THE REMAINDER OF THE NLG BENT BACK CAUSING DAMAGE TO THE BULKHEAD, ATTACHMENT FITTINGS AND	 SURROUNDINGLOWER  FUSELAGE STRUCTURE. FIBREGLASS NOSE CONE ALSO BADLY DAMAGED.				1	H	7	2 	3T			RT	A9EA    					 
2001080700117	20010807	00117	GL  	2001	8	7	AUS20010472      	2	20010426	G	7230	23007196	SEAL            	ALLSN       	250C30P     	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		TURBINE ENGINE C	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1371 		CAC91190					(AUS) COMPRESSOR REAR DIFFUSER LABYRINTH SEAL EXCESSIVELY CORRODED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080800109	20010808	00109	NM  	2001	8	8	AUS20010473      	1	20010504	G	7110	LK47717	FAIRING         	RROYCE      	RB21152436  	BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE COWLING	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 			18631		13462					(AUS) NR 2 ENGINE LT A' FRAME TO FAN CASE AFT LOWER FAIRING MISSING.						2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001080800111	20010808	00111	CE  	2001	8	8	AUS20010474      	1	20010427	G	5540	51310103	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RUDDER	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RUDDER HINGE BEARING INCORRECTLY INSTALLED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001080800113	20010808	00113	NM  	2001	8	8	AUS20010476      	1	20010511	G	7110	13043	PANEL           	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ENGINE COWLING	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			13720		13043					(AUS) NR 3 ENGINE OGV INFILL PANELS MISSING BETWEEN 4 O'CLOCK AND 6O'CLOCK POSITIONS. DAMAGE TO LH COMPRESSOR CORE PANEL	, IP COMPRESSOR BLEED VALVE CONTROL UNIT AIR SENSE PROBE, THRUST REVERSER CORONA AND NO5 AND NO6 THRUST REVERSER BLISTER	 FAIRINGS.				2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080800115	20010808	00115	NM  	2001	8	8	AUS20010477      	1	20010506	G	2761	NAS161210	O-RING          		15425001    	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					DRAG ACTUATOR	DAMAGED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					501					(AUS) NR 8 SPOILER POWER CONTROL ACTUATOR (PCA) FILTER BOSS O' RING SEAL DAMAGED AND LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080800117	20010808	00117	NM  	2001	8	8	AUS20010478      	1	20010505	G	2620	301000223	EXTINGUISHER    			BOEING	767   	767*        	       	NM  										CABIN	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			25012							(AUS) FIRE EXTINGUISHERS LOCATED IN THE MID CABIN LT AND RT TOILETS AND AFT CABIN RT TOILET HAD IMPACT DAMAGE TO THE FUS	EABLE TIP AREA. FOUND DURING INSPECTION IAW 767-A2-25-006.					2	L	7	2 	4F			RT	A1NM    					 
2001080700118	20010807	00118	WP  	2001	8	7	AUS20010479      	1	20010406	G	6310	269A55907	RETAINER        	            	            	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HO360C1A    	41514	EA  	 		            		ENGINE/TRANSMISS	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) THERMOFIT SLEEVE WORN ON RETAINER.						1	G	7	1 	3O	3	O	 	4H12    	E286				 
2001080800119	20010808	00119	EU  	2001	8	8	AUS20010480      	1	20010505	G	2121	D92098	COOLING FAN     			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AIR DISTRIBUTION	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 			7028 		411467					(AUS) CABIN FAN FAILED. INVESTIGATION FOUND BOTH FORE AND AFT FAN MOTOR SHAFT BEARINGS FAILED. THE MOTOR ALSO FAILED ELE	CTRICALLY WITHSIGNS OF OVERHEATING. BEARING PNO S38SS6CXOG33 AND PNOS100SS6CXOG33.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800121	20010808	00121	EU  	2001	8	8	AUS20010482      	1	20010425	G	7160	TU195MM660MMCC	HOSE            	LYC         	IO540       	BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	IO540*      	41532	EA  					ENG AIR INTAKE	COLLAPSED       	W				C				ABORTED TAKEOFF         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) ENGINE INDUCTION HOSE COLLAPSED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4				 
2001080800123	20010808	00123	NM  	2001	8	8	AUS20010483      	1	20010501	G	3242	S160T400510	BRAKE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 1	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			3932 		QF56035					(AUS) NR 1R BRAKE FAILED. INSPECTION FOUND THAT THE REAR STATOR PLATEWAS DAMAGED WITH EVIDENCE OF REAR STATOR BREAKUP. N	O1R WHEEL ALSO DAMAGED TO THE FAILED BRAKE.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700119	20010807	00119	NM  	2001	8	7	AUS20010484      	1	20010514	G	3242	214747300	BRAKE           	            	6558256238  	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		BRAKE	LEAKING         	W			    	K	 	 	 	NONE                    				O	B	 	OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			AU	S 	 									(AUS) LH OUTBOARD AND LH INBOARD BRAKES LEAKING FLUID FROM ACTUATINGPISTONS. TYRES CONTAMINATED WITH HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700120	20010807	00120		2001	8	7	AUS20010485      	4	20010424	G	2230		COMPUTER        	            	            	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		AUTOTHROTTLE SYS	FAULTY          	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 	 									(AUS) THROTTLE CONTROL COMPUTER (TCC) FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001080800124	20010808	00124	EU  	2001	8	8	AUS20010486      	1	20010331	G	5270		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING	OUT OF ADJ      	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800126	20010808	00126	EU  	2001	8	8	AUS20010487      	1	20010331	G	4920	38075411	APU             			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					APU BAY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			415  							(AUS) APU FAULTY. FUMES IN CABIN.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700121	20010807	00121	EU  	2001	8	7	AUS20010489      	1	20010401	G	5753		SEAL            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		TRAILING EDGE FL	SEPARATED       	W			    	K	 	 	 	NONE                    				D	F	 	INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 	 									(AUS) OUTBOARD TRAILING EDGE FLAP RUBBER SEAL SEPARATED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700122	20010807	00122	EU  	2001	8	7	AUS20010490      	1	20010409	G	3610	6272482	CONTROLLER      	            	            	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		PNEUMATIC DISTRI	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 		7141 		111C589					(AUS) NO1 PNEUMATIC SYSTEM CONTROLLER FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001080700123	20010807	00123	NM  	2001	8	7	AUS20010491      	1	20010423	G	3260		SENSOR          	            	            	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW123D      	52152	NE  	 		            		LANDING GEAR POS	CONTAMINATED    	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 	 									(AUS) MAIN LANDING GEAR DOOR SENSORS AND CONNECTORS CONTAMINATED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001080800128	20010808	00128	EU  	2001	8	8	AUS20010492      	1	20010411	G	7603		THROTTLE        	PWA         	PW4152      	AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      	 	NE  					LT & RT ENGINE	FAULTY          	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 										(AUS) LT AND RT ENGINE THROTTLES REDUCED TOWARDS IDLE. INTERMITTENT DEFECT. CAUSE COULD NOT BE IDENTIFIED. SEE MDR 01/04	85 FORFURTHER INFORMATION.					2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001080700124	20010807	00124	SO  	2001	8	7	AUS20010493      	1	20010501	G	3233	452383	ROD END         	PIPER       	ACTUATOR    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR ACT	CONTAMINATED    	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR ACTUATOR RODEND CONTAMINATED AND DRY.SUSPECT CAUSED BY EXHAUST GASES FROM TAILPIPE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080700125	20010807	00125	NE  	2001	8	7	AUS20010494      	2	20010516	G	7261		PIPE            	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	TURBINE ENGINE O	BROKEN          	W			    	K	 	 	 	NONE                    				E	X	 	VIBRATION/BUFFET          	ENGINE FLAMEOUT           		CR	CRUISE         	1			AU	S 	 									(AUS) ENGINE NO6/NO7 BEARING OIL FEED PIPE BROKEN. ENGINE SEIZED WITH EVIDENCE OF FIRE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800131	20010808	00131	NM  	2001	8	8	AUS20010495      	1	20010515	G	4920	38042812	APU             			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					APU BAY	FAULTY          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 			3989 							(AUS) APU FAILED PERFORMANCE MONITORING TEST. EGT ROSE TO 800 DEGREES.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800132	20010808	00132	GL  	2001	8	8	AUS20010496      	1	20010407	G	2752	464300	MOTOR           			PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP MOTOR BURNED OUT.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001080800166	20010808	00166	CE  	2001	8	8	AUS20010498      	1	20010508	G	5500		STRUCTURE       			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	EMPENNAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXTENSIVE SURFACE CORROSION THROUGHOUT THE FIN AND TAIL ASSEMBLY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080800170	20010808	00170	NE  	2001	8	8	AUS20010499      	2	20010510	G	7230	17284	GUIDE VANE      			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					ENGINE	OUT OF ADJ      	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE VIBRATION. POWER INCREASE LED TO HIGH ITT WITH LOW N1 AND LOW EPR WITH LOW N2. INVESTIGATION FOUND THE A	CCELERATION TIME SLOW DUE TO IGV SCHEDULING OUT OF ADJUSTMENT.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001080800172	20010808	00172	NM  	2001	8	8	AUS20010500      	1	20010517	G	3260	864202	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR	OUT OF ADJ      	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOOR PROXIMITY SWITCH OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800173	20010808	00173	NM  	2001	8	8	AUS20010501      	1	20010516	G	2910	MS21904W16	ELBOW           			BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					HYDRAULIC SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC SYSTEM LEAKING FROM CRACKED PRESSURE LINE ELBOW LOCATED UNDER NO3 STRUT REAR SAILBOAT. LOSS OF HYDRAULIC	 FLUID.					2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080800175	20010808	00175	NM  	2001	8	8	AUS20010502      	1	20010517	G	7110	13082	PANEL           	RROYCE      	RB211524H36 	BOEING	767   	767*        	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					ENGINE COWLING	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			43385		13082					(AUS) RH ENGINE BULLNOSE SECTION LOCATED AFT OF THE ACOUSTIC PANELMISSING FROM AREA BETWEEN NO4 AND NO7 BLOCKER DOORS. T	HE MISSINGPIECE WAS APPROXIMATELY 2 METERS (6FT) IN LENGTH. DAMAGE CAUSED TO THREE BLOCKER DOORS, COMBUSTOR FAIRING AND 	BLISTER FAIRING.				2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2001080800178	20010808	00178	NM  	2001	8	8	AUS20010503      	1	20010515	G	7110	12756	LINER           	RROYCE      	RB211524D419	BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					ENGINE COWLING	MISSING         	W				O				OTHER                   				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 			6756 		12756					(AUS) NR 1 ENGINE LOW POWER. INVESTIGATION FOUND ONE SECTION OF FRONTFAN ACOUSTIC LINING BETWEEN 2 O'CLOCK AND 4 O'CLOCK	 AREAS MISSING AND ONE AREA OF ICE IMPACT PANEL BETWEEN 1 O'CLOCK AND 5 O'CLOCKAREAS MISSING WITH LOOSE MATERIAL STILL T	RAPPED BY THEENGINE.				2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001080700126	20010807	00126	CE  	2001	8	7	AUS20010504      	1	20010508	G	5554	513300031	BRACKET         	            	            	CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RUDDER/TAB, ATTA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER LOWER HINGE BRACKET CRACKED AT CORNERS.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080800179	20010808	00179	NM  	2001	8	8	AUS20010505      	1	20010501	G	2934	20044000001	TRANSMITTER     			BOEING	737   	7374Y0      	1384705	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					HYD QTY IND	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM B' OIL QUANTITY TRANSMITTER FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800181	20010808	00181	EU  	2001	8	8	AUS20010506      	1	20010520	G	2612	HC924H4913002	FIRE LOOP       			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENGINE	WORN            	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 			20594							(AUS) NR 1 ENGINE FIRE DETECTOR WIRING LOOM CHAFED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800203	20010808	00203	NE  	2001	8	8	AUS20010507      	2	20010521	G	7261		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT & RT	LACK OF LUBE    	W				C				ABORTED TAKEOFF         				K	E	J	FLUID LOSS                	VIBRATION/BUFFET          	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) LT AND RT ENGINES LOW ON OIL.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080700127	20010807	00127	NM  	2001	8	7	AUS20010508      	1	20010517	G	3233	980044503	BEARING         	            	            	PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LANDING GEAR ACT	BROKEN          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		DE	DESCENT        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR ACTUATOR RODEND BEARING FRACTURED.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2001080800205	20010808	00205	CE  	2001	8	8	AUS20010509      	1	20010118	G	5347	50150191	SEAT TRACK      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					CABIN	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS SEAT TRACK CHANNELS PNO 5015019-1 AND PNO 5015019-3CRACKED THROUGH MOUNT HOLES. ONE CHANNEL HAD BEEN REMANU	FACTUREDFROM A LIGHTER MATERIAL AND WAS ALSO SECURED USING COMMERCIAL POP RIVETS. UNAPPROVED PART. PERSONNEL/MAINTENANCE	 ERROR.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001080800206	20010808	00206	NM  	2001	8	8	AUS20010510      	1	20010516	G	5310		PANEL           			BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUEL CELL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO1 MAIN FUEL TANK INTERNAL RIB ACCESS/BAFFLE PANEL LOOSE. THEPANEL WAS FOUND UNSECURED ON THE FLOOR WITH THE MOUN	TING SCREWS CONTAINED IN A CANVAS SCREW BAG ATTACHED TO THE PANEL. THE AREA HAD RECENTLY BEEN ACCESSED DURING D4 INSPECT	ION.PERSONNEL/MAINTENANCE ERROR.				2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080800209	20010808	00209	NM  	2001	8	8	AUS20010511      	1	20010520	G	3246	162T16211	WASHER          			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WHILE CHANGING THE RH NOSEWHEEL DUE TO FOD IT WAS NOTED THAT THENUT SPACER (WASHER) WAS MISSING. THE LT NOSEWHEEL 	WAS ALSOCHECKED WHERE IT WAS FOUND THAT THE WASHER WAS ALSO MISSING.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700128	20010807	00128	NM  	2001	8	7	AUS20010512      	1	20010521	G	3242	215211400	BRAKE           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		BRAKE	LEAKING         	W			    	K	 	 	 	NONE                    				O	B	 	OTHER                     	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			AU	S 	 		3134 							(AUS) LH INBOARD BRAKE UNIT LEAKING FROM PISTON ASSEMBLY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700129	20010807	00129	NM  	2001	8	7	AUS20010513      	1	20010521	G	2520	22303001	STUD            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		PASSENGER COMPAR	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PASSENGER SEAT 9ABC LOOSE DUE TO INBOARD SEAT LEG FLOOR SPREADERSTUD UNSCREWING FROM ANCHOR NUT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700130	20010807	00130	NM  	2001	8	7	AUS20010514      	1	20010508	G	5230	6546921528	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 	 		42473		1359					(AUS) FORWARD CARGO DOOR CRACKED ON THE INSIDE RADIUS OF THE AFT LOWERCORNER EMANATING UPWARDS FROM THE LOWER CROSS BEAM	 ATTACHMENT POINT. CRACK LENGTH APPROXIMATELY 25.4MM (1IN).					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700131	20010807	00131	NM  	2001	8	7	AUS20010515      	1	20010510	G	5511		SPAR            	            	            	BOEING	737   	7374Q8      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		HORIZONTAL STABI	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH HORIZONTAL STABILISER LOWER FORWARD SPAR DAMAGED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700132	20010807	00132	CE  	2001	8	7	AUS20010516      	1	20010412	G	8011	SA539800M015	SPRING          	CONT        	IO520A      	CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520A      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	ENGINE STARTER	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		2    		552408					(AUS) STARTER CLUTCH SPRING FAILED CAUSING DAMAGE TO THE CRANKSHAFT,CAMSHAFT GEAR AND ATTACHING HARDWARE. ROCKWELL HARDN	ESS TESTREVEALED INCONSISTANT HARDNESS.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P25EA	 
2001080700133	20010807	00133	NM  	2001	8	7	AUS20010517      	1	20010402	G	7500	09880645	SEAL            	GARRTT      	HP6DUCT     	BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  	 		            		ENGINE BLEED AIR	FAILED          	W			    	K	 	 	 	NONE                    				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 				09880645					(AUS) RH ENGINE HP6 DUCT SEALS FAILED AND LEAKING.						2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001080800211	20010808	00211	NM  	2001	8	8	AUS20010518      	1	20010508	G	4930	36080004	FCU             			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					APU ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FUEL CONTROL UNIT FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800212	20010808	00212	SW  	2001	8	8	AUS20010519      	1	20010521	G	3234	CA3108E12S200210	CONNECTOR       			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LANDING GEAR	FAULTY          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE CANNON PLUG WIRE BROKEN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2001080800214	20010808	00214	NE  	2001	8	8	AUS20010520      	2	20010519	G	7260	17287	GEARBOX         			FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY65015    	54557	NE  					TURBINE ENGINE	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE HIGH SPEED GEARBOX CHIP DETECTOR AND OIL FILTER CONTAMINATED WITH FINE METAL PARTICLES. FILTER DIFFERENT	IAL PRESSURE POP-UP INDICATOR OPERATED.					2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001080800218	20010808	00218		2001	8	8	AUS20010522      	4	20010522	G	3460	4058650904	CDU             			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				B	O		SMOKE/FUMES/ODORS/SPARKS  	OTHER                     		CR	CRUISE         	1			AU	S 			21528		89020332					(AUS) RT FLIGHT MANAGEMENT COMPUTER CONTROL DISPLAY UNIT (CDU) FAILED. SMOKE IN COCKPIT AND ELECTRICAL BURNING SMELL WIT	H RT CDU KEYPADWARM TO TOUCH.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080800219	20010808	00219	NE  	2001	8	8	AUS20010525      	2	20010523	G	7200	6058T82GO1	ENGINE          			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	RIGHT	FAILED          	W				C				ABORTED TAKEOFF         				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		TO	TAKEOFF        	1			AU	S 			13931							(AUS) RT ENGINE FAILED. INVESTIGATION FOUND SOME DAMAGE TO THE FIRSTSTAGE COMPRESSOR WHEEL AND THE CENTRE BODY RETAINING	 SCREW STUDSSHEARED. BORESCOPE INSPECTION FOUND MAJOR DAMAGE TO THE FIRST STAGE IGVS AND COMPRESSOR WHEEL WITH ONE COMPR	ESSOR BLADE MISSING ABOUT HALF OF THE AXIAL LENGTH. DOWNSTREAM DAMAGE TO OTHER IGVS AND COMPRESSOR STAGES. THERE IS ALSO	 SEVERE HEAT DISTRESS DAMAGETO THE FIRST AND SECOND STAGE GAS GENERATOR TURBINES AND NOZZLESAS WELL AS THE FIRST STAGE P	OWER TURBINE AND NOZZLE. POWERTURBINE COOLING AIR UPPER AND LOWER TRANSFER TUBES SEPARATED AT WELDS. FOUR RETENTION SCRE	WS ON THE CENTRE BODY HAVE SHEARED OFF.	2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001080800220	20010808	00220	NE  	2001	8	8	AUS20010526      	2	20010521	G	7321	FFR105MK4S	REGULATOR       	RROYCE      	RB211524D4  	BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUEL CONTROL	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			AU	S 			2196 		12775					(AUS) NR 3 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080800221	20010808	00221	EA  	2001	8	8	AUS20010527      	2	20010412	G	8530	LW13622	VALVE           			NEWZE 	FU24  	FU24954     	       	WP  	LYC   	O720  	IO720A1B    	41546	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			394  							(AUS) NO2 CYLINDER INLET VALVE DAMAGED IN THE COLLETT RECESS AREA.VALVE STEM CAP SEPARATED AND ONLY ONE COLLETT HALF WAS	 RETAININGTHE VALVE SPRING. METAL PARTICLES FROM THE DAMAGED VALVE WERE FOUND IN THE OIL FILTER AND PARTICLES OF THE MIS	SING COLLETT WERE FOUND IN THE SUCTION FILTER.				1	L	7	1 	3O	3	O	 	A9PC    	1E15				 
2001080800222	20010808	00222	EA  	2001	8	8	AUS20010528      	2	20010418	G	8530	15F1995758	PUSHROD         			NEWZE 	FU24  	FU24954     	       	WP  	LYC   	O720  	IO720A1B    	41546	EA  					ENGINE	DISTORTED       	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 										(AUS) NR 7 CYLINDER EXHAUST VALVE PUSHROD BENT AND PUSHROD SHROUDDAMAGED CAUSING OIL LEAK. INVESTIGATION FOUND THE VALVE	 STEM CAP SEPARATED AND THE PISTON SUFFERING FROM SLIGHT IMPACT DAMAGE WITH THE EXHAUST VALVE. METAL CONTAMINATION OF OI	L FILTER.				1	L	7	1 	3O	3	O	 	A9PC    	1E15				 
2001080800223	20010808	00223	NM  	2001	8	8	AUS20010529      	1	20010507	G	2722	65C370539	PCU             			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					RUDDER ACTUATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			35274		1899AC					(AUS) RUDDER POWER CONTROL UNIT (PCU) INTERNAL LEAK. FOUND DURING INSPECTION IAW ER B73-27-20-15 AND BOEING SL 737-SL-27	-119. WORKSHOP INSPECTION FOUND THE LEAK WITHIN LIMITS.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800224	20010808	00224	NM  	2001	8	8	AUS20010532      	1	20010316	G	4920	38420723	TURBINE         	GARRTT      	GTCP85129H  	BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					APU CORE ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			3480 							(AUS) APU TURBINE WHEEL DISINTEGRATED. SUSPECT CAUSED WAS A BI-HUBFAILURE OF THE TURBINE WHEEL DUE TO UNDETECTABLE HANIU	M OXIDE INCLUSION FORMED DURING THE CASTING PROCESS.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800225	20010808	00225	NM  	2001	8	8	AUS20010533      	1	20010305	G	4920	38420723	TURBINE         	GARRTT      	GTCP85129K  	BOEING	737   	73733A      	1384673	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					APU CORE ENGINE	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			4146 							(AUS) APU TURBINE WHEEL DISINTEGRATED. SUSPECT CAUSED BY TENSILEOVERLOAD ORIGINATING FROM AN UNDETECTABLE SINGLE HAFNIUM	 OXIDEDROSS CASTING INCLUSION.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800226	20010808	00226	NE  	2001	8	8	AUS20010534      	2	20010207	G	7250	230353601	BEARING         	LYC         	ALF502R5    	BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			20481							(AUS) NO2 ENGINE NO6 BEARING FAILED. CONTAMINATION OF ENGINE OILSYSTEM.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800227	20010808	00227	EU  	2001	8	8	AUS20010535      	1	20010426	G	5711		SPAR            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					LT & RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN AREA BETWEEN RIB 13 AND RIB 18.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800228	20010808	00228	EU  	2001	8	8	AUS20010536      	1	20010330	G	5711		SPAR            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN THE AREA BETWEEN RIB 13 AND RIB 18.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800229	20010808	00229	EU  	2001	8	8	AUS20010537      	1	20010301	G	5711		SPAR            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN THE AREA BETWEEN RIB 13 AND RIB 18.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800231	20010808	00231		2001	8	8	AUS20010538      	4	20010528	G	3130		RECORDER        			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					DATA	UNSERVICEABLE   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OPERATIONAL CHECK AND CALIBRATION CHECK OF FLIGHT DATA RECORDER (FDR) NOT CARRIED OUT. PERSONNEL/MAINTENANCE ERROR	.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800232	20010808	00232	EU  	2001	8	8	AUS20010539      	1	20010528	G	5330		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED IN THE AREA BETWEEN FR 35 AND FR 36 ATSTRINGER LOCATIONS 2L AND 3L. CRACK LENGTH 558.8MM (22	IN).					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700134	20010807	00134	NM  	2001	8	7	AUS20010540      	1	20010526	G	3234	4105DA	VALVE           	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LANDING GEAR SEL	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 				2087					(AUS) LANDING GEAR CONTROL SELECTOR VALVE FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800234	20010808	00234	NE  	2001	8	8	AUS20010541      	2	20010526	G	7321	6068T72P09	HMU             	GE          	CT79B       	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	ENGINE	FAULTY          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) HYDROMECHANICAL UNIT (HMU) SUSPECT FAULTY. WORKSHOP INVESTIGATION AND TESTING COULD FIND NO FAULTS.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001080800236	20010808	00236	NM  	2001	8	8	AUS20010543      	1	20010426	G	2751	2061141	INDICATOR       			BOEING	737   	73733A      	1384673	NM  										TE FLAPS	FAULTY          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 			44431		903					(AUS) FLAP POSITION INDICATOR GAVE CONFLICTING LH AND RH FLAP POSITIONS ALTHOUGH THERE WAS NO EFFECT ON ROLL CONTROL. IN	SPECTION OF THE INDICATOR REVEALED MINOR FAULTS BUT THE INDICATOR WAS OK AND NOTLIKELY TO HAVE CAUSED THE FAULT.					2	L	7	2 	4F			RT	A16WE   					 
2001080700135	20010807	00135	WP  	2001	8	7	AUS20010544      	1	20010522	G	6320	A0061	GEARBOX         	            	            	ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  	 		            		MAIN ROTOR GEARB	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				0375					(AUS) MAIN ROTOR GEARBOX CRACKED IN LOWER AREA.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080800237	20010808	00237	CE  	2001	8	8	AUS20010545      	1	20010512	G	2120	CM361210B130	DUCT            			CESSNA	441   	441         	2076020	CE  										CABIN COOLING	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCYCLE MACHINE DUCT DETERIORATED.						1	L	7	2 	3T			RT	A28CE   					 
2001080800238	20010808	00238	NM  	2001	8	8	AUS20010546      	1	20010523	G	2133		VALVE           			BOEING	737   	73733A      	1384673	NM  										CABIN PRESSURE	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PRESSURISATION SYSTEM AUTOMATIC FLOW CONTROL VALVE FAILED TO CLOSE.						2	L	7	2 	4F			RT	A16WE   					 
2001080800240	20010808	00240	NM  	2001	8	8	AUS20010547      	1	20010214	G	2760	BACC2A3A01853FG	CONTROL CABLE   			BOEING	737   	73733A      	1384673	NM  										DRAG CONTROL SYS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) NR 3 FLIGHT SPOILER CONTROL CABLE BROKEN IN THE AREA OF WBL 73.00LT. THE CABLE FAILED APPROXIMATELY 203.2MM (8IN) 	OUTBOARD OF THETURNBARREL. THE FAILURE WAS A RESULT OF RUST (CORROSION) AND WEAR SUSPECT DUE TO INADEQUATE REAPPLICATION	 OF PROTECTIVE INHIBITNG FLUID.				2	L	7	2 	4F			RT	A16WE   					 
2001080800242	20010808	00242	NM  	2001	8	8	AUS20010548      	1	20010529	G	4920	737M49503011	APU             			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					APU BAY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			2976 							(AUS) APU FAULTY. SMOKE AND FUMES IN CABIN. OIL IN BLEED DUCT.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700136	20010807	00136		2001	8	7	AUS20010549      	4	20010528	G	2565	65C1990115	CABLE           			BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH AFT MAIN ENTRY DOOR ESCAPE SLIDE RELEASE CABLES CONTAINED BROKEN STRANDS. FOUND DURING INSPECTION IAW AD	/B737/42, FAA AD 90-12-11 AND EI 734-025-0086 REV09.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800243	20010808	00243		2001	8	8	AUS20010550      	4	20010528	G	2565	80330033	CABLE           		7A126110    	BOEING	747   	747SP38     	1384817	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					ESCAPE SLIDE	OUT OF ADJ      	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 			1328 		G112					(AUS) NO1 RH DOOR SLIDE FAILED TO DEPLOY DURING TEST. INVESTIGATION FOUND THE DOOR EMERGENCY POWER RESERVOIR FIRING CABL	E OUT OFADJUSTMENT AND FAILING TO RUPTURE THE DISC OF THE EPS BOTTLE. THE EPS CABLE WAS ADJUSTED AND THE SLIDE DEPLOYED 	NORMALLY.				2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080800244	20010808	00244	NM  	2001	8	8	AUS20010551      	1	20010531	G	3520	S417T40127	GENERATOR       			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					PASSENGER OXYGEN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 TOILET AND PSU 21L OXYGEN GENERATORS HAD THE RELEASE PINS INCORRECTLY INSTALLED IN THE SAFETY PIN HOLES.PERSO	NNEL/MAINTENANCE ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700137	20010807	00137	CE  	2001	8	7	AUS20010552      	1	20010426	G	5711	501100037	SPAR CAP        	            	            	BEECH 	65    	A658200     	1152805	CE  	LYC   	O480  	IGSO480A1B6 	41529	EA  	HARTZL	HCB3Z	HCB3Z202    	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH WING UPPER SPAR CAP CORRODED IN THE AREA OF THE FORWARD HINGEEDGE AND FORWARD CAP FLANGE.						1	L	7	2 	3O	3	O	 	3A20    	E284	5	C	P907	 
2001080800245	20010808	00245	NM  	2001	8	8	AUS20010554      	1	20010531	G	3320	60B4002615	TRANSFORMER     			BOEING	747   	747238B     	1384828	NM  										CABIN	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) SIDE WALL LIGHT BALLAST LOCATED IN THE AREA ABOVE SEAT 23J BURNTAND DAMAGED. INVESTIGATION FOUND PIN 14 OF PLUG D2	292P IN THE LIGHTING TRANSFORMER PNO 60B40026-15 DAMAGED.					2	L	7	4 	4F			 	A20WE   					 
2001080800248	20010808	00248	SO  	2001	8	8	AUS20010555      	1	20010530	G	2621	89777601	SQUIB           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14RF	14RF9       	NE  	FIRE BOTTLE	UNAPPROVED PART 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FIRE BOTTLE SQUIB FAULTY (MODIFIED). THE FIRING DEVICE HAD BEEN CUT OFF AND THE SQUIB USED AS A TRANSPORT BLAN	K. THE SQUIB HAD NOT BEEN REPLACED WHEN THE FIRE BOTTLE WAS FITTED TO THE AIRCRAFT. UNAPPROVED PART.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE	 
2001080700138	20010807	00138	SW  	2001	8	7	AUS20010556      	1	20010528	G	3213	ED12758	PIN             	            	            	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR CLEVIS PIN CRACKED FROM BOLT HOLE. FOUND DURING INSPECTION IAW SL 376.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2001080700139	20010807	00139		2001	8	7	AUS20010557      	4	20010518	G	3452	74LS02	TRANSPONDER     	NARCO       	AT150       	CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ATC TRANSPONDER	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 				18821					(AUS) TRANSPONDER GIVING FALSE ALTITUDE READINGS.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001080700140	20010807	00140	EU  	2001	8	7	AUS20010558      	1	20010519	G	8012	P90018	VALVE           	GARRTT      	TPE3312201A 	STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE START VAL	FAULTY          	W			    	K	 	 	 	NONE                    				E	M	 	VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 	 				P90018					(AUS) START PRESSURE REGULATOR INTERNAL FAULT. EGT OVERTEMP ON START. OVERTEMP INSPECTION FOUND NO DEFECTS WITH THE ENGI	NE.					1	H	7	2 	3T	4	T	NT	A15EU   	E3WE	6	C	P15EA	 
2001080700141	20010807	00141	WP  	2001	8	7	AUS20010559      	2	20010524	G	7240	P90018	GASKET          	GARRTT      	TPE3312201A 	STBROS	SC7   	SC7SERIES3  	8100512	EU  	GARRTT	TPE331	TPE3312201A 	 	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	TURBINE ENGINE C	FAILED          	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 	 				P90018					(AUS) LH ENGINE IGNITER PLUG BLANK GASKET FAILED.						1	H	7	2 	3T	4	T	NT	A15EU   	E3WE	6	C	P15EA	 
2001080800249	20010808	00249	NM  	2001	8	8	AUS20010560      	1	20010507	G	2722	65C370539	PCU             			BOEING	737   	737377      	       	NM  										RUDDER ACTUATOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			35274		1899AC					(AUS) RUDDER POWER CONTROL UNIT (PCU) LEAKING INTERNALLY.						2	L	7	2 	4F			RT	A16WE   					 
2001080700142	20010807	00142	EU  	2001	8	7	AUS20010561      	1	20010527	G	2820		SWITCH          	            	            	FOKKER	F28   	F28MK0100   	4990807	EU  	RROYCE	TAY   	TAY62015    	04564	NE  	 		            		AIRCRAFT FUEL DI	FAULTY          	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			TO	TAKEOFF        	1			AU	S 	 									(AUS) FUELLING CONTROL PANEL POWER SWITCH FAULTY. PANEL POWER REMAINEDON WITH THE SWITCH IN THE OFF' POSITION. INVESTIGA	TION FOUND THE ACCESS PANEL CAM OPERATING THE PANEL POWER SWITCH WHEN THE PANEL  IS CLOSED WAS OUT OF ADJUSTMENT AND NOT	 OPERATING THESWITCH.				2	L	7	2 	4F	4	F	RT	        	E25NE				 
2001080800251	20010808	00251	NE  	2001	8	8	AUS20010562      	2	20010531	G	7200	6058T87G01	ENGINE          			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	RIGHT	OVERHEATED      	W				A				UNSCHED LANDING         				E	M		VIBRATION/BUFFET          	OVER TEMP                 		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE OVERTEMPED DURING START UP AFTER INTENTIONAL SHUTDOWN. OVERTEMP WAS ABOVE 1000 DEGREES FOR 9 SECONDS. PE	RSONNEL ERROR.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL	 
2001080800253	20010808	00253	NM  	2001	8	8	AUS20010563      	1	20010420	G	2752	5701802	JACKSCREW       			BOEING	737   	737377      	       	NM  										TE FLAPS	CORRODED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 			18978		2773					(AUS) NR 3 TRAILING EDGE FLAP JACKSCREW CORRODED. SPALLING ON SCREWJACKBALL AND NUT. SUSPECT INCORRECT LUBRICANT USED.						2	L	7	2 	4F			RT	A16WE   					 
2001080800254	20010808	00254	EU  	2001	8	8	AUS20010564      	1	20010531	G	3213	350A41107620	SKID SHOE       			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN LANDING	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) RT SIDE SKID HEEL AND ATTACHMENT RING SEPARATED FROM AIRCRAFT.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080800256	20010808	00256	NM  	2001	8	8	AUS20010565      	1	20010602	G	3240		BRAKE           			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					PARKING BRAKE	FAULTY          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) PARKING BRAKES WOULD NOT RELEASE.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001080700143	20010807	00143	NM  	2001	8	7	AUS20010566      	1	20010602	G	3230	651781914	ACTUATOR        	            	654462514   	BOEING	737   	737376      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		LANDING GEAR RET	FAILED          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		AP	APPROACH       	1			AU	S 	 		29119		SC478					(AUS) NOSE LANDING GEAR DOWNLOCK ACTUATOR FAILED AT RODEND.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800257	20010808	00257	SW  	2001	8	8	AUS20010567      	1	20010604	G	3230	OAS54535	DRAG BRACE      			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DRAG BRACE CRACKED IN UPPER GREASE FITTING SPOT FACE WEB. FOUND DURING FLUORESCENT DYE PENETRANT	 INSPECTION IAW AD/SWSA/226/89 AND SB 227-32-043.					2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
2001080800259	20010808	00259	EU  	2001	8	8	AUS20010568      	1	20010525	G	2910	D2907019000200	MANIFOLD        			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYDRAULIC SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC POWER TRANSFER UNIT (PTU) MANIFOLD CRACKED AND LEAKING IN AREA OF CHECK VALVE MOUNTING FLANGE.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800261	20010808	00261	NM  	2001	8	8	AUS20010569      	1	20010602	G	3250		CONTROL UNIT    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NLG STEERING	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) AIRCRAFT STEERING SYSTEM INTERMITTENT IN OPERATION. THE CABLESAND PULLEYS WERE CHECKED OK AND THE RUDDER PEDAL INT	ERCONNECT MECHANISM WAS LUBRICATED.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080800263	20010808	00263	SW  	2001	8	8	AUS20010570      	1	20010531	G	2160	BYLB504371	VALVE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	CABIN TEMP	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MIXING VALVE ACTUATOR FAILED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2001080800265	20010808	00265	SO  	2001	8	8	AUS20010571      	2	20010522	G	8520	466080	CRANKCASE       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	MISOVERHAULED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CRANKCASE HALVES ASSEMBLED WITH A CONSIDERABLE AMOUNT OF SEALANT BETWEEN THE MATING FACES OF THE MAIN BEARI	NG PEDESTALS. THIS RESULTED IN CRANKCASE FRETTING AND BEARING MOVEMENT. PERSONNEL/MAINTENANCE ERROR. INCORRECT ASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001080800266	20010808	00266	NM  	2001	8	8	AUS20010572      	1	20010531	G	3246	165T01100530	WHEEL           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1154 							(AUS) NR 1 MAIN WHEEL TIRE REMOVED FOR WEAR. DURING REMOVAL THE WHEELNUT RETENTION BOLTS, WASHER AND NUTS WERE FOUND TO 	BE ADRIFT AND THE WHEEL NUT WAS LOOSE AND BACKED OFF APPROXIMATELY FIVE TURNS.THE ANTI-SKID TRANSDUCER HOUSING WAS DAMAG	ED. THE WHEEL NUT HAD IMPACT DAMAGE AND WHEEL NUT WASHER HAD EVIDENCE OF GALLING. NR 1 FRONT WHEEL ASSEMBLY REPLACED.ALS	O REPLACED WERE THE ANTI-SKIDTRANSDUCER PNO 140-025-2, HUB CAP PNO 165T0101-107, WHEEL RETENTION NUT PNO 161T1204-1 ALON	G WITH RETENTION BOLTS WASHERS AND NUTS.		2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080800267	20010808	00267	NM  	2001	8	8	AUS20010573      	1	20010603	G	7603		CABLE           	RROYCE      	RB211524D4  	BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					POWER LEVER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION OF ENGINE THRUST CONTROL CABLES, FITTINGS AND PULLEYS IAW EI 743-076-0002 REV01 FIVE SEPARATE AR	EAS OF CABLEWEAR WERE FOUND. FOUND DURING INSPECTION IAW AD/B747/229 AND FAAAD 2000-05-30 AMDT 39-11640.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080800268	20010808	00268	WP  	2001	8	8	AUS20010574      	2	20010605	G	7210	31071627	GEAR            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			2490 							(AUS) RT ENGINE FAILED. ENGINE OIL SYSTEM HEAVILY CONTAMINATED WITH METAL. INVESTIGATION FOUND FAILURE OF THE SUN/BULL G	EAR.APPROXIMATELY 12 PERCENT OF THE BULL GEAR RIM HAD SEPARATED. DISASSEMBLY OF THE BULL GEAR FROM THE SUN GEAR REVEALED	 SEVERE FRETTING BETWEEN THE SUN GEAR REAR RACE FACE TO BULL GEAR INNER FORWARDINNER RACE FACE AND IN THE SUN GEAR TO BU	LL GEAR SPLINES.			2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001080800269	20010808	00269	CE  	2001	8	8	AUS20010575      	1	20010522	G	2933	51170071R	SIGHT GLASS     			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	HYD QUANTITY	SPLIT           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM SIGHT TUBE SPLIT. PARTIAL LOSS OF HYDRAULICFLUID. SIGHT TUBE HAD ONLY RECENTLY BEEN REPLACED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080700144	20010807	00144	CE  	2001	8	7	AUS20010576      	1	20010418	G	2932	991028710	PRESSURE SWITCH 	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	HYDRAULIC PRESSU	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HYDRAULIC PRESSURE SWITCH FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080700145	20010807	00145	SO  	2001	8	7	AUS20010577      	2	20010521	G	7414		IMPULSE COUPLING	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAGNETO IMPULSE COUPLING WORN BEYOND LIMITS. FOUND DURINGINSPECTION IAW AD/ELEC/68.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080700146	20010807	00146	CE  	2001	8	7	AUS20010578      	1	20010529	G	2410	646655	COUPLING        	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	ALTERNATOR-GENER	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ALTERNATOR ELASTOMER DRIVE COUPLING SLIPPING. FOUND DURING INSPECTION IAW MEB 01-3.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080700147	20010807	00147	EA  	2001	8	7	AUS20010579      	2	20010604	G	7414	ES10357426	DISTRIBUTOR     	BENDIX      	101630509   	PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	2D36C	2D36C28     	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 	 				A34026					(AUS) MAGNETO DISTRIBUTOR BLOCK CENTRAL BUSH LOOSE ALLOWING THE DISTRIBUTOR GEAR TO PARTIALLY DISENGAGE AND SHEAR THE TE	ETH.					1	L	7	1 	3O	3	O	 	1A15    	E295	5	C	P901	 
2001080700148	20010807	00148	NM  	2001	8	7	AUS20010580      	1	20010424	G	3520	417T42050	OXYGEN MASK     	            	            	BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		PASSENGER OXYGEN	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PASSENGER OXYGEN MASKS (7OFF) SUSPECT FAULTY. FOUND DURINGINSPECTION IAW AD/B767/125.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080800270	20010808	00270	NM  	2001	8	8	AUS20010581      	1	20010406	G	2450	941D3352	CIRCUIT BREAKER 			BOEING	737   	737377      	       	NM  										AC POWER DISTRIB	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			42099							(AUS) NR 1 GENERATOR BREAKER FAILED.						2	L	7	2 	4F			RT	A16WE   					 
2001080700149	20010807	00149	NE  	2001	8	7	AUS20010582      	2	20010227	G	7321	77390010	FCU             	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		7600 		F12203					(AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080800271	20010808	00271	NM  	2001	8	8	AUS20010583      	1	20010605	G	5610	NAS71037	SCREW           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	WINDOW	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT DECK SIDE WINDOW REPLACEMENT BOLTS TOO LONG. SB DHC8-56-05 SPECIFIES SCREW PNO NAS7103-7 WHICH WHEN FITTED 	ARE TOO LONG ANDBECOME SHANK BOUND. CONTACT WITH THE AIRCRAFT MANUFACTURER FOUND THAT THE SCREWS SHOULD BE PNO NAS7103-6	. THE RETORQUE PERIOD REQUIREMENT IN THE SERVICE BULLETIN IS ALSO SUSPECT BEING STATEDAS AFTER 24 HOURS'.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800272	20010808	00272	NM  	2001	8	8	AUS20010584      	1	20010605	G	2910	B4706640192	HOSE            			BOEING	737   	737377      	       	NM  										HYDRAULIC SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LH MAIN LANDING GEAR UPLOCK ACTUATOR HOSE LEAKING. METALCONTAMINATION OF NO1 HYDRAULIC PUMP FILTERS.						2	L	7	2 	4F			RT	A16WE   					 
2001080800273	20010808	00273	NM  	2001	8	8	AUS20010585      	1	20010601	G	2621	301000223	EXTINGUISHER    			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					LAVATORY	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO AUTOMATIC FIRE EXTINGUISHER FITTED TO THE FORWARD MID LAVATORY M-37. FOUND DURING INSPECTION IAW CAA AD GENERAL	/48 AND FAA AD74-08-09.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700150	20010807	00150	SO  	2001	8	7	AUS20010586      	1	20010515	G	8120	4066109020	TURBOCHARGER    	LYC         	TIO540A2C   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	EXHAUST TURBOCHA	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		415  							(AUS) LH ENGINE TURBOCHARGER LEAKING OIL. SUSPECT BEARING OR SEAL DAMAGED. AIRCRAFT HAD BEEN OUT OF SERVICE FOR APPROXIM	ATELY NINEMONTHS FOR A SPAR REPLACEMENT.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080700151	20010807	00151	SO  	2001	8	7	AUS20010587      	2	20010604	G	8550	S19644	DRAIN VALVE     	CONT        	IO520F      	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	RECIPROCATING EN	CRACKED         	W			    	K	E	 	 	NONE                    	ENGINE SHUTDOWN         			E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 	 									(AUS) ENGINE OIL DRAIN VALVE SHAFT CRACKED RADIALLY. OIL LEAKING ON SHUTDOWN.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P3EA	 
2001080800274	20010808	00274	EU  	2001	8	8	AUS20010588      	1	20010601	G	7930	154	CONNECTOR       			AEROSP	AS365 	AS365N2     	8680815	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					CHIP DETECTOR	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE CHIP DETECTOR WIRING FAULTY.						1	G	7	2 	3U	3	U	RT	H10EU   	E19EU				 
2001080800275	20010808	00275	EU  	2001	8	8	AUS20010589      	1	20010528	G	3510	MC1012100	OXYGEN MASK     			AMD   	FALC50	FALCON900   	2700160	EU  										COCKPIT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS OXYGEN MASK LEAKING AT OXYGEN SUPPLY QUICK DISCONNECT. THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND	 IS FOR INFORMATION ONLY. AIRCRAFT SERIAL A26-073.					2	L	7	3 	4F			RT	A46EU   					 
2001080800276	20010808	00276	EU  	2001	8	8	AUS20010590      	1	20010604	G	3240	C24837010	MANIFOLD        			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			29336		B728					(AUS) LT BRAKE MANIFOLD LEAKING. INVESTIGATION FOUND A CRACK LOCATEDBETWEEN PORT A (SUPPLY LINE) AND FILTER CHAMBER.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800277	20010808	00277	SO  	2001	8	8	AUS20010591      	2	20010517	G	8530		EXHAUST VALVE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			141  							(AUS) NR 2 CYLINDER EXHAUST VALVE STICKING IN VALVE GUIDE. FURTHER INSPECTION FOUND ALL EXHAUST VALVES STICKING AND ALL 	EXHAUST PUSHRODS BENT. SUSPECT VAVLE TO GUIDE CLEARANCE INSUFFICIENT AT MANUFACTURE.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001080700152	20010807	00152	NM  	2001	8	7	AUS20010592      	1	20010528	G	5610	NP15790114	WINDSHIELD      	            	            	DHAV  	DHC8  	DHC8*       	       	NM  	      		            			 		            		FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) RH WINDSHIELD CRACKED.						2	H	7	2 	4T			RT	A13NM   					 
2001080700153	20010807	00153	SW  	2001	8	7	AUS20010593      	1	20010529	G	5302	206023119063	SUPPORT         	            	            	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		ROTORCRAFT TAIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HORIZONTAL STABILISER UPPER LH SUPPORT CRACKED LONGITUDINALLY ALONG BEND RADIUS. CRACK LENGTH 30MM (1.181IN).						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080700154	20010807	00154	SW  	2001	8	7	AUS20010594      	1	20010530	G	5302	206032400027	BULKHEAD        	            	            	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		ROTORCRAFT TAIL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAILBOOM BULKHEAD CRACKED ALONG THE BEND RADIUS OUTER CIRCUMFERENCE AT THE TOP RH BOLT ATTACHMENT INTERCOSTAL. CRA	CKLENGTH 10MM (0.393IN).					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080800278	20010808	00278	EU  	2001	8	8	AUS20010595      	1	20010517	G	2760		SWITCH          			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DRAG CONTROL	OUT OF ADJ      	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) LIFT DUMPER MANIFOLD NR 2 BYPASS SWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800279	20010808	00279	NE  	2001	8	8	AUS20010597      	2	20010518	G	7310		FILTER          			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  					ENGINE FUEL	CONTAMINATED    	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 HP OUTLET FUEL FILTER CONTAMINATED WITH A DARK BROWN SLUDGE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001080700155	20010807	00155	EU  	2001	8	7	AUS20010598      	1	20010519	G	3241	95427193	GENERATOR       	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		BRAKE ANTISKID S	FAULTY          	W			    	K	 	 	 	NONE                    				O	P	 	OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 	 		3588 		OCT7043					(AUS) RH INBOARD WHEEL SPEED GENERATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700156	20010807	00156	EU  	2001	8	7	AUS20010601      	1	20010526	G	2410		GENERATOR       	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		ALTERNATOR-GENER	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 									(AUS) NO1 GENERATOR FAILED. SUSPECT FAULTY CONSTANT SPEED DRIVE SWITCH.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700157	20010807	00157	EU  	2001	8	7	AUS20010602      	1	20010530	G	2421	976J2555	GENERATOR       	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		AC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			AU	S 	 		397  		MC823					(AUS) NO2 (RH) GENERATOR FAILED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700158	20010807	00158	EU  	2001	8	7	AUS20010603      	1	20010526	G	5330		SKIN            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		FUSELAGE MAIN, P	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TOP FUSELAGE SKIN CRACKED IN AREA BETWEEN STN3845 AND STN4875.CRACK LENGTH 406.4MM (16IN).						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800280	20010808	00280	WP  	2001	8	8	AUS20010604      	2	20010604	G	7250	31038381	ROTOR           			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE T3 TURBINE BLADE DAMAGED.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001080800281	20010808	00281	NM  	2001	8	8	AUS20010605      	1	20010221	G	2540	10101000BA	VALVE           			BOEING	737   	737377      	       	NM  										LAVATORIES	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3340 							(AUS) TOILET DRAIN VALVE FAULTY. FOUND DURING TESTING IAW ER B73-30-11.						2	L	7	2 	4F			RT	A16WE   					 
2001080700159	20010807	00159	NM  	2001	8	7	AUS20010607      	1	20010520	G	2750	7321870011	VALVE           	            	            	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		TRAILING EDGE FL	FAILED          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 				93043					(AUS) FLAP/SLAT SHUTOFF VALVE FAILED.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080800282	20010808	00282	EU  	2001	8	8	AUS20010608      	1	20010607	G	2910	AE7064588	HOSE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	HYDRAULIC SYSTEM	FAILED          	W				C				ABORTED TAKEOFF         				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 			21142							(AUS) NOSE LANDING GEAR HYDRAULIC UP LINE FAILED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE	 
2001080800283	20010808	00283	SO  	2001	8	8	AUS20010609      	2	20010525	G	8530	641917	CYLINDER        			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1500 							(AUS) ENGINE CYLINDER ROCKER SHAFT SUPPORT CRACKED AND SEPARATED FROM CYLINDER HEAD.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001080800284	20010808	00284	EA  	2001	8	8	AUS20010611      	2	20010613	G	8530		PISTON RING     			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1015 							(AUS) NR 3 CYLINDER FIRST AND SECOND PISTON RINGS BROKEN. PISTON LANDERODED. NR 4 CYLINDER NO1 PISTON RING BROKEN. PISTO	N RINGS WERECAST IRON IN CHROME CYLINDERS. SMALL AMOUNT OF ALUMINIUM ALLOYMETAL IN OIL FILTER.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2001080700160	20010807	00160	CE  	2001	8	7	AUS20010612      	1	20010608	G	5610		WINDSHIELD      	CESSNA      	421C        	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FLIGHT COMPARTME	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WINDSHIELD LEAKING. HEATING SYSTEM PIPES BROKEN CAUSING EXCESSHEAT AND WARPING OF WINDSHIELD.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001080800285	20010808	00285	CE  	2001	8	8	AUS20010613      	1	20010612	G	6120	5052447815	SPRING          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LH PROPELLER PITCH CONTROL LEVER FEATHER DETENT FEEL SPRING BROKEN.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2001080700161	20010807	00161	SO  	2001	8	7	AUS20010614      	2	20010612	G	7421	RHB32E	SPARK PLUG      	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	SPARK PLUG/IGNIT	CORRODED        	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) LH ENGINE SPARK PLUG CORRODED AND FOULED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080800286	20010808	00286	NM  	2001	8	8	AUS20010615      	1	20010508	G	4930	36080004	FCU             			BOEING	737   	737377      	       	NM  										APU ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND PISTON ANDSHAFT SET IN TIMER WORN. THE GOVERNOR SHAFT WAS WORN. 	FLYWEIGHT TOES WORN. PACKINGS AND SEALS FLAT AND WORN.					2	L	7	2 	4F			RT	A16WE   					 
2001080800287	20010808	00287	NM  	2001	8	8	AUS20010616      	1	20010426	G	2822	6075504	PUMP            			BOEING	747   	747238B     	1384828	NM  										FUEL BOOST PUMP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			7670 		069714832A					(AUS) NR 3 AFT FUEL BOOST PUMP LEAKING FROM AREA BEHIND ELECTRICAL CONNECTOR.						2	L	7	4 	4F			 	A20WE   					 
2001080800288	20010808	00288	NM  	2001	8	8	AUS20010617      	1	20010415	G	5320		WEB             			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL WELL UPPER WEB LOCATED AT STN291 CRACKED AT RBL19 ANDLBL19.						2	L	7	4 	4F			 	A20WE   					 
2001080700162	20010807	00162	NM  	2001	8	7	AUS20010618      	1	20010420	G	5313	146T30037	STRINGER        	            	            	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		FUSELAGE MAIN, L	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) STRINGER 39L BADLY CORRODED IN THE AREA LOCATED BETWEEN BS1285AND BS1307. APPROXIMATELY 304.8MM (12IN) OF THE HAT 	SECTIONED STRINGER LOWER CHANNEL WAS SEVERELY CORRODED WITH PORTIONS OF THE CHANNEL TOTALLY DESTROYED.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080800289	20010808	00289	NE  	2001	8	8	AUS20010619      	2	20010616	G	7200		ENGINE          			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2	LEAKING         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 ENGINE LEAKING CONTAMINATED AIR INTO CABIN.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800290	20010808	00290	CE  	2001	8	8	AUS20010620      	1	20010612	G	2752	100384040	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	TE FLAPS	BURNED OUT      	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			514  							(AUS) TRAILING EDGE FLAP ELECTRIC MOTOR WINDINGS BURNT OUT. SUSPECT CAUSED BY FAILURE OF DYNAMIC BRAKE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001080700163	20010807	00163	CE  	2001	8	7	AUS20010621      	1	20010608	G	3213	45815237	PIN             	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	D3AF32C35   	GL  	MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH MAIN LANDING GEAR LOWER TORQUE LINK PINS CRACKED IN THE POSITIONING HOLES.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001080800291	20010808	00291	EU  	2001	8	8	AUS20010622      	1	20010616	G	5330		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED IN AREA LOCATED IMMEDIATELY AFT OF FRAME 29 BENEATH THE WING ROOT DOUBLER. FOUND DURING INSP	ECTION IAWISB53-144 AND AD/BAE146/70.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800292	20010808	00292	NE  	2001	8	8	AUS20010623      	2	20010613	G	7230	230318706	SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			4333 							(AUS) NR 2 ENGINE OIL LEAKING IN BLEED BAND AREA. OIL SMELL IN COCKPIT.SUSPECT CAUSED BY NO1 OIL SEAL WORN AND LEAKING.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080800293	20010808	00293	EU  	2001	8	8	AUS20010624      	1	20010607	G	3240	C24837010	MANIFOLD        			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					B353					(AUS) LT MAIN LANDING GEAR BRAKE SERVO MANIFOLD LEAKING FROM AREA OFFILTER CAP. INVESTIGATION FOUND A 19.05MM (0.75IN) C	RACK IN THE FILTER CHAMBER THREADS.					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080700164	20010807	00164	CE  	2001	8	7	AUS20010625      	1	20010603	G	2720	07331131	CLIP            	            	            	CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	RUDDER CONTROL S	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH RUDDER STOP T' CLIP PNO 733113-1 TO SUPPORT PNO 1231021-8 ATTACHMENT RIVETS (2OFF) PNO MS20426-AD4 SHEARED. SUS	PECT CAUSED  BY WIND GUSTS.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001080800294	20010808	00294	NM  	2001	8	8	AUS20010626      	1	20010615	G	5330	149T7500145	PANEL           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) FUSELAGE PANEL MISSING FROM LH WING ROOT AREA LOCATED FORWARD OFTHE LH OFF-WING ESCAPE SLIDE DOOR. SCORE MARKS EVI	DENT ON ADJACENT WING TO BODY FAIRING AND FUSELAGE AT STN1131.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080800295	20010808	00295	NM  	2001	8	8	AUS20010627      	1	20010618	G	7500	65B899268	DUCT            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					ENGINE BLEED AIR	FAILED          	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 3 ENGINE STRUT DUCT HOLED AND DEFORMED. INVESTIGATION COULD FIND NO HEAT DAMAGE IN THE STRUT.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080700165	20010807	00165	CE  	2001	8	7	AUS20010629      	1	20010608	G	5711	0001100132	SPAR CAP        	BEECH       	58          	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	D3AF32C35   	GL  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				TH181					(AUS) RH WING UPPER SPAR CAP CONTAINED PITTING CORROSION IN AN AREA LOCATED 355.6MM (14IN) OUTBOARD OF THE ENGINE NACELL	E. THE PITTED AREA MEASURES APPROXIMATELY 152.4MM (6IN) SPANWISE AND 19.05MM(0.75IN) CHORDWISE. DEPTH OF CORROSION APPRO	XIMATELY 0.508MM(0.020IN). FOUND FOLLOWING STRIPPING FOR REPAINT.				1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2001080700166	20010807	00166	NM  	2001	8	7	AUS20010630      	1	20010127	G	2910	13206001	SWITCH          	            	13206XXX    	BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		HYDRAULIC SYSTEM	FAULTY          	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 									(AUS) LH HYDRAULIC TAIL SHUTOFF VALVE SWITCH MODULE FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001080800296	20010808	00296	NM  	2001	8	8	AUS20010631      	1	20010619	G	2720	2417001007	MODULE          			BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					RUDDER CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			18014		105					(AUS) RUDDER CONTROL MODULE LEAKING.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080800297	20010808	00297	CE  	2001	8	8	AUS20010632      	1	20010611	G	5343	12116013	FITTING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH OUTBOARD LANDING GEAR ATTACHMENT FITTING CRACKED. CRACK LENGTH 19.05MM (0.75IN).						1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001080700167	20010807	00167	EA  	2001	8	7	AUS20010633      	2	20010530	G	8520	38125015	STUD            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				O	E	K	OTHER                     	VIBRATION/BUFFET          	FLUID LOSS                	IN	INSP/MAINT     	1			AU	S 	 				L778561A					(AUS) LH ENGINE NO3 CYLINDER HOLDDOWN STUDS BROKEN. CYLINDER WAS HELD IN PLACE BY THE THROUGH BOLTS ONLY.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800298	20010808	00298	EU  	2001	8	8	AUS20010634      	1	20010619	G	6220	350A31190703	STARFLEX        	AEROSP      	355A310002  	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					MAIN ROTOR HEAD	DEBONDED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 					M1803					(AUS) MAIN ROTOR STAR BEARING BUSH DEBONDED AND MOVED OUTBOARD ALLOWING THE MAIN ROTOR BLADE TO LAG AND CAUSE LATERAL VI	BRATION.					1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2001080800299	20010808	00299	NM  	2001	8	8	AUS20010635      	1	20010618	G	2150	7744694	ACM             			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					CABIN COOLING SY	FAULTY          	W				D				RETURN TO BLOCK         				F	B		FLT CONT AFFECTED         	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			AU	S 			668  							(AUS) NR 1 AIRCONDITIONING SYSTEM AIR CYCLE MACHINE FAULTY.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080800301	20010808	00301	NE  	2001	8	8	AUS20010636      	2	20010617	G	8520		MASTER ROD      			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE NR 5 CYLINDER MASTER ROD FAILED AT BASE. LOSS OF ENGINEOIL.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001080800302	20010808	00302	EU  	2001	8	8	AUS20010637      	1	20010607	G	3240	C24837010	MANIFOLD        			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					B353					(AUS) LH MAIN LANDING GEAR BRAKE SERVO MANIFOLD CRACKED. INVESTIGATIONFOUND A CRACK IN THE FILTER CHAMBER THREADS. CRACK	 LENGTH 19.05MM (0.75IN).					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800303	20010808	00303	EU  	2001	8	8	AUS20010638      	1	20010510	G	5343	D5337061320200	FITTING         			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS CRACKED FROM FASTENERHOLES. FOUND DURING INSPECTION IAW SB A320-53-1135 A	ND ANSETT ERA32-53-40-9C.					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800304	20010808	00304	NM  	2001	8	8	AUS20010639      	1	20010617	G	7110	3859741B12130620	BRACKET         	GE          	CF680C2     	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					ENGINE COWLING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					R648117					(AUS) NR 1 ENGINE INBOARD THRUST REVERSER COWL V' BAND HOOK BRACKET BROKEN.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700168	20010807	00168	SW  	2001	8	7	AUS20010640      	1	20010603	G	2460	A1077V	RELAY           	            	            	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  	 		            		DC POWER DISTRIB	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 									(AUS) GENERATOR LINE CONTACT RELAY FAULTY.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080800305	20010808	00305	SW  	2001	8	8	AUS20010641      	1	20010606	G	2910	2281032135	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	ROTOL	R321	R321482F8   	GL  	HYDRAULIC SYSTEM	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC PIPE CHAFING AGAINST ADJOINING PIPE. LOSS OF HYDRAULICSYSTEM FLUID.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001080700169	20010807	00169	SW  	2001	8	7	AUS20010642      	1	20010614	G	5740	AN616	BOLT            	            	            	BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2D     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING, ATTACH FIT	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LOWER RH SIDE STRUT LOWER BOLT SEIZED. FOLLOWING BOLT REMOVAL ITWAS FOUND TO BE VERY RUSTED AND PITTED.						1	H	7	1 	3O	3	O	 	A759    	E274	5	N	P88614	 
2001080700170	20010807	00170	CE  	2001	8	7	AUS20010643      	1	20010601	G	2720	530040050	CONTROL CABLE   			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	RUDDER CONTROLS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) YAW DAMPER CABLE FRAYED AND STRANDS BROKEN IN AREA WHERE THECABLE PASSES INTO THE TERMINAL FITTING AT THE RUDDER B	ELLCRANK.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2001080800307	20010808	00307	NM  	2001	8	8	AUS20010644      	1	20010620	G	2131	7120977	CONTROLLER      			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					CABIN PRESSURE	FAULTY          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					79G1173					(AUS) PRESSURISATION SYSTEM OUTFLOW VALVES SLIGHTLY OPEN. INVESTIGATION COULD FIND NO CAUSE OF THE DEFECT. THE CABIN PRE	SSURE CONTROLLERWAS REPLACED BUT FOUND TO SERVICEABLE WHEN WORKSHOP TESTED.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080700171	20010807	00171	CE  	2001	8	7	AUS20010645      	1	20010612	G	2434		BEARING         	            	ALV9510R    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 		18   							(AUS) LH ALTERNATOR. INVESTIGATION FOUND REAR BEARING COLLAPSED CAUSING DRIVE ADAPTER FAILURE AND METAL CONTAMINATION OF	 THE ENGINE.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001080700172	20010807	00172	CE  	2001	8	7	AUS20010647      	1	20010621	G	3710	212CW	PUMP            	AIRBORNE    	212CW       	BEECH 	55    	D55         	1152730	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	VACUUM DISTRIBUT	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			NR	NOT REPORTED   	1			AU	S 	 				23J119					(AUS) LH ENGINE DRIVEN VACUUM PUMP ROTOR SEIZED AND DRIVESHAFT SHEARED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2001080700173	20010807	00173	EA  	2001	8	7	AUS20010648      	2	20010531	G	8540	67583	GEAR            	LYC         	VO540C2A    	HILLER	UH12  	UH12E       	4360122	WP  	LYC   	O540  	VO540C2A    	41532	EA  	 		            		RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	Y	 	VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			AU	S 	 				L146243					(AUS) ENGINE DRIVE GEAR PNO 67583 HAD SHEARED ALL THE BOLTS ATTACHING IT TO ACCESSORY DRIVE PNO 67609.						1	G	7	1 	3O	3	O	 	4H11    	E304				 
2001080800315	20010808	00315	NM  	2001	8	8	AUS20010649      	1	20010621	G	3244	A2409	TIRE            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			9652 							(AUS) LT REAR INBOARD MAIN BODY GEAR TYRE (NO4) FAILED. DAMAGE CAUSED TO FUSELAGE AND FAIRINGS AND LANDING GEAR WIRING L	OOM.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080700174	20010807	00174	SW  	2001	8	7	AUS20010650      	1	20010623	G	5313	206031314037	LONGERON        	BELL        	206L1       	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		FUSELAGE MAIN, L	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		10824		45323					(AUS) FUSELAGE LONGERON CRACKED BETWEEN TWO RIVETS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080800316	20010808	00316	EU  	2001	8	8	AUS20010652      	1	20010622	G	5610	NP1701012	WINDSHIELD      			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					96249H6419					(AUS) RT A' WINDSHIELD ASSEMBLY OUTER PANE SHATTERED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800320	20010808	00320	EU  	2001	8	8	AUS20010653      	1	20010607	G	5210	FGFB222030060A2	CLEVIS          			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					PAX/CREW DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ENTRY DOOR COMPENSATING SPRING CLEVIS CRACKED ACROSS ALL THREE CABLE ATTACHMENT LUGS. AIRCRAFT SERIAL NUMBER 	A26-074.FLEET INSPECTION FOUNDTHE CLEVIS CRACKED ON ALL OTHER AIRCRAFTIN THE RAAF FLEET. THIS DEFECT WAS RECEIVED FROM T	HE RAAF AND ISENTERED FOR INFORMATION ONLY.				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2001080800322	20010808	00322		2001	8	8	AUS20010655      	4	20010626	G	3418	18617RX	DETECTOR        			REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	STALL WARNING SY	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIFT DETECTOR FAULTY. SWITCH OPERATES IN OPPOSITE SENSE.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001080800323	20010808	00323		2001	8	8	AUS20010656      	4	20010620	G	3418	18617RX	DETECTOR        			REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	STALL WARNING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					263					(AUS) LIFT DETECTOR FAULTY. DETECTOR MICROSWITCH OPERATES IN OPPOSITE SENSE. SWITCH SPRING LOADED UP. PERSONNEL/MAINTENA	NCE ERROR.MANUFACTURING ERROR.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001080800324	20010808	00324	NE  	2001	8	8	AUS20010657      	2	20010625	G	7250	UL36853	SUPPORT         	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					TURBINE SECTION	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			576  		13044					(AUS) ENGINE HP/IP TURBINE BEARING SUPPORT OIL PIPE LEAKING AT SUPPORTATTACHMENT.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080800325	20010808	00325	EU  	2001	8	8	AUS20010658      	1	20010430	G	5343	D5337061320200	FITTING         		D53370613203	AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (4OFF) CRACKED FROM THEUPPER TWO FASTENER HOLES IN THE VERTICAL FLANGE.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080800327	20010808	00327	NM  	2001	8	8	AUS20010659      	1	20010503	G	5755	656718613	FITTING         			BOEING	737   	737377      	       	NM  										SPOILERS	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					MA2489					(AUS) LT INBOARD GROUND SPOILER CENTRE OUTBOARD HINGE FITTING HAD A MISSING PIECE ALLOWING THE HINGE BEARING TO LOOSEN I	N THE FITTING.					2	L	7	2 	4F			RT	A16WE   					 
2001080700175	20010807	00175	NM  	2001	8	7	AUS20010660      	1	20010615	G	6310	A1681	PLATE           	            	            	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O360  	O360J2A     	41514	EA  	 		            		ENGINE/TRANSMISS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) CLUTCH SEAL PLATE CRACKED IN MORE THAN ONE PLACE ON BOTH SIDES.						1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2001080800328	20010808	00328	EU  	2001	8	8	AUS20010661      	1	20010510	G	5343	D5337061320200	FITTING         			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR ACTUATOR ATTACHMENT FITTINGS (4OFF)CRACKED FROM TOP TWO FASTENER HOLES IN THE VERTICAL FLAN	GE.					2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080700176	20010807	00176	SO  	2001	8	7	AUS20010662      	1	20010626	G	5540	4004009	TORQUE TUBE     	            	            	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	RUDDER STRUCTURE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7066 							(AUS) RUDDER TORQUE TUBE CORRODED BOTH INTERNALLY AND EXTERNALLY.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P9EA	 
2001080700177	20010807	00177	NM  	2001	8	7	AUS20010663      	1	20010625	G	3230	DSC1831	RELAY           	            	            	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			AU	S 	 									(AUS) LANDING GEAR DOOR SEQUENCE CONTROL RELAY K12 FAULTY. DURING FUNCTION CHECKS RELAY K13 PNO DSC183-2 WAS ALSO FOUND 	TO BE FAULTY.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800330	20010808	00330	NM  	2001	8	8	AUS20010664      	1	20010308	G	5210	BACB10FK6F6HS	ROLLER          			BOEING	737   	73733A      	1384673	NM  										PAX DOOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER DOOR R1 SEQUENCING CAM ROLLER SEIZED AND DISINTEGRATEDPREVENTING CORRECT OPERATION OF DOOR.						2	L	7	2 	4F			RT	A16WE   					 
2001080700178	20010807	00178	CE  	2001	8	7	AUS20010665      	1	20010426	G	3243	98820104	CYLINDER        	            	            	CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540AB1A5  	 	EA  	MCAULY	3D36C	B3D36C431   	GL  	MASTER CYLINDER/	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH BRAKE MASTER CYLINDER LEAKING AT ELBOW FITTING. INVESTIGATIONFOUND THAT THE ELBOW HAD NOT BEEN FULLY SCREWED IN	 AND THESEALING O' RING WAS DISPLACED ONTO THE THREADS OF THE ELBOW  INSTEAD OF FITTING INTO THE SEAL RECESS DUE TO THE 	B' NUTCOVERING THE RECESS.				1	H	7	1 	3O	3	O	NT	3A13    	1E4	5	C	 	 
2001080800331	20010808	00331	NE  	2001	8	8	AUS20010666      	2	20010624	G	7260	208315905	MOUNT           			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE CSD MOUNTING RING MOUNTING BOSSES (5OFF) BROKEN AWAY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800332	20010808	00332	NM  	2001	8	8	AUS20010667      	1	20010628	G	7830	13169	DOOR            	RROYCE      	RB211524G   	BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					THRUST REVERSER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			12575		13169					(AUS) NR 3 ENGINE NR 10 THRUST REVERSER BLOCKER DOOR PARTLY MISSING WITH DAMAGE TO THE CORONA LOCATED AFT OF THE DOOR PO	SITION AND A SMALL TEAR ON THE CORONA ACOUSTIC PANEL.					2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080800334	20010808	00334	NE  	2001	8	8	AUS20010668      	2	20010628	G	7200	RB211524D419	ENGINE          			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 2	VIBRATES        	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 			254  							(AUS) NR 2 ENGINE EXCESSIVE VIBRATION. ENGINE INSPECTED IAW MAINTENANCEMANUALS WITH NO FAULTS FOUND. HPC STAGES 5/6 BORO	SCOPED AND FOUND OK. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080700179	20010807	00179	NM  	2001	8	7	AUS20010669      	1	20010620	G	5230	6546921225	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 	 		35309		001895					(AUS) FORWARD CARGO DOOR CRACKED IN THE RADIUS OF THE FORWARD OUTBOARDCORNER ANGLE. CRACK LENGTH 35.56MM (1.4IN). FOUND 	DURINGINSPECTION IAW EI 737-052-0003, FAA AD2000-07-06 AND AD/B737/142.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800335	20010808	00335	SO  	2001	8	8	AUS20010670      	1	20010627	G	5741	401187	BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING REAR SPAR ATTACHMENT BOLTS LOOSE WITH NUT HOLDING BY ONLY THREE THREADS. SUSPECT NUTS NOT TIGHTENED AT LAS	T MAINTENANCE INSPECTION FOLLOWING WORK CARRIED OUT IN THE AREA.PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2001080800337	20010808	00337	NM  	2001	8	8	AUS20010671      	1	20010626	G	3520	335841	COMPENSATOR     			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					PASSENGER OXYGEN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			10501							(AUS) NO6 PASSENGER OXYGEN BOTTLE THERMAL COMPENSATOR SWAGED FITTINGCORRODED. AIRCRAFT IS REGISTERED DQ-FJE.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001080800338	20010808	00338	NM  	2001	8	8	AUS20010672      	1	20010628	G	5753	7337515505	PIN             			BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					TE FLAPS	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP BYPASS VALVE ROTARY ACTUATOR PIN MIGRATED OUT OF POSITIONLEVER.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080700180	20010807	00180	SW  	2001	8	7	AUS20010673      	1	20010621	G	2841	1820002	INDICATOR       	            	            	GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK4     	GL  	FUEL QUANTITY IN	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			CR	CRUISE         	1			AU	S 	 		1    							(AUS) TRIPLE GAUGE FAILED AND FILLED WITH FUEL.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2001080700181	20010807	00181	CE  	2001	8	7	AUS20010674      	1	20010619	G	3213	51411021	BARREL          	            	            	CESSNA	402   	402C        	207590R	CE  	      		            			 		            		MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR LOWER TORQUE LINK ATTACHMENT LUGS CRACKED.FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION 	IAW MEB 89-2R1. LOWER ATTACHMENT LUGS ARE NOT CALLED FOR IN THISINSPECTION.					1	L	7	2 	3O			 	A7CE    					 
2001080800347	20010808	00347	EU  	2001	8	8	AUS20010675      	1	20010628	G	6220	206010102121	GRIP            	BELL        		AGUSTA	206AGS	206AAGUSTA  	0260301	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			583  		GDLM11933					(AUS) MAIN ROTOR GRIP BLADE BOLT BORES DAMAGED. INVESTIGATION FOUND THAT THE MAIN ROTOR BLADE BUFFER PAD WAS DISLODGED D	URING BLADE INSTALLATION. THE BLADE BOLT WAS FORCED IN CAUSING THE EDGE OFTHE BUFFER PAD INTO THE BLADE BOLT HOLE. DAMAG	E CAUSED TO BLADE BOLT PNO 206-010-152-003 AND MAIN ROTOR BLADE PNO 206-010-200-033. PERSONNEL/MAINTENANCE ERROR.				1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2001080800350	20010808	00350	NM  	2001	8	8	AUS20010676      	1	20010630	G	4920		APU             			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					APU BAY	FIRE            	W				K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			AU	S 										(AUS) FOLLOWING APU BATTERY FITMENT AND WHILE INSTALLATION CHECKS WERE CARRIED OUT ON THE THERMAL SWITCH, A FLASH FIRE O	CCURRED WHICH SET FIRE TO THE THERMAL BLANKET LOCATED UNDER THE APU BATTERY TRAY AND ALSO CAUSED FLASH BURNS TO MAINTENA	NCE PERSONNEL. THEFIRE WAS CONTAINED AND QUICKLY EXTINGUISHED. THE FIRE MAY HAVE BEEN CAUSED BY COMBINATION OF AN IGNITI	ON SOURCE FROM A PREVIOUSLY UNDISCOVERED BROKEN/CHAFFED WIRING IN LOOM ADJACENT TO APU BATTERY TRAY AND USE OF AN UNAPPR	OVED  COOLANT SOURCE THAT WAS INFLAMMABLE.		2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080700182	20010807	00182	CE  	2001	8	7	AUS20010677      	1	20010627	G	5753	052390134	FLAP            	            	            	CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	TRAILING EDGE FL	DAMAGED         	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 									(AUS) RH TRAILING EDGE FLAP TOP AND BOTTOM SKINS, LEADING EDGE SKIN AND SPAR DAMAGED. INVESTIGATION FOUND THE DAMAGE WAS	 CAUSED BY THEINBOARD FORWARD FLAP ROLLER JAMMING DUE TO EXCESSIVE WEAR OF THEFLAP TRACK AND ROLLERS.					1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2001080700183	20010807	00183	CE  	2001	8	7	AUS20010678      	1	20010626	G	5610	10132402522	WINDSHIELD      	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) RH WINDSHIELD INNER PANE CRACKED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2001080800352	20010808	00352	NE  	2001	8	8	AUS20010679      	3	20010629	G	6114	660714255	HUB             	ROTOL       	R3904123F   	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5054 		DRG1268390					(AUS) PROPELLER HUB CRACKED IN AREA AROUND TWO OF THE MOUNT BOLT HOLES. FOUND USING EDDY CURRENT INSPECTION IAW AD/PR/33	.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001080700184	20010807	00184	NM  	2001	8	7	AUS20010680      	1	20010701	G	2750	285T004953	FSEU            	            	            	BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		TRAILING EDGE FL	FAULTY          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		LD	LANDING        	1			AU	S 	 		6848 							(AUS) FLAP/SLAT ELECTRONIC UNIT (FSEU) SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001080800353	20010808	00353	NM  	2001	8	8	AUS20010681      	1	20010621	G	7603		CABLE           	RROYCE      	RB211524D4  	BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					POWER LEVER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THRUST CONTROL CABLE GUARDS AND COVERS CRACKED/DAMAGED.GUARDS ARE FOR CABLES T1, T2, T3, T4A, T4B, STN940 T	O STN960 LT AND RT. CABLE PULLEY FOR CABLE T3A CRACKED AND CABLE T3A WORN AT RT WING INBOARD LOCATION 352.00. FOUND DURI	NG INSPECTION IAW EI 742-076-0005 REV02, CASA AD/B747/299 AND FAA AD 2000-05-30 AMDT 39-11640. AIRCRAFT IS FOREIGN REGIS	TRATION DQ-FJE.			2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001080800354	20010808	00354	NM  	2001	8	8	AUS20010682      	1	20010626	G	2530	GENM2585015	OVEN            			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					GALLEY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			19905							(AUS) OVEN C207 CONTAMINATED. WHEN THE OVEN WAS OPERATED A LARGE AMOUNT OF SMOKE WAS GENERATED DUE TO EXCESS OIL IN THE 	OVEN COMPARTMENT.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080700185	20010807	00185	NE  	2001	8	7	AUS20010683      	2	20010704	G	7260	310623101	SHAFT           	PWA         	PW123D      	DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	TURBINE ENGINE A	SHEARED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				123308					(AUS) NO2 ENGINE ACCESSORY GEARBOX TOWER SHAFT SHEARED AT THE MATINGPOINT WITH GEAR CAUSING THE SHEARED STUB TO JAM BETW	EEN THE DRIVESHAFT BEVEL GEARS. SUSPECT CAUSED BY INCORRECT ASSEMBLYPROCEDURE DURING PRODUCTION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800355	20010808	00355	GL  	2001	8	8	AUS20010684      	1	20010530	G	5710		STRUCTURE       			AMTR  	MK1   	MK1         	05620JY	GL  										WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INTERNAL DELAMINATION OF WING/FUEL TANK. SEVERE FUEL LEAKAGE. THE AIRCRAFT IS A HOMEBUILT AND IT IS SUSPECTED THAT	 INCORRECTTECHNIQUES WERE USED IN THE CONSTRUCTION.					1	H	7	1 	3O			NC	EXPA1H71					 
2001080800356	20010808	00356	SO  	2001	8	8	AUS20010685      	2	20010621	G	8530	654961	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 CYLINDER LEAKING PAST EXHAUST VALVE AND PISTON RINGS.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001080700186	20010807	00186	CE  	2001	8	7	AUS20010686      	1	20010622	G	3710	1H59	VALVE           	AIRBORNE    	1H59        	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	VACUUM DISTRIBUT	FAULTY          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			CR	CRUISE         	1			AU	S 	 				8A					(AUS) RH VACUUM SYSTEM MANIFOLD CHECK VALVE FAULTY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001080800357	20010808	00357	SO  	2001	8	8	AUS20010687      	1	20010704	G	2432	1406902	LEAD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	BATTERY/CHARGER	FRACTURED       	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) BATTERY POSITIVE LEAD LOCATED INSIDE THE BATTERY BOX FRACTURED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800362	20010808	00362	EA  	2001	8	8	AUS20010688      	2	20010617	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1677 							(AUS) ENGINE CYLINDER HEAD SEPARATED FROM BARREL IN THREADED AREA.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800363	20010808	00363	EA  	2001	8	8	AUS20010689      	2	20010622	G	8530	LW13532	CYLINDER        			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			632  							(AUS) ENGINE CYLINDER HOLED IN AREA ADJACENT TO TOP SPARK PLUG HOLE.						1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2001080800364	20010808	00364		2001	8	8	AUS20010690      	4	20010702	G	3418	18617	DETECTOR        			REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	STALL WARNING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LIFT DETECTOR FAULTY. INVESTIGATION FOUND THAT THE AIRCRAFT WIRING (WIRE NO A2K4S-20P3) HAD BEEN CUT APPROXIMATELY	 76.2MM (3IN) UP FROM THE FORWARD SIDE CONSOLE CONNECTOR AND CONNECTED TO THE STALL WARNING HORN. PERSONNEL/MAINTENANCE 	ERROR. UNAPPROVED MODIFICATION.				1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001080800365	20010808	00365	NE  	2001	8	8	AUS20010691      	2	20010707	G	7200	200304004	ENGINE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2	MALFUNCTIONED   	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 										(AUS) NR 2 ENGINE HAD NO OIL PRESSURE. LIMITED INFORMATION PROVIDED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080800366	20010808	00366	SW  	2001	8	8	AUS20010692      	1	20010706	G	3210	2751540003	PIN             			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LANDING GEAR	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR UPPER TORQUE LINK PIN SHEARED.						2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001080700187	20010807	00187	CE  	2001	8	7	AUS20010693      	1	20010709	G	7602	5038901019	CABLE           	CONT        	IO470L      	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	MIXTURE CONTROL	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE MIXTURE CUTOFF CONTROL CABLE WORN AND BROKEN AT A POINT 190MM (7.48IN) FROM THE ENGINE END ATTACHMENT BE	ARING.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2001080800367	20010808	00367	WP  	2001	8	8	AUS20010694      	2	20010630	G	7210	310703710	GEAR            			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SUN/BULL GEAR TEETH AND CORRESPONDING HIGH SPEED PINIONGEARSHAFT TEETH WORN. FOUND DURING ENGINE DISASSEMBL	Y FOLLOWING SOAP ANALYSIS WHICH SHOWED CARBON STEEL FINES. SERVICE BULLETIN A72-2062 HAD NOT BEEN COMPLIED WITH.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE	6	C	3PNE	 
2001080800368	20010808	00368		2001	8	8	AUS20010695      	4	20010624	G	3414	1013840743	INDICATOR       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	OUT OF ADJ      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRSPEED INDICATOR READING 5 KNOTS OUT OVER THE ENTIRE RANGE. FOUND DURING INSPECTION IAW AD/INST/9 AMDT5.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001080800369	20010808	00369	EU  	2001	8	8	AUS20010696      	1	20010703	G	7810	4606AC	CLAMP           	ALLSN       	250C20B     	AGUSTA	206AGS	206AAGUSTA  	0260301	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE COLLECTOR	CRACKED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST STACK CLAMP LOOSE DUE TO A FRACTURE ORIGINATINGFROM THE ATTACHMENT LUG SECURING RIVET. COWLING DISC	OLOURED AND BURNT.					1	G	7	1 	3U	3	U	 	EXPA1G71	E4CE				 
2001080800370	20010808	00370	EU  	2001	8	8	AUS20010697      	1	20010627	G	7120	9448121409	MOUNT           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE SHOCK MOUNT RUBBERS SEPARATED FROM METAL BACKING ALLOWINGENGINE TO SLUMP. SUSPECT MANUFACTURING FAULT.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001080700188	20010807	00188	SO  	2001	8	7	AUS20010698      	2	20010626	G	8530		PISTON RING     	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NO3 CYLINDER PISTON RINGS WORN AND LEAKING.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001080800371	20010808	00371	CE  	2001	8	8	AUS20010699      	1	20010705	G	2797		WIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	FLIGHT CONTROLS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) FLAP SELECTOR LOOM WIRE BROKEN FROM CRIMP TO FLAP MICROSWITCH.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001080700189	20010807	00189	SO  	2001	8	7	AUS20010700      	1	20010705	G	2840	8004804	HOSE            	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL INDICATING	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL PRESSURE HOSE TO FUEL FLOW GAUGE LEAKING UNDER PRESSURE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001080800372	20010808	00372	NM  	2001	8	8	AUS20010701      	1	20010704	G	5520	85520271003	STOP            			DHAV  	DHC8  	DHC8202     	2809007	NM  	PWA   	120   	PW123D      	52152	NE  	HAMSTD	14SF	14SF23      	NE  	ELEVATOR	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR BUMPER RUBBER DETERIORATED AND PERISHED. FOUND DURINGINSPECTION IAW AD/DHC-8/078.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080800373	20010808	00373	EU  	2001	8	8	AUS20010702      	1	20010601	G	2130		CONTROLLER      			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					CABIN PRESSURE	ERRATIC         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) PRESSURISATION SYSTEM ERRATIC IN OPERATION. INVESTIGATION FOUND THAT THE AIR FILTER AND VENTURI LINES WERE TRANSPO	SED AT THE PRESSURISATION CONTROLLER CONNECTIONS. PERSONNEL/MAINTENANCEERROR.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700190	20010807	00190	EU  	2001	8	7	AUS20010703      	1	20010601	G	2910		PIPE            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		HYDRAULIC SYSTEM	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) UTILITY HYDRAULIC SYSTEM SUCTION PIPE CONTAINED A PIN HOLE LEAK.LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700191	20010807	00191	EU  	2001	8	7	AUS20010704      	1	20010601	G	3234		LEVER           	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR SEL	STUCK           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) LANDING GEAR LEVER OBSTRUCTED IN DOWN POSITION.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700192	20010807	00192	EU  	2001	8	7	AUS20010705      	1	20010527	G	3610		DUCT            	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		PNEUMATIC DISTRI	MISALIGNED      	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			AU	S 	 									(AUS) LH BLEED AIR SYSTEM LEAKING AT ENGINE HP OUTLET CHECK VALVE DUCT. INVESTIGATION FOUND THE DUCT MATING SURFACES TO 	BE BADLY ALIGNED.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080800374	20010808	00374		2001	8	8	AUS20010706      	4	20010625	G	2565		CABLE           			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM565B4    	 	NE  					ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD GALLEY DOOR ESCAPE SLIDE RELEASE CABLE FRAYED. FOUNDDURING INSPECTION IAW AD/B737/042.						2	L	7	2 	4F	4	F	RT	A16WE   	E38NE				 
2001080700193	20010807	00193	NE  	2001	8	7	AUS20010707      	2	20010509	G	7250	9234M22G07	SUPPORT         	GE          	CF680A      	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		TURBINE SECTION	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE FIRST STAGE HPT INNER NOZZLE SUPPORT CRACKED. TURBINEDAMAGE AND METAL IN TAILPIPE.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080800375	20010808	00375	EU  	2001	8	8	AUS20010708      	1	20010707	G	3260		SWITCH          			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	LANDING GEAR	OUT OF ADJ      	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR MICROSWITCH OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE	 
2001080800376	20010808	00376	NM  	2001	8	8	AUS20010709      	1	20010701	G	2540		VALVE           			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM565B4    	 	NE  					LAVATORIES	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD TOILET DRAIN VALVE POPPET BROKEN. INNER POPPET WASMISSING.						2	L	7	2 	4F	4	F	RT	A16WE   	E38NE				 
2001080800377	20010808	00377	NM  	2001	8	8	AUS20010710      	1	20010706	G	2910	AS154A06NN0336T	HOSE            			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					HYDRAULIC SYSTEM	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR EXTENSION FLEXIBLE HOSE RUPTURED. LOSS OF SYSTEM A' HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080800378	20010808	00378	EU  	2001	8	8	AUS20010711      	1	20010627	G	5610		WINDSHIELD      			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) FRONT LH WINDSHIELD CRACKED FOLLOWING FAILURE OF WINDSHIELD HEATING.						2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001080900003	20010809	00003	EU  	2001	8	9	AUS20010712      	1	20010703	G	5415		BOLT            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					PYLON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING/PYLON BOLT CORRODED UNDER HEAD. FOUND DURING INSPECTION IAWER BA6-54-40-4.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080900004	20010809	00004		2001	8	9	AUS20010713      	4	20010614	G	2210		AUTOPILOT SYS   			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	FAULTY          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) AUTOPILOT FAULTY.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080900005	20010809	00005	EU  	2001	8	9	AUS20010714      	1	20010704	G	5415		BOLT            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NACELLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING/PYLON BOLTS (3OFF) CORRODED UNDER THE HEAD AND ON THE BOLT SHANK. FOUND DURING INSPECTION IAW ER BA6-54-40-4 	REV E.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700194	20010807	00194	SO  	2001	8	7	AUS20010716      	2	20010703	G	8530	654004	EXHAUST VALVE   	CONT        	O200A       	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	RECIPROCATING EN	ERODED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				205622					(AUS) ALL ENGINE EXHAUST VALVES EXHIBITED SEVERE EROSION BETWEEN THEVALVE STEM AND VALVE HEAD.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2001080700195	20010807	00195	EA  	2001	8	7	AUS20010717      	2	20010613	G	8520	L801776	CRANKCASE       	LYC         	O320H2AD    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RECIPROCATING EN	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				L801776					(AUS) CRANKCASE INCORRECTLY LINE BORED REDUCING DECK HEIGHT BY 1.016MM(0.040IN). THIS ALLOWED NO3 PISTON TO CONTACT THE 	CYLINDER HEAD.METAL CONTAMINATION OF ENGINE. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001080900006	20010809	00006	NE  	2001	8	9	AUS20010718      	2	20010708	G	7321	FFR105MK2S	REGULATOR       	RROYCE      	RB211524D4  	BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUEL CONTROL	FAULTY          	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			9145 		B1734					(AUS) NO2 ENGINE FUEL FLOW REGULATOR FAULTY.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080900007	20010809	00007	NM  	2001	8	9	AUS20010719      	1	20010710	G	3242	S160T400510	BRAKE           	MESSIER     	MAINWHEEL   	BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 2	FIRE            	W				D				RETURN TO BLOCK         				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			AU	S 			2667 		QF15175					(AUS) NR 2 RT BRAKE FIRE. FIRE SELF-EXTINGUISHED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700196	20010807	00196	EA  	2001	8	7	AUS20010720      	2	20010703	G	7321	25244405	FCU             	BENDIX      	DPF2        	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 	 				A48954					(AUS) FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND THE PY RESTRICTOR PARTIALLY BLOCKED BY SUSPECTED PAINT FLAKES.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001080700197	20010807	00197	CE  	2001	8	7	AUS20010721      	1	20010702	G	3710		HOSE            	            	            	CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	VACUUM DISTRIBUT	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) INSTRUMENT VACUUM HOSES LOCATED BEHIND THE INSTRUMENT PANEL DETERIORATED. HOSES ARE BRANDED IMPERIAL EASTMAN REDI-	SEAL.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P22EA	 
2001080900009	20010809	00009	NM  	2001	8	9	AUS20010722      	1	20010706	G	3040		HEATER          		8SC004301   	DHAV  	DHC8  	DHC8106     	       	NM  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF7       	NE  	WINDSHIELD	FAULTY          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) LT WINDSHIELD HEATING TERMINAL BLOCK OVERHEATING. NO EVIDENCE OFHEAT DAMAGE TO THE WINDSHIELD.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080900010	20010809	00010		2001	8	9	AUS20010723      	4	20010711	G	3460	4081600930	DISPLAY         			BOEING	737   	737724      	       	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					FMC	FAULTY          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) NR 1 DISPLAY ELECTRONIC UNIT (DEU) FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E29NE				 
2001080700198	20010807	00198	GL  	2001	8	7	AUS20010724      	1	20010525	G	6220	281432015	BEARING         	            	            	ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  	 		            		MAIN ROTOR HEAD	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 									(AUS) MAIN ROTOR HEAD LAMIFLEX BEARING FAILED. SUSPECT CAUSED BY GREASE CONTAMINATION.						1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2001080700199	20010807	00199	EA  	2001	8	7	AUS20010725      	2	20010624	G	8520		BOLT            	LYC         	IO540K1G5   	PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 	 									(AUS) CYLINDER HOLDDOWN BOLTS FAILED.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001080700200	20010807	00200	SO  	2001	8	7	AUS20010726      	1	20010706	G	3242	93956	PLATE           	            	            	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	BRAKE	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				0480					(AUS) LH OUTBOARD BRAKE WORN TO LIMITS. STRIP INSPECTION FOUND THAT WEAR PLATES HAD SPREAD PAST THE OUTER DIAMETER OF TH	E BRAKE PLATES AND CONTACTED THE WHEEL PNO 3-1544.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001080900011	20010809	00011	NE  	2001	8	9	AUS20010727      	2	20010710	G	7200		ENGINE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3	FAILED          	W				A				UNSCHED LANDING         				K	E	J	FLUID LOSS                	VIBRATION/BUFFET          	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) NR 3 ENGINE OIL PRESSURE LOSS.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080900013	20010809	00013	NM  	2001	8	9	AUS20010728      	1	20010711	G	3242	S160T400510	BRAKE           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					NR 3 MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2907 							(AUS) NR 3 MAIN LANDING GEAR BRAKE LEAKING. FURTHER INVESTIGATION SHOWED EVIDENCE OF DISINTEGRATION OF THE REAR STATOR.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080900014	20010809	00014	NM  	2001	8	9	AUS20010729      	1	20010711	G	2910	K2231	LINE            	ABEX        	PUMP        	BOEING	737   	737724      	       	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					HYDRAULIC SYSTEM	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					K2231					(AUS) HYDRAULIC SUPPLY LINE FOUND DISCONNECTED. SUSPECT LINE NOTRECONNECTED FOLLOWING MAINTENANCE. SYSTEM A' HYDRAULIC P	UMP  INTERNAL FAILURE DUE TO LACK OF FLUID. PERSONNEL/MAINTENANCE  ERROR.					2	L	7	2 	4F	4	F	RT	A16WE   	E29NE				 
2001080900016	20010809	00016	NE  	2001	8	9	AUS20010731      	2	20010712	G	7200	0292005250	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NACELLE	FAILED          	W				A				UNSCHED LANDING         				E	T	J	VIBRATION/BUFFET          	ENGINE CASE PENETRATION   	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) ENGINE SUFFERED SEVERE INTERNAL FAILURE. COMPRESSOR AND TURBINE SEIZED. GAS GENERATOR AND POWER TURBINE BLADES BAD	LY DAMAGED. EXTERNAL DAMAGE ALSO EVIDENT.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080900017	20010809	00017	SW  	2001	8	9	AUS20010732      	1	20010309	G	6120	86913019	BETA SWITCH     	HARTZL      	HCB3TN5     	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	PROPELLER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER BETA SWITCH FAULTY.						2	L	7	2 	4T	3	T	RT	A8SW    	E2WE	6	C	P15EA	 
2001080900019	20010809	00019	WP  	2001	8	9	AUS20010733      	2	20010705	G	7261	3199741	VALVE           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OIL VENT VALVE STUCK OPEN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA	 
2001080700201	20010807	00201	EU  	2001	8	7	AUS20010734      	1	20010622	G	2710		CONTROL CABLE   			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AILERON CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH AILERON CABLES (4OFF) LOCATED IN WING WORN.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2001080900020	20010809	00020	NM  	2001	8	9	AUS20010735      	1	20010715	G	7714		WIRE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENGINE INDICATOR	FAULTY          	W				D				RETURN TO BLOCK         				E	N		VIBRATION/BUFFET          	FALSE WARNING             		TX	TAXI/GRND HDL  	1			AU	S 			35105							(AUS) NR 1 ENGINE ITT GAUGE FLUCTUATING. SUSPECT WIRING PROBLEM.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080900025	20010809	00025		2001	8	9	AUS20010736      	4	20010711	G	2565	63800103	LIFE RAFT       																	CABIN	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			10392							(AUS) DURING SERVICING OF LIFERAFT IT WAS FOUND THAT THE PACKING STRAP WAS STILL IN PLACE AROUND THE CIRCUMFERENCE OF TH	E RAFT. STRAP WOULD PROBABLY PREVENTED CORRECT DEPLOYMENT. LIFERAFT HAD BEEN IN SERVICE FOR APPROXIMATELY THREE YEARS. P	ERSONNEL/MAINTENANCEERROR.																	 
2001080700202	20010807	00202	SO  	2001	8	7	AUS20010737      	2	20010714	G	7414	1051676	CAPACITOR       	BENDIX      	107902016   	CESSNA	337   	T337G       	2075726	CE  	CONT  	O360  	TSIO360C    	17025	SO  	MCAULY	2AF34C	D2AF34C303  	GL  	MAGNETO/DISTRIBU	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				A98935					(AUS) MAGNETO CAPACITOR FAULTY. CAPACITOR LEAD LOOSE.						1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA	 
2001080900027	20010809	00027	NE  	2001	8	9	AUS20010738      	2	20010712	G	7323	12664	GOVERNOR        			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 2 ENGINE	FAULTY          	W				D				RETURN TO BLOCK         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 ENGINE RPM DECREASED AND EGT INCREASED. VIGV AIR FLOW CONTROL UNIT PNO 754-1-32148-019A AND PUMP AND GOVERNOR	 UNIT (PAG) PNOPAC102MK4S CHANGED.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001080900029	20010809	00029	NE  	2001	8	9	AUS20010739      	2	20010712	G	7260	1765MK1	HOUSING         			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					GENERATOR	FAILED          	W				A				UNSCHED LANDING         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 										(AUS) NR 4 ENGINE DEDICATED GENERATOR DAMAGED AND ADRIFT FROM ADAPTER GEARBOX. LOSS OF ENGINE OIL.						2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080900030	20010809	00030	EU  	2001	8	9	AUS20010740      	1	20010716	G	3040	S2653010	CIRCUIT BREAKER 			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R3A   	41580	NE  					WINDSHIELD HEAT	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) LT A' SCREEN HEAT CIRCUIT BREAKER FAULTY. INVESTIGATION FOUND  THE CIRCUIT BREAKER BURNED OUT ON A' PHASE.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700203	20010807	00203	NM  	2001	8	7	AUS20010741      	1	20010716	G	2520		SEAT            	            	            	BOEING	737   	737476      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		PASSENGER COMPAR	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PASSENGER SEAT 10ABC LOOSE IN TRACKS.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080900032	20010809	00032	NM  	2001	8	9	AUS20010742      	1	20010716	G	5330	149T76086	PANEL           			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					FUSELAGE	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 										(AUS) ADP ACCESS PANEL/DOOR 195SL MISSING. DAMAGE TO FUSELAGE PANELS195LL, 195QL AND 195NL.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080700204	20010807	00204	SO  	2001	8	7	AUS20010743      	1	20010519	G	3213	79543002	BOLT            	            	            	PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAIN LANDING GEA	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LH MAIN LANDING GEARLOWER LEG SEPARATED FROM UPPER LEG. SUSPECT CAUSED BY FAILURE OF THE CENTRE TORQUE LINK BOLT. 	LOWER LEG HOLED LH FLAP DURING SEPARATION.					1	L	7	1 	3O	3	O	 	A3SO    	E295	5	C	P920	 
2001080900033	20010809	00033	EA  	2001	8	9	AUS20010744      	1	20010712	G	5610	NP1393225	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 					99343H5435					(AUS) LT PILOTS SIDE WINDSHIELD INNER PLY CRACKED DIAGONALLY FROM THE FORWARD LOWER CORNER.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001080900034	20010809	00034	NM  	2001	8	9	AUS20010745      	1	20010716	G	5753	69577055	FAIRING         			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					TE FLAPS	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) NR 3 TRAILING EDGE FLAP CANOE/FAIRING ASSEMBLY INBOARD END DOORPOSITION DATA BROKEN OFF AND JAMMING FLAP.						2	L	7	2 	4F	4	F	RT	A16WE   	E29NE				 
2001080900036	20010809	00036	CE  	2001	8	9	AUS20010746      	1	20010713	G	3246	16110900	WHEEL           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR WHEEL INNER HALF WORN IN BEARING BORE. BEARING SPINNING IN HUB.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001080900037	20010809	00037	NM  	2001	8	9	AUS20010747      	1	20010717	G	3520	117003	GENERATOR       			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					PASSENGER OXYGEN	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OXYGEN GENERATORS LOCATED AT SEATS 24AB, 25AB, 27AB AND 30FG HADTHE RELEASE PINS INCORRECTLY INSTALLED.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080700205	20010807	00205	CE  	2001	8	7	AUS20010748      	1	20010717	G	5521	0532001103	RIB             	            	            	CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	ELEVATOR, SPAR/R	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		8881 							(AUS) ELEVATOR END RIB EXTENSIVELY CORRODED.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2001080900038	20010809	00038	SO  	2001	8	9	AUS20010749      	1	20010711	G	3260	MS3126E106P	CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	LANDING GEAR	SHORTED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RT LANDING GEAR AIR/GROUND PROXIMITY SENSOR ELECTRICAL CONNECTORMOISTURE CONTAMINATION AND SHORT CIRCUIT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001080900039	20010809	00039	SO  	2001	8	9	AUS20010750      	1	20010713	G	3260	XAIN103	RELAY           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	LANDING GEAR	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) GROUND/FLIGHT RELAY BOX RELAY K0290 FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001080700206	20010807	00206	NE  	2001	8	7	AUS20010751      	2	20010717	G	7321	7863911028	HMU             	PWA         	PW120A      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FUEL CONTROL/TUR	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 		2034 		F26904					(AUS) RH ENGINE HYDRO MECHANICAL UNIT (HMU) FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080900040	20010809	00040	NM  	2001	8	9	AUS20010752      	1	20010718	G	2822	6072101	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL SYSTEM	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TRANSFER PUMP CONNECTORS INCORRECTLY WIRED. THE PUMPS HAD WIRINGSWAPPED AT PIN 2 AND PIN 3. THE WIRES WERE RECONNE	CTED IN THE BELIEF THAT THE WIRING CONFIGURATION WAS INCORRECT. THE AIRCRAFTHAD BEEN SUPPLIED WITH THE WIRING IN A NON-S	TANDARD FORMAT. INVESTIGATION FOUND THAT SOME AIRCRAFT HAD BEEN WIRED DIFFERENTLY AT MANUFACTURE. THIS WIRING CHANGE WAS	 NOT INCORPORATED IN THESERVICE BULLETIN.			2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080900041	20010809	00041	NM  	2001	8	9	AUS20010753      	1	20010717	G	2822	6072101	PUMP            			BOEING	747   	747438      	       	NM  	RROYCE	RB211 	RB211524G19 	 	NE  					FUEL SYSTEM	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			210  							(AUS) HORIZONTAL STABILISER FUEL TANK RT TRANSFER / JETTISON PUMP WIRINGCONNECTIONS AT PIN 2 AND PIN 3 REVERSED AT PUMP 	CONNECTOR PLUGDM7863. WIRING WAS CORRECT AS PER WIRING DIAGRAM BUT INCORRECT AS PER BSB 747-28-2217 FIG10. INVESTIGATION	 FOUND THAT SOME AIRCRAFT HAD BEEN WIRED DIFFERENTLY AT MANUFACTURE. THIS WIRING CHANGE WAS NOT INCORPORATED IN THE SERV	ICE BULLETIN.			2	L	7	4 	4F	4	F	RT	A20WE   	E30NE				 
2001080900042	20010809	00042		2001	8	9	AUS20010754      	4	20010706	G	6122	B41832	FLYWEIGHT       	HARTZL      	F624L       															PROP GOVERNOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B1798T					(AUS) ENGINE CONSTANT SPEED UNIT FLYWEIGHT ASSEMBLY BROKEN.																			 
2001080700207	20010807	00207	CE  	2001	8	7	AUS20010755      	1	20010705	G	5551	1016200191	FITTING         	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HORIZONTAL STABI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HORIZONTAL STABILISER AFT UPPER FITTING CONTAINED SEVEREINTERGRANNULAR CORROSION. NDI CARRIED OUT ON FITTING FOLLO	WINGREMOVAL FOUND THREE CRACKS BETWEEN THE BOLT HOLES.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001080900048	20010809	00048	CE  	2001	8	9	AUS20010756      	1	20010710	G	3230	1068100111	UPLOCK CABLE    		358150722   	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	LANDING GEAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK CABLE LOOSE. FURTHER INVESTIGATION FOUND THAT THE UPLOCK BLOCK HAD BEEN CONTACTED BY	 THE UPLOCK ROLLER AND HAD BEEN MOVED OUT OF POSITION. UPLOCK CABLE RETAINING NUTS HAD TORN THROUGH NR 1 WING RIB.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001080900050	20010809	00050	CE  	2001	8	9	AUS20010757      	1	20010710	G	3230	35810142	SHAFT           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	LANDING GEAR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR ACTUATOR MANUAL EXTENSION HANDLE SHAFT INSTALLED 120 DEGREES OUT OF POSITION PREVENTING CORRECT OPERA	TION OF HANDLE.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001080900052	20010809	00052	CE  	2001	8	9	AUS20010758      	1	20010710	G	3242		HOSE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	BRAKE	FOULED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR BRAKE LINES FOULING ON LANDING GEAR DOORS DURING RETRACTION. INVESTIGATION FOUND THAT 	THE BRAKE HOSES WERE APPROXIMATELY 53.975MM (2.125IN) LONGER THAN THOSE FITTED TO SIMILAR AIRCRAFT. IN ADDITION THE BRAC	KETS PNO 35-815264-1 AND PNO 35-815264-2 WHICH ATTACH THE HOSES TO THE MLG LEGS WERE FITTED TO THE WRONG SIDES. PERSONNE	L/MAINTENANCE ERROR.			1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001080700208	20010807	00208	CE  	2001	8	7	AUS20010759      	1	20010705	G	8000	08504691	CONTACTOR       	CONT        	GTSIO520L   	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE STARTING	STUCK           	W			    	K	 	 	 	NONE                    				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 	 									(AUS) LH ENGINE STARTER CONTACTOR STUCK CLOSED. LH ALTERNATOR DAMAGED.STARTER MOTOR TERMINAL POST DAMAGED.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001080900055	20010809	00055	EU  	2001	8	9	AUS20010760      	2	20010714	G	7200		ENGINE          			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LEFT	FAULTY          	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE OIL CONSUMPTION EXCESSIVE AT APPROXIMATELY 0.8 LITRES TO 1 LITRE PER HOUR.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080900062	20010809	00062	NM  	2001	8	9	AUS20010761      	1	20010718	G	2621	35207900M	SQUIB           			BOEING	747   	747SP38     	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FIRE BOTTLE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			15092							(AUS) NR 1 MAIN CARGO FIRE EXTINGUISHER BOTTLE FORWARD AND AFT SQUIBSCROSS CONNECTED.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001080900068	20010809	00068	GL  	2001	8	9	AUS20010762      	2	20010712	G	7261	23038160	OIL SYSTEM      			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE	BLOCKED         	W				J				DUMP FUEL               				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			AU	S 										(AUS) NR 6 AND NR 7 BEARING OIL SCAVENGE PORT PARTIALLY BLOCKED BY CARBON DEPOSITS. OIL TYPE HAD BEEN CHANGED FROM MOBIL	 254 TO MOBIL 291.					1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2001080900069	20010809	00069	NE  	2001	8	9	AUS20010763      	2	20010715	G	7200		ENGINE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3	LEAKING         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) NR 3 ENGINE HP COMPRESSOR CONTAMINATED WITH OIL. FUMES IN CABIN.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080700209	20010807	00209	SW  	2001	8	7	AUS20010764      	1	20010718	G	6322	209062502101	FAN BLADE       	            	            	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		ROTORCRAFT COOLI	FAILED          	W			    	K	 	 	 	NONE                    				E	K	 	VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 	 									(AUS) NO1 ENGINE OIL COOLER BLOWER FAN BLADES SEPARATED FROM HUB.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001080700210	20010807	00210	SW  	2001	8	7	AUS20010765      	1	20010608	G	8120		BEARING         	PWA         	R1340AN1    	GULSTM	G73   	G73         	3951802	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  	EXHAUST TURBOCHA	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 	 		1159 							(AUS) RH ENGINE FAILED. CAUSED BY FAILURE OF SUPERCHARGER SUPPORT BEARING.						1	H	7	2 	3R	3	R	 	A783    	5E2	6	C	P719	 
2001080900071	20010809	00071	EU  	2001	8	9	AUS20010766      	1	20010719	G	7700		CONNECTOR       			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502*     	41580	EA  					INDICATOR	LOOSE           	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NR 4 ENGINE VIBRATION HARNESS PLUG LOOSE.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001080900072	20010809	00072	NM  	2001	8	9	AUS20010767      	1	20010722	G	3620		PRESSURE SWITCH 			BOEING	767   	767338      	1385151	NM  	GE    	CF6   	CF680C2*    	 	GL  					PNEUMATIC SYS	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) PNEUMATIC SYSTEM OVERPRESSURE SWITCHES CONTAMINATED WITH WATER.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA				 
2001080900073	20010809	00073	NM  	2001	8	9	AUS20010768      	1	20010215	G	2910	BACH8AEE0250T	HOSE            			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					HYDRAULIC SYSTEM	RUPTURED        	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) LT MAIN LANDING GEAR ACTUATOR UP HOSE BURST. LOSS OF SYSTEM A' HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001080900074	20010809	00074	NM  	2001	8	9	AUS20010769      	1	20010705	G	7112		SHROUD          	LYC         	O320B2C     	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					AIR BAFFLE	MISINSTALLED    	W				A				UNSCHED LANDING         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) ENGINE TO OIL COOLER WORN AND HOLED BY RUBBING ON CARBURETTOR HEAT SHROUD.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001080900075	20010809	00075	NE  	2001	8	9	AUS20010770      	3	20010724	G	6114	660714259	HUB             			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6574 							(AUS) PROPELLER HUB SUSPECT CRACKED AROUND THE MOUNTING BOLT HOLE LOCATED AT THE 6.30 POSITION. FOUND DURING EDDY CURREN	T INSPECTION IAW AD/PR/33.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE	 
2001080700211	20010807	00211	NE  	2001	8	7	AUS20010771      	2	20010726	G	7260		MOUNT           	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		TURBINE ENGINE A	DAMAGED         	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 									(AUS) NO4 INTEGRATED DRIVE GENERATOR (IDG) BROKEN AWAY FROM GEARBOX DUE TO FAILURE OF THE MOUNT.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080700212	20010807	00212	SO  	2001	8	7	AUS20010772      	1	20010721	G	3260	922AA2YA6PZ722	SENSOR          	            	            	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOWNLOCK PROXIMITY SENSOR INTERNAL FAULT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001080900076	20010809	00076	EA  	2001	8	9	AUS20010773      	2	20010723	G	7324	2538993	GASKET          	LYC         	IO720A1B    						LYC   	O720  	IO720A1B    	41546	EA  					FUEL DIVIDER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOW DIVIDER GASKET FAULTY. NEW ITEM FROM MANUFACTURER.											3	O			1E15				 
2001080700213	20010807	00213	NM  	2001	8	7	AUS20010774      	1	20010323	G	2920	59855	VALVE           	SUNDSTRANDEM	729550C     	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		HYDRAULIC SYSTEM	CRACKED         	W			    	K	 	 	 	NONE                    				J	K	 	WARNING INDICATION        	FLUID LOSS                		DE	DESCENT        	1			AU	S 	 		49754		129					(AUS) RAM AIR TURBINE (RAT) MODULE LEAKING DUE TO CRACKED CHECK VALVE.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001080900084	20010809	00084	EU  	2001	8	9	AUS20010775      	1	20010726	G	3242	5008744	DISK            		50079961    	FOKKER	F27   	F27MK50     	       	EU  	PWA   	PWA120	PW125B      	 	NE  	ROTOL	R352	R3526123F1  	GL  	BRAKE	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					JAN8761					(AUS) BRAKE ROTATING DISC FAILED. A PART OF THE FAILED DISC PUNCTURED THE WHEEL INNER HALF AND DEFLATED THE TUBE. INVEST	IGATION FOUND NO DISCOLOURATION BUT FOUND THAT THE SLOTS HAD SPREAD FLATTENING THE OUTER CIRCUMFERENCE BETWEEN THE DRIVE	 RECESSES. THE THREE ROTATING DISCS ON THE BRAKE UNIT HAD CRACKS EMINATING FROM THEEXPANSION SLOTS.				2	H	7	2 	4T	4	T	RT	A817    	E20NE	6	C	P16NG	 
2001080700214	20010807	00214	NE  	2001	8	7	AUS20010776      	2	20010709	G	7260		MOUNT           	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		TURBINE ENGINE A	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 									(AUS) NO4 CSD MOUNT FAILED. IDG ASSEMBLY SEPARATED FROM GEARBOX.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001080700215	20010807	00215	SO  	2001	8	7	AUS20010777      	2	20010725	G	7310	641486	PIPE            	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE FUEL DIST	FRACTURED       	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		1012 							(AUS) RH ENGINE NO6 CYLINDER FUEL INJECTION LINE NIPPLE BROKEN OFF.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001080700216	20010807	00216	CE  	2001	8	7	AUS20010778      	1	20010723	G	7810	24540250	CLAMP           	CONT        	TSIO520P    	CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	ENGINE COLLECTOR	BROKEN          	W			    	K	 	 	 	NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE FORWARD LH EXHAUST CLAMP BROKEN. FORWARD AIRFRAMESTRUCTURE, COWL AND NOSE TYRE TORCHED.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001080900086	20010809	00086	CE  	2001	8	9	AUS20010779      	1	20010723	G	5512	07326133781	STRUCTURE       	CESSNA      	185         	CESSNA	185   	185         	2072802	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	HORIZONTAL STAB	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1850271					(AUS) HORIZONTAL STABILISER TIP DAMAGED.						1	H	7	1 	3O	3	O	NC	3A24    	E5CE	5	C	P3EA	 
2001080900090	20010809	00090	EU  	2001	8	9	AUS20010781      	1	20010626	G	2742	MC103	ACTUATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					STABILIZER	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 			110  							(AUS) STABILIZER ACTUATOR LEAKING. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700217	20010807	00217	EU  	2001	8	7	AUS20010782      	1	20010701	G	3411		DRAIN VALVE     	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		PITOT/STATIC SYS	STUCK           	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			NR	NOT REPORTED   	1			AU	S 	 									(AUS) PITOT STATIC SYSTEM DRAIN LINE VALVE STUCK IN OPEN POSITION.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700218	20010807	00218	EU  	2001	8	7	AUS20010784      	1	20010705	G	5210		CABLE           			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PAX DOOR	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) PASSENGER DOOR DECLUTCH CABLE TERMINAL END BROKEN.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700219	20010807	00219		2001	8	7	AUS20010785      	4	20010715	G	3460	B471ABM3	COMPUTER        	            	            	AIRBUS	310   	A310304     	       	EU  	PWA   	4152  	PW4152      	 	NE  	 		            		FLIGHT MANAGEMEN	FAULTY          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 		4363 		303					(AUS) FLIGHT AUGMENTATION COMPUTER FAULTY.						2	L	7	2 	4F			RT	A35EU   	E24NE				 
2001080900097	20010809	00097	EU  	2001	8	9	AUS20010786      	1	20010722	G	2910	296801	REDUCER         			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					HYDRAULIC SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			55929		640					(AUS) LANDING GEAR HYDRAULIC SYSTEM PRESSURE REDUCER CRACKED. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080900098	20010809	00098	EU  	2001	8	9	AUS20010787      	1	20010724	G	5270		BOSS            			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					DOOR WARNING SYS	OUT OF ADJ      	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) SERVICE / EMERGENCY DOOR STRIKER BOSS LOOSE AND MISALIGNED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001080700220	20010807	00220	SW  	2001	8	7	AUS20010788      	1	20010630	G	5313	206031314125	LONGERON        	BELL        	206L1       	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		FUSELAGE MAIN, L	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				45323					(AUS) FUSELAGE UPPER FORWARD LONGERON CRACKED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080700221	20010807	00221	SW  	2001	8	7	AUS20010789      	1	20010630	G	5320	206032307031	ANGLE           	BELL        	206L1       	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  	 		            		FUSELAGE, MISCEL	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				45323					(AUS) FUSELAGE ANGLE CRACKED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080900099	20010809	00099	NM  	2001	8	9	AUS20010790      	1	20010730	G	2910	BACC27AC12121006	FITTING         			BOEING	747   	747430      	1384942	NM  	RROYCE	RB211 	RB211524*   	 	NE  					HYDRAULIC SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LTBODY LANDING GEAR RETRACTION ACTUATOR LINE UNION CRACKED AND LEAKING. HYDRAULIC PIPE ALSO LEAKING.						2	L	7	4 	4F	4	F	RT	A20WE   	E12EU				 
2001090500195	20010905	00195	SO  	2001	9	5	AUS20010791      	1	20010724	G	2752		CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	FLAP ACTUATOR	CONTAMINATED    	W				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) RT OUTBOARD FLAP ACTUATOR ELECTRICAL CONNECTOR CONTAMINATED WITH MOISTURE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001090500196	20010905	00196	EU  	2001	9	5	AUS20010793      	1	20010710	G	2913	716988	PUMP            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HYDRAULIC PUMP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3740 							(AUS) ENGINE DRIVEN HYDRAULIC PUMP INTERNAL AND EXTERNAL DRIVE SPLINES WORN EXCESSIVELY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001090500197	20010905	00197	EA  	2001	9	5	AUS20010797      	2	20010801	G	8530	LW12933	COLLET          								LYC   	O540  	IO540K1G5   	41532	EA  					CYLINDER	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CYLINDER KIT PN 05K21102 FAULTY. CYLINDER PN LW012993 CONTAINED ONE CORRECT AND ONE INCORRECT (SMALLER) VAL	VE RETAINING COLLET FITTED TO THE EXHAUST VALVE. THE INCORRECT COLLET HAD DAMAGED THE VALVE STEM RENDERING IT UNSERVICEA	BLE.									3	O			1E4				 
2001090500204	20010905	00204	WP  	2001	9	5	AUS20010798      	2	20010724	G	7261	31032173	PUMP            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE331*     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	OIL SYSTEM	CRACKED         	W				K				NONE                    				K	E		FLUID LOSS                	VIBRATION/BUFFET          		NR	NOT REPORTED   	1			AU	S 			90   							(AUS) LT ENGINE OIL PUMP HOUSING CRACKED.						1	L	7	2 	3T	3	T	RT	A28CE   	E2WE	6	C	P15EA	 
2001090500054	20010905	00054	EU  	2001	9	5	AUS20010799      	1	20010725	G	5344	350A25122726	HINGE           	            	            	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  	 		            		FUSELAGE DOOR HI	BROKEN          	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 	 									(AUS) DOOR HINGE BROKEN.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001090500231	20010905	00231	CE  	2001	9	5	AUS20010800      	1	20010726	G	7603	1317652F	ROD END         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN5     	GL  	POWER LEVER	OUT OF ADJ      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE POWER LEVER CABLE TO POWER INPUT LEVER ROD END OUT OF ADJUSTMENT AND THE LOCKNUT WAS LOOSE. THE ROD END 	AND LOCKNUT HAD NOT BEEN CORRECTLY INSTALLED FOLLOWING FCU CHANGE.PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001090500232	20010905	00232	NM  	2001	9	5	AUS20010801      	1	20010729	G	3242	26056623	ROTOR           			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			13222							(AUS) NR 7 MAIN BODY WHEEL BRAKE ROTOR SEGMENT FAILED.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001091300255	20010913	00255	NM  	2001	9	13	AUS20010802      	1	20010731	G	2530	41610015	COFFEEMAKER     			BOEING	767   	767330      	       	NM  										GALLEY	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 					0632					(AUS) FORWARD GALLEY CENTRE COFFEE MAKER FAULTY. DURING RECTIFICATION OF THE FAULT IT WAS FOUND THAT THE COFFEEMAKER WAS	 THE INCORRECT PART NUMBER FOR FITMENT TO THIS MODEL AIRCRAFT. UNAPPROVED PART.					2	L	7	2 	4F			RT	A1NM    					 
2001090500055	20010905	00055	NM  	2001	9	5	AUS20010803      	1	20010731	G	3230	273T63041	ACTUATOR        	BOEING      	273T63016   	BOEING	767   	767204      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		LANDING GEAR RET	FAULTY          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 	 		40536		00164					(AUS) LH MAIN LANDING GEAR FORWARD DRAG BRACE DOWNLOCK ACTUATOR FAULTY. INVESTIGATION FOUND THE ACTUATOR PISTON ROD DETA	CHED FROM THE ACTUATOR BODY DUE TO FAILURE OF THE PISTON ROD IN THE THREADEDAREA WHICH ENGAGES THE PISTON RETAINING NUT.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001091300261	20010913	00261	NE  	2001	9	13	AUS20010804      	2	20010726	G	7310	40885	CONTROL UNIT    			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524*   	 	NE  					FUEL DIST	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					3474					(AUS) NR 4R REFUEL VALVE CONTROL UNIT HOUSING LEAKING.						2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2001091300267	20010913	00267	CE  	2001	9	13	AUS20010805      	1	20010726	G	3230	3581507715	BRACKET         			BEECH 	36    	A36         	1151604	CE  										LANDING GEAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK BRACKET CORRODED AT PIVOT POINT.						1	L	7	1 	3O			 	3A15    					 
2001091300268	20010913	00268	SO  	2001	9	13	AUS20010806      	1	20010730	G	2910		RESERVOIR       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	HYDRAULIC SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LOSS OF FLUID FROM GREEN HYDRAULIC SYSTEM. SUSPECT CAUSED BY INCORRECT BRAKING SEQUENCE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001091300269	20010913	00269	EA  	2001	9	13	AUS20010807      	2	20010724	G	8500	L575861A	ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LEFT	FAILED          	W				O				OTHER                   				E	R	F	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLT CONT AFFECTED         	CL	CLIMB          	1			AU	S 			1041 							(AUS) LT ENGINE POWER LOSS AND VIBRATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091300270	20010913	00270	SO  	2001	9	13	AUS20010808      	1	20010510	G	2730		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR CONTROL	UNAPPROVED PART 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR PUSHROD BOLTS INCORRECT TYPE AS REQUIRED BY AD/PA31/121AMDT1. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERRO	R.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500056	20010905	00056	EA  	2001	9	5	AUS20010809      	2	20010428	G	7310		FILTER          	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL DIST	LEAKING         	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 	 									(AUS) RH ENGINE FUEL FILTER SEAL LEAKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091300271	20010913	00271	SO  	2001	9	13	AUS20010810      	1	20010515	G	5210	4225000	HANDLE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	PAX DOOR	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR INNER HANDLE HAD UNAPPROVED REPAIR. HANDLE HAD BEENWELDED IN TWO PLACES. PERSONNEL/MAINTENANCE ERROR. U	NAPPROVED REPAIR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500057	20010905	00057	SO  	2001	9	5	AUS20010811      	1	20010424	G	7920	3999502	HOSE            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL DISTR	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL PRESSURE HOSE LOCATED BETWEEN VERNATHERM AND OIL COOLER INCORRECTLY ROUTED CAUSING PREMATURE DETERIORAT	ION DUE TOHEAT DAMAGE. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500058	20010905	00058	EA  	2001	9	5	AUS20010812      	2	20010419	G	7310	74134	FILTER          	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL DIST	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL FILTER LEAKING. FILTER BOWL LOOSE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500059	20010905	00059	EA  	2001	9	5	AUS20010813      	2	20010212	G	7310	74134	FILTER          	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL DIST	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) FUEL FILTER BOWL LEAKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091300272	20010913	00272	SO  	2001	9	13	AUS20010814      	1	20010419	G	7603	24894	CABLE           	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	POWER LEVER	MISRIGGED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) THROTTLE CABLE INCORRECTLY ASSEMBLED AND RIGGED.PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500060	20010905	00060	SO  	2001	9	5	AUS20010815      	1	20010329	G	3230		UPLOCK          	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	SHEARED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR UPLOCK EYE SHEARED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500061	20010905	00061	SO  	2001	9	5	AUS20010816      	1	20010410	G	7603	2489402	CABLE           	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	POWER LEVER	SEPARATED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE THROTTLE CABLE SECTIONS LOCKWIRED TOGETHER. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700185	20010917	00185	SO  	2001	9	17	AUS20010817      	1	20010412	G	7603	24894	ROD END         	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	POWER LEVER	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE CONTROL ARM RODEND INCORRECTLY ASSEMBLED ON THE WRONG SIDE OF THE ARM CAUSING LOAD ON THE CABLE BALL END	.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500062	20010905	00062	SO  	2001	9	5	AUS20010818      	1	20010412	G	7920	3999505	HOSE            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL DISTR	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL COOLER HOSE DETERIORATED DUE TO BEING INCORRECTLYROUTED CLOSE TO TURBOCHARGER. HOSE ALSO HAD EXCESSIVE 	BENDRADIUS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500063	20010905	00063	SO  	2001	9	5	AUS20010819      	1	20010412	G	7810		EXHAUST PIPE    	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE COLLECTOR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE EXHAUST SYSTEM TRANSITIONS HOLED AND CRACKED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700187	20010917	00187	SO  	2001	9	17	AUS20010820      	1	20010412	G	7810		EXHAUST PIPE    	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE COLLECTOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT TAILPIPE INCORRECTLY FITTED TO TURBOCHARGER CAUSING BURNING OF THE EXHAUST CLAMP.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500064	20010905	00064	SO  	2001	9	5	AUS20010821      	1	20010412	G	7810		GASKET          	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE COLLECTOR	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE TURBOCHARGER EXHAUST TRANSITIONS FITTED WITHOUT A CRUSH GASKET. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500065	20010905	00065	EA  	2001	9	5	AUS20010823      	2	20010803	G	7313	74151	INJECTOR        	LYC         	IO540K1B5   	BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL INJECTOR NO	BLOCKED         	W			    	K	 	 	 	NONE                    				E	A	 	VIBRATION/BUFFET          	FLAME/FIRE                		LD	LANDING        	1			AU	S 	 									(AUS) NO1 ENGINE FUEL INJECTOR NOZZLE PARTIALLY BLOCKED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001090500067	20010905	00067	CE  	2001	9	5	AUS20010825      	1	20010710	G	5712	08221757	RIB             	            	            	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING, RIB/BULKHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING RIBS LOCATED IN LH WHEEL BAY CRACKED AS INDICATED IN CESSNASERVICE LETTER ME76-2.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001090500068	20010905	00068	CE  	2001	9	5	AUS20010826      	1	20010731	G	7920	111F4176S0220	HOSE            	LYC         	O320E2D     	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE OIL DISTR	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE OIL COOLER HOSE POROUS AND LEAKING IN THE AREA ON THEOUTSIDE OF THE BEND AT THE ENGINE END. FIRE SLEEVINGCO	NTAMINATED. HOSE MANUFACTURED 30 DECEMBER 1996.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001090500069	20010905	00069	SO  	2001	9	5	AUS20010827      	1	20010419	G	7920		HOSE            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL DISTR	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TURBOCHARGER OIL SUPPLY LINE DETERIORATED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700191	20010917	00191	SO  	2001	9	17	AUS20010828      	1	20010805	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	OUT OF ADJ      	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR DOOR MICROSWITCHES OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500070	20010905	00070	SO  	2001	9	5	AUS20010829      	1	20010424	G	7920		HOSE            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE OIL DISTR	DETERIORATED    	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TURBOCHARGER OIL PRESSURE HOSE INCORRECTLY ROUTED. HOSE DETERIORATED DUE TO HEAT. HOSE LOOSE ON END FITTING.PERSON	NEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500071	20010905	00071	SO  	2001	9	5	AUS20010830      	1	20010402	G	7112		BAFFLE          	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE AIR BAFFL	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LOWER ENGINE BAFFLE MISSING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700192	20010917	00192	EA  	2001	9	17	AUS20010831      	2	20010727	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE NR 2 CYLINDER FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500072	20010905	00072	SO  	2001	9	5	AUS20010832      	1	20010727	G	2140		HEATER          	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	FAILED          	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 	 									(AUS) HEATER FAILED. SPARKING BEHIND INSTRUMENT PANEL CAUSED BY FOREIGN OBJECT FALLING ACROSS TERMINALS.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700193	20010917	00193	EA  	2001	9	17	AUS20010833      	2	20010727	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE NR 2 CYLINDER FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700195	20010917	00195	EA  	2001	9	17	AUS20010834      	2	20010529	G	8530		CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE NR 2 CYLINDER FAILED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091700197	20010917	00197	SW  	2001	9	17	AUS20010836      	1	20010801	G	2910	212076176001	PIPE            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYDRAULIC SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE CRACKED IN RADIUS.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001091700199	20010917	00199	SO  	2001	9	17	AUS20010837      	1	20010609	G	5751	62373000	DOUBLER         			PIPER 	PA28  	PA28140     	7102802	SO  										AILERONS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT AILERON DOUBLER CRACKED.						1	L	7	1 	3O			 	2A13    					 
2001091700202	20010917	00202	NE  	2001	9	17	AUS20010839      	2	20010731	G	7321	12773	FUEL CONTROL    			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 4 ENGINE	FAULTY          	W				E				ENGINE SHUTDOWN         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		DE	DESCENT        	1			AU	S 			6396 							(AUS) NR 4 ENGINE FUEL FLOW REGULATOR FAULTY. AIRCRAFT IS FOREIGN REGISTRATION DQ-FJE.						2	L	7	4 	4F	4	F	 	A20WE   	E12EU				 
2001090500073	20010905	00073	CE  	2001	9	5	AUS20010840      	1	20010614	G	3230	98820152	ACTUATOR        	            	            	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR RET	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR ACTUATOR FAULTY.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001091700207	20010917	00207	CE  	2001	9	17	AUS20010843      	1	20010803	G	5540	51310103	HINGE           			CESSNA	441   	441         	2076020	CE  										RUDDER	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER RUDDER HINGE BRACKET INSTALLED UPSIDE DOWN. FOUND DURINGINSPECTION IAW CESSNA CQB00-2 R1. MANUFACTURING ERRO	R.					1	L	7	2 	3T			RT	A28CE   					 
2001091700208	20010917	00208		2001	9	17	AUS20010844      	4	20010713	G	6122	5AA228	GOVERNOR        			LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  	HAMSTD	43E	43E60       	NE  	PROPELLER	FAULTY          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NR 4 ENGINE GOVERNOR FAULTY.						2	L	7	4 	4R	4	R	 	6A5     	E272	6	C	P871	 
2001091700210	20010917	00210	NE  	2001	9	17	AUS20010845      	2	20010714	G	8500		ENGINE          			DOUG  	DC3   	C47B        	3021467	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	LEFT	MAKING METAL    	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE OIL FILTER METAL CONTAMINATION. ENGINE CHANGED.						2	L	7	2 	4R	4	R	 	A669    	5E4	6	C	P603	 
2001090500074	20010905	00074	GL  	2001	9	5	AUS20010846      	2	20010728	G	7230	6898607	BEARING         	ALLSN       	250C20F     	AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20F     	03013	GL  	 		            		TURBINE ENGINE C	DAMAGED         	W			    	K	 	 	 	NONE                    				E	 	J	VIBRATION/BUFFET          		WARNING INDICATION        	DE	DESCENT        	1			AU	S 	 				CAC40345					(AUS) NO2 ENGINE NO1 BEARING FAILED.						1	G	7	2 	3U	3	U	 	H11EU   	E4CE				 
2001091700214	20010917	00214	NE  	2001	9	17	AUS20010848      	2	20010626	G	7230		SEAL            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENGINE	LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) NR 1 ENGINE OIL LEAKING AROUND BLEED BAND AREA. NR 1 SEAL LEAKING.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001091700215	20010917	00215	NM  	2001	9	17	AUS20010850      	1	20010807	G	6310	A1902	BELT            			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					TRANSMISSION	FRAYED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					7390					(AUS) REAR DRIVE BELT FRAYED, SPLIT AND ROLLED OFF PULLEY.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001091700217	20010917	00217	SO  	2001	9	17	AUS20010851      	1	20010723	G	3260		SWITCH          			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A     	41532	EA  	MCAULY	2D36C	2D36C28     	GL  	MLG	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWN LIMIT MICROSWITCH INCORRECTLY WIRED.WHEN THE NLG MICROSWITCH WIRES WERE DISCONNECTED THE	 DOWN LIGHT WAS STILL ON. INVESTIGATION FOUND THE RT LANDING GEAR MICROSWITCH WIRING WAS INCORRECT. PERSONNEL/MAINTENANC	E ERROR.				1	L	7	1 	3O	3	O	 	1A15    	E295	5	C	P901	 
2001091700219	20010917	00219	SW  	2001	9	17	AUS20010852      	1	20010802	G	6210	212015501115	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) MAIN ROTOR BLADE SKIN DELAMINATED AT THE BLADE TIP JUST AFT OFTHE D' SPAR. AREA OF DELAMINATION 55MM BY 75MM (2IN 	BY 3IN).					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001091700222	20010917	00222	NM  	2001	9	17	AUS20010855      	1	20010803	G	5311	A0202	FRAME           			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER FUSELAGE FRAME CRACKED. FOUND DURING MAGNETIC PARTICLE INSPECTION.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001091700223	20010917	00223	CE  	2001	9	17	AUS20010856      	1	20010808	G	2434	ALV9501R	ALTERNATOR      			CESSNA	404   	404CESSNA   	2075901	CE  										ENGINE	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 										(AUS) ALTERNATOR FAILED IN FLIGHT. INVESTIGATION FOUND THE ALTERNATOR HOUSING ASSEMBLY BOLTS LOOSE WITH TWO OF THE BOLTS	 HAVING COMPLETELY SEPARATED AND LAYING IN THE BOTTOM OF THE ENGINE COWL. REAR BEARING COLLAPSED. INCORRECT TAB WASHERS 	USED. TAB WASHERS WERE FOR USE ON A 6.35MM (0.25IN) BOLT WHEREAS THE BOLTS USED ONTHE ALTERNATOR WERE 4.762MM (0.185IN).	 UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.			1	L	7	2 	3O			 	A25CE   					 
2001091700224	20010917	00224	EU  	2001	9	17	AUS20010857      	1	20010716	G	5730		SKIN            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SKIN CORRODED IN AREA BETWEEN RIB 13 AND RIB 15.CORROSION WAS BEYOND ALLOWIABLE LIMITS.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001091700226	20010917	00226	CE  	2001	9	17	AUS20010858      	1	20010809	G	3233	1CH1066	SWITCH          	TEIJINSEIKI 	99101393    	CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG ACTUATOR	OUT OF ADJ      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1851					(AUS) NOSE LANDING GEAR ACTUATOR POSITION SWITCH INCORRECTLY ADJUSTED.PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001091700228	20010917	00228	NM  	2001	9	17	AUS20010859      	1	20010809	G	5270	284A3539	SWITCH          			BOEING	737   	737*        	       	NM  	CFMINT	CFM56 	CFM565A1    	 	NE  					DOOR WARNING	FAULTY          	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) LT OVERWING EXIT WARNING SWITCH FAULTY.						2	L	7	2 	4F	4	F	RT	A16WE   	E29NE				 
2001090500077	20010905	00077	CE  	2001	9	5	AUS20010860      	1	20010713	G	2434	ALV9510R	ALTERNATOR      	            	            	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	DC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 		100  		9011080					(AUS) ALTERNATOR ROTOR SHAFT WORN IN AREA OF FORWARD ARMATURE SLIPRING.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001091700229	20010917	00229	NE  	2001	9	17	AUS20010861      	2	20010807	G	7421	CH34055	IGNITER         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) NR 1 ENGINE LOWER IGNITER CENTRE CORE MISSING. P3 AIR LEAKING INTO ENGINE BAY.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001091700232	20010917	00232	NM  	2001	9	17	AUS20010862      	1	20010201	G	5311		FRAME           			BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT BULKHEAD OUTER CHORD LOCATED AT BS1809.5 CRACKED IN AREA OFLOWER TWO FASTENERS IN INSPECTION AREA 1.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001090500078	20010905	00078	CE  	2001	9	5	AUS20010863      	1	20010810	G	7931		PIPE            	CONT        	O470R       	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE OIL PRESS	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		7167 							(AUS) ENGINE OIL PRESSURE PIPE FROM FIREWALL TO GAUGE CORRODED IN AREAOF CONTACT WITH SOUNDPROOFING MATERIAL. PIPE IS MA	NUFACTURED FROM ALUMINIUM.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001091800002	20010918	00002	EU  	2001	9	18	AUS20010864      	1	20010813	G	6410	109813201107	BLADE           			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			113  							(AUS) TAIL ROTOR BLADE CRACKED ON INNER FACE. THE CRACK LENGTH RUNS FOR ALMOST THE FULL CHORD OF THE BLADE. FOUND DURING	 INSPECTION IAW AD/119/1 PT1.					1	G	7	2 	3U	4	U	 	H7EU    	E22EA				 
2001090500079	20010905	00079	NM  	2001	9	5	AUS20010865      	1	20010323	G	2920	59855	VALVE           	            	            	BOEING	767   	767277      	       	NM  	GE    	CF6   	CF680A      	30025	NE  	 		            		HYDRAULIC SYSTEM	CRACKED         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			DE	DESCENT        	1			AU	S 	 		49754		129					(AUS) RAM AIR TURBINE (RAT) MODULE CHECK VALVE CRACKED. LOSS OF HYDRAULIC FLUID. INVESTIGATION FOUND THAT THE HEX HEAD S	EPARATEDFROM THE CHECK VALVE BODY DUE TO A FRACTURE BETWEEN THE UPPER O' RING GROOVE AND THE INTERNAL BODY THREAD RELIEF	.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001091800004	20010918	00004	NM  	2001	9	18	AUS20010867      	1	20010313	G	5312		BULKHEAD        			BOEING	737   	737377      	       	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD LOCATED AT BS178 CRACKED IN TWO LOCATIONS. ONE CRACK FOUND IN LBL 5.7 LOCATED THROUGH IN	SULATIONBLANKET HOLE. CRACK LENGTH 15.875MM (0.625IN). ONE CRACK FOUND IN RBL 17.1 LOCATED THROUGH INSULATION BLANKET HO	LE. CRACK LENGTH15.875MM (0.625IN). FOUND DURING HIGH FREQUENCY EDDY CURRENTINSPECTION.				2	L	7	2 	4F			RT	A16WE   					 
2001091800005	20010918	00005	SO  	2001	9	18	AUS20010868      	1	20010716	G	2912	756164	SPRING          			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					HYDRAULIC FILTER	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC FILTER SPRING MISSING.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001091800006	20010918	00006	SO  	2001	9	18	AUS20010869      	1	20010716	G	3242	16405700	DISK            	CLEVELAND   	16405700    	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					BRAKE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BRAKE DISCS WORN BELOW MINIMUM THICKNESS. BOTH DISCS ALSO EXHIBITED EVIDENCE OF RADIAL HEAT STRESS CRACKING.						1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001090500081	20010905	00081	SO  	2001	9	5	AUS20010871      	1	20010808	G	2910		PIPE            	            	            	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HYDRAULIC SYSTEM	FRACTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HYDRAULIC PIPE FRACTURED. PIPE IS LOCATED IN RH NOSE AREA.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091800007	20010918	00007	CE  	2001	9	18	AUS20010872      	1	20010814	G	3244	29X111010PR	TIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR TIRE SUSPECT FAULTY. DURING LANDING THE TIRE EXHIBITED EXCESSIVE SIDEWARD DEFLECTION COUPLED WIT	H MINIMAL CLEARANCE CAUSED THE INSIDE WALL OF THE TIRE TO CONTACT THE BRAKE ASSEMBLY.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001090500082	20010905	00082	CE  	2001	9	5	AUS20010873      	1	20010612	G	5343	244110010	PIVOT           	            	            	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR ATT	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) MAIN LANDING GEAR PIVOTS FAILED PROVISIONS OF CESSNA SERVICEBULLETIN SEB 90-1 REVISION3.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001091800008	20010918	00008	NE  	2001	9	18	AUS20010874      	2	20010625	G	7250	2303713	SEAL            	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE SECTION	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE NR 9 BEARING SEAL LEAKING. SUSPECT FUMES ENTERING CABIN AND CAUSING CREW PROBLEMS.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001090500083	20010905	00083	EA  	2001	9	5	AUS20010875      	2	20010813	G	8520	SL13884M06	BEARING         	LYC         	IO540E1B5   	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	RECIPROCATING EN	DELAMINATED     	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		118  		L595548					(AUS) ENGINE FRONT MAIN BEARING DEFECTIVE. BEARING MATERIAL APPEARS TOBE DELAMINATED FROM BEARING SHELL. METAL CONTAMINA	TION OF OIL SYSTEM. SUSPECT MANUFACTURING FAULT.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P25EA	 
2001091800009	20010918	00009	NE  	2001	9	18	AUS20010876      	2	20010726	G	7230	230318706	SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE ENGINE	WORN            	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			AU	S 										(AUS) NR 3 ENGINE LEAKING OIL FROM BLEED BAND AREA. FUMES ENTERING CABIN THROUGH AIR CONDITIONING SYSTEM. INVESTIGATION 	FOUND NO1 BEARINGSEAL AND FACE PLATE ASSEMBLY WORN.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001091800010	20010918	00010	EU  	2001	9	18	AUS20010877      	1	20010509	G	2120		HOSE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	AIR DISTRIBUTION	CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) AVIONICS COOLING SCAT HOSE CHAFED ON PRINTED CIRCUIT BOARD. HOSEINNER WIRE SHORT CIRCUITED CAUSING HOSE TO BURN.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2001090500084	20010905	00084	SO  	2001	9	5	AUS20010878      	1	20010515	G	5753	12021940001	BRACKET         	            	            	EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  	HAMSTD	14SF	14SF9       	NE  	TRAILING EDGE FL	BROKEN          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) LH OUTBOARD FLAP SHROUD INBOARD ROLLER AND BRACKET BROKEN OFF CAUSING FLAP TRACK TO FOUL ON SHROUD.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	N	P11NE	 
2001090500087	20010905	00087	EA  	2001	9	5	AUS20010882      	2	20010801	G	8520		CRANKCASE       	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE CRANKCASE DAMAGED. NO3 CYLINDER EXHAUST TAPPET BODY ALSO DAMAGED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001091800013	20010918	00013	EA  	2001	9	18	AUS20010885      	2	20010813	G	7250	3010311	ENGINE          			DHAV  	DHC6  	DHC6100     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FOLLOWING REPAIR FOR OVERTEMP AND FOD IN THE USA THE RT ENGINE WAS FITTED AND PREPARED FOR STARTING. THE ENGINE WA	S WOUND OVER WITHOUT LIGHTING UP AND AN INTERNAL RUBBING NOISE WAS HEARD. THE ENGINE WAS PARTIALLY DISMANTLED AND INSPEC	TION FOUND THE COMPRESSOR TURBINE RUBBING ON SEGMENTS IN SMALL EXIT DUCT.FURTHER STRIPPING AND INSPECTION FOUND ABRASIVE	 MATERIAL IN THE COMBUSTION CHAMBER. INSPECTION ALSO FOUND THAT THE POWER TURBINE LOCK WIRING WAS CARRIED OUT WITH STAIN	LESS STEEL LOCKWIRE INSTEAD OF ICONEL LOCKWIRE. THE ITT PROBES WERE FOUND TO BE FINGER TIGHT AND INCORRECTLY SECURED. PE	RSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.	1	H	7	2 	3T	3	T	 	A9EA    	E4EA	6	C	P15EA	 
2001091800014	20010918	00014	NM  	2001	9	18	AUS20010886      	1	20010117	G	3230	BACB10A554	BEARING         			BOEING	737   	737377      	       	NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					NLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR MANUAL EXTENSION RELEASE MECHANISM TORQUE SHAFT BEARINGS SEIZED.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001091800015	20010918	00015	EU  	2001	9	18	AUS20010888      	1	20010805	G	2731	NB45C1867	ROD END         			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ELEVATOR TAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB DRIVE ROD END WORN. INSPECTION FOUND THE LEFT THREADED LOCKNUT STRIPPED.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001090500088	20010905	00088	CE  	2001	9	5	AUS20010889      	1	20010816	G	2910	581710219	PIPE            	            	            	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	HYDRAULIC SYSTEM	CRACKED         	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CR	CRUISE         	1			AU	S 	 									(AUS) MAIN LANDING GEAR EXTENSION SYSTEM HYDRAULIC PIPE CRACKED INBEND. LOSS OF HYDRAULIC FLUID.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001090500089	20010905	00089	NE  	2001	9	5	AUS20010890      	2	20010811	G	7230		SEAL            	LYC         	ALF502R5    	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		TURBINE ENGINE C	LEAKING         	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			AU	S 	 									(AUS) NO1 ENGINE NO9 BEARING SEAL LEAKING. FUMES IN CABIN.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001090500090	20010905	00090	NE  	2001	9	5	AUS20010892      	2	20010817	G	7321	324476812	FCU             	PWA         	PT6A42      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUEL CONTROL/TUR	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		3597 							(AUS) LH ENGINE FUEL CONTROL UNIT FAULTY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2001091800017	20010918	00017	SW  	2001	9	18	AUS20010893      	1	20010712	G	6420	206011812001	TRUNNION        	BELL        	206011810   	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2400 		AAG00543					(AUS) TAIL ROTOR TRUNNION SUSPECT CRACKED. TRUNNION GAVE A POSITIVE CRACK INDICATION USING BOTH MPI AND FPI INSPECTIONS.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001091800018	20010918	00018	GL  	2001	9	18	AUS20010894      	2	20010614	G	7250	23063354	ENGINE          			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47B     	 	GL  					NACELLE	OVERHEATED      	W				E				ENGINE SHUTDOWN         				E	M		VIBRATION/BUFFET          	OVER TEMP                 		NR	NOT REPORTED   	1			AU	S 										(AUS) TURBINE OVER TEMPERATURE DURING ENGINE SHUTDOWN.						1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2001090500091	20010905	00091	EU  	2001	9	5	AUS20010895      	1	20010601	G	7710		LINE            	RROYCE      	SPEY55515   	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		POWER INDICATING	LOOSE           	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 	 									(AUS) NO2 ENGINE THRUST FEED SENSE LINE TO GAUGE LOOSE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001091800019	20010918	00019	EU  	2001	9	18	AUS20010897      	1	20010605	G	3232	AH533	ACTUATOR        			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					MLG DOOR	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 			6320 							(AUS) LT MAIN LANDING GEAR DOOR AFT ACTUATOR CRACKED AND LEAKING. LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001090500092	20010905	00092	EU  	2001	9	5	AUS20010898      	1	20010621	G	3230		LEVER           	            	            	FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		LANDING GEAR RET	STUCK           	W			    	K	 	 	 	NONE                    				O	F	 	OTHER                     	FLT CONT AFFECTED         		TO	TAKEOFF        	1			AU	S 	 									(AUS) LANDING GEAR RETRACTION LEVER STUCK IN DOWN POSITION. CIRCUIT BREAKER L8 POPPED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2001091800020	20010918	00020	EU  	2001	9	18	AUS20010899      	1	20010726	G	7931	642514172	TRANSMITTER     			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					ENGINE OIL PRESS	FAILED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 			266  							(AUS) NR 3 ENGINE OIL PRESSURE TRANSMITTER FAULTY.						2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2001091800023	20010918	00023	EU  	2001	9	18	AUS20010902      	2	20010627	G	7250		BLADE           			BOEING	737   	737400      	       	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			20631							(AUS) NR 1 ENGINE HIGH PRESSURE TURBINE BLADE CRACKED FROM HOLE. FOUND DURING BOROSCOPE INSPECTION IAW EI 737-72-525.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2001091900166	20010919	00166	SO  	2001	9	19	AUS20010903      	1	20010515	G	2710		CONTROL UNIT    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL SYSTEM HAD EXCESSIVE PLAY. INVESTIGATION FOUNDUNIVERSAL PNO 46203-02 WORN COMPLETELY THROUGH BUSH 	PNO 453-824 AND INTO BRACKET PNO 29197-02 MOUNTED ON FORWARD BULKHEAD.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001090500093	20010905	00093	EA  	2001	9	5	AUS20010904      	2	20010814	G	8520	L1959448	STUD            	LYC         	IO540E1B5   	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	RECIPROCATING EN	SHEARED         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 		1340 		L1959448					(AUS) LH ENGINE NO4 CYLINDER HOLDDOWN STUDS (3OFF) SHEARED. FOLLOWING REMOVAL OF THE CYLINDER THE CRANKCASE WAS FOUND TO	 BE CRACKED THROUGH THE AREA OF THE HOLDDOWN STUDS.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2001090500094	20010905	00094	CE  	2001	9	5	AUS20010908      	1	20010712	G	2711	AN36A	BOLT            	            	            	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	AILERON TAB CONT	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ELEVATOR TRIM TAB ACTUATOR TO TRIM TAB ROD ATTACHMENT BOLTS WORN. FOUND DURING INSPECTION IAW AD/B55/59.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001090500099	20010905	00099	WP  	2001	9	5	AUS20010919      	2	20010731	G	7314	8974007	PUMP            	GARRTT      	TPE33112UA  	BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	ENGINE FUEL PUMP	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		4306 		P6012					(AUS) ENGINE FUEL PUMP HOUSING CRACKED IN AREA OF CONCENTRIC SHAFTSUPPORT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE	 
2001090500101	20010905	00101	NE  	2001	9	5	AUS20010921      	2	20010628	G	7230	PCE93406	COMPRESSOR      	PWA         	PT6A42      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE ENGINE C	FOD             	W			    	K	 	 	 	NONE                    				E	B	 	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		TO	TAKEOFF        	1			AU	S 	 				PCE93406					(AUS) ENGINE COMPRESSOR EXTENSIVELY DAMAGED BY FOD. INVESTIGATION FOUND A DAMAGED WASHER IN THE COWL. SUSPECT CAME FROM 	BOLT SECURING COMPRESSOR SCREEN REMOVED DURING MAINTENANCE PRIOR TO THISFLIGHT. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001091900180	20010919	00180	CE  	2001	9	19	AUS20010923      	1	20010814	G	3244	29X111010PR	TIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	FAULTY          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR TYRE HAD EXCESSIVE SIDEWARDS DEFLECTION DURING LANDING CAUSING THE TYRE TO CONTACT THE BRAKE ASS	EMBLY. TYRE SIZE 29X11.0X10 10PLY.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001090500103	20010905	00103	WP  	2001	9	5	AUS20010925      	1	20010824	G	6520	369A54083	SHAFT           	HUGHES      	369A5400    	HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20      	03013	GL  	 		            		TAIL ROTOR GEARB	DISTORTED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		344  		B222					(AUS) TAIL ROTOR GEARBOX OUTPUT SHAFT BEARINGS BREAKING UP AND SHAFTRUNOUT EXCESSIVE. SHAFT RUNOUT APPROXIMATELY 0.457MM	 (0.018IN). MAXIMUM RUNOUT 0.0254MM (0.001IN).					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001091900185	20010919	00185		2001	9	19	AUS20010927      	4	20010205	G	2565	D30665101MOD	SLIDE           			AIRBUS	320   	A320*       	       	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 			5003 							(AUS) SLIDERAFT SEAL FAILED DURING INFLATION TEST. SEAL SEPARATION OCCURRED IN THE UPPER CHAMBER AT THE INTERSECTION OF 	THE UPPERAND SIDE TUBES. LENGTH OF TEAR 304.8MM (12IN). SLIDE HAD BEEN SENT TO WORKSHOP FOR REPAIR FOLLOWING AN INCIDENT	 WITH MOBILE STAIRS.				2	L	7	2 	4F	4	F	RT	A46NM   	E29NE				 
2001090500105	20010905	00105	EA  	2001	9	5	AUS20010930      	2	20010822	G	7322	30804	FLOAT           	FACET       	MA4SPA      	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL CONTROL/REC	DAMAGED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		163  		BL198636					(AUS) CARBURETTOR FLOAT CONTAMINATED WITH FUEL CAUSING CARBURETTOR TO FLOOD.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001090500106	20010905	00106	GL  	2001	9	5	AUS20010932      	1	20010726	G	8120	3BT5EE10J2	TURBOCHARGER    	LYC         	HIO360E1AD  	ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  	 		            		EXHAUST TURBOCHA	FOD             	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TO	TAKEOFF        	1			AU	S 	 									(AUS) ENGINE TURBOCHARGER INGESTED A NUT FROM THE AIR STATIC TUBE LOCATED INSIDE THE AIR CLEANER. FOD.						1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2001092000029	20010920	00029	CE  	2001	9	20	AUS20010934      	1	20010823	G	5531	07310292	SPAR            			CESSNA	185   	185F        	2072820	CE  	CONT  	O470  	O470R       	17026	SO  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PN073100149					(AUS) VERTICAL STABILISER REAR SPAR ASSEMBLY CRACKED IN TWO AREAS ADJACENT TO THE FUSELAGE BULKHEAD ATTACHMENT POINT.						1	H	7	1 	3O	3	O	 	3A24    	E273				 
2001090500107	20010905	00107	CE  	2001	9	5	AUS20010935      	1	20010810	G	3230	HMX5FG	ROD END         	            	            	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	E	 	OTHER                     	VIBRATION/BUFFET          		TO	TAKEOFF        	1			AU	S 	 									(AUS) LH LANDING GEAR INBOARD RETRACTION ROD OUTBOARD RODEND BALL SOCKET FRACTURED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001090500108	20010905	00108	SO  	2001	9	5	AUS20010936      	2	20010827	G	8520		CRANKSHAFT      	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 									(AUS) CRANKSHAFT BROKEN AT NO4 MAIN BEARING JOURNAL.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001091900194	20010919	00194	SO  	2001	9	19	AUS20010938      	2	20010214	G	8530		PISTON          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	ENGINE	DAMAGED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 										(AUS) NR 2 CYLINDER PISTON HOLED IN AREA OF RING GROOVES. EXCESSIVE CRANKCASE PRESSURE VENTED OIL THROUGH THE BREATHER. 	LOSS OF OIL PRESSURE CAUSED NR 1 CYLINDER CONNECTING ROD BIGEND FAILURE. INVESTIGATION FOUND A PIECE OF BROKEN PISTON RI	NG HAD BEEN WORKING IN THE RING GROOVE CAUSING FAILURE OF THE LAND.				1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2001091900197	20010919	00197	SW  	2001	9	19	AUS20010939      	1	20010827	G	5620	412670101	WINDOW          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COCKPIT	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 										(AUS) LT SLIDING DOOR REAR WINDOW FAILED. MINOR DAMAGE TO HF RADIO ANTENNA CONNECTOR AND HORIZONTAL STABILISER.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001091900203	20010919	00203	NM  	2001	9	19	AUS20010941      	1	20010401	G	5310		STRUCTURE       			BOEING	737   	737377      	       	NM  										FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CORROSION CONTROL INSPECTION FOUND AREAS OF LEVEL 2 CORROSION.FOUND DURING INSPECTION IAW AD/B737/52 AMDT2.						2	L	7	2 	4F			RT	A16WE   					 
2001091900204	20010919	00204	NM  	2001	9	19	AUS20010942      	1	20010401	G	5310		STRUCTURE       			BOEING	737   	73733A      	1384673	NM  										FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CORROSION CONTROL INSPECTION FOUND AREAS OF LEVEL 2 CORROSION.FOUND DURING INSPECTION IAW AD/B737/52 AMDT2.						2	L	7	2 	4F			RT	A16WE   					 
2001090500109	20010905	00109	SO  	2001	9	5	AUS20010943      	2	20010820	G	8520	634503	BEARING         	CONT        	GTSIO520H   	CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		600  		235015R					(AUS) ENGINE OIL FILTER CONTAMINATED WITH METAL. INVESTIGATION FOUNDNO1 AND NO2 BEARINGS HAD COMPLETELY FAILED WITH THE 	BEARING SHELLS BROKEN IN HALF. TRANSVERSE CRACKS WERE FOUND AROUND THECRANKSHAFT NO2 MAIN JOURNAL WITH CATASTROPHIC FAIL	URE IMMINENT.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2001091900237	20010919	00237	CE  	2001	9	19	AUS20010944      	1	20010824	G	3260	727725	CIRCUIT BREAKER 			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					MLG INDICATOR	FAULTY          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR INDICATION SYSTEM CIRCUIT BREAKER HAD HIGH RESISTANCE.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001101500028	20011015	00028	CE  	2001	10	15	AUS20010947      	1	20010824	G	7602	MC98620661	LEVER           	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MIXTURE CONTROL	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) MIXTURE CONTROL VERNIER FAILED. CENTRE KNOB AND SHAFT SEPARATED FROM MIXTURE CONTROL.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002010800002	20020108	00002	GL  	2002	1	8	AUS20010948      	1	20010825	G	3211	AN531A	BOLT            			AMTR  	MK1   	MK1         	05620JY	GL  										MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR REAR MOUNT BOLT FAILED DURING HEAVY LANDING. MINOR DAMAGE TO REAR OF SPAR.						1	H	7	1 	3O			NC	EXPA1H71					 
2001101500030	20011015	00030	EA  	2001	10	15	AUS20010952      	2	20010829	G	7310	3011849	PIPE            	PWA         	PT6A34      	EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE FUEL DIST	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2002010800006	20020108	00006	CE  	2002	1	8	AUS20010955      	1	20010823	G	2612	473275	DETECTOR        			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					FIRE DETECTION	UNSERVICEABLE   	W				O				OTHER                   				N	O		FALSE WARNING             	OTHER                     		CR	CRUISE         	1			AU	S 										(AUS) FIRE DETECTOR FAULTY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001101500031	20011015	00031	NM  	2001	10	15	AUS20010956      	1	20010904	G	3520	28003101	LANYARD         	            	            	BOEING	767   	767238      	       	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		PASSENGER OXYGEN	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) OXYGEN MASKS LOCATED AT SEATS 26J/K HAD MISSING LANYARDS (3OFF).						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001101500033	20011015	00033	EU  	2001	10	15	AUS20010960      	1	20010820	G	5720		BRACKET         	PARTEN      	P68         	PARTEN	P68   	P68B        	       	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	WING, MISCELLANE	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING LEADING EDGE TOP FORWARD ATTACHMENT BRACKET CORRODED.						1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2001101500034	20011015	00034	GL  	2001	10	15	AUS20010962      	1	20010822	G	3710	215CC	PUMP            	            	            	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	VACUUM DISTRIBUT	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			NR	NOT REPORTED   	1			AU	S 	 				11609					(AUS) VACUUM PUMP SEIZED AND DRIVE SHAFT SHEARED.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2002010800009	20020108	00009	CE  	2002	1	8	AUS20010963      	1	20010828	G	2434		SEAL            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	DC GENERATOR-ALT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			9    							(AUS) LT ENGINE DRIVEN ALTERNATOR DRIVE SEAL LEAKING. INVESTIGATION FOUND THAT THE SEAL WAS INCORRECTLY FITTED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001101500035	20011015	00035	CE  	2001	10	15	AUS20010964      	1	20010903	G	5730	552212126	SPLICE          	CESSNA      	550         	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  	 		            		WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				550054					(AUS) RH WING SKIN SPLICE CORRODED. AREAS OF SPLICE ASSEMBLY DISBONDED.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002010800010	20020108	00010	NM  	2002	1	8	AUS20010965      	1	20010904	G	3242	AS11506K0346	HOSE            			BOEING	737   	737400      	138449A	NM  	CFMINT	CFM56 	CFM563B1US  	 	GL  					BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 BRAKE HOSE FRACTURED AND LEAKING.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL				 
2002010800015	20020108	00015	NE  	2002	1	8	AUS20010970      	2	20010905	G	7230	MS9390290	PIN             								LYC   	ALF502	ALF502R3A   	41580	NE  					ENGINE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FAN DISC RETAINING NUT LOCK CUP WASHER LOCKING PINS FLUSHWITH SHAFT MAKING LOCKING MECHANISM NON FUNCTIONAL	. THE FAN HAD BEEN REMOVED TO SERVICE ANOTHER ENGINE.										4	F			E6NE				 
2001101500036	20011015	00036	CE  	2001	10	15	AUS20010971      	1	20010822	G	5610	10138402521	WINDSHIELD      	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FLIGHT COMPARTME	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) LH WINDSHIELD SHATTERED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002010800016	20020108	00016	NE  	2002	1	8	AUS20010972      	2	20010829	G	7260	PLE94397	GEARBOX         			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE ACCESSORY	DISCONNECTED    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) ENGINE ACCESSORY GEARBOX DECOUPLED PREVENTING ACCESSORIES FROM OPERATING.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2001101500037	20011015	00037	SO  	2001	10	15	AUS20010973      	2	20010820	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 	 									(AUS) ENGINE MAIN BEARING BROKEN INTO SEVERAL PIECES. METAL CONTAMINATION OF OIL SYSTEM. BEARING WAS A GENUINE CONTINENT	ALITEM.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001101500038	20011015	00038	SO  	2001	10	15	AUS20010974      	2	20010820	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 	 									(AUS) ENGINE MAIN BEARING BROKEN INTO THREE PIECES. METAL CONTAMINATION OF ENGINE.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002010800018	20020108	00018	EU  	2002	1	8	AUS20010977      	1	20010807	G	2913	2912	MOTOR           			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYDRAULIC PUMP	DIRTY           	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR HYDRAULIC POWER PACK ELECTRIC MOTOR FAULTY.INVESTIGATION FOUND LIGHT CORROSION IN COMMUTATOR END OF M	OTOR. THE MOTOR WAS ALSO DIRTY WITH THE BRUSHES STICKING IN THE BRUSH HOLDERS. HYDRAULIC RETURN FILTER DIRTY.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001101500040	20011015	00040	CE  	2001	10	15	AUS20010979      	1	20010901	G	7602	MC98620661	SHAFT           	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MIXTURE CONTROL	SEPARATED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) MIXTURE CONTROL VERNIER FAILED CAUSING CENTRE KNOB AND 177.8MM(7IN) OF SHAFT TO SEPARATE FROM MIXTURE CONTROL.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002010800021	20020108	00021	NE  	2002	1	8	AUS20010981      	2	20010903	G	7240	9560151480	SWIVEL          			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					COMBUST CHAMBER	LOOSE           	W				O				OTHER                   				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 ENGINE COMBUSTION CHAMBER P2 AIR TAP SWIVEL UNION ASSEMBLY CONE LOOSE.						1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001101500042	20011015	00042	EA  	2001	10	15	AUS20010986      	2	20010829	G	7414	10349234	GEAR            	CONT        	BL3493704   	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAGNETO/DISTRIBU	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		727  		A250007FR					(AUS) LH MAGNETO FAULTY. INSPECTION FOUND THAT ONE OF THE COILRETAINING WEDGES PNO 10-349219 WAS ADRIFT INSIDE THE CASE.	 THEDISTRIBUTOR GEAR PNO 10-349234 WAS FOUND TO HAVE THREE TEETHMISSING. SUSPECT WEDGE JAMMED GEAR CAUSING TEETH TO STRI	P AND ALLOW THE INTERNAL TIMING TO CHANGE.				1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2001101500044	20011015	00044	CE  	2001	10	15	AUS20010990      	1	20010904	G	7810	K9695000277	EXHAUST PIPE    	CONT        	IO520C      	BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	ENGINE COLLECTOR	FAULTY          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			NR	NOT REPORTED   	1			AU	S 	 									(AUS) LH ENGINE EXHAUST PIPE HELD ON BY REAR CLAMP ONLY AND TOUCHINGFIREWALL. HEAT AFFECTED PLASTIC JOINER TUBE FOR PITO	T SYSTEMLOCATED BEHIND FIREWALL.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002010800025	20020108	00025	CE  	2002	1	8	AUS20010991      	1	20010829	G	5220		DOOR            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	EMERGENCY EXIT	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 										(AUS) EMERGENCY EXIT SEPARATED DURING FLIGHT. NO DAMAGE TO AIRCRAFT.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001101500045	20011015	00045	GL  	2001	10	15	AUS20010992      	1	20010803	G	7820		MUFFLER         	CONT        	IO360HB     	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE NOISE SUP	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) RH MUFFLER CRACKED. CARBON MONOXIDE FUMES IN COCKPIT.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001101500046	20011015	00046	GL  	2001	10	15	AUS20010993      	1	20010908	G	5720		TAPE            	            	            	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	WING, MISCELLANE	SEPARATED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 									(AUS) LH WING ROOT SEALING TAPE SEPARATED. CARBON MONOXIDE FUMESENTERED COCKPIT.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001101500047	20011015	00047	CE  	2001	10	15	AUS20010994      	1	20010831	G	3213	50450182	WASHER          	            	            	CESSNA	402   	402CESSNA   	207590K	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MAIN LANDING GEA	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR TORQUE LINK CENTRE PIVOT WASHER NOT FITTED.TORQUE LINKS SEPARATED ALLOWING AIRCRAFT TO GROUND	 LOOP.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001101500048	20011015	00048	CE  	2001	10	15	AUS20010997      	1	20010915	G	7120	5854002	MOUNT           	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE MOUNT SEC	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE MOUNT CROSS MEMBER CRACKED.						1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2001101500049	20011015	00049		2001	10	15	AUS20010998      	4	20010906	G	2565	D31591478	SLIDE           	            	            	      		            			      		            			 		            		ESCAPE SLIDE	FAULTY          	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 	 		225  		2321					(AUS) ESCAPE SLIDE TEST LIGHTS FAILED TO ILLUMINATE DURING TEST.INSPECTION FOUND SWITCH PIN LANYARD TOO LONG.																			 
2002010800028	20020108	00028	CE  	2002	1	8	AUS20010999      	1	20010605	G	2810	33400512	FUEL TANK       			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					FUSELAGE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANKS DETERIORATED. FUEL SYSTEM AND FUEL FILTERS CONTAMINATED WITH FOAM MATERIAL.						1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2001101500050	20011015	00050	EU  	2001	10	15	AUS20011004      	1	20010918	G	2913	99101371	PUMP            	            	            	REIMS 	406   	F406        	       	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	HYDRAULIC PUMP,	FAILED          	W			    	K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			CL	CLIMB          	1			AU	S 	 				1107					(AUS) HYDRAULIC PUMP FAULTY. INVESTIGATION FOUND THE PUMP CIRCLIP GROOVE WORN ALLOWING THE CIRCLIP TO SEPARATE AND THE S	PLINE ADAPTER PNO 24100-646 TO DISENGAGE FROM THE ENGINE DRIVE.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002010800033	20020108	00033	CE  	2002	1	8	AUS20011006      	1	20010912	G	3260	S13771	SWITCH          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MLG DOWNLOCK	FAULTY          	W				O				OTHER                   				P			NO WARNING INDICATION     			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN FROM SWITCH BODY.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P47GL	 
2001101500051	20011015	00051	CE  	2001	10	15	AUS20011007      	1	20010830	G	3230	MS16562130	PIN             	            	            	CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	SHEARED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LANDING GEAR UPPER MANUAL EMERGENCY EXTENSION SYSTEM INTERCONNECT SHAFT SPROCKET ROLL PIN SHEARED.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2001101500052	20011015	00052	SO  	2001	10	15	AUS20011008      	2	20010916	G	8597		WIRE            	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				E	A	 	VIBRATION/BUFFET          	FLAME/FIRE                		CR	CRUISE         	1			AU	S 	 									(AUS) ELECTRICAL WIRES (2OFF) LOCATED IN ENGINE COMPARTMENT CHAFING ONSOLID FUEL LINE. WIRES ARCED AND BLEW A SMALL HOLE	 IN THE FUELLINE RESULTING IN A FIRE IN THE ENGINE COMPARTMENT. INADEQUATEMAINTENANCE. PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001101500053	20011015	00053	EA  	2001	10	15	AUS20011009      	2	20010915	G	8520		CRANKCASE       	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	E	B	OTHER                     	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE NO4 CYLINDER HOLDDOWN STUDS (2OFF) BROKEN. CRANKCASECRACKED VERTICALLY UP FROM TOP STUD. CRACK LENGTH 76	.2MM (3IN).					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002010800034	20020108	00034	SO  	2002	1	8	AUS20011010      	2	20010910	G	7414	K3823	DISTRIBUTOR     			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MAGNETO	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO DISTRIBUTOR BLOCK BADLY BURNT DUE TO TRACKING FROM DISTRIBUTOR WHEEL SPRING TO MAGNETO HOUSING.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002010800035	20020108	00035	EA  	2002	1	8	AUS20011011      	2	20010819	G	7414	K3823	DISTRIBUTOR     								LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	MAGNETO	BURNED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 										(AUS) MAGNETO DISTRIBUTOR BLOCK BADLY BURNT BY TRACKING FROM SPRING INDISTRIBUTOR WHEEL TO MAGNETO HOUSING.											3	O			1E4	5	C	P920	 
2001101500056	20011015	00056	SW  	2001	10	15	AUS20011017      	1	20010921	G	5730		PLATE           	            	            	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1A5   	41532	EA  	HARTZL	HCA3X	HCA3XK2     	GL  	WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) EXTERNAL SPAR CAP SUPPORT PLATE RH SIDE CORRODED IN AREA OF JOINT BETWEEN TWO PLATES. EVIDENCE OF CORROSION IN SIM	ILAR AREA ON LH SIDE.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2001101500057	20011015	00057	SO  	2001	10	15	AUS20011018      	1	20010922	G	2140	461731	REGULATOR       	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	LEAKING         	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 	 									(AUS) FUEL PRESSURE REGULATOR DIAPHRAGM LEAKING WHEN CABIN HEATER TURNS OFF.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002010800040	20020108	00040	GL  	2002	1	8	AUS20011019      	1	20010918	G	2821		FILTER          			NAMER 	NA260 	T28*        	       	GL  	WRIGHT	R1820 	R1820*      	67020	EA  	HAMSTD	43D	43D50       	NE  	FUEL SYSTEM	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT FUEL FILTER CONTAMINATED. CONTAMINATION ALSO FOUND IN CARBURETTOR FUEL FILTER.						1	L	7	1 	4R	4	R	 	1A18    	5E10	6	C	P8879	 
2002010800044	20020108	00044	CE  	2002	1	8	AUS20011022      	1	20010914	G	5751	NAS2219	SCREW           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	LT AILERON	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 										(AUS) LT AILERON ATTACHMENT SCREWS INCORRECTLY LOCATED. AILERON HAD PREVIOUSLY BEEN REMOVED FOR ACCESS AND SCREWS HAD MI	SSED THE ANCHOR NUTS DURING REPLACEMENT. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002010800045	20020108	00045	SO  	2002	1	8	AUS20011023      	1	20010921	G	3260	487862ALT1CH214	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	MLG DOWLOCK	OUT OF ADJ      	W				O				OTHER                   				P	O		NO WARNING INDICATION     	OTHER                     		LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK MICROSWITCH OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001101500058	20011015	00058	EA  	2001	10	15	AUS20011024      	2	20010925	G	7250	310103702	DUCT            	PWA         	PT6A27      	AMTR  	MK1   	MK1         	05620JY	GL  	PWA   	PT6   	PT6A27      	52043	EA  	 		            		TURBINE SECTION	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1448 		PS41991100					(AUS) ENGINE POWER SECTION EXHAUST DUCT EXTENSIVELY CRACKED. AIRCRAFT IS FOREIGN REGISTRATION 5W-FAY.						1	H	7	1 	3O	4	T	NC	EXPA1H71	E4EA				 
2001101500059	20011015	00059	CE  	2001	10	15	AUS20011026      	1	20010917	G	2434	DOFF10300R	ALTERNATOR      	            	            	CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	DC GENERATOR-ALT	FAILED          	W			    	K	 	 	 	NONE                    				H	 	 	ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 	 				5110753					(AUS) ALTERNATOR OUTPUT TERMINAL FRACTURED AND ADJACENT WIRING MELTED.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA	 
2001120400069	20011204	00069	SO  	2001	12	4	AUS20011032      	1	20010924	G	5711	3516808	SPAR            	PIPER       	PA28161     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				288216109					(AUS) LH AND RH WING SPARS PNO 35168-08 (LH) AND PNO 35168-09 (RH)CONTAINED SEVERE EXFOLIATION CORROSION.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002011400003	20020114	00003	EA  	2002	1	14	AUS20011033      	2	20010914	G	8520	SL743001	BEARING         			GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD BIG END BEARING MATERIAL FLAKING OFF FROM BEARING BASE.						1	L	7	1 	3O	3	O	NC	A00001LA	1E4	5	C	P920	 
2001120400070	20011204	00070	EA  	2001	12	4	AUS20011034      	2	20010927	G	8520		STUD            	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		218  							(AUS) LH ENGINE NO1 CYLINDER HOLDDOWN STUDS FAILED. CRANKCASE CRACKED IN TOP RIGHT STUD HOLE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002010800061	20020108	00061	SO  	2002	1	8	AUS20011035      	2	20010912	G	8530		PISTON          								CONT  	O520  	IO520M      	17032	SO  					ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NEW CYLINDER KIT FAULTY. OIL HOLES NOT DRILLED IN PISTON DURING MANUFACTURE.											3	O			E5CE				 
2001120400071	20011204	00071	CE  	2001	12	4	AUS20011036      	1	20010928	G	2710	S1997610	BEARING         	            	            	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	AILERON CONTROL	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 	 									(AUS) LH AILERON OUTBOARD BELLCRANK UPPER AND LOWER BEARINGS STIFF DUETO LACK OF LUBRICATION AND CORROSION. SUSPECT INAD	EQUATE SEALINGOF RUBBER BUNG ON TOP OF WING ALLOWED WATER TO WASH OUT THE LUBRICATION FROM THE BEARINGS.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2001120400072	20011204	00072	CE  	2001	12	4	AUS20011037      	1	20010929	G	5312	07126161	BULKHEAD        	            	            	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE MAIN, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) AFT TAILCONE BULKHEAD CRACKED IN AREA AT TOP OF RUDDER CABLECUTOUT.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001120400073	20011204	00073	CE  	2001	12	4	AUS20011038      	1	20010929	G	5511		SPAR            	            	            	CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	HORIZONTAL STABI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) TAILPLANE REAR SPAR CONTAINED SEVERE EXFOLIATION CORROSION IN THREE SEPARATE AREAS. SUSPECT CORROSION CAUSED BY WA	TER INGRESS.PNO 1232610-3 (X2), PNO 0732603-2 AND PNO 1232114-1 AFFECTED. OTHER PARTS ALSO FOUND CORRODED WAS RIB PNO 12	31006-1 INTHE FIN  AND THE LEFT HAND ELEVATOR TORQUE TUBE AND INBOARD ADAPTOR PNO  0734110-3 AND PNO 0734110-7. THE AFFE	CTED AREAS WERE NOT PRIMED DURING MANUFACTURE AND THE AIRCRAFT SPENT A CONSIDERABLE AMOUNT OF ITS LIFE IN THE OPEN IN CO	ASTAL AREAS.		1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001120400074	20011204	00074	EA  	2001	12	4	AUS20011039      	2	20010924	G	8530	73111	EXHAUST VALVE   	LYC         	IO360A1B6D  	MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		1462 		L1721451A					(AUS) ENGINE NO3 CYLINDER EXHAUST VALVE FAILED.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P920	 
2002010800076	20020108	00076	CE  	2002	1	8	AUS20011042      	1	20010907	G	3233	358251722	ARM             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR RETRACTION MOTOR ARM CRACKED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001120400076	20011204	00076	NM  	2001	12	4	AUS20011043      	1	20010705	G	7810	320006519	TAILPIPE        	LYC         	IO540S1A5   	PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540S1A5   	41532	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	ENGINE COLLECTOR	CRACKED         	W			    	K	 	 	 	NONE                    				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 	 									(AUS) RH ENGINE TAILPIPE CRACKED ALLOWING HOT EXHAUST GAS TO ACTIVATE FIRE WARNING SYSTEM.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4	5	C	P25EA	 
2001120400078	20011204	00078	CE  	2001	12	4	AUS20011045      	1	20010918	G	5730	552212126	SKIN            	CESSNA      	C550        	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  	 		            		WING, PLATES/SKI	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				5500054					(AUS) RH WING SKIN SPLICE CORRODED. SUBSEQUENT INVESTIGATION REVEALED EXTENSIVE DEBONDING. ULTRASONIC INSPECTION OF LH W	ING FOUND SIMILAR RESULTS.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002010800078	20020108	00078	CE  	2002	1	8	AUS20011047      	1	20011001	G	2810		FUEL CELL       			CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LEFT	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			54   							(AUS) LH FUEL SYSTEM CONTAINED SIGNIFICANT AMOUNTS OF SOLID CONTAMINATION. SUSPECT CONTAMINATION IS FROM FUEL STORAGE SY	STEM.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002010800079	20020108	00079	WP  	2002	1	8	AUS20011048      	1	20010918	G	5711	U2727MK2	SPAR            			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  	AMTR	C8289	C8289       	GL  	WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BATCHNO48601					(AUS) ALL FOUR WINGS PNO U2727 MK2 (LT LOWER), PNO U2728 MK2 (RT LOWER), PNO U2729 MK2 (LT UPPER) AND PNO U2730 MK2 (RT 	UPPER) WERE REJECTED FOLLOWING REBUILD. NUMEROUS HOLES DRILLED IN ALL FOUR WING SPARS WERE OVERSIZE OR DRILLED IN A FIGU	RE 8. AILERON BELLCRANK CONTROL BOX ALSO CRACKED. PERSONNEL/MAINTENANCE ERROR.				1	Q	7	1 	3I	3	I	 	A8EU    	A8EU	5	N	EXPP5N	 
2002010800080	20020108	00080	CE  	2002	1	8	AUS20011049      	1	20010926	G	2460	W31X100050	CIRCUIT BREAKER 			CESSNA	441   	441         	2076020	CE  										DC POWER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 AVIONICS SWITCH / CIRCUIT BREAKER FAILED INTERNALLY. SUSPECT CAUSED BY RAIN WATER CORROSION DUE TO LOCATION O	F CIRCUIT BREAKER BELOW THE LT OPENING WINDOW.					1	L	7	2 	3T			RT	A28CE   					 
2001120400080	20011204	00080	EA  	2001	12	4	AUS20011053      	2	20010715	G	8530		EXHAUST VALVE   	LYC         	O235L2C     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) NO3 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM CAUSING MAJOR DAMAGE TO CYLINDER AND PISTON. SUSPECT CAU	SED BY CORROSIONAND EROSION DAMAGE. INVESTIGATION FOUND TWO OF THE OTHER THREEEXHAUST VALVES IN SIMILAR CONDITION WITH T	HE LAST EXHAUST VALVE NOT AS BADLY ERODED BUT STILL CONSIDERED UNSERVICEABLE. FURTHER INVESTIGATION FOUND THE CAMSHAFT A	ND CAM FOLLOWERS PITTED AND WORN DUE TO CORROSION.AIRCRAFT IS ONLY OPERATED FOR APPROXIMATELY 20 TO 50 HOURS PER YEAR.			1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002010800085	20020108	00085	WP  	2002	1	8	AUS20011055      	1	20010930	G	5311	269A2234	FRAME           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CRACKED AT LT CLUSTER. FOUND VISUALLY AND CONFIRMED USING DYE PENETRANT INSPECTION. AIRCRAFT HAD OP	ERATED FOR 192.2 HOURS SINCE AD/HU269/57 AMDT2 WAS CARRIED OUT.AD/HU269/57 AMDT2 IS CARRIED OUT EVERY 200 HOURS.					1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001120400082	20011204	00082	CE  	2001	12	4	AUS20011057      	1	20010715	G	2700		CABLE           	            	            	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	FLIGHT CONTROL S	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) SEVERAL FLIGHT CONTROL CABLES RUSTY. THE FOLLOWING CABLES WEREFOUND TO BE UNSERVICEABLE:- 1. PNO 0400107-41 AILERO	N CABLE (2OFF)2. PNO 0400107-21 BALANCE CABLE 3. PNO 0400107-45 FLAP CABLE4. PNO 0400107-46 FLAP CABLES 5. PNO 0400107-3	0 TRIM CABLE6. PNO 0400107-57 TRIM CABLE7. PNO 0400107-49 RUDDER CABLE				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001120400083	20011204	00083	EA  	2001	12	4	AUS20011059      	2	20011003	G	8520	LW13827	CRANKCASE       	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH ENGINE CRANKCASE CRACKED ON NO5 CYLINDER BASE PAD IN THE 8 O'CLOCK POSITION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002010800095	20020108	00095	GL  	2002	1	8	AUS20011060      	2	20011004	G	7230	23064577A	VANE            			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COMPRESSOR SCROLL ASSEMBLY RT TURNING VANE CRACKED. A PIECE OF THE VANE APPROXIMATELY 38.1MM BY 17.78MM (1.5IN BY 	0.7IN) WAS MISSING. A SMALL PIECE OF THE LT VANE ALSO APPEARS TO BE MISSING.					1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2001120400089	20011204	00089	CE  	2001	12	4	AUS20011076      	1	20011012	G	5751	122005312	BRACKET         	            	            	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	AILERONS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH AILERON INBOARD AND OUTBOARD HINGE BRACKETS CRACKED ANDDISTORTED.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2002011400004	20020114	00004	EU  	2002	1	14	AUS20011077      	1	20010928	G	5551	GA538021233	BRACKET         			GIPPLD	GA8   	GA8         	       	EU  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	HORIZONTAL STAB	SHEARED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			745  							(AUS) RT HORIZONTAL STABILISER ATTACHMENT BRACKET RIVETS SHEARED.						1	H	7	1 	3O	3	O	NT	        	1E4	5	C	P920	 
2002010800114	20020108	00114	SO  	2002	1	8	AUS20011078      	2	20011010	G	8530	SA10200A20P	CYLINDER        			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  	AMTR	C8289	C8289       	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 CYLINDER CRACKED FOR APPROXIMATELY 80 PERCENT OF CIRCUMFERENCE ATTHE BASE OF THE THREAD ON THE CYLINDER BARRE	L BETWEEN THE TOP BARREL FIN AND THE BOTTOM FIN ON THE CYLINDER HEAD.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	EXPP5N	 
2001120400090	20011204	00090	CE  	2001	12	4	AUS20011079      	1	20011011	G	2612	303267	AMPLIFIER       	            	            	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	FIRE DETECTION	FAULTY          	W			    	K	 	 	 	NONE                    				E	B	J	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	CR	CRUISE         	1			AU	S 	 				0079					(AUS) LH ENGINE FIRE WARNING SYSTEM CONTROL AMPLIFIER SUSPECT FAULTY.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	3PNE	 
2002010800122	20020108	00122	EA  	2002	1	8	AUS20011082      	2	20011010	G	8520	LW17828	CRANKSHAFT      			PIPER 	PA36  	PA36375     	7103620	SO  	LYC   	O720  	IO720D1C    	41546	EA  					ENGINE	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CRANKSHAFT BROKEN IN WEB LOCATED FORWARD OF MAIN BEARING JOURNAL BETWEEN NO5/NO6 AND NO7/NO8 CYLINDER BANKS	. ONE CONNECTING ROD CRACKED.					1	L	7	1 	3O	3	O	 	A10SO   	1E15				 
2001120400091	20011204	00091	SO  	2001	12	4	AUS20011083      	2	20010906	G	7322	626813	PIN             	CONT        	6297032     	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	FUEL CONTROL/REC	MISSING         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 				G148205RA					(AUS) FUEL CONTROL UNIT FUEL METERING LEVER TO SHAFT ATTACHMENT PIN MISSING.						1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA	 
2001120400092	20011204	00092	GL  	2001	12	4	AUS20011085      	1	20011009	G	7603	07431031	SHAFT           	CONT        	IO360HB     	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	POWER LEVER	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) THROTTLE LAYSHAFT CABLE CONNECTION FITTING BROKEN.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001120400093	20011204	00093	CE  	2001	12	4	AUS20011086      	1	20010214	G	5511	04320016	RIB             	CESSNA      	150M        	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	AMTR	C8289	C8289       	GL  	HORIZONTAL STABI	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HORIZONTAL STABILISER RIBS PNO 0432001-6 AND PNO 0432001-36 CRACKED FROM FORWARD ATTACHMENT POINT NUTPLATE RIVETS.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	EXPP5N	 
2001120400094	20011204	00094	EA  	2001	12	4	AUS20011087      	2	20011015	G	8520	640761A	BEARING         	LYC         	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				640761A					(AUS) DURING LH ENGINE STRIP FOR REPAIR TO A CRACKED CRANKCASE, THE CENTRE MAIN BEARING WAS FOUND TO BE BADLY WORN AND T	HE LOCATING LUGS WERE BADLY DAMAGED. THE CRANKSHAFT WAS ALSO FOUND TO BEDAMAGED ON THE FORWARD AND REAR SURFACES CONTACT	ED BY THE BEARING DUE TO EXTREME LONGITUDINAL MOVEMENT OF THE BEARING. SEALANT WASFOUND ON THE BEARING WEBS. THE THROUGH	 STUD SEALING O'RINGS  BETWEEN THE CRANKCASE HALVES WERE MISSING. TO STOP THE OIL LEAK SILK THREAD AND LOCTITE 515 WAS A	ROUND THE THROUGH BOLT HOLES.  NON-APPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000002	20020110	00002	CE  	2002	1	10	AUS20011088      	1	20010822	G	2434	ES4118	BRUSHES         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	DC GENERATOR-ALT	WORN            	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR BRUSHES WORN PREMATURELY.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001120400095	20011204	00095	SO  	2001	12	4	AUS20011091      	2	20010911	G	8520	654811	BOLT            	CONT        	IO470L      	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 	 				27214R					(AUS) LH ENGINE NO4 CYLINDER CONNECTING ROD BOLT BROKEN. COWLING HOLED.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P25EA	 
2002011000005	20020110	00005	SO  	2002	1	10	AUS20011092      	1	20010925	G	2720	0106Y10	SERVO           			PIPER 	PA46  	PA46500TP   	7104622	SO  										RUDDER CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) YAW DAMPER SERVO FAULTY. DUST COVER OVER THE MOTOR COLLECTING WATER (CONDENSATION). THE MOISTURE DRAIN HOLE IS LOC	ATED AT THE 12 O'CLOCK POSITION INSTEAD OF THE 6 O'CLOCK POSITION. AS A RESULT THE SERVO MOTOR IS BADLY CORRODED AND BUR	NT.				1	L	7	1 	3O			RT	A25SO   					 
2002011000006	20020110	00006	SO  	2002	1	10	AUS20011093      	1	20010925	G	5712	102718005	RIB             			PIPER 	PA46  	PA46500TP   	7104622	SO  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING LEADING EDGE RIB CRACKED IN STIFFENER.						1	L	7	1 	3O			RT	A25SO   					 
2001120400096	20011204	00096	EU  	2001	12	4	AUS20011094      	1	20011019	G	2612	173462410	FIRE DETECTOR   	            	            	BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  	 		            		FIRE DETECTION	FAULTY          	W			    	K	 	 	 	NONE                    				E	J	B	VIBRATION/BUFFET          	WARNING INDICATION        	SMOKE/FUMES/ODORS/SPARKS  	NR	NOT REPORTED   	1			AU	S 	 				173462600					(AUS) NO2 ENGINE FIRE DETECTOR ACTIVATION. FIRE BOTTLE OPERATED.INVESTIGATION FOUND THAT THE AIRCRAFT WAS IN AN UNUSUAL 	NOSE HIGH TURN AT THE TIME WHICH HAS IN THE PAST CAUSED THE FIRE DETECTOR TO ACTIVATE FOR SHORT PERIODS.					1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10				 
2002011000007	20020110	00007	GL  	2002	1	10	AUS20011095      	3	20011020	G	6114		HUB             			AMTR  	VANS  	RV8         	       	GL  	AMTR  	CHEVY8	CHEVYV8     	 	GL  	AMTR	C8289	C8289       	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			317  							(AUS) PROPELLER HUB CRACKED. FOUND DURING INSPECTION IAW AIRCRAFT MANUFACTURERS ALERT.						1	L	7	1 	3O	3	V	NT	EXPA1L71	EXPE3V	5	N	EXPP5N	 
2002011000010	20020110	00010	SO  	2002	1	10	AUS20011098      	2	20011012	G	8520	571043	CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	ENGINE	DAMAGED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			11   							(AUS) ENGINE CRANKCASE HOLED IN AREA OF NR 5 AND NR 6 CYLINDERS.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P36EA	 
2001120400097	20011204	00097	SO  	2001	12	4	AUS20011099      	1	20011019	G	5610	7929616	WINDSHIELD      	            	            	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	FLIGHT COMPARTME	UNAPPROVED PART 	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WINDSHIELD INCORRECT PART. WINDSHIELD THICKNESS OF 2.5146MM(0.100IN) INSTEAD OF 6.858MM (0.270IN). EXCESSIVE SI	LASTIC SEALER USED TO FILL GAPS CAUSED BY POOR FIT. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002011000013	20020110	00013	EU  	2002	1	10	AUS20011102      	1	20010621	G	3246	C201801202A	WHEEL           			AMD   	FALC50	FALCON900   	2700160	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION.						2	L	7	3 	4F			RT	A46EU   					 
2002011000014	20020110	00014	EU  	2002	1	10	AUS20011103      	1	20010626	G	3246	C201801202A	WHEEL           			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U285					(AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION.						2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2002011000015	20020110	00015	EU  	2002	1	10	AUS20011104      	1	20010714	G	3246	C201801202A	WHEEL           			AMD   	FALC50	FALCON900   	2700160	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U1010					(AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION.						2	L	7	3 	4F			RT	A46EU   					 
2001120400098	20011204	00098	GL  	2001	12	4	AUS20011106      	1	20011019	G	3710		PUMP            	            	            	PAC   	CT4   	CT4B        	       	GL  	CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	VACUUM DISTRIBUT	FAILED          	W			    	K	 	 	 	NONE                    				I	 	 	FLT. ATTITUDE INST.       			AP	APPROACH       	1			AU	S 	 									(AUS) VACUUM PUMP FAILED AND DRIVE SHAFT SHEARED.						1	L	7	1 	3O	3	O	RT	A9PC    	E1CE	5	C	P920	 
2001120400099	20011204	00099	CE  	2001	12	4	AUS20011107      	1	20011012	G	5744	122005317	BRACKET         	            	            	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	WING, CONTROL SU	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) INBOARD AILERON BRACKET BROKEN INTO TWO PIECES.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002011000018	20020110	00018	CE  	2002	1	10	AUS20011108      	1	20011012	G	5711	65110387	SPAR CAP        			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT & RT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING SPAR CAPS DEBONDED AND CORRODED. FOUND DURING ULTRASONIC INSPECTION IAW JWP/2531/01 AND JWP/2503/01	.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002011000019	20020110	00019	EU  	2002	1	10	AUS20011109      	1	20011024	G	6410	109813201111	BLADE           			AGUSTA	A109  	A119        	0261102	EU  										TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR BLADE CRACKED IN AREA OF DOUBLER WHERE THE FINGERS ARE BLENDED INTO THE BLADE SKIN. CRACKS FOUND USING 	THE NAKED EYE AND CONFIRMED USING DYE PENETRANT INSPECTION.					1	G	7	2 	3U			 	H7EU    					 
2002011000021	20020110	00021	SO  	2002	1	10	AUS20011110      	1	20011008	G	5540	4004626	STRUCTURE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CORRODED IN AREA BETWEEN TORQUE TUBE AND LOWER END CAP.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000023	20020110	00023	NE  	2002	1	10	AUS20011112      	2	20011019	G	7230		COMPRESSOR      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	FOD             	W				O				OTHER                   				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			AU	S 										(AUS) ENGINE FIRST STAGE COMPRESSOR DAMAGE. FOD.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002011000024	20020110	00024	CE  	2002	1	10	AUS20011113      	1	20011008	G	5310	57111455	DOOR FRAME      			CESSNA	441   	441         	2076020	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER CABIN DOOR FRAME CRACKED IN AREA ADJACENT TO AFT HINGEPOINT.						1	L	7	2 	3T			RT	A28CE   					 
2001120400100	20011204	00100	CE  	2001	12	4	AUS20011114      	1	20011022	G	2741	03101243	PIN             	CESSNA      	55657544    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  	 		            		STABILIZER POSIT	WORN            	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 	 									(AUS) ELEVATOR TRIM INDICATOR SKIPPED GROOVES ON TRIM WHEEL GIVINGINCORRECT TRIM POSITION INDICATION. BOTH WHEEL FUSE PL	UGS BLEWDUE TO EXCESSIVE BRAKING.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002011000025	20020110	00025	CE  	2002	1	10	AUS20011116      	1	20011001	G	5751	122005217	BRACKET         			CESSNA	206   	U206E       	2073350	CE  	CONT  	O520  	IO520F      	17032	SO  	HARTZL	HCC3Y	HCC3YF1     	GL  	LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON HINGE BRACKET CRACKED AND BROKEN AT LOWER ATTACHMENT POINTS. LT INBOARD AND RT OUTBOARD BRACKETS ALSO C	RACKED. SPAR AND RIB ALSO CRACKED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P25EA	 
2002011400005	20020114	00005	EA  	2002	1	14	AUS20011117      	2	20010925	G	7414		GEAR            			GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAGNETO TIMING GEAR DRIVESHAFT FAILED.						1	L	7	1 	3O	3	O	NC	A00001LA	E295	5	N	P874	 
2002011000026	20020110	00026	SO  	2002	1	10	AUS20011120      	2	20010821	G	7414		IMPULSE COUPLING			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MAGNETO	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ENGINE RT MAGNETO IMPULSE COUPLING NOT INSTALLED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000028	20020110	00028	CE  	2002	1	10	AUS20011121      	1	20010821	G	5610	964200291	WINDSHIELD      			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WINDSHIELD CRACKED AND INCORRECTLY INSTALLED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000029	20020110	00029	CE  	2002	1	10	AUS20011122      	1	20010821	G	2720	9652400029P	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					RUDDER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) RT REAR RUDDER CABLE INCORRECTLY ROUTED. CABLE EXCESSIVELY WORN.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000030	20020110	00030	CE  	2002	1	10	AUS20011123      	1	20010821	G	5340	951100172	FITTING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT REAR LOWER BATHTUB FITTING DAMAGED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000031	20020110	00031	CE  	2002	1	10	AUS20011124      	1	20010215	G	7921	8526250	OIL COOLER      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	ENGINE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL COOLER CONTAINED UNAUTHORISED REPAIRS AND WELDING.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002011000036	20020110	00036	EA  	2002	1	10	AUS20011125      	2	20010215	G	7310	240001046	LINE            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUEL DIST	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FUEL PRIMER LINE CHAFED THROUGH AND THEN INCORRECTLY REPAIRED. ELECTRICAL TAPE HAD BEEN WRAPPED AROUND THE 	LINE TO STOP FUEL LEAKS.					1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002011000037	20020110	00037	CE  	2002	1	10	AUS20011126      	1	20010215	G	2820	240001058	LINE            			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUEL DIST	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN FUEL SUPPLY LINE CHAFED THROUGH BY COWL FLAP CABLE. NYLONWRAP USED TO PROTECT WORN AREA.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001120400103	20011204	00103	CE  	2001	12	4	AUS20011127      	1	20010215	G	2910	248000119	PIPE            	            	            	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	HYDRAULIC SYSTEM	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) HYDRAULIC PRESSURE LINE WORN. LINE WAS INADEQUATELY SECURED.PERSONNEL/MAINTENANCE ERROR.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002011000038	20020110	00038	CE  	2002	1	10	AUS20011128      	1	20010124	G	5321	04102361	FLOOR PANEL     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOOR CRACKED EXCESSIVELY.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002011000039	20020110	00039	CE  	2002	1	10	AUS20011129      	1	20010319	G	5321	04102361	FLOOR PANEL     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FLOOR CRACKED EXCESSIVELY.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2002011000043	20020110	00043	SO  	2002	1	10	AUS20011134      	2	20010719	G	8520	630066A	CRANKSHAFT      			AMTR  	VANS  	RV8         	       	GL  	CONT  	O200  	O200*       	17020	SO  	AMTR	C8289	C8289       	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			38   							(AUS) CRANKSHAFT CRACKED. SUSPECT CAUSED BY UNREPORTED PROPELLER STRIKE. CAM DRIVE BOLTS SHEARED. NO EVIDENCE OF LOCKWIR	ING ON BOLTS.					1	L	7	1 	3O	3	O	NT	EXPA1L71	E252	5	N	EXPP5N	 
2002011000044	20020110	00044	CE  	2002	1	10	AUS20011135      	1	20011023	G	2435	03601018	BEARING         	LEARSIEGLER 		CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	STARTER GEN	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					5135					(AUS) STARTER-GENERATOR BEARINGS FAILED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001120400104	20011204	00104	EU  	2001	12	4	AUS20011136      	1	20011025	G	5730		SKIN            	            	            	MUDRY 	10    	CAP10B      	0950102	EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	WING, PLATES/SKI	FRACTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH WING LOWER SKINFRACTURED BETWEEN SPARS ADJACENT TO NO3 RIB.CRACK LENGTH 600MM (23.6IN).						1	L	7	1 	3O	3	O	 	A36EU   	1E10	5	N	P3EU	 
2002011000045	20020110	00045	SO  	2002	1	10	AUS20011137      	1	20011025	G	3231		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT MLG DOOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR TO LANDING GEAR DOOR FORWARD ROD BOLT FAILED. INSPECTION OF REMAINING THREE ATTACHMENT BOLTS 	FOUND THEM TO BE THE INCORRECT PART.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001120400105	20011204	00105	SO  	2001	12	4	AUS20011138      	1	20011025	G	3260		SWITCH          	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR POS	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CL	CLIMB          	1			AU	S 	 									(AUS) MAIN LANDING GEAR SQUAT SWITCH WIRE BROKEN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001120400106	20011204	00106	CE  	2001	12	4	AUS20011139      	1	20011024	G	5230		HINGE           	            	            	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	CARGO/BAGGAGE DO	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH REAR NOSE BAGGAGE DOOR AFT HINGE FAILED DURING DOOR CLOSURE. DOOR STAY WAS BENT SLIGHTLY.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001120400107	20011204	00107	CE  	2001	12	4	AUS20011140      	1	20011012	G	2823	SL60043	LEVER           	            	            	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUEL SELECTOR/SH	BROKEN          	W			    	K	E	 	 	NONE                    	ENGINE SHUTDOWN         			O	 	 	OTHER                     			NR	NOT REPORTED   	1			AU	S 	 									(AUS) FUEL CONDITION LEVER BROKE AT THE LOWER BEND IN THE CONTROL KNOBARM.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011000046	20020110	00046	SO  	2002	1	10	AUS20011142      	1	20011022	G	3250		BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG STEERING	SHEARED         	W				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 										(AUS) NOSE WHEEL STEERING BRACKET TO NOSE LEG ATTACHMENT BOLTS (2OFF3) SHEARED. INVESTIGATION OF NLG LEG FOUND ONE OF TH	E BOLTS HOLES WAS FITTED WITH A HELICOIL INSERT. SUSPECT UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001120400109	20011204	00109	SO  	2001	12	4	AUS20011144      	1	20011026	G	2820	5052012035	TUBE            	PIPER       	PA31350     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AIRCRAFT FUEL DI	CORRODED        	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 				317652119					(AUS) FUEL CROSSFEED PIPE LOCATED BELOW CABIN FLOOR CORRODED INTERNALLY PRODUCING A SMALL PIN HOLE LEAK. LEAKING FUEL CO	NTAMINATED THESURROUNDING INSULATION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000048	20020110	00048	SO  	2002	1	10	AUS20011145      	1	20011028	G	2844	6770055	LINE            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320*       	41508	EA  	AMTR	C8289	C8289       	GL  	FUEL PRESS IND	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGID COPPER FUEL LINE TO GAUGE FRACTURED. SUSPECT INADEQUATE SUPPORT.						1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	EXPP5N	 
2002011000049	20020110	00049	EA  	2002	1	10	AUS20011146      	1	20010609	G	3230	6A09000097	HOSE            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN1     	52008	NE  	HAMSTD	2D	2D30        	NE  	FLOAT STRUT	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) RT LANDING GEAR HYDRAULIC HOSE CHAFED INSIDE FLOAT STRUT. HOSE BURST. LOSS OF HYDRAULIC FLUID. AIRCRAFT IS A FLOAT	PLANE.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206	 
2002011000050	20020110	00050	CE  	2002	1	10	AUS20011148      	1	20011023	G	5311	0024300536	FRAME           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT EXIT FRAME CRACKED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000051	20020110	00051	CE  	2002	1	10	AUS20011149      	1	20011016	G	3230	00241003217	BRACKET         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ALIGNMENT GUIDE BRACKET CRACKED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011000052	20020110	00052	CE  	2002	1	10	AUS20011150      	1	20011016	G	3233	9581001723	WORM GEAR       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR GEARBOX / ACTUATOR HOURS UNKNOWN (2000 HOURS OVERHAUL). LANDING GEAR GEARBOX FOUND TO HAVE NO OIL. GE	AR ACTUATOR WORM DRIVE PNO 35-810076-3 FOUND TO HAVE FATIGUE CRACKS (MECHANICAL HANDLE ATTACHMENT END).					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2001120400110	20011204	00110	SO  	2001	12	4	AUS20011152      	1	20011026	G	3245		TUBE            	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	TIRE TUBE	PUNCTURED       	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) NOSEWHEEL TYRE AND TUBE PUNCTURED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000054	20020110	00054	SO  	2002	1	10	AUS20011153      	1	20011027	G	3260		SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT MLG DOWNLOCK	STUCK           	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH STICKING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001120400111	20011204	00111	NE  	2001	12	4	AUS20011154      	2	20011012	G	7230		SEAL            	LYC         	LTS101      	BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  	 		            		TURBINE ENGINE C	LEAKING         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 									(AUS) ENGINE NO1 CARBON SEAL LEAKING.						1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001120400112	20011204	00112	SO  	2001	12	4	AUS20011157      	2	20011030	G	8530	646657	STUD            	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	RECIPROCATING EN	MISSING         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 									(AUS) RH ENGINE NO4 CYLINDER EXHAUST STUDS (4OFF) MISSING ALLOWINGEXHAUST GAS TO BE DIRECTED ONTO THE CHT PROBE.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001120400113	20011204	00113	EA  	2001	12	4	AUS20011158      	2	20011030	G	7414	S4LN200	MAGNETO         	LYC         	O360A1D     	MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D34C	2D34C53     	GL  	MAGNETO/DISTRIBU	FAULTY          	W			    	K	 	 	 	NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 	 				915094919614					(AUS) MAGNETOS INTERMITTENT IN OP. INSP FOU NDFOLLOWING FAULTS ON BOTH UNITS:-1. CAPACITORS FOUND TO LEAKING ELECT.LY.2.	 SPUR GEAR FOUND TO BE OF NYLON TYPE WHICH HAS BEEN  OBSOLETE FOR MANY YRS&REQD AS PER BENDIX MASTER MANUAL TO BE REPL. 	3. DISTRIBUTOR BLOCK CONTAMINATED WITH FOREIGN MATERIAL &CRACKS WERE FOUND RADIATING OUT FROM THE ELECTRODES&  THERE EVI	DENCE OF TRACKING ALONG THESE CRACKS4. INTERNAL TIMING FOUND TO BE SET AT 6 DEGS MOST LIKELY DUE TO CAM  FOLLOWER WEAR O	N CONTACTS AS CONTACT  GAPAT 0.1778MM (0.007IN).THESE VALUES COMPARED TOACCEPTABLE LIMITS OF 10 DEGS +/-2 DEGS&CONTACT G	APOF APPROX 0.4064MM (0. 016IN) SUGGESTS THAT THESE MAGNETOS HAVE NOT BEEN REMVD FOR SOME TIME.01115830-	1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P7EA	 
2002011000064	20020110	00064	EU  	2002	1	10	AUS20011160      	1	20011029	G	2932	9738114306	SWITCH          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD PRESSURE	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	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	 
2001120400115	20011204	00115	EA  	2001	12	4	AUS20011163      	2	20011103	G	8520	L206168A	STUD            	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		1723 		L206168A					(AUS) RH ENGINE CYLINDER HOLDDOWN STUDS CRACKED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000065	20020110	00065	EU  	2002	1	10	AUS20011164      	1	20011106	G	5302	109037043205	STRUCTURE       			AGUSTA	A109  	A119        	0261102	EU  										TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL BOOM CRACKED.						1	G	7	2 	3U			 	H7EU    					 
2002011000066	20020110	00066	NE  	2002	1	10	AUS20011165      	2	20010210	G	7321	105MK2S	REGULATOR       			BOEING	747   	747338      	       	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 4 FUEL FLOW	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			2766 							(AUS) NR 4 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY. INVESTIGATION FOUND THE CAUSE TO BE FAILURE OF THE VMO QUILLSHAFT CU	P WASHER DUE TO HIGH CYCLE FATIGUE.					2	L	7	2 	4F	4	F	RT	A20WE   	E12EU				 
2002011000068	20020110	00068		2002	1	10	AUS20011168      	4	20011105	G	3460	09601820038	CAPACITOR       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	MCAULY	2D34C	B2D34C214   	GL  	FLT MANAGEMENT	BURNED OUT      	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) NAVCOM CAPACITOR C491 BURNT.						1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P7EA	 
2001120400117	20011204	00117	SO  	2001	12	4	AUS20011169      	2	20011017	G	8520	632018	GEAR            	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RECIPROCATING EN	LOOSE           	W			    	K	 	 	 	NONE                    				O	H	J	OTHER                     	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        	IN	INSP/MAINT     	1			AU	S 	 		721  		811610R					(AUS) RH ENGINE ALTERNATOR DRIVE GEAR TO CRANKSHAFT ATTACHMENT BOLTSPNO 649205 LOOSE AND GEAR PNO 632018 LOOSE AND TEETH	 DAMAGED. ALTERNATOR BEARINGS FAILED. METAL CONTAMINATION OF OIL FILTER.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002011000069	20020110	00069	SW  	2002	1	10	AUS20011170      	1	20011101	G	2710	705541	CONTROL ROD     			AIRTRC	AT802 	AT802       	0390305	SW  										AILERON CONTROL	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AILERON CONTROL ROD BENT. SUSPECT CAUSED BY WIND GUST.						1	L	7	1 	3T			NC	A19SW   					 
2002011000070	20020110	00070	NM  	2002	1	10	AUS20011171      	1	20011106	G	4920	38002981	APU             			BOEING	767   	767*        	       	NM  										APU BAY	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			3562 		P1022					(AUS) APU FAILED TO START.						2	L	7	2 	4F			RT	A1NM    					 
2001120400119	20011204	00119	CE  	2001	12	4	AUS20011174      	1	20011108	G	5711		SPAR            	            	            	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	WING SPAR	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING RH FORWARD SPAR WEB CRACKED AROUND BEND RADIUS AND FORWARD FACE. FOUND DURING INSPECTION IAW BEECH SB 2269 RE	V1 ANDAD/BEECH55/62 AMDT4.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2001120400120	20011204	00120	CE  	2001	12	4	AUS20011175      	1	20011102	G	7820	125025116	MUFFLER         	CONT        	IO520F      	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE NOISE SUP	FAILED          	W			    	K	 	 	 	NONE                    				O	E	R	OTHER                     	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH EXHAUST MUFFLER INTERNAL BAFFLE COLLAPSED PARTIALLY BLOCKING MUFFLER AND CAUSING LOSS OF ENGINE PERFORMANCE.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2001120400121	20011204	00121	CE  	2001	12	4	AUS20011176      	1	20011107	G	3230	08411132	SCREW           	CESSNA      	310R        	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LANDING GEAR RET	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR DOWNLOCK ADJUSTING SCREW FAILED IN THREADEDAREA. RH MLG COLLAPSED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002011000078	20020110	00078	SO  	2002	1	10	AUS20011181      	1	20011009	G	2140	A99100009	COMBUST CHAMBER 			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HEATING SYSTEM	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HEATER COMBUSTION TUBE DISTORTED IN AREA OF FIRST AIR REVERSAL. SUSPECT CAUSED BY FAILURE OF TUBE MATERIAL TO COPE	 WITH THE HIGHTEMPERATURE OF THE HEATER.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000079	20020110	00079	SO  	2002	1	10	AUS20011182      	2	20011106	G	8550		O-RING          			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	FAILED          	W				D				RETURN TO BLOCK         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RT ENGINE UPPER APC OIL FITTING O' RING SEAL FAILED AND LEAKING.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001120400124	20011204	00124	SO  	2001	12	4	AUS20011183      	1	20011102	G	8120	LH1398RH170	HOUSING         	CONT        	TSIO360E    	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	EXHAUST TURBOCHA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		339  		LH1398RH170					(AUS) LH AND RH ENGINE TURBOCHARGER TURBINE HOUSINGS CRACKED. FOUND DURING INSPECTION IAW AD/TURBO/1. LH ENGINE - CONTIN	ENTAL TSIO-360-E - SERIAL NUMBER 307156 TSO 338.6 HOURS - TSLSV 119.6 HOURS RH ENGINE - CONTINENTAL LTSIO-360-E - SERIAL	 NUMBER 306161TSO 338.6 HOURS - TSLSV 119.6 HOURS				1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2001120400125	20011204	00125	CE  	2001	12	4	AUS20011184      	1	20011102	G	7110	1019100251	COWLING         	PWA         	PT6A41      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE COWLING S	SEPARATED       	W			    	K	 	 	 	NONE                    				D	 	 	INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 	 									(AUS) LH ENGINE FORWARD UPPER COWL ASSEMBLY SEPARATED IN FLIGHT. PILOTHAD RECENTLY PERFORMED MAINTENANCE ON THE COWL. MI	NOR DAMAGE TO COWLS AND LEADING EDGE CAUSED BY COWL SEPARATION. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001120400127	20011204	00127	EA  	2001	12	4	AUS20011186      	2	20011107	G	8520	LW11021	BEARING         	LYC         	IO320B1A    	PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		285  		L246155A					(AUS) CONNECTING ROD BIGEND BEARING MATERIAL SEPARATED FROM BEARING SHELL.						1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2002011000080	20020110	00080	SW  	2002	1	10	AUS20011187      	1	20011102	G	6410	212010750105	BLADE           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TAIL ROTOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			281  							(AUS) TAIL ROTOR BLADE CORE CONTAMINATED WITH WATER. FOUND DURING X-RAY INSPECTION AFTER BLADE WAS UNABLE TO BE BALANCED	 AND WAS FOUND TO BE 66 GRAMS HEAVIER THAN THE MASTER BLADE.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002011000081	20020110	00081	SO  	2002	1	10	AUS20011188      	2	20011107	G	8530		EXHAUST VALVE   			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 AND NR 3 CYLINDER EXHAUST VALVES BURNED AND ERRODED.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001120400132	20011204	00132	EU  	2001	12	4	AUS20011195      	1	20011110	G	5311		FASTENER        	            	            	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  	 		            		FUSELAGE MAIN, F	SHEARED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) FRAME 29 RH SIDE HILOK FASTENER SHEARED IN AREA ADJACENT TO STRINGER NO11.						2	H	7	4 	4F	4	F	 	A49EU   	E6NE				 
2001120400134	20011204	00134	CE  	2001	12	4	AUS20011197      	1	20011113	G	5341	NAS15035M	BOLT            	            	            	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	FUSELAGE, WING A	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING ATTACHMENT BOLT CRACKED. FURTHER INVESTIGATION FOUND THATTHE WASHER HAD BEEN INCORRECTLY FITTED WITH THE WASH	ER BEVELLED EDGE FACING AWAY FROM THE BOLT HEAD. THE WASHER WAS ALSO DAMAGED. FOUND DURING INSPECTION IAW AD/BEECH55/79 	AMDT1.PERSONNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA	 
2001120400136	20011204	00136	NM  	2001	12	4	AUS20011199      	1	20010404	G	3230	BACF8A06EN0700B	HOSE            	            	            	BOEING	767   	767238      	1385114	NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  	 		            		LANDING GEAR RET	LEAKING         	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR TILT ACTUATOR HYDRAULIC HOSE LEAKING.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001120400137	20011204	00137	CE  	2001	12	4	AUS20011201      	1	20011113	G	7430	A3600	IGNITION SWITCH 	LYC         	O360F1A6    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	IGNITION SWITCHI	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) IGNITION SWITCH CONTACTS WORN BEYOND LIMITS AS DETAILED INSEB91-5.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2002011000087	20020110	00087	EU  	2002	1	10	AUS20011205      	1	20011102	G	2752	9787320003	PDU             			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP POWER DRIVE UNIT (PDU) FAILED. INTERNAL THERMAL SWITCH TRIPPED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001120400139	20011204	00139	CE  	2001	12	4	AUS20011207      	1	20011016	G	3411		PIPE            	            	            	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	GTSIO520E   	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	PITOT/STATIC SYS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ALTITUDE ENCODER STATIC PIPE CRACKED. FOUND DURING INSPECTION IAW AD/RAD/43 AND AD/RAD/47.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2002011000090	20020110	00090		2002	1	10	AUS20011212      	4	20011104	G	6122	L16694SIA	CLAMP           			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCM2Y	HCM2YR      	GL  	PROP GOVERNOR	MISSING         	W				O				OTHER                   				K	F		FLUID LOSS                	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 			1070 							(AUS) PROPELLER GOVERNOR OIL LINE CRACKED AT FLANGE IN AREA OF ATTACHMENT TO THE GOVERNOR. LOSS OF ENGINE OIL CAUSED ENG	INE TO SEIZE. INVESTIGATION FOUND THAT THE TWO CLAMPS REQUIRED BYAD/LYC/86 AMDT2 WERE NOT FITTED. PERSONNEL/MAINTENANCE 	ERROR.				1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P43GL	 
2001120400142	20011204	00142	SO  	2001	12	4	AUS20011213      	1	20011103	G	7332	633869	LINE            	CONT        	LTSIO360E   	PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	FUEL PRESSURE IN	CRACKED         	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 	 		1513 		304379					(AUS) RH ENGINE FUEL PUMP SENSE LINE CRACKED APPROXIMATELY 10MM (0.393IN) FROM THE FLARED END.						1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002011000091	20020110	00091	SO  	2002	1	10	AUS20011214      	1	20011101	G	3233	452729	BEARING         			PIPER 	PA28  	PA28R201    	7102816	SO  	CONT  	IO360 	IO360*      	17025	CE  	MCAULY	2D34C	B2D34C213   	GL  	MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR BEARING CRACKED AND BROKEN.						1	L	7	1 	3O	3	O	 	2A13    	E1CE	5	C	P7EA	 
2001120400143	20011204	00143	CE  	2001	12	4	AUS20011215      	1	20010903	G	3233	12810013	ACTUATOR        	            	            	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 	 									(AUS) LH AND RH MAIN LANDING GEAR ACTUATOR BODIES CRACKED IN AREA INDICATED BY SEB 01-2 FIG1 PAGE4.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001120400144	20011204	00144	CE  	2001	12	4	AUS20011216      	1	20010903	G	3230	24411001	PIVOT           	            	            	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH MAIN LANDING GEAR PIVOT ASSEMBLIES CRACKED IN INSPECTION AREA 1B OF SEB 90-1 REV3.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001120400145	20011204	00145	CE  	2001	12	4	AUS20011219      	1	20011106	G	3213	12412021	FITTING         	            	            	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAIN LANDING GEA	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR FITTING CRACKED AND RUBBING ON BRAKE DISC.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2001120400146	20011204	00146	SO  	2001	12	4	AUS20011220      	1	20011030	G	2810		VALVE           	            	            	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL STORAGE	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH MAIN FUEL CELL RH FLAPPER VALVE DOOR MISSING.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000097	20020110	00097	SO  	2002	1	10	AUS20011221      	1	20011110	G	3230		LANDING GEAR    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NOSE	OUT OF ADJ      	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR OUT OF ADJUSTMENT. NLG NOT COMPLETELY ENGAGING WITH UPLOCK HOOK DURING RETRACTION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000098	20020110	00098	SO  	2002	1	10	AUS20011222      	1	20011111	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NLG UPLOCK	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK MICROSWITCH INTERMITTENT IN OPERATION.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011000102	20020110	00102	WP  	2002	1	10	AUS20011224      	2	20011112	G	7261	11405700182	HOUSING         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	OIL PUMP	CRACKED         	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			333  							(AUS) ENGINE OIL PUMP HOUSING CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001120400148	20011204	00148	CE  	2001	12	4	AUS20011225      	1	20011120	G	5741	082255014	FITTING         	            	            	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	WING, FUSELAGE A	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH WING UPPER FORWARD ATTACHMENT FITTING CONTAINED INTERGRANNULAR CORROSION IN THE UPPER SURFACES AND TWO AREAS OF	 PITTINGCORROSION. FOUND DURING INSPECTION IAW AD/C310/53.					1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002011000103	20020110	00103	NE  	2002	1	10	AUS20011226      	2	20011113	G	7200		ENGINE          			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					NACELLE	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) NEWLY INSTALLED ENGINE FAILED TO CORRECTLY CONTROL PROPELLER.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001120400149	20011204	00149	CE  	2001	12	4	AUS20011227      	1	20011108	G	5312	0512187	BULKHEAD        	            	            	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2H     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE MAIN, B	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) BULKHEAD CRACKED. FOUND DURING INSPECTION IAW CESSNA SEB 97-1 AND AAC 1-95.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011400007	20020114	00007	CE  	2002	1	14	AUS20011228      	1	20011119	G	2701	05131822	WHEEL           			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	CONTROL COLUMN	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) PILOTS CONTROL WHEEL BROKE INTO SEVERAL PIECES. INVESTIGATION FOUND THE COPILOTS CONTROL WHEEL CRACKED BEYOND LIMI	TS.					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2002011400008	20020114	00008	GL  	2002	1	14	AUS20011230      	3	20011119	G	6114	C471698	HUB             			CESSNA	188   	A188A       	2073008	CE  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER HUB CRACKED IN AREA OF NR 1 BLADE SOCKET.  FOUND DURING EDDY CURRENT INSPECTION.						1	L	7	1 	3O			 	A9CE    		5	C	P3EA	 
2001120400152	20011204	00152	SO  	2001	12	4	AUS20011237      	1	20011108	G	5541	4006805	SPAR            	            	            	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RUDDER, SPAR/RIB	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RUDDER FORWARD SPAR CRACKED. FOUND DURING INSPECTION IAWAD/PA31/129.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011400013	20020114	00013	GL  	2002	1	14	AUS20011238      	2	20011114	G	7230	6858348	BLADE           			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C18      	03011	GL  					COMPRESSOR	FAILED          	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			AU	S 			1483 							(AUS) SECOND STAGE COMPRESSOR BLADES (2OFF) FAILED). MAJOR DOWNSTREAM DAMAGE. SEVERAL OTHER SECOND STAGE ROTOR BLADES WE	RE FOUND TO BECRACKED FROM THE TRAILING EDGE.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002011400014	20020114	00014	CE  	2002	1	14	AUS20011239      	1	20011121	G	3297	6508012202	WIRE HARNESS    			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D1      	52060	NE  					MLG	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LT ANTISKID TRANSDUCER WIRING HAD AN INTERMITTENT FAULT.  NO BRAKING DURING LANDING RESULTED IN EMERGENCY BRAKING 	SYSTEM OPERATION. RH TYRE FAILED DUE TO WHEEL SKIDDING.  RT MAIN WHEEL HUB ALSO DAMAGED.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2001120400153	20011204	00153	CE  	2001	12	4	AUS20011241      	1	20011109	G	5412	402B0622	BEAM            	            	            	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NACELLE/PYLON, B	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				402B0622					(AUS) ENGINE BEAMS AND CANTED BULKHEADS CORRODED BEYOND LIMITS. FOUND DURING NDT INSPECTION.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001120400154	20011204	00154	CE  	2001	12	4	AUS20011242      	1	20011109	G	3221	584200111	TRUNNION        	CESSNA      	402B        	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NOSE/TAIL LANDIN	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				402B0622					(AUS) NOSE LANDING GEAR TRUNNION CRACKED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001120400155	20011204	00155	SO  	2001	12	4	AUS20011243      	2	20010914	G	8520	6419311075	BOLT            	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 		637  		574058					(AUS) LH ENGINE CRANKCASE THOUGH BOLT BROKEN. SEE ALSO MDR 01/1244.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001120400156	20011204	00156	SO  	2001	12	4	AUS20011244      	2	20010914	G	8520	6461401	STUD            	CONT        	IO520M      	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RECIPROCATING EN	BROKEN          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 				574058					(AUS) LH ENGINE CYLINDER HOLDDOWN STUD BROKEN. CRANKCASE CRACKED. SEE ALSO MDR 01/1243.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2001120400157	20011204	00157	NE  	2001	12	4	AUS20011245      	2	20011001	G	7321	164448480	FCU             	TMECA       	164448480   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				O	K	 	OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 	 				A444B					(AUS) FUEL CONTROL UNIT LEAKING. FUEL LEAKING FROM FCU DRAIN WITH BOOST PUMP ON AND ENGINE NOT RUNNING.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001120400158	20011204	00158	NE  	2001	12	4	AUS20011246      	2	20011003	G	7321	164448480	FCU             	TMECA       	164448480   	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		FUEL CONTROL/TUR	FAULTY          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		8    		98B					(AUS) FCU FAULTY. ENGINE HUNG ON START.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011400017	20020114	00017		2002	1	14	AUS20011250      	4	20011123	G	2561	P0640101	LIFE VEST       																	CABIN	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) OVERHAULED LIFE JACKETS INCORRECTLY MARKED.  LIFE JACKETS ARE EITHER INFANT OR ADULT FIT ITEMS BUT ARE ALL MARKED 	ON THE OUTSIDE OF THE STORAGE BAGS AS KSE-35L8 WHICH ARE ADULT FIT ITEMS.  THE INFANT FIT JACKETS SHOULD BE MARKED P0640	.101.  THE INCORRECT MARKING ON THE STORAGE BAGS COULD RESULT IN THE INCORRECT ITEM BEING USED IN AN EMERGENCY.  THE OVE	RHAUL FACILITYHAS BEEN NOTIFIED AND WILL CORRECTLY MARK ALL LIFE JACKETS FROM NOW ON.  INCORRECTLY MARKED LIFE JACKETS I	N THE SYSTEM WILL BE IDENTIFIED AND CORRECTLY MARKED BY MAINTENANCE.															 
2001120400160	20011204	00160	WP  	2001	12	4	AUS20011251      	1	20011119	G	3213	269A3150	DAMPER          	            	            	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  	 		            		MAIN LANDING GEA	LOOSE           	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) LH REAR LANDING GEAR DAMPER UPPER CAP UNSCREWED AND SEPARATED FROM PISTON. SUSPECT CAUSED BY VIBRATION.						1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001120400161	20011204	00161	SO  	2001	12	4	AUS20011252      	1	20011113	G	3230	9564308	BRACKET         	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR DOWNLOCK BRACKET CRACKED.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2001120400162	20011204	00162	EA  	2001	12	4	AUS20011253      	2	20011113	G	8520	LW16508	CAMSHAFT        	LYC         	O360E1A6    	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	RECIPROCATING EN	UNSERVICEABLE   	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH ENGINE CAMSHAFT NO1 AND NO4 TAPPETS UNSERVICEABLE. FOUND DURING INSPECTION IAW PIPER MSB 446D.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2001120400163	20011204	00163	SO  	2001	12	4	AUS20011254      	1	20011113	G	5712	7847506	RIB             	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	WING, RIB/BULKHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING RIB CRACKED. RIB SUPPORTS UNDERCARRIAGE DOWNLOCK.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2001120400164	20011204	00164	SO  	2001	12	4	AUS20011255      	1	20011113	G	5712	7847507	RIB             	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	WING, RIB/BULKHE	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) WING RIB CRACKED. RIB SUPPORTS UNDERCARRIAGE DOWNLOCK.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2001120400165	20011204	00165	SO  	2001	12	4	AUS20011256      	1	20011113	G	3230	9564309	BRACKET         	            	            	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC3Y	HCC3YR2     	NE  	LANDING GEAR RET	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR UPLOCK BRACKET CRACKED.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P25EA	 
2002011400018	20020114	00018	CE  	2002	1	14	AUS20011257      	1	20011030	G	2752	45521212607	ACTUATOR        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					TE FLAP	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING FLAP ACTUATOR INCORRECTLY INSTALLED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400019	20020114	00019	CE  	2002	1	14	AUS20011258      	1	20011030	G	5720	00243002027	FITTING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR ACTUATOR SUPPORT FITTING CRACKED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400020	20020114	00020	CE  	2002	1	14	AUS20011259      	1	20011030	G	3233	45521212604	ACTUATOR        			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					MLG ACTUATOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR ACTUATOR INCORRECTLY FITTED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400021	20020114	00021	CE  	2002	1	14	AUS20011260      	1	20011105	G	2752	355212133	ATTACH FITTING  			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					TE FLAP ACTUATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			204  							(AUS) TRAILING EDGE FLAP ACTUATOR INTERNALLY CORRODED. ATTACHMENT LUG ALSO CORRODED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400022	20020114	00022	CE  	2002	1	14	AUS20011261      	1	20011105	G	2752	3536415157	BRUSH HOLDER    			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520M      	17032	SO  					TE FLAP ACTUATOR	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			120  							(AUS) TRAILING EDGE FLAP ACTUATOR MOTOR BRUSH HOLDER ASSEMBLIES CRACKED.  EXCESSIVE HEAT THROUGH FIELD WINDINGS.  INSUFF	ICIENT GREASE OF INCORRECT TYPE IN GEARBOX ASSEMBLY. UNAPPROVED PART.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400023	20020114	00023	CE  	2002	1	14	AUS20011262      	1	20011105	G	2520		SEAT            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					PASSENGER COMPAR	UNSERVICEABLE   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN SEATS UNSERVICEABLE. PARTS MISSING. REAR SEAT LUMBAR SUPPORTS CRACKED. VARIOUS SEAT ASSEMBLIES MODIFIED. PER	SONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400024	20020114	00024	CE  	2002	1	14	AUS20011263      	1	20011105	G	2820	002920000191	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL DIST	CHAFED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CROSSFEED LINE LOCATED IN RT WHEEL BAY CHAFING ON UNDERCARRIAGE DOWNLOCK BACKUP CABLE. SUSPECT LINE INADEQUAT	ELY SECURED. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400025	20020114	00025	CE  	2002	1	14	AUS20011264      	1	20011105	G	2820	00292000077	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL DIST	CHAFED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CROSSFEED FUEL LINE LOCATED IN LT WHEEL WELL CHAFING ON UNDERCARRIAGE ACTUATOR CONTROL ROD. THE FUEL LINE HAD BEEN	 COVERED WITH A PLASTIC SLEEVE AFTER THE DAMAGE HAD OCCURRED.  SUSPECT CAUSED BY INADEQUATE SECURING OF FUEL LINE. PERSO	NNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400026	20020114	00026	CE  	2002	1	14	AUS20011266      	1	20011123	G	3297		WIRE            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG DOWNLOCK	MISINSTALLED    	W				A				UNSCHED LANDING         				W	N		INADEQUATE Q C            	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRING INCORRECTLY ROUTED CAUSING A STRAIN ON THE MICROSWITCH.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002011400027	20020114	00027	EU  	2002	1	14	AUS20011267      	1	20011123	G	3233	C243532	ACTUATOR        			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					RT MLG	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 			7803 							(AUS) RT MAIN LANDING GEAR ACTUATOR HYDRAULIC UNIT FAULTY.						2	G	7	2 	4U	4	U	 	H4EU    	E12NE				 
2001120400166	20011204	00166	EA  	2001	12	4	AUS20011268      	2	20011122	G	7310	5011849	PIPE            	PWA         	PT6A34      	EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE FUEL DIST	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2002010400040	20020104	00040	CE  	2002	1	4	AUS20011271      	1	20011119	G	2731	455260053	SPROCKET        	            	            	BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	ELEVATOR TAB CON	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ELEVATOR TRIM TAB ACTUATOR SPROCKET SHAFT BADLY WORN.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002010400041	20020104	00041	NE  	2002	1	4	AUS20011272      	1	20011129	G	3260	7655200904045	WIRE            	            	            	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  	 		            		LANDING GEAR POS	BROKEN          	W			    	K	 	 	 	NONE                    				O	N	 	OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR DOWNLOCK SENSOR HARNESS WIRE BROKEN.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002011400030	20020114	00030	CE  	2002	1	14	AUS20011273      	1	20011006	G	3246		PANEL           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FLOAT COVER	SEPARATED       	W				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT HAND FLOAT HATCH COVER SEPARATED IN FLIGHT. THE COVER CONTACTED THE RIGHT HAND TAILPLANE CAUSING CONSIDERABL	E DAMAGE AND CONTROL PROBLEMS. VIBRATION CAUSED FAILURE OF SEVERAL HYDRAULIC LINES IN THE RIGHT HAND FLOAT. LOSS OF HYDR	AULIC FLUID THEN LEAD TO ONLY PARTIAL LANDING GEAR EXTENSION.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011400035	20020114	00035		2002	1	14	AUS20011279      	4	20011023	G	3414	610400106	INDICATOR       			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	AIRSPEED	READS HIGH      	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AIRSPEED INDICATOR FAULTY.  INDICATOR WAS READING 180 KNOTS WHEN THE AIRCRAFT WAS STATIONARY.  PITOT AND STATIC LI	NES CHECKED WITH NO FAULTS.  ARTIFICIAL HORIZON ALSO TOPPLING IN FLIGHT.					1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2002011400036	20020114	00036	SW  	2002	1	14	AUS20011280      	1	20011129	G	2720	472105	CONTROL CABLE   			GULSTM	112   	114         	7630314	SW  	LYC   	O540  	IO540T4B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	RUDDER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) LT RUDDER CONTROL CABLE INCORRECTLY ROUTED UNDER SUPPORT BRACKET. CABLE RUBBING ON PULLEY SUPPORT BRACKET.  ELEVAT	OR TRIM CABLE ALSO INCORRECTLY ROUTED AND FOULING ON STRUCTURE.  PERSONNEL/MAINTENANCE ERROR.					1	L	7	1 	3O	3	O	 	A12SO   	1E4	5	C	P920	 
2002010400043	20020104	00043	EU  	2002	1	4	AUS20011281      	1	20011127	G	3240		BRAKE           	            	            	PARTEN	P68   	P68B        	6780104	EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LANDING GEAR BRA	MISSING         	W			    	K	 	 	 	NONE                    				O	C	 	OTHER                     	F.O.D.                    		TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) AIRCRAFT NOSE SPAT AND PITOT TUBE DAMAGE WHEN AIRCRAFT RAN INTO THE SIDE OF THE HANGAR WHILE BEING TAXIED FOR REFU	ELLING. INVESTIGATION FOUND THAT THE PILOT WAS SITTING IN THE RH SEAT AND THAT THE BRAKES HAD BEEN REMOVED FROM THE RH S	IDE POSITION. THE REMOVAL OF THE BRAKES HAD NOT BEEN PLACARDED. PERSONNEL/MAINTENANCE ERROR.				1	H	7	2 	3O	3	O	 	A31EU   	1E10	5	C	P920	 
2002010400044	20020104	00044	NM  	2002	1	4	AUS20011282      	1	20011124	G	2820	5324	VALVE           	            	            	BOEING	737   	7374Q8      	138447Q	NM  	CFMINT	CFM56 	CFM563C     	13802	EU  	 		            		AIRCRAFT FUEL DI	FOD             	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			AU	S 	 				5324					(AUS) FUEL SYSTEM NON-RETURN VALVE JAMMED OPEN BY FOD CAUSING A FUELIMBALANCE BETWEEN NO1 AND NO2 TANKS. INVESTIGATION F	OUND APLASTIC BLANK WAS JAMMING THE VALVE OPEN. SUSPECT FOD WAS A BLANKING CAP FROM BOOST PUMP PRESSURE LINE. BOOST PUMP	 HAD BEEN REPLACED PRIOR TO RECEIPT BY VIRGIN BLUE. PERSONNEL/MAINTENANCE ERROR. FOD.				2	L	7	2 	4F	4	F	RT	A16WE   	E21EU				 
2002011400037	20020114	00037	SO  	2002	1	14	AUS20011283      	1	20011203	G	5220	40979	DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	EMERGENCY EXITS	SEPARATED       	W				A				UNSCHED LANDING         				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) CABIN EMERGENCY EXIT DOOR SEPARATED FROM AIRCRAFT. INVESTIGATIONOF THE LATCH MECHANISM FOUND THAT THE LATCH HAD NO	T BEEN FULLY ENGAGING FOR A CONSIDERABLE TIME. LATCHES HAD ONLY BEEN CLOSING APPROXIMATELY 30 DEGREES INSTEAD OF THE FUL	L 90 DEGREES. CLOSEINSPECTION OF THE HANDLE ASSEMBLY SHOWED THAT IT WAS BENT IN THEAREA WHERE THE VERTICAL TUBE IS WELDE	D TO THE BELLCRANK CROSSTUBE RESULTING IN LIMITED TRAVEL OF THE DOOR LATCHES.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011400045	20020114	00045	SO  	2002	1	14	AUS20011293      	2	20011129	G	8530		EXHAUST VALVE   			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	NR 1 CYLINDER	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 CYLINDER EXHAUST VALVE LEAKING PAST VALVE SEAT.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002010400047	20020104	00047	EU  	2002	1	4	AUS20011294      	1	20011209	G	2120		COOLING FAN     	            	            	REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	AIR DISTRIBUTION	FAILED          	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 	 									(AUS) SURVEILLANCE RADAR COOLING FAN FAILED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002010400048	20020104	00048	EU  	2002	1	4	AUS20011298      	1	20010904	G	3150	1097811	WARNING SYSTEM  	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		CENTRAL WARNING	FAULTY          	W			    	K	 	 	 	NONE                    				F	N	 	FLT CONT AFFECTED         	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 	 									(AUS) UNSAFE CONFIGURATION WARNING SOUNDED. INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM. LH ELEVATOR BYPASS SWITCH	 CHANGED AS A PRECAUTION.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002010400051	20020104	00051	EA  	2002	1	4	AUS20011304      	2	20011203	G	7322	229164	NOZZLE          	LYC         	O320H2AD    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUEL CONTROL/REC	MISSING         	W			    	K	 	 	 	NONE                    				E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 	 		501  		CK10488V					(AUS) CARBURETTOR DISCHARGE NOZZLE MISSING.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011400055	20020114	00055	EU  	2002	1	14	AUS20011309      	1	20011206	G	2731		ACTUATOR        			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	ELEVATOR TAB	CONTAMINATED    	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR TRIM TAB ACTUATORS LUBRICATED WITH THE INCORRECT GREASE. ACTUATORS FREEZING IN FLIGHT. MAINTENANCE MANUAL	 SPECIFIES "TRIBOLUBE" ONLY. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART.					1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002010400054	20020104	00054	EU  	2002	1	4	AUS20011310      	1	20011206	G	5343	571304013	CHANNEL         	            	            	REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	LANDING GEAR ATT	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) NOSE LANDING GEAR ACTUATOR ATTACHMENT STRUCTURE CHANNEL CRACKED.FOUND DURING INSPECTION IAW AD/F406/7.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002011400056	20020114	00056	NE  	2002	1	14	AUS20011311      	2	20011206	G	7420		IGNITION LEAD   			REIMS 	406   	F406        	7535723	EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	RT ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT IGNITER LEAD ON BOTH ENGINES CHAFING ON FUEL LINE TO FLOW DIVIDER.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL	 
2002010400055	20020104	00055	WP  	2002	1	4	AUS20011318      	1	20011211	G	6310	269A55177	BRACKET         	            	            	HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  	 		            		ENGINE/TRANSMISS	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LOWER DRIVE PULLEY SUPPORT BRACKET CRACKED. ONE ATTACHMENT LUGSEPARATED.						1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2002010400056	20020104	00056	CE  	2002	1	4	AUS20011319      	1	20011211	G	7810	265401415	EXHAUST PIPE    	PWA         	PT6A114A    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE COLLECTOR	CRACKED         	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 	 				PCE19248					(AUS) ENGINE PRIMARY EXHAUST DUCT CRACKED AND HOLED. HOLE WAS APPROXIMATELY228.6MM (9IN) BY 146MM (5.75IN). ESCAPING EXH	AUSTGAS DAMAGED OIL COOLER SHROUD RUBBERS AND DISCOLOURED THE PAINT ON THE LOWER RH COWL.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011400061	20020114	00061	NE  	2002	1	14	AUS20011320      	2	20011209	G	7420	CH5339907	IGNITION LEAD   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) IGNITER LEAD INSULATION SHORT.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002011400062	20020114	00062	EU  	2002	1	14	AUS20011324      	1	20010811	G	2421		WARNING SYSTEM  			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					AC GENERATOR	FALSE ACTIVATION	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) NR 2 GENERATOR HIGH INLET TEMPERATURE. INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM. PLUGS AND CONNECTORS CLE	ANED.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002011400066	20020114	00066	NM  	2002	1	14	AUS20011330      	1	20011123	G	6210		BLADE           			ROBSIN	R22   	R22MARINER  	7640115	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADES SUSPECT CRACKED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002010400059	20020104	00059	EA  	2002	1	4	AUS20011331      	2	20010903	G	7414	10357584	GEAR            	LYC         	O320B2C     	ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  	 		            		MAGNETO/DISTRIBU	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		400  							(AUS) MAGNETO GEAR TEETH BROKEN.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002011400067	20020114	00067	CE  	2002	1	14	AUS20011336      	1	20011210	G	2450	7270530	CIRCUIT BREAKER 			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AC DISTRIBUTION	FAILED          	W				O				OTHER                   				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) NR 1 AVIONICS BUS CIRCUIT BREAKER/SWITCH INTERNAL FAILURE.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011400068	20020114	00068	CE  	2002	1	14	AUS20011337      	1	20011211	G	2820	314200	VALVE           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL DIST	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL SYSTEM CHECK VALVE EXCESSIVELY CORRODED AND CONTAMINATED DUE TO WATER IN FUEL CROSSFEED LINE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400069	20020114	00069	CE  	2002	1	14	AUS20011338      	1	20011211	G	2820	60292000031	LINE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL DIST	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL LINE EXCESSIVELY COORODED DUE TO WATER CONTAMINATION.						1	L	7	2 	3O	3	O	 	3A16    	E5CE				 
2002011400070	20020114	00070	CE  	2002	1	14	AUS20011340      	1	20011211	G	2450	70HF10	DIODE           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					AC POWER DIST	FAILED          	W				O				OTHER                   				G			MULTIPLE FAILURE          			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 2 BUS SYSTEM FEED DIODES FAILED.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002011400071	20020114	00071	SO  	2002	1	14	AUS20011341      	1	20011214	G	5342	553266	BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360E    	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	HORIZONTAL  STAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILISER ATTACHMENT FITTING BOLTS BENT (2OFF) AND BROKEN(2OFF). INVESTIGATION FOUND THAT THE BOLTS WERE THE INCO	RRECT TYPE. THE PART NUMBER OF THE INCORRECT BOLTS WAS PNO NAS425-3-7.UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P920	 
2002011400075	20020114	00075	SO  	2002	1	14	AUS20011347      	2	20011211	G	8530	639272P1O	CYLINDER        			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	RT ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			456  							(AUS) RT ENGINE NR 4 CYLINDER AND PISTON SEPARATED IN FLIGHT. RT ENGINE COWL SEPARATED ALONG HINGE.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P22EA	 
2002011400078	20020114	00078	NE  	2002	1	14	AUS20011350      	1	20011212	G	6210	7615009000046	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE CRACKED.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002010400067	20020104	00067	EA  	2002	1	4	AUS20011357      	2	20011214	G	7414	104001678	CAM             	BENDIX      	S6LN1227    	BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO/DISTRIBU	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				C0891					(AUS) MAGNETO CAM PIVOT PIN HAD EXCESSIVE PLAY. PIN HAD APPROXIMATELY 0.508MM (0.020IN) OF PLAY. MAXIMUM PLAY 0.3556MM (	0.014IN).					1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002011400085	20020114	00085	CE  	2002	1	14	AUS20011361      	1	20011213	G	3260	574122215	HOOK            			CESSNA	441   	441         	2076020	CE  										LT MLG UPLOCK	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK HOOK FAILED AT PIVOT POINT.						1	L	7	2 	3T			RT	A28CE   					 
2002011400088	20020114	00088		2002	1	14	AUS20011365      	4	20011218	G	2350	IU396002	AUDIO PANEL     			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 			1446 							(AUS) AUDIO PANEL FAILED. SUSPECT INTERNAL TRANSFORMER BURNT.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2002011400089	20020114	00089	EU  	2002	1	14	AUS20011366      	1	20011121	G	5523	BURKLIN12H3668	CAP             			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ELEVATOR	DISLODGED       	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) ELEVATOR BALANCE HORN BLANKING CAP DISLODGED AND RESTRICTED ELEVATOR MOVEMENT. FOD.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA	 
2002011400091	20020114	00091	EA  	2002	1	14	AUS20011369      	2	20011218	G	8530	IO540K1B5	ROCKER          			GIPPLD	GA200 	GA200       	       	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE ROCKER COVER GASKETS INCORRECTLY FITTED. FOLLOWING REMOVAL OF THE ROCKER COVERS IT WAS FOUND THAT THE ROCKE	RS WERE ALSO INCORRECTLY FITTED. SOME INLET ROCKERS WERE FITTED TO EXHAUST POSITIONS AND VICE VERSA. NR 5 CYLINDER EXHAU	ST VALVE ALSO HAD EXCESSIVE CLEARANCE OF 3.2MM (0.126IN) WHEN THE RECOMMENDED CLEARANCE WAS BETWEEN 0.711MM (0.028IN) AN	D 2.032MM (0.080IN).THE ENGINE HAD JUST BEEN RECEIVED FROM OVERHAUL AND WAS BEING BUILT UP TO QEC STATUS. PERSONNEL/MAIN	TENANCE ERROR.		1	L	7	1 	3O	3	O	NC	A00001LA	1E4	5	C	P920	 
2002020500150	20020205	00150	EA  	2002	2	5	AUS20011373      	2	20011218	G	8520	SL13885M10	BEARING         	LYC         	IO720B1B    	GULSTM	680   	680FL       	0141608	SW  	LYC   	O720  	IO720B1B    	41546	EA  	HARTZL	HCB3Z	HCB3Z302    	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 FILTER.						1	H	7	2 	3O	3	O	 	2A4     	1E15	5	C	P907	 
2002020500152	20020205	00152	SO  	2002	2	5	AUS20011375      	1	20011219	G	3213	AN3104	NUT             	            	            	PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAIN LANDING GEA	MISSING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH MAIN LANDING GEAR TORQUE LINK CONNECTING BOLT NUT MISSING.						1	L	7	2 	3O	3	O	 	A7SO    	1E10	5	C	P920	 
2002020500153	20020205	00153	SO  	2002	2	5	AUS20011376      	2	20011219	G	7414	103493504	MAGNETO         	CONT        	IO520F      	CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		807  							(AUS) RH MAGNETO COUPLING PINS WORN EXCESSIVELY.						1	H	7	1 	3O	3	O	 	A16CE   	E5CE	5	C	P47GL	 
2002020500154	20020205	00154	SO  	2002	2	5	AUS20011378      	1	20011214	G	3213	6531904	CYLINDER        	            	            	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAIN LANDING GEA	BROKEN          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) AFTER A HEAVY LANDING THE LH LANDING GEAR WAS FOUND TO BE LOWER THAN THE RH GEAR AND SITTING AT AN ODD ANGLE. INVE	STIGATION FOUND THAT THE LH MAIN LANDING GEAR CYLINDER TORQUE LINK ATTACHMENT LUGS BROKEN OFF.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002020500155	20020205	00155	EA  	2002	2	5	AUS20011379      	2	20011212	G	8520	LW11021	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) NO3 MAIN BEARING SHELL DELAMINATED AND SHEDDING LARGE FLAKES OF BEARING MATERIAL. METAL CONTAMINATION OF OIL FILTE	R. BEARING HADA MANUFACTURERS STAMP (ML-KS) DATE 2-00.					1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P913	 
2002020500156	20020205	00156	EA  	2002	2	5	AUS20011380      	2	20011218	G	7414	104001678	CAM             	BENDIX      	10349370A   	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				D299916FR					(AUS) MAGNETO IMPULSE CAM PAWL PIVOTS WORN TO LIMITS.						1	L	7	1 	3O	3	O	 	A3SO    	1E4	5	C	P920	 
2002020500157	20020205	00157	SO  	2002	2	5	AUS20011382      	2	20011010	G	8530	646640	EXHAUST VALVE   	CONT        	IO360K      	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	RECIPROCATING EN	WORN            	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 	 		1459 							(AUS) EXHAUST VALVE GUIDE WORN EXCESSIVELY. INVESTIGATION FOUND SPRINGCAP RIDING UP ON VALVE AND CONTACTING ROCKER ARM D	UE TO WORNCOLLETS.					1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA	 
2002020600003	20020206	00003	CE  	2002	2	6	AUS20011384      	1	20011205	G	7810	31015828	EXHAUST STACK   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST DUCT CRACKED AT AFT FLANGE ATTACHMENT WELD.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002020500158	20020205	00158	CE  	2002	2	5	AUS20011385      	1	20011130	G	7430	C2925010100	IGNITION SWITCH 	CONT        	IO520F      	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	IGNITION SWITCHI	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) IGNITION SWITCH TERMINALS WORN BEYOND LIMITS.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P21EA	 
2002020600004	20020206	00004	CE  	2002	2	6	AUS20011386      	1	20011218	G	3260	GE327	BULB            			CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520K    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG INDICATOR	BURNED OUT      	W				O				OTHER                   				P			NO WARNING INDICATION     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN AND LOCKED LIGHT BULBS (2OFF) BLOWN.						1	L	7	2 	3O	3	O	 	3A25    	E8CE	5	C	P22EA	 
2002020600006	20020206	00006	EA  	2002	2	6	AUS20011388      	2	20011227	G	7321	312275805	FUEL CONTROL    			AGUSTA	A109  	A119        	0261102	EU  	PWA   	PT6   	PT6B36      	52043	EA  					ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CONTROL UNIT CONTAMINATED WITH BRONZE PARTICLES.						1	G	7	2 	3U	4	U	 	H7EU    	E4EA				 
2002020600008	20020206	00008	WP  	2002	2	6	AUS20011390      	1	20011211	G	7921	111F4178D0440	HOSE            	GARRTT      	TPE3316252M 	FLTCHR	24    	FU24AIRPTS  	3530202	WP  	GARRTT	TPE331	TPE3316252M 	01514	NE  					ENG OIL COOLER	DETERIORATED    	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE OIL COOLER FAILED FROM OVER-PRESSURISATION. INVESTIGATION FOUND PARTICLES OF RUBBER IN THE OIL COOLER BLOCK	ING THE RETURN OIL FLOW TO THE OIL TANK. THE RUBBER PARTICLES APPEAR TO HAVE COME FROM INTERNAL FAILURE OF OIL HOSE PNO 	111F417-8D0440. THE BLOCKAGE OF THE OIL COOLER CAUSED AN OVER-PRESSURISATION OF APPROXIMATELY 300 PSI.				1	L	7	1 	3O			 	4A12    	E2WE				 
2002020600009	20020206	00009	WP  	2002	2	6	AUS20011393      	2	20011227	G	8530	802	EXHAUST VALVE   			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					NR 2 CYLINDER	FAULTY          	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 CYLINDER EXHAUST VALVE FAULTY.						1	Q	7	1 	3I	3	I	 	A8EU    	A8EU				 
2002020500161	20020205	00161	EA  	2002	2	5	AUS20011394      	2	20011217	G	7414	10401678	CAM             	BENDIX      	S6LN1227    	BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MAGNETO/DISTRIBU	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				K069918FR					(AUS) MAGNETO IMPULSE CAM WORN BEYOND LIMITS.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2002020500162	20020205	00162	EU  	2002	2	5	AUS20011395      	1	20011113	G	2742		ACTUATOR        	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		STABILIZER ACTUA	FAILED          	W			    	K	 	 	 	NONE                    				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 	 									(AUS) STABILISER ACTUATOR FAILED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020500163	20020205	00163	EU  	2002	2	5	AUS20011396      	1	20011116	G	2742		ACTUATOR        	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		STABILIZER ACTUA	FAULTY          	W			    	K	 	 	 	NONE                    				F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 	 									(AUS) STABILISER ACTUATOR SUSPECT FAULTY.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020500166	20020205	00166	SW  	2002	2	5	AUS20011399      	1	20010826	G	2510	206031121023	WEB             	BELL        	206L3       	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  	 		            		FLIGHT COMPARTME	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) COPILOTS SEAT WEB CRACKED.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002020600011	20020206	00011	EU  	2002	2	6	AUS20011400      	1	20010804	G	2821		CLAMP           			BNORM 	BN2   	BN2A26      	1520226	EU  										GASCOLATOR	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GASCOLATOR FILTER BOWL UNSECURELY CLAMPED. INVESTIGATION FOUND INADEQUATE DEPTH OF HOLE PREVENTED FULL ENGAGEMENT 	OF ONE LEG OFTHE SADDLE CLAMP.					1	H	7	2 	3O			 	A17EU   					 
2002020600013	20020206	00013	WP  	2002	2	6	AUS20011402      	2	20010616	G	7261	31080261	SCAVENGE PUMP   			SWRNGN	SA227 	SA227*      	       	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  					ENGINE	SEIZED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			2521 							(AUS) RT ENGINE TURBINE SCAVENGE PUMP SHAFT SEIZED AND TEETH STRIPPED FROM SCAVENGE PUMP GEAR PNO 3108028-1 AND DRIVESHA	FT SPUR GEARPNO 3102270-4.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE				 
2002020600014	20020206	00014	CE  	2002	2	6	AUS20011403      	1	20011129	G	7120	121343316	MOUNT           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520*      	17032	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT REAR ENGINE MOUNT SUPPORT BRACKETS CRACKED FROM REAR INBOARD BEND RADIUS. NUMEROUS RIVETS IN SURROUNDING	 STRUCTURE FRETTING.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002020500167	20020205	00167	SW  	2002	2	5	AUS20011404      	1	20011123	G	5521	206023119007	SPAR            	            	            	BELL  	206   	206L3       	1182108	SW  	      		            			 		            		ELEVATOR, SPAR/R	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 		6357 		AO00972					(AUS) ELEVATOR SPAR CRACKED. CRACK LENGTH 82.5MM (3.25IN).						1	G	7	1 	3U			 	H2SW    					 
2002020600015	20020206	00015	EA  	2002	2	6	AUS20011405      	2	20011126	G	7250		BLADE           			DHAV  	DHC6  	DHC6200     	2802620	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LT ENGINE INTERNAL FAILURE. INITIAL REPORTS INDICATE POWER TURBINE BLADE FAILURE.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA	6	C	P15EA	 
2002020600016	20020206	00016	SO  	2002	2	6	AUS20011406      	1	20010721	G	3242	PBA920	PAD             			EMB   	110   	EMB110*     	       	SO  										BRAKE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2564 							(AUS) BRAKE PRESSURE PLATE WORN. BOTH BRAKE PADS ON PRESSURE PLATE MISSING. SUSPECT PAD HAD SEPARATED FROM PLATE CAUSING	 THE OTHER PAD TO SEPARATE AS WELL.					1	L	7	2 	4T			RT	A21SO   					 
2002020500168	20020205	00168	EU  	2002	2	5	AUS20011407      	1	20010723	G	2410		CSD             	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		ALTERNATOR-GENER	DISCONNECTED    	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 									(AUS) NO1 CONSTANT SPEED DRIVE (CSD) DISCONNECTED IN FLIGHT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020500169	20020205	00169	EU  	2002	2	5	AUS20011408      	1	20010727	G	2163		LINE            	            	            	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  	 		            		CABIN TEMPERATUR	LEAKING         	W			    	K	 	 	 	NONE                    				O	J	 	OTHER                     	WARNING INDICATION        		CR	CRUISE         	1			AU	S 	 									(AUS) TURBINE BYPASS VALVE DOWNSTREAM SENSE LINE LEAKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020500170	20020205	00170	EA  	2002	2	5	AUS20011411      	2	20011215	G	8520	13F17751	CRANKSHAFT      	LYC         	LTIO540J2BD 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RECIPROCATING EN	SHEARED         	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 	 				L209668A					(AUS) ENGINE CRANKSHAFT SHEARED AT NO6 BEARING JOURNAL. INTERNAL DAMAGE TO ENGINE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002020500171	20020205	00171	CE  	2002	2	5	AUS20011412      	1	20011224	G	7160	265895716	LEVER           	PWA         	PT6A114A    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE AIR INTAK	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE INERTIAL SEPARATOR SELECTION LEVER CRACKED AT MID POINT.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002020600018	20020206	00018	EU  	2002	2	6	AUS20011415      	1	20010811	G	3620		INDICATOR       			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PNEUMATIC SYS	STUCK           	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) NR 1 HIGH PRESSURE VALVE SWITCH INDICATOR STICKING.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020600032	20020206	00032	WP  	2002	2	6	AUS20011439      	2	20011224	G	7261	31032173	HOUSING         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENG OIL PUMP	CRACKED         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) ENGINE OIL PUMP HOUSING CRACKED.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2002020600033	20020206	00033	SO  	2002	2	6	AUS20011440      	2	20011224	G	8530		CYLINDER        			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	2AF34C	2AF34C55    	GL  	ENGINE	CRACKED         	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 			636  							(AUS) RT ENGINE NR 2 AND NR 4 CYLINDERS CRACKED IN AREA OF HEAD / BARRELJOINT.						1	L	7	2 	3O	3	O	 	3A16    	E5CE	5	C	P5EA	 
2002020500178	20020205	00178	SO  	2002	2	5	AUS20011441      	2	20011224	G	8530		CONNECTING ROD  	CONT        	GTSIO520M   	CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RECIPROCATING EN	FAILED          	W			    	K	 	 	 	NONE                    				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 	 		127  							(AUS) NO5 CONNECTING ROD FAILED. NO1, NO2 AND NO4 MAIN BEARINGS OVERHEATED. SIGNS OF OVERHEATING ON ALL BIGEND BEARINGS.	INVESTIGATION INDICATES INCORRECT MACHINING OF CRANKCASE OILPASSAGES IN MAIN BEARING SUPPORT.					1	L	7	2 	3O	3	O	 	A25CE   	E7CE	5	C	P45GL	 
2002020600051	20020206	00051	NM  	2002	2	6	AUS20011445      	1	20010326	G	2432	18850	BATTERY         			BOEING	767   	767300      	1385204	NM  	RROYCE	RB211 	RB211524*   	 	NE  					MAIN	OVERHEATED      	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN BATTERY OVERHEATED. INVESTIGATION COULD FIND NO CAUSE FOR THE DEFECT AND THE BATTERY HAS OPERATED OK SINCE. T	HE BATTERY CHARGER WAS ALSO REMOVED FOR TESTING WITH NO FAULT FOUND.					2	L	7	2 	4F	4	F	RT	A1NM    	E12EU				 
2002020500180	20020205	00180	EA  	2002	2	5	AUS20011446      	1	20011208	G	3213		BLOCK           	            	            	DHAV  	DHC6  	DHC6300     	2802606	EA  	      		            			 		            		MAIN LANDING GEA	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			AU	S 	 									(AUS) RH MAIN LANDING GEAR COMPRESSION BLOCKS FAILED. DAMAGE CAUSED TOTHE FUSELAGE LOCATED INBOARD OF THE RH MLG.						1	H	7	2 	3T			RT	A9EA    					 
2002020600053	20020206	00053	EU  	2002	2	6	AUS20011451      	2	20010611	G	7250		BLADE           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					TURBINE SECTION	DAMAGED         	W				C				ABORTED TAKEOFF         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) NR 1 ENGINE HP TURBINE BLADES (6OFF) DAMAGED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU				 
2002020600056	20020206	00056	EA  	2002	2	6	AUS20011452      	2	20011212	G	8530	LW13820	CONNECTING ROD  								LYC   	O360  	O360A4M     	41514	EA  					NR 2 CYLINDER	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			120  							(AUS) FOLLOWING BULK STRIP DUE TO FAILURE OF THE NR 2 CYLINDER CONNECTING ROD IT WAS FOUND THAT THE OIL GALLERY SUPPLYIN	G NR 2 MAIN BEARING WAS NOT DRILLED INTO THE MAIN OIL GALLERY.										3	O			E286				 
2002020600057	20020206	00057	NE  	2002	2	6	AUS20011453      	2	20010112	G	7230	9380M28P05	COMPRESSOR      								GE    	CF6   	CF680C2B6   	30025	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			6513 							(AUS) HPC ROTOR SPOOL 3-9 GAVE CRACK INDICATIONS DURING ULTRASONIC INSPECTION IAW EI GEN-072-1792R05. FURTHER INSPECTION	 AT MANUFACTURER FOLLOWING ENGINE STRIP COULD NOT CONFIRM THE CRACKING.										4	F			E13NE				 
2002020500183	20020205	00183	SW  	2002	2	5	AUS20011454      	1	20011228	G	3222	AN723	BOLT            	SCOTT       	CITABRIATYP 	BBAVIA	7     	7GCAA       	21101N8	SW  	LYC   	O320  	O320A2D     	41508	EA  	AMTR	C8289	C8289       	GL  	NOSE/TAIL LANDIN	FAILED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 	 									(AUS) TAIL WHEEL ATTACHMENT BOLT FAILED. TAIL WHEEL SEPARATED FROM TAIL LEAF SPRING.						1	H	7	1 	3O	3	O	 	A759    	E274	5	N	EXPP5N	 
2002020500184	20020205	00184	SW  	2002	2	5	AUS20011455      	1	20011217	G	6320	2060401223	GEAR            	BELL        	206040002025	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  	 		            		MAIN ROTOR GEARB	DAMAGED         	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			AU	S 	 		707  		BKW841					(AUS) MAIN TRANSMISSION SUN GEAR TEETH (2OFF) CHIPPED WITH SUBSTANTIALSECONDARY DAMAGE. METAL CONTAMINATION OF TRANSMISS	ION. SUSPECTPNO 206-040-122-3 GEAR IS NOT TO BE USED IN A PNO 206-040-002-025 MODEL TRANSMISSION AS PER TB 206-75-12.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002020500185	20020205	00185	SO  	2002	2	5	AUS20011456      	1	20011219	G	5753		RIB             	            	            	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	TRAILING EDGE FL	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH FLAP NOSE RIBS SEVERELY CORRODED. SUSPECT CAUSED BY DISSIMILAR METAL CONTACT BETWEEN RIBS AND HINGE BRAC	KETS. CORROSION WAS ALSO FOUND ON THE LOWER RUDDER RIB WHERE IT CONTACTED THE CONTROL HORN (DISSIMILAR METALS CORROSION)	. THE LOWER SECTION OF THE FIN AND ON THE TOP FUSELAGE SKIN UNDER THE FIN ALSO CONTAINS CORROSION. THE CORROSION ON THE 	FUSELAGE SKIN AND IN THE FIN WAS CAUSED PRIMARILY BY THE ACCUMULATION OF DEBRIS IN THE LOWER HALF OF THE FIN (MUD, WASPS	 NESTS) THAT ALLOWEDPROLONGED MOISTURE CONTACT IN THIS AREA. THE AIRCRAFT IS LOCATEDIN A CORROSIVE SEACOAST ENVIRONMENT.		1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002020500186	20020205	00186	SO  	2002	2	5	AUS20011457      	1	20011219	G	5711		SPAR            	            	            	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	WING SPAR	CORRODED        	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) LH AND RH WING REAR SPAR ATTACHMENT POINTS CORRODED AS DESCRIBEDIN AD/PA28/40. INSPECTION WAS CARRIED OUT IAW AD/P	A28/40 WHICHWAS NOT DUE FOR ANOTHER TWO YEARS.					1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2002020600058	20020206	00058	SW  	2002	2	6	AUS20011458      	1	20011220	G	2560	BL7505	CABLE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					RESCUE HOIST	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			HO	HOVERING       	1			AU	S 										(AUS) RESCUE HOIST CABLE BROKE IN AN AREA APPROXIMATELY 100MM (4IN) ABOVE RESCUE HOOK ATTACHMENT POINT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002020500187	20020205	00187	SO  	2002	2	5	AUS20011459      	2	20011212	G	8530		EXHAUST VALVE   	CONT        	TSIO520VB   	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	RECIPROCATING EN	LEAKING         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 									(AUS) ENGINE EXHAUST VALVE LEAKING DURING COMPRESSION TEST.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2002020500188	20020205	00188	NE  	2002	2	5	AUS20011460      	3	20011202	G	6110	2D30	PROPELLER       	HAMSTD      	2D30        	SCWZER	G164  	G164A       	3952704	EA  	PWA   	R985  	R985AN1     	52008	NE  	HAMSTD	2D	2D30        	NE  	PROPELLER ASSEMB	FAULTY          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			AU	S 	 				119789					(AUS) THE FOLLOWING DEFECTS WERE FOUND ON THE PROPELLER WHEN RECEIVED FOR OVERHAUL:-1. ZERO BEARING TENSION ON BOTH BLAD	ES2. REAR BARREL HALF HAS BEEN DRILLED, TAPPED AND GREASE NIPPLES  FITTED. NO CERTIFICATION COULD BE FOUND TO SUBSTANTIA	TE THIS MODIFICATION WHICH HAD BEEN CARRIED OUT WHEN THE PROPELLER WASDISMANTLED AS THE BARREL HALF HAD BEEN REPLATED AF	TER THE MODIFICATION HAD BEEN CARRIED OUT  3. NON-MATCHING PART NUMBER BLADES FITTED 4. EXCESSIVE WEAR IN CYLINDER COUNT	ERWEIGHTBUSH BORESPERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION.		1	Q	7	1 	3R	3	R	 	1A16    	5E1	5	C	P206	 
2002020600059	20020206	00059		2002	2	6	AUS20011463      	4	20011228	G	2210	0119244TF	CONTROLLER      			BNORM 	BN2   	BN2B20      	1520302	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	AUTOPILOT SYSTEM	FAULTY          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AUTOPILOT CONTROL PROGRAMMER FAULTY.						1	H	7	2 	3O	3	O	 	A17EU   	1E4	5	C	P920	 
2001080200272	20010802	00272		2001	8	2	B3OR20010003     	4	20010130	G	2215	10150004717	SERVO           			BEECH 	200   	C12C        	       	CE  										ELEVATOR	BINDING         	B			B3OR	A				UNSCHED LANDING         				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CR	CRUISE         	1			SW	03	1553					BC30				DURING A FLIGHT, THE PILOT EXPERIENCED SLUGGISH ELEVATOR CONTROL WHEEL MOVEMENT. ELEVATOR CONTROL WOULD MOVE FREELY IN N	OSE UP DIRECTION BUT THE MOVEMENT IN THE NOSE DOWN DIRECTION WOULD SOMETIMES BE HARD TO MOVE AND THEN EASY TO MOVE. THIS	 CAUSED SEVERE PITCH OSCILLATION. PILOT FOUND THAT IF HE MOVED THE CONTROL SLOWLY, ALL WAS OK. AIRCRAFT LANDED WITHOUT I	NCIDENT. INVESTIGATION FOUND THE ELEVATOR AUTOPILOT SERVO INTERMITENTLY LOCKING UP IN THE THE NOSE DOWN DIRECTION CAUSIN	G THE PILOT TO HAVE TO FIGHT THE SERVO CLUTCH. REPLACED SERVO MOTOR. ALTHOUGH THIS IS A MILITARY AIRCRAFT, THE SAME SERV	O IS INSTALLED IN OTHER RAYTHEON A200 AIRCRAFT.	1	L	7	2 	4T			 	A24CE   					 
2001080200273	20010802	00273	EU  	2001	8	2	B3OR20010004     	1	20010621	G	7722	0301037070	THERMOCOUPLE    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	OUT OF TOLERANCE	B			B3OR	E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			SW	03	5204X	802  	20   			3099	9570			AIRCRAFT HAD SUFFERED A SERIES OF HUNG STARTS, ENGINE WOULD HANG UP AT 30%. IF THE ENGINE WOULD START, IT WOULD BE A SLO	W START. USUALLY, THE PILOT WOULD REACH THE STARTER TIME LIMIT OF 45 SEC'S BEFORE THE ENGINE WOULD START AND BE SELF-SUS	TAINING,AND HE WOULD HAVE TO ABORT THE START SEQUENCE. TROUBLE SHOOTING FOUND THE INJECTORS WERE "DRIBBLEING" FUEL INSTE	AD OF A SMOOTH,EVEN,FAN PATTERN. CHANGED THE OVERSPEED AND DRAIN VALVE. AFTER HAVING THE SAME RESULTS: SLOW/HUNG STARTS,	 CALLED A TURBOMECCA TECH REP.HE SUGGESTED THAT WE CHECK THE T4 HARNESS.HARNESS WAS OHMED OUT, ONE PROBE SHOWED AN OPEN 	PROBE. REPLACED T4 HARNESS, GROUND RUN AIRCRAFT HAD 3 SUCCESSFUL STARTS. OPS CHECK WAS NORMAL. THE SLOW START HUNG START	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001080200274	20010802	00274	CE  	2001	8	2	B3OR20010005     	1	20010629	G	3260	S13771	SWITCH          			CESSNA	210   	T210N       	2073456	CE  										MLG	IMPROPER PART   	B			B3OR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	6621A					21063559				DURING INSTALLATION OF MAIN LANDING GEAR ACTUATORS AFTER COMPLIANCE WITH SEB01-2, A MAIN LANDING GEAR DOWN INDICATION SW	ITCH WAS FOUND DAMAGED. THE SWITCH, P/N S1377-1 FROM THE ILLUSTRATED PARTS MANUL, WAS ORDERED FROM CESSNA. WHAT WAS RECE	IVED HAD THE CORRECT P/N ON THE PACKAGING BUT THE P/N ON THE PART WAS P6-340005. CESSNA WAS CONTACTED AND WE WERE INFORM	ED THAT THIS IS THE REPLACEMENT PART. AN ATTEMPT WAS MADE TO PUT THE PART IN THE AIRCRAFT TO NO AVAIL. THE SHAPE OF THE 	OLD SWITCH HOUSING IS BASICALLY RECTANGULAR WITH A SHAVED OFF CORNER. THE NEW SWITCH HAD NO SHAVED OFF CORNER. THE NEW S	WITCH WOULD CONTACT A FORK ASSEMBLY IN THE GEAR. CESSNA WAS NOTIFIED AND THEY RECALLED THE SWITCHES. AS OF 7-11-2001, CE	1	H	7	1 	3O			 	3A21    					 
2001080200275	20010802	00275	EU  	2001	8	2	B3OR20010006     	1	20010709	G	6730	AC67032	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										HYD SYSTEM	LEAKING         	B			B3OR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5204X	808  				3099				DURING A PREFLIGHT INSPECTION, HYDRAULIC FLUID WAS FOUND UNDER THE FORWARD PORTION IF THE TAIL BOOM. INVESTIGATION FOUND	 TAIL ROTOR SERVO LEAKING. AREA WAS CLEANED AND HYDRAULIC POWER UNIT WAS RUN ON AIRCRAFT TO LOCATE LEAK. SERVO WAS LEAKI	NG FROM THE SHAFT TWICE THE ALLOWABLE LEAK RATE AND THE SERVO WAS ALSO LEAKING FROM A NON SERVICABLE PLUG ON THE HOUSING	. UNIT WAS REPLACED WITH SERVICABLE UNIT.			1	G	7	1 	3U			 	H9EU    					 
2001101500109	20011015	00109	CE  	2001	10	15	B3OR20010009     	1	20011006	G	2730	MS27645A4	BEARING         			CESSNA	500   	550         	2076604	CE  										ELEVATOR	CORRODED        	B			B3OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2649	5513 	150  			5500607				THE ELEVATOR WAS REMOVED TO FACILLITATE OTHER MAINTENANCE. UPON REMOVAL OF THE RIGHT HAND ELEVATOR, THE INBOARD ELEVATOR	 BEARING, INNER RACE CAME OFF WITH THE INBOARD MOUNT BOLT. DURING THE REMOVAL OF THE ELEVATOR, THE BALL BEARINGS FELL OU	T OF THE OUTER RACE. UPON FURTHER INVESTIGATION, THE INNER AND OUTER RACE HAD RUST AND RUST POWDER ON THE INNER AND OUTE	R SURFACES OF THE RACES. THE INNER RACE WAS NOT "SEIZED" TO THE MOUNT BOLT. SOME OF THE BALL BEARINGS WERE MISSING, WHIL	E SOME SHOWED SIGNS OF CORROSION AND METAL TO METAL CONTACT, SOME WERE NOT FOUND AT ALL. THE BARING, P/N MS27645-A4, WAS	 REPLACED WITH A NEW BEARING AND STAKED IN ACCORDANCE WITH CESSNA MAINTENANCE INSTRUCTIONS.	1	L	7	2 	4F			 	A22CE   					 
2001080900256	20010809	00256	GL  	2001	8	9	BB1              	3	20010720	G	6110	RB2000	BLADE           			AMTR  	PULSAR	SUPERPULSAR 	       	GL  	CONT  	O240  	IO240B      	17063	SO  	AMTRRX	BK	BK063       	GL  	PROPELLER	SEPARATED       	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			WP	23						601	806949			EXPERIMENTAL AMATEUR BUILT AIRCRAFT, INITIAL FLIGHT WITH NEW NON-CERTIFICATED VARIABLE PITCH PROPELLER MANUFACTURED BY A	EROTEK AUCKLAND, NEW ZEALAND.  BOTH COMPOSITE BLADES SEPARATED SIMULTANEOUSLY ON TAKE OFF AT 500 FT. AGL.  INSPECTION RE	VEALED THAT THE BLADE FAILURE OCCURRED AT THE BOND BETWEEN THE BLADES AND THE RETAINING PLUG, TEARING THROUGH THE DOWEL 	PIN HOLES.  SUSPECT A DESIGN AND/OR MANUFACTURING DEFECT.			1	L	7	1 	3O	3	O	NT	EXPA1L71	E7SO	5	N	EXPP5N	 
2001050200061	20010502	00061	CE  	2001	5	2	BF8R0320         	1	20010320	G	3245	0923150	VALVE           			BEECH 	76    	76          	1153005	CE  										TUBE VALVE	SCORED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	6627U					ME214				DEFECTIVE VALVE CORE MATING SEAL.						1	L	7	2 	3O			 	A29CE   					 
2001080200286	20010802	00286	SO  	2001	8	2	BIER0056         	1	20010510	G	7100	LW12892	THRUST PLATE    			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540*       	41532	EA  					ROCKER ARM SHAFT	BROKEN          	B			BIEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	43595	1435 	400  			288411018	L2107240A			AT 400 HR VALVE INSPECTION FOUND ROCKER ARM SHAFT THRUST BUTTONS BRITTLE AND CRACKED.  SUBMITTER RECOMMENDATION: STRESS 	THE IMPORTANCE OF THE 400 HR VALVE INSPECTION.					1	L	7	1 	3O	3	O	 	2A13    	E295				 
2001080200295	20010802	00295	EA  	2001	8	2	BIER200103057    	2	20010703	G	7322	105217	CARBURETOR      			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					ENGINE	LOOSE           	B			BIER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	331AC	400  	90   			82021C	L1803039A			FOUND FUEL BOWL ATTACH SCREWS LOOSE WITH SUBSEQUENT FUEL LEAK AT BOWL GASKET, REQUIRED CARBURETOR REPLACEMENT DUE TO SCR	EW HOLE ELONGATION. SUBMITTER NOTES: LYCOMING SB 366, DATED SEPT 14, 1973 REFERENCES THIS FOR MARVEL-SCHEBLER CARBURETOR	S, WITH NO MENTION OF FACETS. SUBMITTER RECOMMENDS ANNUAL/250 HR SCREW TORQUE CHECK AS A MINIMUM INSPECTION INTERVAL.				1	L	7	1 	3O	3	O	NT	A57EU   	E274				 
2001032000183	20010320	00183	SO  	2001	3	20	BJ3RE000007      	2	20010226	G	8530	SA643873	EXHAUST VALVE   	CONT        		CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  					ENGINE	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	69604	46   	46   			310Q0812	14953672V			DURING AN IRAN INSPECTION, IT WAS NOTICED THAT THE AMOUNT OF VALVE SHOWING ABOVE THE KEEPER WAS LESS ON ONE CYINDER THAN	 ON THE OTHERS.  UPON DISASSEMBLY IT WAS FOUND THAT #3 CYLINDER EXHAUST VALVE WAS 1/16TH INCH SHORTER THAN THE OTHER VAL	VES. A SLIGHT MUSHROOMING LIP WAS ABLE TO BE FELT AROUND THE TOP OF THE VALVE. IT APPEARS THAT THIS IS THE SAME TYPE OF 	WEAR AS INDICATED IN CSB98-1B ON CONTINENTAL VALVES.			1	L	7	2 	3O	3	O	 	3A10    	3E1				 
2001030500093	20010305	00093	NM  	2001	3	5	CA010105006      	1	20010103	G	2761	65448517	HOUSING         	BOEING      	65448517    	BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					SPOILER ACTUATOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						3251					(CAN) DURING INSPECTION, 17C CHECK OF NR 4 GROUND SPOILER, SPOILER FOUND TO BE LOOSE. FOUND NR 4 SPOILER ACTUATOR, BODY 	END THAT ENCLOSED THE BEARING, BROKEN AWAY. ACTUATOR REPLACED AS PER WORK CARD 51160.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001011100074	20010111	00074	EU  	2001	1	11	CA010105010      	1	20010103	G	2621		FIRE BOTTLE     			AIRBUS	310   	A310304     	       	EU  	GE    	CF6   	CF680C2*    	 	GL  					ENGINE	DISCHARGED      	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) A/C 212, DEC 17/2000, FLT 92577, YQM, LOG SEQUENCE 0292319. DURING CLIMB, MAIN DECK (FWD AND MID) SMOKE WARNING OC	CURRED. SMELL AND SMOKE AND MIST WAS DETECTED IN COCKPIT. FIRE BOTTLES WERE DISCHARGED AND AIRCRAFT RETURNED TO YMQ. AFT	ER CREW DEBRIEF, MIST AND ODOR WAS ATTRIBUTED TO INGESTION OF GLYCOL INTO PNEUMATIC SYSTEM DURING DEICE IN YMQ. FIRE BOT	TLES WERE REPLACED AS PER WORK CARDS 26-210-005, AND 26-130-103. AIRCRAFT SERVICEABLE.			2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2001030500107	20010305	00107		2001	3	5	CA010110005      	4	20010110	G	2562	400010	ELT             			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					CABIN	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION, THIS ELT FAILED BECAUSE OF BORDERLINE OUTPUT POWER AND NO G SWITCH. THE ELT WAS RETURNED	 TO THE MANUFACTURER FOR REPAIR.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001030600028	20010306	00028	EU  	2001	3	6	CA010111019      	1	20010103	G	3060	3E32602	HARNESS         	BFGOODRICH  		PILATS	PC12  	PC1245      	       	EU  						HARTZL	HCE4A	HCE4A3D     	GL  	ANTI-ICE SYSTEM	FAULTY          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA			1351 								(CAN) ONE PROPELLER FOUND NOT TO BE HEATING WHILE PERFORMING SCHEDULED PROPELLER DEICER TEST. TROUBLESHOOTING LEAD US TO	 FIND AN OPEN WIRE IN THE HARNESS. PART ORDERED.					1	L	7	1 	3T			RT	A78EU   		5	C	P210NE	 
2001030600046	20010306	00046	EA  	2001	3	6	CA010116027      	1	20010103	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA						95144H8592					(CAN) IN CRUISE, THE F/OS FRONT WINDSHIELD SHATTERED AT 31,000 FEET.THE MAINTENANCE REPLACED THE WINDSHIELD AND RETURNED	 THE AIRCRAFT TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001030600047	20010306	00047	EA  	2001	3	6	CA010116028      	1	20010101	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			AP	APPROACH       	1			CA						00231H5852					(CAN) ON APPROACH TO YUL, THE F/OS FRONT WINDSHIELD SHATTERED AT 6,000 FEET.THE MAINTENANCE REPLACED THE WINDSHIELD AND 	RETURNED THE AIRCRAFT TO SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001033000066	20010330	00066	NM  	2001	3	30	CA010129018      	1	20010104	G	2750	65162266	SWITCH          			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					KRUGER FLAP	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER DEPARTER&UPON FLAP RETRACTION, NR 5 LEADING EDGE FLAP IN TRANSIT LIGHT ILLUMINATED. FUEL DUMPED & A/C RETURN	ED TO AIRPORT OF DEPTR: MAINT CHANGED OUT FLAP SWITCH, P/N 40174 & SYS TESTED & FUNCTIONED NORMALLY. A/C DEPARTED & SAME	 FAULT RECURRED. MAINT REPL NR 5 LEADING EDGE FLAP ACTUATOR, P/N 65-17818-20 & LEADING EDGE POS CNTL MODEL, P/N 65-60212	-11, AS PRECAUTIONARY MEASURE: SYS AGAIN TESTED AS PER THE MM& OPALLY CHECKED SEVERAL TIMES W/O FAULT. A/C RT-SRV. DISCR	EPANCY RETURNED ON NEXT DEPTR: A/C RETURNED AGAIN FOR MAINT TROUBLESHOOTING. FINAL RPT: L/E FLAP POS SWITCHES SWAPP ED B	ETWEEN 5 & 3 FLAP. WIRING FROM COCKPIT T	2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001033000067	20010330	00067		2001	3	30	CA010130007      	4	20010120	G	2200	065006415	COMPUTER        	BENDIX      	220         	PILATS	PC12  	PC1245      	       	EU  										AUTOPILOT	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA						1964					(CAN) IN THE CLIMB, SHORTLY AFTER ENGAGING AUTOPILOT, AUTOPILOT DISENGAGED FOR NO APPARENT REASON. AFTER A SUCCESSFUL RE	TEST, REENGAGING IS POSSIBLE WITH NO FURTHER PROBLEMS. THIS PROBLEM HAS OCCURRED IN THE RECENT PAST.THE AUTOFLIGHT COMPU	TER WAS REPLACED FOR TROUBLESHOOTING AND ITS PERFORMANCE WILL BE MONITORED.				1	L	7	1 	3T			RT	A78EU   					 
2001033000068	20010330	00068	EU  	2001	3	30	CA010130009      	1	20010103	G	5510	9412259360	BUSHING         	PILATS      	5551012036  	PILATS	PC12  	PC1245      	       	EU  										HORIZONTAL STAB	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1351 	1351 		272					(CAN) HORIZONTAL STABILIZER HAS MOVEMENT OF .003 AT ATTACHMENT POINTS, WHEN TIP OF STAB IS MOVED IN A UP AND DOWN MOTION	. THIS AIRCRAFT HAS BEEN LIKE THIS SINCE NEW. AS PER PILATUS, 0 TOLERANCE ALLOWED AT ATTACHMENT POINT. BUSHINGS WERE REP	LACED WITH NO IMPROVEMENT. BOLTS PLACED ON ORDER TO TRY TO ILLIMINATE THE PLAY.				1	L	7	1 	3T			RT	A78EU   					 
2001033000069	20010330	00069	EA  	2001	3	30	CA010130011      	2	20010105	G	7200		ENGINE          			DHAV  	DHC6  	DHC6        	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RIGHT	FAILED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) RT ENGINE SHUT DOWN DUE TO LOW OIL PRESSURE. AFTER REACHING CRUISING ALTERNATE RT ENGINE LOW OIL PRESSURE CAPTION 	APPEARED. LOW OIL PRESSURE GAUGE INDICATION OBSERVED. PRECAUTIONARY ENGINE SHUT DOWN. DIVERTED BACK TO AIRFIELD.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001033000070	20010330	00070	NM  	2001	3	30	CA010130012      	1	20010101	G	3040	07802	WINDSHIELD      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			10554								(CAN) LEFT WINDSHIELD SHATTERED INFLIGHT. AIRCRAFT LANDED. WINDSHIELD REPLACED IN  ACCORDANCE WITH DHC8 MM 56-10-11. RAN	 AIRCRAFT OPERATIONS CHECKED, OK. AIRCRAFT RETURNED TO SERVICE. NOTE PCA A0101001					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001033000071	20010330	00071	GL  	2001	3	30	CA010131009      	1	20010101	G	7160	653885	FLANGE          			DIAMON	DA20  	DA20C1      	2990001	GL  	CONT  	O240  	IO240B      	17063	SO  	SNSNCH	W69EK	W69EK63     	EA  	INTAKE PIPE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			569  								(CAN) FLANGE CRACKED.						1	L	7	1 	3O	3	O	NT	TA4CH   	E7SO	5	N	TA4CH	 
2001033000072	20010330	00072	EA  	2001	3	30	CA010131015      	1	20010105	G	5753	F35	SEALANT         	DHAV        		DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	UNDER NR 4 FLAP	PEELING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10482								(CAN)  THE SEALANT USED UNDER THE NR 4 FLAP TRACK AS PER AD CF-87-04, SB 7-57-30 WAS FOUND PEELING OFF. 10481.68 HOURS H	AVE ACCUMULATED ON THIS AIRCRAFT AFTER INITIAL APPLICATION BACK IN OCTOBER OF 1987. THIS AIRCRAFT HAS BEEN OPERATING IN 	ASIA.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001033000073	20010330	00073	SO  	2001	3	30	CA010131016      	1	20010105	G	8120	46C1983985	TURBOCHARGER    			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA				159  							(CAN) PILOT REPORTED LOSS IN MANIFOLD PRESSURE FOUND TURBOCHARGER TURBINE MISSING A BLADE AND TURBO SEIZED.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA				 
2001033000074	20010330	00074		2001	3	30	CA010131017      	4	20010104	G	2562	0004006A	BATTERY         	LEIGH       	SHARC7H2184 															ELT	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						132428					(CAN) ELT WAS SUBMITTED FOR ANNUAL RECERT. UNAPPROVED BATTERY WAS CERTIFIED WITH ELT NOV.1/2000 - ELT AS SUCH IS NOT TC 	APPROVED. AND INSTALLED HORIZONTALLY IN AIRCRAFT (CESSNA, AS PER CUSTOMER), AND THE G SWITCH IS INSTALLED FOR A VERTICAL	 MOUNT INSIDE THE UNIT. ELT RETURNED AS IS, CUSTOMER ADVISED TO FIND ALTERNATE REPLACEMENT.																	 
2001033000075	20010330	00075	CE  	2001	3	30	CA010131018      	1	20010110	G	5511	12326194	RIB             	CESSNA      	183260029   	CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 50 HOUR INSPECTION OF THE HORIZONTAL STAB, THE 4 RIBS WERE FOUND TO BE LOOSE & CRACKED. THIS IS DONE BY S	QUEEZING THE NOSE RIBS (WITH A MODERATE AMOUNT OF PRESSURE) AND LISTEN FOR CLICKING SOUNDS & FEELING OF LOOSE RIVETS. TH	EREFORE, THE LOWER SKIN WAS PEELED BACK THE 4 RIBS WERE REMOVED AND REPLACED WITH NEW RIBS. THE SKIN WAS RIVETED BACK ON	. STAB WAS INSTALLED AND AIRCRAFT WAS RETUNED TO SERVICE. 7 B&C S.D. FOUND DUING 50 HOUR INSPECTION. NO ACTION REQUIED B	Y FLIGHT CREW.		1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2001033000085	20010330	00085	EA  	2001	3	30	CA010202005      	1	20010107	G	3244	256K433	TIRE            		60085123    	CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF341A      	 	NE  					MLG	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TO	TAKEOFF        	1			CA			249  								(CAN) ON TAKEOFF CREW HEARD MUFFLED BANG. NO AIRCRAFT CONTROL PROBLEMS NOTED. CONTINUED TO DESTINATION LANDED WITHOUT IN	CIDENT. DURIG POST FLIGHT FOUND THE NR 3 TIRE HAD LOST ALL TREAD. THE TIRE WAS STILL INFLATED. DAMAGE TO RIGHT INBOARD F	LAPS LOWER SURFACE AND THE RIGHT MAIN LANDING GEAR INBOARD WEIGHT ON WHEEL ANTI-SKID HARNESS.				2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001033000087	20010330	00087	EA  	2001	3	30	CA010202008      	1	20010103	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED THAT THE CAPTS FRONT WINDSHIELD SHATTERED IN CRUISE. THE LANDING WAS UNEVENTFUL.THE MAINTENANCE 	REPLACED THE WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000088	20010330	00088	EA  	2001	3	30	CA010202011      	1	20010103	G	2752		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					RT FLAP	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED THE FLAP FAIL CAUTION MESSAGE WHICH APPEARED ON APPROACH (SELECTIION OF 45 DEGREES, STOPPED AT 3	7). THE MAINTENANCE REPLACED THE RT OUTBOARD FLAP INBOARD ACTUATOR					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000089	20010330	00089	EA  	2001	3	30	CA010202013      	1	20010106	G	2612	47259701	FIRE DETECTOR   			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 1 ENGINE	FAILED          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			DE	DESCENT        	1			CA											(CAN) DURING DESCENT INTO MEMPHIS, THE CREW ON AIRCRAFT 7416 SHUT DOWN ENGINE NR 1 PER THE EMERGENCY PROCEDURES DUE TO T	HE POSTING OF AN INTERMITTENT LT ENGINE FIRE MESSAGE ON THE EICAS. DURING TROUBLESHOOTING THE MECHANICS FOUND THE FIRE D	ETECTION UNIT UNDER THE LT CONSOLE SHORTED AND CONTAMINATED (COFFEE) WITH LIQUID. A NEW CONTROLLER AND BOTTLE WAS INSTAL	LED AND THE SYSTEM SUCCESSFULLY TESTED PER THE AMM.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000090	20010330	00090	NE  	2001	3	30	CA010202022      	2	20010107	G	7210		GEARBOX         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	FAILED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) NR 2 ENGINE VIBRATION FLUCTUATION INDICATED .4 TO .7 MILS APPROXIMITELY 3 TO 5 MIN. LATER, NR 2 ENGINE SHUT DOWN U	NCOMMANDED. PERFORMED QRH PROCEDURE & DIVERTED INTO NEXT AIRPORT (ISO), THE FLIGHT CREW DECLARED EMERGENCY (UNEVENTFUL).	FOUND METAL IN CHIP DETECTOR (SUSPECT GEARBOX - INTERNAL) NOT CONFIRMED. REPLACEMENT OF ENGINE S/N 807528 IN PROGRESS.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000091	20010330	00091	EA  	2001	3	30	CA010205006      	1	20010111	G	3040	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1566 								(CAN) THE CREW REPORTED THAT THE LT WINDSHIELD CORE PLY CRACKED DURING FLIGHT.THE MAINTENANCE REPLACED THE WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001033000092	20010330	00092	EA  	2001	3	30	CA010205008      	1	20010101	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) THE CREW REPORTED THAT THE RT WINDSHIELD CARACKED IN FLIGHT. THE MAINTENANCE REPLACED THE RT WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040200252	20010402	00252	SO  	2001	4	2	CA010206004      	2	20010104	G	8530	628309	VALVE GUIDE     			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					EXHAUST VALVE	WORN            	W				E	D	 	 	ENGINE SHUTDOWN         	RETURN TO BLOCK         			R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				1439 							(CAN) ENGINE RAN VERY ROUGH AT START UP.CYLINDER NR 3 REMOVED DUE TO LOW COMPRESSION. EXHAUST GUID WORN CAUSING CARBON T	O JAM VALVE IN OPEN POSITION. CYLINDER RELACED DUE TO ABOVE PROBLEM.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040300124	20010403	00124	EU  	2001	4	3	CA010208013      	1	20010123	G	2431	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					MAIN BATTERY	OVERHEATED      	W				O	 	 	 	OTHER                   				M	B	 	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			407  								(CAN)   ENGINE ROTATION TOO SLOW AT START ATTEMPTS FOR SUCCESSFUL ENGINE LIGHT OFF.  BATTERY VENTED EXCESSIVE AMOUNTS OF	 SMOKE AND VAPOR (STEAM AND ACID GAS) DUE TO SEVERAL SUCCESSIVE FAILED ENGINE START ATTEMPTS WITHOUT ALLOWING SUFFICIENT	 RECHARGING BY AIRCRAFT ELECTRICAL SYSTEM. HOT BATTERIES REMOVED FROM AIRCRAFT. STRUCTURE NEUTRALIZED AND RINSED WITH FR	ESH WATER. - NEW BATTERIES FITTED.			2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001040300125	20010403	00125	NE  	2001	4	3	CA010208014      	1	20010124	G	6220	7610308010103	HUB             			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3985 	3985 							(CAN)  DURING THE POST FLIGHT INSPECTION BY AME A FINE LINE WAS NOTICED ON THE UPPER DAMPER ATTACH LUG. THE LUG WAS PAIN	T STRIPPED AND A DEFINITE CRACK CAN BE SEEN. STARTING NEAR THE BOLT HOLE PROGRESSING INBOARD FOR APPROXIMATELY 1 1/4 INC	H. THE MAIN ROTOR HUB WAS REPLACED.				1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001040300126	20010403	00126	SW  	2001	4	3	CA010208016      	1	20010122	G	6220	471202527	GRIP            			BELL  	47    	47J2        	1181104	SW  	LYC   	O435  	TVO435*     	41516	EA  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2261 	31   							(CAN) AIRCRAFT IS BEING IMPORTED INTO CANADA. CRACKS IN ROOT OF THREADS FOUND DURING EDDY CURRENT INSPECTION.						1	G	7	1 	3O	3	O	 	2H1     	1E13				 
2001040300127	20010403	00127	EU  	2001	4	3	CA010209002      	1	20010124	G	2612		FIRE DETECTOR   			FOKKER	F28   	F28MK1000   	4990808	EU  										NR 2 ENGINE	INTERMITTENT    	W				F	A	 	 	ACTIVATE FIRE EXT.      	UNSCHED LANDING         			N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) FLT 8473SHORTLY AFTER DEPARTURE OUT OF KELOWNA (YLW), FLT CREW REPORTED THAT NR 2 ENGINE FIRE WARNING CAME ON. NR 	2 ENGINE SHUTDOWN & BOTH FIRE BOTTLES WERE DISCHARGED. PILOTS REPORTED THAT FIRE WARNING LIGHTS REMAINED ON AFTER THE BO	TTLES WERE DISCHARGED.  A/C ROUTED TO VANCOUVER (YVR) DUE TO WEATHER MINS IN INTERIOR. REMAINDER OF FLT UNEVENTFUL & A/C	 LANDED IN YVR WITH NO FURTHER INCIDENTS TO REPORT. MAINT INSPECTION AFTER LANDING CONFIRMED FAULTY INDICATOR ONLY. CRA 	FLEET RELIABILITY DEPT CREATED WORK PACKAGE FOR INDICATION PROBLEM.		2	L	7	2 	4F			RT	A20EU   					 
2001040300128	20010403	00128	SO  	2001	4	3	CA010209003      	1	20010209	G	6310		ENGINE          			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NACELLE	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA				1231 							(CAN) ENGINE LOSSED MANIFOLD PRESSURE FOLLOWED BY LOSS OF OIL PRESSURE. VISUAL INSPECTION REVEALS CRACKED CASE.						1	L	7	2 	3O	3	O	 	A8EA    	E19EA				 
2001040300129	20010403	00129	WP  	2001	4	3	CA010209004      	1	20010112	G	2435	230321183	BELL ASSY       	LUCAS       	23032018    	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					STARTER GEN	UNAPPOVED PART  	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1177 		2514					(CAN) STARTER GEN RECEIVED FOR OVERHAUL. FOUND THE ADE (COMM END) END BELL ASSEMBLY TO BE 3, WHICH ACCORDING TO THE OEM 	IS AN OLD, OBSOLETED PART THAT WAS APPLICABLE ONLY TO THE 23032-005 STARTER-GENERATOR, WHICH IS ITSELF OBSOLETE, UNSUPPO	RTED AND NOT LISTED IN THE OVERHAUL MANUAL. THE ASSEMBLY IS ALSO CORRODED AND CRACKED AROUND THE MOUNTING HOLES. THE COR	RECT ASSY IS P/N 23032-1423. A CORRECT ASSY WAS INSTALLED DURING OVERHAUL, ALONG WITH THE CORRECT BEARING RETAINER AND F	AN COVER.THE OFFENDING PARTS ARE BEING TRANSMITTED TO THE AIRCRAFT OPERATOR FOR FOLLOW-UP.		1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001040300130	20010403	00130	SW  	2001	4	3	CA010209006      	1	20010129	G	2435	230791281	BRUSHES         	LUCAS       	230790001   	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	STARTER GEN	UNAPPOVED PART  	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			499  			10020					(CAN) DURING SCHEDULED MAINTENANCE, AT BRUSH INSPECTION IT WAS FOUND THAT THE BRUSHES INSTALLED IN THIS STARTER-GENERATO	R WERE. THIS BRUSH IS ONLY APPROVED FOR THE STARTER GEN MODELS 23079-009 AND 23079-000-2.THE BRUSHES WERE REMOVED AND RE	PLACED WITH FAA-PMA LONG LIFE BRUSH PART NO.M23088-1320, WHICH IS APPROVED FOR THIS STARTER-GENERATOR MODEL 23079-000-1 	WHEN USED ON THE FAIRCHILD SA227AC AIRCRAFT. THE STARTER GEN WAS RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL	 
2001040300131	20010403	00131	EU  	2001	4	3	CA010209007      	1	20010131	G	3240	9595601511	BRAKE           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT MLG	FROZEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA											(CAN) TAKEOFF IN FT ST. JOHN IN POWDER SNOW MAY HAVE CAUSED MOISTURE TO ENTER LT BRAKE ASSEMBLY. DURING FLIGHT TO FT NEL	SON, BRAKE FROZE. ON LANDING IN FT. NELSON LT TIRE WOULD NOT ROTATE AND TIRE FLAT SPOTTED AND BLEW. AIRCRAFT WAS STOPPED	 ON RUNWAY AND MAINTENANCE WAS CALLED. TIRE AND WHEEL ASSEMBLY WAS REPLACED AND GEAR ASSEMBLY INSPECTED FOR DAMAGE. THIS	 IS THE 3RD SUCH INCIDENT IN THE LAST 12 MONTHS.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001040300132	20010403	00132	NE  	2001	4	3	CA010209009      	2	20010116	G	7230	4036T24P01	BLADE           			LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					ENGINE	SEPARATED       	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			2264 	2264 							(CAN) AIRCRAFT IN CLIMB FL110, LOUD BANG HEARD, RT FIRE WARNING ACTIVATED. POWER REDUCED, FUEL SHUT OFF, FIRE WARNING DE	-ACTIVATED. AIRCRAFT RETURNED TO DEPARTURE AIRPORT AND SINGLE ENGINE LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. GROUN	D INSPECTION REVEALED THAT FINAL STAGE TURBINE HAD LOST ONE BLADE (CONTAINMENT RING DAMAGED BUT NOT PENETRATED) RESULTAN	T IMBALANCE CAUSED SEVERE DAMAGE TO REMAINING BLADES AND SHROUD AND CAUSED EXHAUST TAIL PIPE TO SEPARATE AT MOUNTING FLA	NGE. HOT GASES RELASED INSIDE COWLING CAUSED FIRE WARNING TO ACTIVATE. ENGINE OVERHAUL AGENCY MAY HAVE MORE INFORMATION 	AFTER THEIR ANALYSIS.	2	L	7	2 	4J	4	J	 	A10CE   	1E16				 
2001040300133	20010403	00133	SW  	2001	4	3	CA010209015      	1	20010121	G	5610	412669001100	WINDOW          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COCKPIT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE IN STRAIGHT AND LEVEL FLIGHT A LOUD BANG WAS HEARD. IT WAS DISCOVERED THAT THE RT REAR SLIDING DOOR WINDOW H	AD SHATTERED. AN UNEVENTFUL LANDING WAS CARRIED OUT. ALLL PIECES WERE RECOVERED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001040300134	20010403	00134	EU  	2001	4	3	CA010209017      	1	20010131	G	3310	MS24149A1	RELAY           			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					LIGHTING	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER TAXI IN AT YVR THE NR 2 AC INVERTER FAIL LIGHT ILLUMINATED AS WELL AS XS2 BUSS FAIL LIGHT ILLUMINATED. RESET	 THE NR 2 INVERTER SWITCH FAILED TO RESET THE SYSTEM. MAINTENANCE TROUBLESHOOT THE PROBLEM BACK TO A FAULTY RELAY WITHIN	 THE CABIN LIGHTING SYSTEM. FURTHER INVESTIGATION FOUND THE LIGHTING RELAY CHATTERING, CAUSED A FLUCTUATING VOLTAGE ON T	HE XS2 BUSS RESULTING IN THE NR 2 INVERTER TRIPPING OFF LINE. AFTER TRACING THE HISTORY OF THIS PROBLEM IT WAS FOUND THA	T IN MORE THAN ONE OCCASIION THE CABIN LIGHTING HAS CAUSED A TOTALFAILURE OF THE AIRCRAFTS RIGHT AC BUSS THUS LEAVING CO	NCERNS AS TO HOW A SECONDARY SYSTEM CAN FAIL A PRIMARY SYSTEM ON THE AIRCRAFT.	2	L	7	2 	4F	4	F	 	A3EU    	E6WE				 
2001040300136	20010403	00136	CE  	2001	4	3	CA010212005      	1	20010123	G	5312	24120651	BULKHEAD        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			10545								(CAN) DURING INSPECTION OF AIRCRAFT FOLLOWING A GEAR UP LANDING, THE TWO BULKHEADS RUNNING VERTICALLY IN FRONT OF CABIN 	DOORS WERE FOUND CRACKED AT FLOOR LEVEL. THE CRACK IS LOCATED AT THE CUT OUT FOR THE HEAT DISCHARGE DUCT. THESE CRACKS W	ERE NOT CAUSED BY THE GEAR UP LANDING.				1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001040300137	20010403	00137	CE  	2001	4	3	CA010212006      	1	20010123	G	5312	05120122	BULKHEAD        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			15904								(CAN) DURING ROUTINE CESSNA PROGRESSIVE CARE INSPECTION, THE BULKHEAD AT THE BACK END OF THE BAGGAGE COMPARTMENT STATION	 108 WAS FOUND TO BE CRACKED AT BOTH LOWER CORNERS, AND THE UPPER RIGHT CORNER. THE CRACKS ARE APPROXIMATELY 2 INCHES LO	NG. THIS AIRCRAFT IS USED FOR FLIGHT TRAINING AND ON OCCASION BANNER TOWING.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040300138	20010403	00138	EA  	2001	4	3	CA010212007      	1	20010125	G	2701	C3CF3913	CONTROL COLUMN  			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT AIRWORTHINESS DIRECTIVE CF-82-34 WE FOUND A CRACK IN THE LOWER WELD ASSEMBLY OF THE AILERON CON	TROL COLUMN LOCATED AT THE CUT HOLE FOR THE AILERON CHAIN. THE CRACK WAS APPROXIMATELY 1/4 INCH LONG.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001040300139	20010403	00139	NE  	2001	4	3	CA010212011      	2	20010118	G	7200		ENGINE          			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NR 1	FAILED          	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE TO CPH FROM EMA NR 1 ENGINE OIL QUANTITY SLOWLY DECREASED TO 1 GALLON AT WHICH POINT THE INFLIGHT SHUT DOW	N WAS PERFORMED. THE A/C LANDED WITHOUT INCIDENT AT CPH. THE ENGINE MAINTAINED POSITIVE OIL PRESSUE FOR THE 20-25 MINUTE	 PERIOD OF WINDMILL CONDITION. THE ENGINE WAS REMOVED AND IS ENROUTE FOR ASSESSMENT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001040300078	20010403	00078		2001	4	3	CA010212033      	4	20010123	G	2562	R889V	BATTERY         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ELT	UNAPPOVED PART  	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELT SENT IN FOR RECERTIFICATION. WAS EQUIPPED WITH A NON-APPROVED BATTERY PACK ARTEX . ONLY APPROVED BATTERY IS TE	CHNISONIC. BATTERY REPLACED AND ELT RECERTIFIED.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001040300080	20010403	00080	CE  	2001	4	3	CA010213003      	1	20010118	G	7160		HOSE            			CESSNA	150   	150         	2071802	CE  	CONT  	O200  	O200*       	17020	SO  					CARB HEAT	CONTAMINATED    	W				C	 	 	 	ABORTED TAKEOFF         				R	E	 	PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		TO	TAKEOFF        	1			CA											(CAN) DURING THE WINTER MONTHS WE ARE RECEIVING COMPLAINTS OF A SERIOUS NATURE. UPON TAKEOFF, USUALLY THE FIRST ONE, THE	 AIRCRAFT RUNS VERY ROUGH. I HAVE EXPERIENCED THIS PERSONALLY. WE HAVE DETERMINED THAT SNOW COLLECTS IN THE SCAT HOSE TH	AT PROVIDES AIR FOR CARB HEAT. THIS SNOW MELTS AFTER THE ENGINE HAS WARMED UP AND UPON SELECTION OF CARB HEAT THE ENGINE	 WANTS TO QUIT. WE HAVE REMEDIED THIS ON SEVERAL AIRCRAFT BYMAKING A SMALL HOLE IN THE LOW SPOT OF THE SUBJECT SCAT HOSE	, USING A SOLDERING IRON.		1	H	7	1 	3O	3	O	NT	3A19    	E252				 
2001040300081	20010403	00081	EA  	2001	4	3	CA010213004      	1	20010119	G	3310	2LFV4090600AA	COAX            			CNDAIR	CL600 	CL600*      	       	EA  										INSTRUMENT PANEL	BURNED          	W				H	A	 	 	DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B		 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED CENTER INSTRUMENT PANEL FLOOD LIGHTING INOPERATIVE WITH BRIGHT/DIM POTENTIOMETER. KNOB SWITCHED OFF	 AND LIGHTING OPERATED WITH BRIGHT/DIM SWITCH. INVESTIGATION AREVEALED THAT CABLE ASSY, CONNECTOR PIN AT INVERTER END WA	S BURNED OFF.CABLE ASSY AND INVERTER/POWER SUPPLY. THE CONNECTOR WAS PROBABLY NOT SEATED CORRECTLY AT ONE TIME, BUT AT T	IME OF INVESTIGATION THE CONNECTOR WAS PROPERLY INSTALLED. ARCING AT THE INVERTER CONNECTOR PIN COULD HAVE RESULTED IN A	N OVERHEAT AND/OR FIRE CONDITION.		2	L	7	2 	4F			RT	A21EA   					 
2001032700204	20010327	00204	EA  	2001	3	27	CA010213005      	1	20010203	G	3244	256K433	TIRE            			CNDAIR	CL601 	CL6012A12   	1900303	EA  										SIDEWALL	BULGED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			199  			93170620					(CAN) BULGE IN TIRE SIDEWALL/TREAD RADIUS EDGE. IT APPEARS THAT AIR IS LEAKING INTO THE RADIUS AND GETTING TRAPPED BETWE	EN PLIES. THIS IS THE THIRD TIRE THAT I KNOW OF WITH THIS PROBLEM.					2	L	7	2 	4F			RT	A21AE   					 
2001032700205	20010327	00205	SO  	2001	3	27	CA010213006      	2	20010126	G	8530		CYLINDER HEAD   	CONT        	642344      	CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	SP PLUG-INJECTR	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				100  							(CAN) AT 100 HOUR INSPECTION IN NOVEMBER 2000, FOUND FOUR CYLINDERS WITH SIMILAR CRACKS. AT NEXT 100 HOUR INSPECTION IN 	JANUARY 2001 FOUND SIX MORE CYLINDERS WITH CRACKS IN SAME LOCATION (BETWEEN SPARK PLUG HOLE AND INJECTOR HOLE). CYLINDER	S REPLACED AFTER DETECTING CRACKS. PAST EXPERIENCE SHOWS THAT CRACKS ARE VERY COMMON IN THIS AREA.2001-02-15 TC: PART #S	, TSN, ADDITIONAL CONTRIBUTING FACTORS WERE NOT GIVEN.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA	 
2001032700206	20010327	00206	SO  	2001	3	27	CA010213008      	1	20010122	G	5280	4752932	HINGE           	PIPER       	PA31        	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					IN RADIUS	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						317712043					(CAN) DURING INSPECTION AS PER AIRWORTHINESS DIRECTIVE 200-25-01,(2)TWO GEAR DOOR HINGES FOUND CRACKED. HINGES REPLACED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001032700207	20010327	00207	EA  	2001	3	27	CA010213009      	1	20010124	G	2701	C2CF834A	CONTROL COLUMN  	DHAV        		DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					AT WELD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			15576			497					(CAN) COMPLETED INSPECTION AS PER SB 2/28 AND AD CF-84-01R1, FOUND CRACK IN WELD. 128 HOURS SINCE LAST INSPECTION.SUBMIT	TER FEELS LACK OF MAINTENANCE MAY BE RESPONSIBLE FOR THIS CRACK BEING NOTED EARLY.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001032700209	20010327	00209	EA  	2001	3	27	CA010213018      	1	20010125	G	2760		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ACTUATOR LUG	BROKEN          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) ON APPROACH, AT LAST FLP SELECTION, A/C ROLLED TO THE RIGHT FOLLOWED BY FLT SPLR DEPLOY CAUTION MESSAGE.CREW DECLA	RED EMERGENCY AND LANDED WITHOUT ANY FURTHER EVENT. MAINTENANCE FOUND FLIGHT SPOILER PANEL ACTUATOR LUG BROKEN. PANEL RE	PLACED. AIRCRAFT RETURNED TO SERVICE. AD IN PROGRESS				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700210	20010327	00210	EA  	2001	3	27	CA010213019      	1	20010124	G	2611		SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					LAV SMOKE DETCTR	FAULTY          	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON SHORT FINAL, SMOKE TOILET CAUTION MESSAGE CAME ON. CREW DECLARED AN EMERGENCY AND LANDED WITHOUT ANY FURTHER EV	ENT.LAV SMOKE DETECTOR FOUND FAULTY & REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040300084	20010403	00084	EA  	2001	4	3	CA010213020      	1	20010124	G	2740		ACTUATOR        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZONTAL STAB	FAILED          	W				C		 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DURING TAKEOFF ROLL, CONFIG TRIM AND CONFIG STAB WARNINGS APPEARED. CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS.H	STA AND MCU REPLACED. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700211	20010327	00211	EA  	2001	3	27	CA010213021      	1	20010124	G	2740		STABILIZER      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					HORIZ STAB	FAILED          	W				O	 	 	 	OTHER                   				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, STAB AND MACH TRIM DISENGAGED AT 8.2 UNITS AT NOSE UP TRIM. WOULD NOT RE-ENGAGE. AIRCRAFT PERFORMED A	 FLAP 20 DEGREES PER QRH WITHOUT ANY FURTHER EVENT. MAINTENANCE REPLACED THE HORIZONTAL STAB TRIM PANEL AND RETURNED AIR	CRAFT TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700212	20010327	00212	EA  	2001	3	27	CA010213023      	1	20010125	G	5610		WINDSHIELD      	CNDAIR      	CL6002B19   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					F/O WINDSHIELD	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			CA						7037					(CAN) IN CRUISE FLIGHT, F/O WINDSHIELD SHATTERED. NO INFO ON ALTITUDE OR IF EMERGENCY WAS DECLARED. AIRCRAFT RETURNED IN	TO SERVICE AFTER WINDSHIELD REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700213	20010327	00213	EA  	2001	3	27	CA010213024      	1	20010117	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					L/H WINDSHIELD	CRACKED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA						00201H3495					(CAN) DURING TAXI, CAPTAIN WINDSHIELD CRACKED.AIRCRAFT RETURNED INTO SERVICE AFTER WINDSHIELD REPLACEMENT.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700214	20010327	00214	EA  	2001	3	27	CA010213025      	1	20010113	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					R/H WINDSHIELD	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA						99298H2154					(CAN) CREW RPORTED THAT PASSING FLT 160 AT A DIFFERENTIAL CABIN PRESSURE 6,4, R/H WINDSHIELD CRACKED. NO INFO IF EMERGEN	CY WAS DECLARED.AIRCRAFT RETURNED INTO SERVICE AFTER WINDSHIELD REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040300085	20010403	00085	EA  	2001	4	3	CA010213027      	1	20010213	G	5730		PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					RT AND LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE JACKING AIRCRAFT, MAINTENANCE FOUND TWO CRACKS ON AFT SECTION OF LOWER WING PLANK. ONE ON THE LT AND ONE ON 	THE RT SIDE, AT WS 148, NEAR THE WING JACKING POINTS. REPAIR ACTIVE, AIRCRAFT WILL RETURN INTO SERVICE SOON.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700215	20010327	00215	EA  	2001	3	27	CA010213028      	1	20010130	G	7800	NAS6303U4	BOLT            	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					DELTA BRCKET POS	SHEARED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3100 								(CAN) MAINTENANCE FOUND THE L/H EXHAUST NOZZLE CRACKED DURING A CHECK INSPECTION. DURING REPLACEMENT OF THE EXHAUST NOZZ	LE, MAINTENANCE FOUND TWO (OUT OF THREE) DELTA BRACKETS ATTACH BOLTS SHEARED, AT 2 AND 10 OCLOCK POSITION.FAULTY PARTS R	EPLACED PER AMM.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001032700216	20010327	00216	EA  	2001	3	27	CA010213032      	1	20010129	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					L/H WINDSHIELD	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CUSTOMER ACCEPTANCE FLIGHT, IN CRUISE, L/H WINDSHIELD CRACKED. L/H WINDSHIELD REMOVED AND REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040300086	20010403	00086	EA  	2001	4	3	CA010214004      	1	20010201	G	5210	601R31765303	STRUCTURE       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR LATCH	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE E3 (1200 HOURS) INSPECTION WHEN REMOVING THE PASSENGER DOOR SIDE PANELS A CRACK WAS FOUND IN THE 	PASSENGER DOOR LATCH BOX ASSEMBLY 601R31765-3/03. THE AIRCRAFT REMAINED GROUNDED UNTIL A NEW LATCH BOX WAS INSTALLED. FO	LLOWING THE REPLACEMENT OF THE FAULTY COMPONENT, THE AIRCRAFT WAS THEN RELEASED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040300087	20010403	00087	EA  	2001	4	3	CA010214008      	2	20010112	G	8500		ENGINE          			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					ENGINE BAY	FAILED          	W				A	 	 	 	UNSCHED LANDING         				Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			687  								(CAN) ENGINE HAD STOPPED / SEIZED AFTER THE ENGINE HEATER PLATE WHICH HAD BEEN INSTALLED THE DAY BEFORE THE FLIGHT WAS D	ISLODGED WHEN THE NOSE LANDING GEAR DRAG LINK CONTACTED WITH THE PLATE IN GEAR UP POSITION. THE PLANE LANDED THE PILOT D	IDNT NOTICE ANYTHING. ON THE SECOND FLIGHT WHEN SELECTING GEAR UP THE PLATE WAS PUSHED ON THE QUICK DRAIN BY THE LANDING	 GEAR AND ALLOWED THE ENGINE OIL TO DRAIN COMPLETELY. ENGINE STOPPED THE PILOT HAD TO MAKE A FORCED LANDING IN A FIELD. 	ONLY MINOR DAMAGES WERE MADE TO THE PLANE.		1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001040300089	20010403	00089	SW  	2001	4	3	CA010214011      	1	20010119	G	2510	502565213	SHOULDER BELT   			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					COCKPIT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) MAIN STRAP SHREADED.REPLACED SHOULDER STRAP.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2001040300091	20010403	00091	CE  	2001	4	3	CA010214027      	1	20010125	G	5753	0621229	HINGE           			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					LT WING TE FLAPS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3667 								(CAN) WING FLAP HINGE INBOARD FOUND CRACKED AT BOTH LOWER FLANGES THAT ATTACH TO THE SPAR. PART REPLACED WITH NEW.						1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001040400014	20010404	00014	CE  	2001	4	4	CA010219009      	1	20010129	G	2750	05235372	ROD             			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					TE FLAPS	BENT            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9627 								(CAN) FLAP ROD BENT.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040400017	20010404	00017	EU  	2001	4	4	CA010219018      	1	20010201	G	2611	72111211000	SMOKE DETECTOR  			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	CARGO POD	FAILED          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) JUST AFTER TAKEOFF OUT OF LA RONGE HEADING NORTH APPROXIMATELY 80 MILES, THE BAGGAGE POD SMOKE ALARM WENT OFF. THE	 AIRSCREW TURNED AROUND, & DECLARED AN EMERGENCY TO LANDED BACK IN YVC. MAINTENANCE FOUND NO SMOKE OR FIRE IN THE POD. T	HE SMOKE DETECTOR WAS REMOVED, THE LENSE WAS CLEANED, DETECTOR REINSTALLED AND TESTED S. THIS IS AN ONGOING PROBLEM WITH	 THIS UNIT IN THAT IF THE LENSE (SENSOR) GET A LITTLE DUSTY, IT WILL GIVE FALSE INDICATION. AIRCRAFT WAS REKEASED FOR SE	RVICES.		2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2001040400019	20010404	00019	EA  	2001	4	4	CA010219021      	2	20010205	G	8500		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				821  							(CAN) AFTER TAKEOFF OUT OF URANIUM CITY PILOT HAD TO RETURN TO AIRPORT AFTER EXPERIENCING LOSS OF POWER ON RT ENGINE. MA	INTENANCE INVESTIGATED AND FOUND THAT THE ACCESSORY CASE COMPONENT DRIVE GEARS WOULD NOT TURN. ALSO FOUND OIL FILTER FUL	L OF METAL. MATINTENANCE SUSPECTS THAT ONE OF THE DRIVE GEARS IN THE ACCESSORY CASE HAS LET GO. ENGINE IS BEING SENT TO 	PRO AERO ENGINES FOR STRIP DOWN AND REPAIR. FURTHER REPORT TO FOLLOW.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001040400023	20010404	00023	NM  	2001	4	4	CA010222010      	1	20010205	G	2720	82700544001	CONTROL CABLE   			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  					RUDDER	BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER ENGINE STARTING, BEFORE TAXIING OUT FOR TAKEOFF, CREW CHECKED CNTLS FOR FREEDOM OF MOVEMENT. AT THAT TIME, P	ILOT FOUND THAT RUDDER PEDALS WERE NOT HAVING ANY RESISTANCE WHEN MOVED&WITH BOTH ENGINES RUNNING HE COULD NO T SEE ANY 	RUDDER MOVEMENT ON AFCS IND. AT TIME HE CALLED OFF FLT, SHUTDOWN ENGINES&CALLED MAINT. MAINTENACE CREW ARRIVED ATTHE SCE	NE FOUND RUDDER CABLE ASSY BROKEN. DETAILED INSP IN THE AREA REVEALED RUDDER CABLE ASSY NEXT TO 1ST ONE - DAMAGED, CORRO	DED, WITH 30 PERCENT OF DIAMETER, WIRES BROKEN. LOOKING TO GET ACCESS TO ALL INVOLVED AREA, THOROUGH INSP REVEALED PORT 	SIDE ELEV CABLE ASSY	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001040400024	20010404	00024	NM  	2001	4	4	CA010222011      	1	20010206	G	4940	8Z7591125	BRACKET         			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					APU	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING TROUBLESHOOTING FOR APU FAILED START, THE GROUND CABLE FROM APU SHUNT WAS FOUND SEPARATED FROM 4900-GS10 (S	TN X792) ON BRACKET. THE ATTACHMENT BRACKET WAS FOUND BURNT AS WELL AS THE CABLE CONNECTION. SYD  WAS ISSUED AND THE CAB	LE WAS REPAIRED AND INSTALLED. BASED ON THE INFORMATION PROVIDED BY THE OPERATOR, IT IS BELIEVED THAT THE MOST PROBABLE 	CAUSE OF DAMAGE WAS IMPROPER INSTALLATION TORQUING OF THE GROUND STUD AND ATTACHING HARDWARE.			2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2001040400025	20010404	00025	CE  	2001	4	4	CA010222015      	1	20010212	G	2752	D14500462	TRANSMISSION    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAPS	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				F	 	 	FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LANDING THE PILOTS SELECTED FLAPS TO THE UP POSITION AND THE FLAP CIRCUIT BREAKER POPPED. THE FLAP CIRCUIT B	REAKER WAS RESET AND THE FLAPS WERE SELECTED UP NORMALLY. WHEN THE FLAPS WERE RESELECTED TO THE DOWN POSITION THE CIRCUI	T BREAKER POPPED AGAIN. THE FLAP TRANSMISSION AND MOTOR ASSEMBLY WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001040400026	20010404	00026	CE  	2001	4	4	CA010222016      	1	20010212	G	7160	NAS561C410	ROLL PIN        	CESSNA      	26520251    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	BELLCRANK	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE ROUTINE 100 HOUR INSPECTION THE AIRCRAFT ENGINEER FOUND THAT THE ROLL PINS, QUANTITY 4, SECURING THE BE	LL CRANK TO THE AIR BYPASS DUCT FOR THE ENGINE, WERE LOOSE. UPON RMEOVAL WE FOUND THAT ALL FOUR PINS WERE BROKEN. PIN RE	PLACED WITH NEW.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001040400028	20010404	00028	CE  	2001	4	4	CA010223002      	1	20010206	G	6100		BLADE           	MCAULY      	1C172MDM    	CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1C172	1C172MDM    	GL  	PROPELLER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			765  	633  		71581					(CAN) EXTRA WORK REQUIRED TO REMOVE CORROSION FROM BLADE FACE (CAMBER FACE) IN ACCORDANCE WITH MCCAULEY MANUAL 730720.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910	 
2001040400032	20010404	00032	NM  	2001	4	4	CA010223007      	1	20010131	G	2435	23088002B	STARTER GEN     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 ENGINE	DISINTEGRATED   	W				D	 	 	 	RETURN TO BLOCK         				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA			15963	773  		611A					(CAN) A VIBRATION WAS FELT DURING START-UP ON NR 2 ENGINE AND THEN DURING TAXI THE NR 2 D.C. GENERATOR LIGHT CAME ON. TH	E CREW WERE UNABLE TO SUCCESSFULLY RESET THE NR 2 GENERATOR AND RETURNED TO THE GATE. INVESTIGATION REVEALED THE NR 2 GE	NERATOR FAN END BEARING HAD FAILED. STARTER GENERATOR REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040400033	20010404	00033	NM  	2001	4	4	CA010223008      	1	20010120	G	2910	82970010391	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			31326								(CAN) UPON ARRIVAL AT THE GATE HYDRAULIC FLUID WAS NOTICED TO BE LEAKING FROM THE LT WHEEL WELL AREA. INVESTIGATION REVE	ALED THAT THE AFT NR 1 DOOR CLOSE LINE WAS LEAKING.LINE REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040400034	20010404	00034	NM  	2001	4	4	CA010223010      	1	20010120	G	2910	82950010277	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			25366								(CAN) A PUDDLE OF HYDRAULIC FLUID WAS NOTICED AROUND THE LT MAIN WHEEL AREA. INVESTIGATION REVEALED THAT THE LEAK WAS CO	MING FROM THE LT OUTBOARD ROLL SPOILER LIFT DUMP LINE.LINE REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040400038	20010404	00038	CE  	2001	4	4	CA010226002      	1	20010215	G	2431	A876K	TERMINAL        			CESSNA	560   	560XL       	       	CE  	PWA   	545   	PW545A      	 	NE  					BATTERY	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			474  								(CAN) AIRCRAFT ARRIVED AT ST. HUBERT (YHU) PILOTS SHUT DOWN ENGINES AND APU, HAD NO POWER ON AIRCRAFT WITH BATTERY SWITC	H ON BATTERY. PILOT TOOK SWITCH AND TOGGLED IT TO OFF AND THEN TO EMERGENCY POWER AND STILL NO POWER ON AIRCRAFT. UNABLE	 TO PUT BATTERY ON LINE.				2	L	7	2 	4F	4	F	RT	A22CE   	E00059EN				 
2001040400039	20010404	00039	EA  	2001	4	4	CA010226005      	1	20010203	G	4990		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					APU BAY	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) THE CREW REPORTED THE SMOKE TOILET CAUTION MESSAGE AT 9000 FEET. SMOKE WAS VISIBLE WHEN BLEED WAS TRANSFERRED IN C	ABIN AND COCKPIT WHEN BLEEDS WERE TRANSFERRED TO APU. AIRCRAFT DID AN EMERGENCY LANDING.THE MAINTENANCE FOUND OIL COMING	 FROM COMPRESSOR DRAIN OF THE APU. APU WAS DEFERRED TO BE REPLACED LATER.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040400040	20010404	00040	EA  	2001	4	4	CA010226008      	1	20010206	G	5610	601R3303312	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) THE RT WINDSHIELD SHATTERED IN CRUISE DURING THE FLIGHT NR 5.THE MAINTENANCE REPLACED THE WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040400041	20010404	00041	EA  	2001	4	4	CA010226009      	1	20010206	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) THE LT WINDSHIELD SHATTERED IN CRUISE AT 35,000 DURING THE FLIGHT NR 5.THE MAINTENANCE REPLACED THE WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040400042	20010404	00042	EA  	2001	4	4	CA010226010      	1	20010202	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) THE RT WINDOW CRACKED IN CRUISE. THE MAINTENANCE REPLACED THE WINDOW.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040400043	20010404	00043	EA  	2001	4	4	CA010226011      	2	20010205	G	7414	4347	MAGNETO         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA				576  							(CAN) AIRCRAFT HARD TO START. RETARD LOW INTENSITY SPARK. REPLACED MAGNETO.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2001040400044	20010404	00044	SW  	2001	4	4	CA010226012      	1	20010125	G	8011	SAZ4401	RELAY           			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					STARTER	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) ENGAGEMENT INTERMITTENT DUE TO VIBRATION. REPLACED STARTER RELAY.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2001040400046	20010404	00046	EA  	2001	4	4	CA010226018      	2	20010101	G	7414	4250R	MAGNETO         			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			525  								(CAN) ENGINE STARTING RUNNING ROUGH IN CRUISE FLIGHT PILOT RETURNED TO STATION. GROUND RUN INDICATED EXCESSIVE RPM LOSS 	ON RT MAGNETO. MAGNETO REPLACED AND FOLLOW UP GROUND RUN CARRIED OUT RESULTING IN NORMAL RPM (STATIC) AND RT RPM DROP WI	THIN LIMITS. NO APPARENT EXTERNAL PROBLEMS WITH MAGNETO COULD BE IDENTIFIED. AN SC REPORT MAY FOLLOW SHOULD WE CHOOSE TO	 HAVE THE MAGNETO OVERHAULED.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001040400047	20010404	00047	WP  	2001	4	4	CA010226020      	2	20010201	G	7412	103784005C	EXCITER         			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE331*     	01514	WP  	ROTOL	R306	R306382F7   	GL  	LT ENGINE	SHORTED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA				5    							(CAN) LT ENGINE WOULD NOT START. NO IGNITION. IGNITION SYSTEM CHECKED AND THE EXCITER WAS FOUND TO BE AT FAULT.						1	H	7	2 	3T	3	T	 	2A4     	E2WE	6	C	P8EU	 
2001040400048	20010404	00048	NM  	2001	4	4	CA010228008      	1	20010206	G	6320	A0061	GEARBOX         			ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O360  	O360J2A     	41514	EA  					MAIN ROTOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			1747 								(CAN) MAIN ROTOR GEARBOX CHIP DETECTOR LIGHT ACTIVATED IN FLIGHT. PILOT LANDED ON GROUND LIGHT WENT OUT. CHIP DETECTOR R	EMOVED AT MAINTENANCE FACILITY. FUZZ PARTICULATE FOUND, DETECTOR CLEANED, INSPECTED, REINSTALLED. HELICOPTER GROUND RUN 	ON GROUND FOR 30 MINUTES WITH NO LIGHT INDICATION. GEARBOX OIL REPLACED AT CUSTOMER REQUEST.				1	G	7	1 	3O	3	O	 	H10WE   	E286				 
2001040400049	20010404	00049	EU  	2001	4	4	CA010228009      	1	20010227	G	5302		SKIN            			SNIAS 	350   	AS350BA     	8680817	EU  										TAILBOOM	WRONG PART      	W				O	 	 	 	OTHER                   				W	 	 	INADEQUATE Q C            			LD	LANDING        	1			CA			14116								(CAN) - TAILBOOM COLLAPSED AFTER LANDING. - TAIL ROTOR DRIVE DISCONNECTED, FAILING DAMAGE.- LOWER FORWARD SKIN BUCKLED A	ND FRACTURED BETWEEN NR 3 AND 4 BEARING. - FAILURE ANALYSIS FOUND WRONG SKIN THICKNESS.- MEASURES 0.0325 INCH, SHOULD BE	 1.0MM (0.03937 INCH). - OPERATOR INSPECTED FLEET OF 6 OTHERS AND FOUND AIRCRAFT S/N 2495 ALSO HAS INCORRECT SKIN. - BOO	MS ARE FACTORY ORIGINAL - NO REPAIR HISTORY. - EUROCOPTER USA ADN HAWAII FAA NOTIFIED.			1	G	7	1 	3U			NC	H9EU    					 
2001040400050	20010404	00050	NE  	2001	4	4	CA010301002      	2	20010103	G	7310	226311001	LINE            	HONEYWELL   		BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE FUEL	MISREPAIRED     	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING RECEIPT OF A LOANER ENGINE, IT WAS NOTED THAT ONE OF THE INSTALLED LINES FROM THE FLOW DIVIDER TO THE FUEL 	MANIFOLD HAD AN UNAPPROVED WELD REPAIR ACCOMPLISHED ON IT. THE LINE WAS REPLACED.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001040400051	20010404	00051	NM  	2001	4	4	CA010301004      	1	20010127	G	2910	82950010175	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYDRAULIC SYS	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE INSPECTION, HYDRAULIC FLUID WAS FOUND LEAKING FROM THE LT WING INBOARD FLAP CANOE. INVESTIGAITON RE	SULTED IN REPLACEMENT OF A LEAKING FLIGHT SPOILER UNLOAD LINE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040400052	20010404	00052	EA  	2001	4	4	CA010301005      	1	20010209	G	7112	311269001	ADAPTER         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	VENTURI	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED INSPECTION OF THE R/H ENGINE, THE ENGINE BLEED AIR VENTURI ADAPTER WAS FOUND TO HAVE A V SHAPED C	RACKED ON THE OUTSIDE OF THE 90 DEGREE BEND OF THE VENTURI. THE VEE HAD OPENED UP, ALLOWING BLEED AIR TO BE DUMPED INTO 	THE ENGINE COMPARTMENT. THE ADAPTER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (THIS AREA OF THE ADAPTER IS 	COVERED WITH A SHROUD, MAKING INSPECITON A DELIBERATE ACTION.)			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040400196	20010404	00196	NE  	2001	4	4	CA010301017      	2	20010117	G	7200		ENGINE          			BOEING	767   	7673S1      	1385211	NM  	GE    	CF6   	CF680C2B2   	30025	NE  					RIGHT	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				Y	 	 	ENGINE STOPPAGE           			LD	LANDING        	1			CA			32338	32338		720611					(CAN) ON FINAL INTO YYZ, RIGHT ENGINE SHUTDOWN, 4 MINUTES TO LANDING. ENGINE SHUTDOWN CHECKLIST COMPLETED. LANDED WITHOU	T INCIDENT. ON INSPECTION OF RT ENGINE METAL FOUND IN TAILPIPE. RT ENGINE REPLACED. OFF PART NUMBER 6-7200-9-0002, SERIA	L NUMBER 2611.2001-03-06 TC: EXPECT OPERATOR TO FOLLOW-UP WHEN TEAR DOWN AVAILABLE.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE				 
2001040400199	20010404	00199	NE  	2001	4	4	CA010301029      	1	20010216	G	6210	S611520107	BLADE           			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR	DEBONDED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8770 								(CAN) AIRCRAFT LANDED TO REFUEL. IT WAS NOTED THAT DURING A WALKAROUND THAT, A ROTOR BLADE POCKET HAD BECOME DEBONDED. A	 TEMPORARY REPAIR WAS MADE AND THE AIRCRAFT WAS FLOWN BACK TO BASE.					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001040400200	20010404	00200	EA  	2001	4	4	CA010301030      	1	20010301	G	2750	72740196011	TUBE            			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FLAP DRIVE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, SEVERE WEARING WAS NOTED ON OUTBOARD FLAP DRIVE SECONDARY DRIVE TUBE P/N 72740196-011 BY THE ST	EADY BEARINGS. UNABLE TO DETECT WEAR PROPERLY UNLESS STEADY BEARING REMOVED. WEAR WAS FOUND ON BOTH SIDES OF FLAP DRIVE 	SYSTEM. MAXIMUM WEAR FOUND 0.0265 INCH. TUBE THICKNESS APPROXIMATELY 0.040. BOTH WORN TUBES REPLACED WITH SERVICEABLE UN	ITS.			2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001040400201	20010404	00201	NE  	2001	4	4	CA010301031      	1	20010209	G	2910	3935	SHUTOFF VALVE   			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ACTUATOR	LEAKING         	W				E	D	 	 	ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA						162					(CAN) ON START UP THE NR 1 SERVO JAM WARNING LIGHT WOULD NOT EXTINGUISH WHEN NORMAL HYDRAULIC PRESSURE WAS REACHED. THE 	FLIGHT CREW SHUT DOWN AND UPON EXITING THE AIRCRAFT SAW HYDRAULIC FLUID UNDER THE AIRCRAFT. THE ENGINEER FOUND THE NR 1 	HYDRAULIC SYSTEM FLUID LOW WHICH CAUSED THE NR 1 SERVO JAM LIGHT TO STAY ON. FURTHER INVESTIGATION FOUND THE TAIL SERVO 	SHUT OFF VALVE LEAKING FROM THE ELECTRICAL ACTUATOR BODY. THE VALVE WAS REPLACED, NR 1 HYDRAULIC SYSTEM REPLENISHED AND 	BLED. THE AIRCRAFT WAS TEST FLOWN AND THEN RETURNED TO SERVICE.		1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001040400202	20010404	00202	EA  	2001	4	4	CA010301032      	1	20010213	G	3246	901230602	FITTING         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT FLOAT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION AND STRESS CRACK DEVELOPED ON THE TAPER HOLE OF THE SPREADER BAR ATTACH FITTING LT FLOAT AFT SPREADER AT	TACH P/N 901-23060-2 WAS REMOVED AND QUARANTINED. REPLACEMENT P/N S1901-23060-2 INSTALLED AS PER STC SF-92-7.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001040400203	20010404	00203	EA  	2001	4	4	CA010301033      	1	20010213	G	3246	901230602	FITTING         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT FLOAT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION AND STRESS CRACK DEVELOPED ON THE TAPER HOLE OF THE SPREADER BAR ATTACH FITTING RT FLOAT FORWARD SPREADE	R ATTACH WAS REMOVED AND QUARANTINED. REPLACEMENT P/N S1901-23060-2 INSTALLED AS PER STC SF-92-7.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001040400204	20010404	00204	EA  	2001	4	4	CA010301035      	2	20010216	G	8540	LW10292	IDLER GEAR      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				820  							(CAN) THE IDLER GEAR BETWEEN THE CRANKSHAFT AND THE CAMSHAFT GEAR DISENGAGED DUE TO FRACTURING OF THE CRANKCASE AND ACCE	SSORY CASE. THESE FRACTURES ARE DIRECTLY OPPOSITE THE CRAN GEAR AND WOULD INDICATE THAT A SOLID OBJECT WENT IN BETWEEN T	HE CRANK GEAR AND IDLER GEAR. THE UPPER ROW OF TEETH ON THE IDLER, DRIVES THE MAGNETO AND THERE IS ONE TOOTH MISSING. TH	IS MISSING TOOTH IS PROBABLY WHAT WENT IN BETWEEN THE GEARS.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001040400205	20010404	00205	EA  	2001	4	4	CA010301036      	2	20010212	G	7250	3027102	TURBINE BLADES  								PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				3000 							(CAN) POWER TURBINE SECTION  DISASSEMBLED FOR EVALUATION. POWER TURBINE BLADES SHOWED A DIFFERENT CONFIG THAN P/N 302710	2 POWER TURBINE BLA DES NORMALLY FOUND ON THIS MODEL ENGINE. ALSO PART NO (P/N 3013102) STAMPED ON BLADES WAS CROSSED OU	T & P/N 3027102 WAS ENGRAVED. P&W WAS NOTIFIED & RESPONDED THAT SUBJECT BLADES WERE APPLICABLE TO A PT6A ENGINE & NOT PT	6T. THEY ALSO STATED THAT THERE IS NO APPRD MODS THAT WOULD ALLOW 3013102 BLADES TO BE REIDENTIFIED. P&WSTATES BLADES MU	ST BE REMVD FROM SERVICE. 2001-03-05 TC: FORWAEDED TO MAINT & MFG S.U.P.							4	U			E22EA				 
2001040400229	20010404	00229	CE  	2001	4	4	CA010302006      	1	20010214	G	5312	07126161	BULKHEAD        			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	VERTICAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			4269 								(CAN) CRACK ABOVE LT RUDDER STOP BOLT LOCATION ON (BULKHEAD) FLANGE BEND RADIUS DIRECTLY ABOVE BOLT. A/C HANGARED FOR LA	ST 15 YRS & NOT SUBJECTED TO WIND. REMOVAL & INSP SHOWS POOR STANDARD PRACTISE OF DRIVING 90 DEGS STIFFENER INTO BEND RA	DIUS OF FLANGE (ASSY IS SANDWICH OF STIFFENERS). THUS WHEN RUDDER STOP BOLT JAM NUT IS TIGHTENED, STIFFENER CUTS INTO BE	ND RADIUS. REPL PART WORSE&REJECTED (NEW). NEW BULKHEAD STIFFENER PLAC ED SO AS TO RIDE UP BEND RADIUS ENOUGH TO FIT 0.0	15 FEELER GAUGE. ASSY MANUFACTURED & RIVETED WITH GAP. FEW STROKES WITH FILE WOULD MATCH BEND RADIUS & NOT CAUSE PROBLEM	 DURING MANUFACTURE: SK210-161-1 WILL BE INST (SEB99-12R1).	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001040400207	20010404	00207	EU  	2001	4	4	CA010302007      	1	20010214	G	2912	583400	FILTER          		704A44633025	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					HYD SYSTEM	CLOGGED         	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			HO	HOVERING       	1			CA			257  								(CAN) - UPON HOVERING IN AERIAL LONG LINE WORK. THE PILOT NOTICED SOME FEEDBACK IN CYCLIC CONTROLS WHEN INPUTING AGGRESS	IVE MOVEMENTS (I.E. WINDY CONDITIONS). HE IMMEDIATELY ABORTED THE TASK AT HAND AND LANDED.- ON INSPECTION OF HYDRAULIC F	ILTER FOUND A BLACK DEPOSIT IN FILTER MEDIA.- THIS IS ABNORMAL CONSIDERING THE 500 HR FILTER LIFE, AND TAFT OF 257.2 HOU	RS. - POSSIBLE CAUSE: DEPOSITS INSIDE HYDRAULIC LINES AND COMPONENTS AT TIME OF MANUFACTURE AND HIGH DETERGENT ATTRIBUTE	S OF AEROSHELL FLUID 41).		1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040400210	20010404	00210	CE  	2001	4	4	CA010302010      	1	20010131	G	3230	ALM50	CURRENT LIMITER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	MLG	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) AIR NUNAVUT KING AIR WAS ON APPROACH TO IGALUIT AT NIGHT. FLIGHT CREW SELECTED GEAR, THEY RECEIVED AN UNSAFE GEAR 	INDICATION AND HAD TO USE GEAR EMERGENCY EXTENSION METHOD, AFTER WHICH GAVE 3 GREEN GEAR DOWN AND LOCKED INDICATION. THE	 AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. AN INSPECTION OF LANDING GEAR SYSTEM WAS ACCOMPLISHED. IT WAS DISCOVERED THAT	 R/H GENERATOR BUS POWER LIMITER HAD FAILED. MAINTENANCE WAS UNSUCCESSFUL AT FINDING A CAUSE FOR LIMITER FAILURE. NEW PO	WER LIMITER INSTALLED. GEAR SWINGS ACCOMPLISHED AS PER AVIA DESIGNS MAINTENANCE MANUAL. AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2001040400211	20010404	00211	EU  	2001	4	4	CA010302012      	1	20010302	G	6240	1179405303	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TRIPLE TACH	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CR	CRUISE         	1			CA				12   		468					(CAN) NR (ROTOR RPM) NEEDLE STARTED TO READ LOW. PILOTS RECOGNIZED THIS AS AN INDICATION PROBLEM. PILOTS LANDED AT BASE 	WITHOUT INCIDENT. PROBLEM WAS CORRECTED BY INSTALLING A SERVICEABLE TACHOMETER.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001040400213	20010404	00213	CE  	2001	4	4	CA010302014      	1	20010209	G	3040	10138402522	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			1205 			98108H3288					(CAN) WHILE IN CRUISE FLIGHT AT FL310 AND OAT -46 DEGREES C, A LOUD BANG WAS HEARD AND THE RT WINDSHIELD CRACKED. (WINDS	HIELD HEAT HAD BEEN ON FOR THE ENTIRE FLIGHT (1 HOUR PLUS)). FLIGHT CREW REFERENCED ABNORMAL OCCURRENCE IN POH AND MADE 	AN UNSCHEDULED, UNEVENTFUL LANDING IN YYC. AIRCRAFT GROUNDED FOR WINDSHIELD REPLACEMENT. NOTE: SIMILAR OCCURRENCE TO LT 	WINDSHIELD FAILURE IN OCTOBER 1999.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001040400221	20010404	00221	NM  	2001	4	4	CA010306015      	1	20010128	G	2120		UNKNOWN         			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					CABIN	ODOR            	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA											(CAN) DURING A TAKEOFF A SMELL WAS NOTED AND INCREASE DRAMATICALLY DURING THE CLIMB. CREW NOTED THAT THERE WAS NO VISIBL	E SIGN OF SMOKE. CREW RETURNED TO BASE FOR INVESTIGATION. MAINTENANCE CARRIED OUT AN APU START, BLEED ON, SMELL PRESENT 	FOR 2 MIN. THEN DISAPPEARED. ENGINE RUN PERFORMED NO SMELL. DC CONTACTOR BOXES CHECKED, NO FAULT. AREA AROUND WATER BOIL	ER INSPECTED, NO FAULT. EPCU CHECKED FOR FAULT CODES, NO FAULT. CDS CHECKED, NO FAULT. ENGINE RUN PERFORMED AGAIN, NO FA	ULT. AIRCRAFT RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2001040500066	20010405	00066	CE  	2001	4	5	CA010307004      	1	20010220	G	3246	C1630030201	WHEEL           	MCAULY      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NLG	DAMAGED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) REPORTED TO MAINTENANCE OF CLICKING NOISE FROM FRONT AREA DURING TAXI. INSPECTION REVEALED THREE (3) THRU BOLTS MI	SSING ON WHEEL RIM RESULTING IN DAMAGE TO NOSE FORK. TWO OF THREE REMAINING BOLTS FOUND LOOSE. SUSPECT INCORRECT TORQUE 	ON WHEEL BOLTS.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001040500067	20010405	00067	SW  	2001	4	5	CA010307007      	1	20010214	G	6230	206010332121	BEARING         	BELL        	206040002007	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAST	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4456 	1461 		NOF4734					(CAN) SEVERE PITTING OF LOWER BEARING JOURNAL INNER RACE AT LOWER PORTION OF MAST ASSEMBLY.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001040500072	20010405	00072	SW  	2001	4	5	CA010307013      	1	20010109	G	6510	206040102103	COVER           			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R COUPLING	GROOVED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				15   							(CAN)WHEN REINSTALLING A MAIN DRIVESHAFT AFTER A INPUT TRANSMISSION SEAL REPLACEMENT, FOUND THAT THE TRANSMISSION END OF	 THE SHAFT COULD NOT MOVE.  OPENED THE COUPLING END FOUND THAT SPRINGS  WAS NOT INSTALLED PROPERLY. THE COVER WAS GROOVE	D. INSPECTED THE INNER AND OUTER COUPLING ON BOTH END OF DRIVESHAFT ASSEMBLY. NO MORE DAMAGE FOUND 15.0 HOUR SINCE LAST 	INSPECTION. COMPLETED THE SHAFT INSPECTION AFTER REPLACING THE COVER AND THE SPRING THAT WERE DAMAGED BY NEW PARTS. A/C 	WAS RETURNED TO SERVICE.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001040500074	20010405	00074	WP  	2001	4	5	CA010307015      	1	20010225	G	6310		ENGINE          			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					ENGINE	FAILED          	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA			47592								(CAN) AFTER TAKEOFF ENGINE NR 3 VIBS INCREASED TO 2.5 UNITS, THROTTLE RETARDED TO KEEP BELOW LIMITS. AIRCRAFT RETURNED T	O MAINTENANCE BASE YMX. TROUBLESHOOTING CARRIED OUT AS PER MM 79-00-00 PAGE 121, ENGINE RUNS CARRIED OUT AS PER TEST NR 	21 VIBRATIONS WITHIN LIMITS, AIRCRAFT RETURNED TO SERVICE.SUSPECT OIL FINDING.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001040500076	20010405	00076	NE  	2001	4	5	CA010307017      	2	20010218	G	7200		ENGINE          			LKHEED	1011  	1011385115  	5265015	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NR 2	VIBRATION       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			44530								(CAN) AFTER TAKEOFF (DURING FIRST STAGES OF CLIMB) THE NR 2 ENGINE VIBRATION INCREASED, FLIGHT CREW SHUTDOWN ENGINE IN A	CCORDANCE WITH OPERATING PROCEDURE AND RTURNED TO BASE. MAINTENANCE PERFORMED TEST 21 IN ACCORDANCE WITH ROLLS ROYCE PRO	CEDURES, ENGINE VIBRATIONS RETURNED TO NORMAL, AIRCRAFT RETURNED TO SERVICE. NO FURTHER REPORTED INCIDENTS.MAINTENANCE S	USPECT OIL HIDING AS CAUSE OF ENGINE VIBRATION .			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001040500077	20010405	00077	EA  	2001	4	5	CA010307018      	1	20010220	G	3232		BRACE           			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG DOOR	SHEARED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT 604-54F05 WITH TSN OF 611.3 HOURS AND 304 CYCLES HAS BEEN FOUND TO HAVE A BROKEN TRUNNION PIN AT L/H MLG 	SIDE BRACE ACTUATOR INBOARD END.THIS WAS FOUND AS THE AIRCRAFT WAS ON JACKS AND A TECHNICIAN NOTICED THAT THE GEAR MOVED	. THE FORWARD ATTACH NUT WAS SHEARED OFF AND LAYING ON TOP OF THE WING. THIS ALLOWED THE PIN TO MIGRATE APPROXIMATELY 0.	3 INCHES AFT, ALLOWING THE GEAR TO MOVE. PART REPLACED. BROKEN PART RETURNED TO BOMBARDIER FOR ANALYSIS.UNDER INVESTIGAT	ION		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500078	20010405	00078	EA  	2001	4	5	CA010307021      	1	20010219	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE PRE-FLIGHT INSPECTION, IT WAS NOTICED THAT THE CAPTAINS WINDSHIELD WAS CRACKED. THE AIRCRAFT RETURNED T	O SERVICE AFTER REPLACEMENT OF THE WINDSHIELD.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500079	20010405	00079	NE  	2001	4	5	CA010307024      	2	20010219	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA											(CAN) PILOT REPORT IN DESCENT: AUDIT ENGINE OIL AND MASTER WARNING. ENGINE NR 2 OIL PRESSURE RAPIDLY DROPPED TO 0 PSI. C	REW INITATED AN IN-FLIGHT SHUTDOWN PROCEDURE, AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND PARTICLE ON NR 2 CHIP 	DETECTOR. AT THE TIME OF WRITING THE CAUSE FOR THE LOSS OIL PRESSURE HAS NOT BEEN DETERMINDED. THE CUSTOMER AND THE MANU	FACTURER WILL CONTINUE THE INVESTIGATION.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500080	20010405	00080	EA  	2001	4	5	CA010307026      	1	20010219	G	5730	601R10046	PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF34*       	 	NE  					LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			18652								(CAN) DURING A SERVICE CHECK, THE MECHANIC FOUND A SUSPECTED CRACK N THE LT WING LOWER SKIN AT WING STATION WS 148.019. 	THE CRACK WAS CONFIRMED WITH LPI AND EDDY CURENT NDT. THE REPAIR WAS CARRIED OUT PER REPAIR ENGINEERING ORDER 601R-57-21	-130. THE AIRCRAFT SUBSEQUENTLY RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500081	20010405	00081	EA  	2001	4	5	CA010307027      	1	20010219	G	5730	601R10046	PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13895								(CAN) DURING A C CHECK INSPECTION, A CRACK WAS FOUND IN THE LOWER WING PLANK AT WING STATION WS 148.019.AT THE TIME OF R	EPORT, THE AIRCRAFT WAS STILL IN C CHECK. REPAIR ENGINEERING ORDER (REO) 601R-57-21-130 WILL BE APPLIED PRIOR TO RETURNI	NG THE AIRCRAFT INTO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500082	20010405	00082	EA  	2001	4	5	CA010307028      	1	20010219	G	5600	NP1393215	WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE MANOEUVRING ON THE GROUND, THE LT SIDE WINDOW WAS FOUND CRACKED. THE WINDOW WAS REPLACED AND THE AIRCRAFT RE	TURNED INTO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500083	20010405	00083	NE  	2001	4	5	CA010307030      	2	20010221	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					LEFT	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CL	CLIMB          	1			CA											(CAN) ENGINE VIBRATION DURING CLIMB OUT AND LEVEL FLIGHT (FL230). MAXIMUM VALUE WAS 3.3 MILS. LATER FLUCTUATION BETWEEN 	2.3 AND 3.3 MILS. ENGINE SHUT DOWN IN FLIGHT. SINGLE ENGINE OPERATION AS PER QRH. CHANGE LEFT ENGINE. REASON: HIGH N1 VI	BRATION.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500084	20010405	00084	EA  	2001	4	5	CA010307033      	1	20010222	G	5270	601R317001	SENSOR          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PASSENGER DOOR	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) DURING CLIMB CREW RECD PASSENGER ENTRANCE DOOR WARNING MESSAGE PAX DR LATCH (AMBER) & PASSENGER DOOR (WARNING) EIC	AS MESSAGES. A/C RETURNED TO DEPTR AIRPORT&LANDED W/O INCID.&LATER FERRIED TO MAINT BA SE. MAINT FINDINGS: 1. PSEU FAULT	 LOG 2 RECORDED S47 & S46;2. FLT CREW RPT EICAS MESSAGES EXTINGUISHED BELOW 7000 ASI; 3. GREEN ALIGNMENT MARKS ON CAM LA	TCHES NOT WITHIN RANGE WHEN INNER DOORHANDLE IS SLOWLY ENGAGED; 4. PROX SENSOR PSSMB GAP .068 INCH, .018 INCH BEYOND LIM	ITS;5. A/C RECORDS SHOWN HAVE BEEN NO ADJUSTMENT MADE TO PSSMB SENSOR OR DOOR MECHANISM WITHIN PAST 30 DAYS. RECTIFICATI	ON 1. PROX SENSOR PSSMB GAP ADJUSTED WITHIN LIMITS;2. INNER DOOR HANDLE STOP ADJUSTED;3. DOOR MECHANISM LUBRICATED A	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500090	20010405	00090	EA  	2001	4	5	CA010308007      	1	20010202	G	4920	49100011	APU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	DAMAGED         	W				K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) SMELL OF FUEL AND SMOKE IN AIRCRAFT AFTER APU STARTED ON DESCENT. EMERGENCY RESPONSE CALLED. FLIGHT LANDED AND TAX	IED TO THE GATE WITHOUT FURTHER INCIDENT. APU REPLACED OPERATION AND LEAK CHECK CARRIED OUT AND SYSTEM CHECKED SERVICEAB	LE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500091	20010405	00091	EA  	2001	4	5	CA010308010      	1	20010212	G	2910	AE3660010K0270	LINE            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										HYDRAULIC SYSTEM	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 60 MONTH/2400 HOUR INSPECTION, THE FLEXIBLE HYDRAULIC LINE (SUCTION TO THE ENGINE DRIVEN PUMP) OF THE NR 	1 SYSTEM WAS FOUND TO HAVE CHAFED A HOLE THROUGH FUEL SHROUD SUPPLY LINE TO THE EDP.HYDRAULIC LINE P/N: AE3660010K0270FU	EL SHROUD P/N: 601R62701-45 ACTT: 2261.5TOTAL LANDINGS: 1082				2	L	7	2 	4F			RT	A21EA   					 
2001040500092	20010405	00092	NM  	2001	4	5	CA010308011      	1	20010208	G	2497		WIRE            			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FIREWALL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WIRE W200-453-06 CHAFED THROUGH INSULATION AND WIRE. LENGTH & WIDTH OF CHAFE IS 3/8 INCH, DEPTH 1/8 INCH. APPEARS 	TO HAVE RUBBED AGAINST COWLING AT SOME TIME. HOWEVER, AT TIME OF DISCOVERY, IT WAS NOT APPARENT WHAT THE WIRE HAD CHAFED	. THERE HAD BEEN NO REPORTED ELECTRICAL POWER DEFECT. THE HARNESS HAS BEEN REPLACED WITH PARTICULAR EMPHASIS TO CORRECT 	ROUTING AND CLAMPING.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001040500093	20010405	00093	NM  	2001	4	5	CA010308012      	1	20010219	G	2761	654456113	ACTUATOR        			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					SPOILER	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			DE	DESCENT        	1			CA											(CAN) AT APPROXIMATELY 20 MINUTES OUT, THE A SYSTEM HYDRAULIC LIGHT ILLUMINATED. THE HYDRAULIC FLUID GAUGE WAS CHECKED A	ND FOUND TO BE EMPTY. THE USE OF ALTERNATE FLAP AND GEAR EXTENSION WAS REQUIRED. THE AIRCRAFT LANDED WITHOUT INCIDENT. T	HE FIRE DEPARTMENT WAS ALERTED AND STANDING BY AS A PRECAUTION MEASURE. MAINTENANCE FOUND THE LEFT INBOARD FLIGHT SPOILE	R ACTUATOR LEAKING.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001040500094	20010405	00094	CE  	2001	4	5	CA010308013      	1	20010212	G	5510	10138000110	BOOT            	BEECH       	B300        	BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					HORIZ STAB DEICE	DETACHED        	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			3880 			FL26					(CAN) AIRCRAFT WAS IN CLIMBOUT FROM ST.JOHNS AIRPORT, AT 22,000 FEET, AIRSPEED 140 KNOTS, RATE OF CLIMB 1,800 F.P.M., PI	LOT EXPERIENCED SEVERE BUFFETING TO THE POINT THAT A/C WAS ABOUT TO STALL. STALL WARNING DID NOT ACTIVATE, A/C WAS PLACE	D IN LEVEL FLIGHT AND BUFFETING STOPPED. A/C RETURNED TO ST. JOHNS FOR MAINTENANCE. UPON INSPECTION MAINTENANCE DISCOVER	ED THAT THE RIGHT DE-ICER BOOT HAD DETACHED FROM THE HORIZONTAL STABILIZER ON THE OUTBOARD END. NEW DE-ICER BOOTS WRE IN	STALLED ON THE LEFT AND RIGHT SIDE, A/C WAS TEST FLOWN ALL FLIGHT CHARACTERISTICS NORMAL.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001040500095	20010405	00095		2001	4	5	CA010313009      	4	20010226	G	8300	BP252	GEARBOX         			KAMOV 	KA32  	KA32A1      	       	SW  										ACCESSORY	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			HO	HOVERING       	1			CA			148  			L20011007K					(CAN) CAUTION SYSTEM - GEARBOX CHIP LIGHT, SMALL FLAT FLAKES FOUND IN OIL.						1	G	7	2 	4U			NC	        					 
2001040500096	20010405	00096	SW  	2001	4	5	CA010313014      	1	20010228	G	6220	471401241	TUBE            			BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1F    	41516	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				79   							(CAN) DURING DAILY INSPECTION ON MAIN CONTROL STABILIZER BAR AS PER AD 74-08-02. PILOT FOUND STABILIZER BAR TUBE WAS CRA	CKED.					1	G	7	1 	3O	3	O		H1      	E279				 
2001040500097	20010405	00097	NM  	2001	4	5	CA010313015      	1	20010304	G	2913	570347	PUMP            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			13770	3804 		MX452601C					(CAN) HYDRAULIC PUMP FAILED CAUSING FAILURE OF NR 1 HYDRAULIC SYSTEM.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040500098	20010405	00098	CE  	2001	4	5	CA010313016      	1	20010209	G	2435	SBC9401	RELAY           	PRESTOLITE  	MHB4016     	BEECH 	76    	76          	1153005	CE  										LT STARTER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			10775			30000047					(CAN) LT ENGINE STARTER REMAINED ON AFTER SWITCHING STARTER OFF. STARTER RELAY HAD STUCK ON DUE TO ERRODED CONTACTS. STA	RTER SUBSEQUENTLY OVERHEATED AND FUSED ITSELF. THIS CONDITION CAUSED ALL ELECTRICAL POWER AVAILABLE FROM THE AIRCRAFT CH	ARGING SYSTEM AND BATTERY TO GO TO THE STARTER AS A DEAD SHORT, THEREFORE ALL ELECTRICAL SYSTEMS WENT COMPLETELY DEAD IN	 APPROXIMATELY 30 SECONDS.			1	L	7	2 	3O			 	A29CE   					 
2001040500099	20010405	00099	CE  	2001	4	5	CA010313017      	1	20010215	G	7721	RHM38E	SPARK PLUG      			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G6D   	 	EA  					ENGINE	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			300  								(CAN) IN CRUISE PILOT REPORT RT ENGINE SURGING, THEN COMPLETELY ROUGH RUNNING. ENGINE SHUTDOWN, AIRCRAFT LANDED SAFELY. 	COMPRESSION TEST REVEALED ONE WEAK CYLINDER 50/80 PSI. BOTH SPARK PLUGS IN THAT CYLINDER SHORTED DUE TO BEING PEENED OVE	R BY FOREIGN OBJECT BOUNCING BACK AND FORTH IN CYLINDER. SUSPECT CERAMIC PIECE FROM A PLUG CAME OFF AND DID DAMAGE, HOWE	VER PIECE NOT FOUND, NEW CYLINER ASSEMBLY INSTALLED, SPARK PLUGS ARE RECONDITIONED IN HOUSE USING CHAMPION PLUG CLEANER/	TESTER.		1	L	7	2 	3O	3	O	 	A29CE   	E286				 
2001040500149	20010405	00149	EA  	2001	4	5	CA010313019      	2	20010228	G	7414	10382681	CAPACITOR       	BENDIX      	D6LH3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	FAILED          	W				K	 	 	 	NONE                    				R	 	 	PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			124  								(CAN) AIRCRAFT HAD FLOWN 2-3 HOURS ENGINE SHUT DOWN TO UNLOAD PASSENGERS. PILOT STARTED 1 ENGINE BUT 2ND WOULD NOT START	. PROBLEM WAS INVESTIGATED AND CAPACITOR FOUND U/S. CAPACITOR REPLACED AND ENGINE STARTED. WE HAVE HAD 3 SUCH CASES IN T	HE LAST MONTH. WE HAE TESTED THE U/S CAPACITORS AS PER MANUFACTURERS INSTRUCTIONS AND CAPACITORS CHECK OUT SERVICEABLE. 	WE HAVE ALSO NOTICED THAT POINTS ARE NOT LASTING AS LONG IN THE MAGS. ALL CAPACITORS WERE REPLACED AS PER TELEDYNE CSB 6	62A.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001040500154	20010405	00154	CE  	2001	4	5	CA010313024      	1	20010309	G	2431		BATTERY         			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	MAIN BATTERY	FAILED          	W				A	 	 	 	UNSCHED LANDING         				H	G	J	ELECT. POWER LOSS-50 PC   	MULTIPLE FAILURE          	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) PILOT ENCOUNTERED COMPLETE (GREATER THAN 50 PERCENT) ELECT. FAILURE IN FLT. AFTER ATTEMPTING TO GET A/C RADIOS TO 	TRANSMIT/RECEIVE, PILOT SQUAKED RADIO FAILURE CODE. FURTHER ATTEMTPS AT GETTING OTHER ELECT. SYSS TO FUNCTION,  PILOT FO	UND THAT ALL ELECT. SYS WAS UNSERVICEABLE. A/C RETURNED TO POINT OF DEPTR & THEN CONTACTED TOWER ON LAND LINE.AFTER BRIE	F INSP , FOUND THAT A/C BATTERY COMPLETELY DISCHARGED. BATTERY (NEW & INST NOV.2000) ELECTROLYTE LEVEL INSP OK, BATTERY 	CHARGED OVERNIGHT. AFTER BATTERY CHARGED, GROUND RUN/FUNCTION CHECKED. NOTED WITH CHARGING SYS COMPLETELY LOADED UP, CHA	RGE IND. WEAK. SUSPECT BATTERY VOLTAGE INITY LOW & CHARGING SYS UNABLE TO KEEP UP WITH DE	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001040500155	20010405	00155	EU  	2001	4	5	CA010313025      	1	20010226	G	5302	3160S451010060	GUARD           			AEROSP	SA316 	SA315B      	8680615	EU  	TMECA 	ARTST3	ARTOUSTE3B  	60003	EU  					TAIL ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				2714 							(CAN) WHILE CLEANING AIRCRAFT, AME FOUND CRACK COMING FROM UNDER BOTTOM CLAMP.NEW TAIL ROTOR GUARD WAS INSTALLED.						1	G	7	1 	4U	3	U	 	H1IN    	E11N				 
2001040500159	20010405	00159	CE  	2001	4	5	CA010314003      	1	20010226	G	5610	10138402522	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA			5    								(CAN) WHILE IN CRUISE FLIGHT AT FL310 AND OAT -50 DEGREES C, FLIGHT CREW OBSERVED RT WINDSHIELD OUTER PANE CRACK DEVELOP	. CRACK WAS DIAGONAL IN LOWER INBOARD CORNER (APPROXIMATELY 6 INCHES). POH ABNORMAL CHECKLIST FOLLOWED AND FLIGHT RETURN	ED TO POINT OF DEPARTURE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001040500161	20010405	00161	WP  	2001	4	5	CA010314007      	2	20010312	G	7230	31037081	BEARING         			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					COMPRESSOR	WRONG PART      	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) GARRETT SB 72-0634 DATED AUG 17 1989 (OPTIONAL COMPLIANCE) LISTED COMPRESSOR BEARING P/N 3103708-1 AS REPL FOR P/N	 3101405-1. BULLETIN APPLICABLE TO ALL MODELS OF TPE 331 ENGINE WHICH PREV HAD P/N 3101405-1 BEARING. SUBSEQUENT REVISIO	N NR 1 TO SB DATED APR 27, 1990 DELETED SOME ENGINE MODELS FROM EFFECTIVITY LIST. ENGINE MODEL DELETED FROM LIST, HOWEVE	R IT NOT RECOMMENDED TO REMOVE ANY P/N 3103708-1 BEARINGS INST IN COMPLIANCE WITH T HE 1ST ISSUE OF SB- IN NOV 1998 P/N 	3103708-1 BEARING INST INTO ENGINE. SUBSEQUENET REVIEW OF LIFE LIMITED COMPONENTS IN ENGINE, AGAINST REQMTS OF SB 72-018	0 TBO REQMTS, INDICATED PART NO LONGER LISTED ON APPLICABLE LIFE LIMIT TABLES.	1	H	7	2 	3T	4	T	RT	A10SW   	E4WE				 
2001040500162	20010405	00162	NE  	2001	4	5	CA010314009      	3	20010218	G	6114	7827015	HUB             			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LT PROPELLER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9085 								(CAN) DURING ROUTINE MAINTENANCE CHECK, FOUND LEFT PROPELLER ASSEMBLY HAD EVIDENCE OF OIL LEAK. UPON FURTHER INVESTIGATI	ON LEAK WAS FOUND TO BE COMING FROM NR 4 BLADE. AFTER REMOVING THE LEFT NR 4 BLADE THE OUTER BEARING RACE WITHIN THE PRO	PELLER HUB WAS FOUND TO BE CRACKED AND GALLED.LEFT PROPELLER HUB, PROPELLER ACTUATOR, AND 3 BLADES WERE REPLACED DUE TO 	OIL CONTAMINATION AND AN ADDITIONAL BEARING RACE FOUND GALLED. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001040500167	20010405	00167	SO  	2001	4	5	CA010314023      	1	20010223	G	5620	45099013	WINDOW          			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					FUSELAGE	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA			12355								(CAN) - THE AIRCRAFT WAS CLIMBING THROUGH 16,000 FEET WHEN THE CABIN PRESSURIZATION WAS LOST. - THE PILOTS INITIATED EME	RGENCY DESCENT TO 10,000 FEET AND DECLARED EMERGENCY. - THE CAUSE FOR DEPRESSURIZATION WAS FOUND TO BE A BROKEN WINDOW I	N THE CABIN AREA (3RD WINDOW ON LT SIDE).- AIRCRAFT LANDED SAFELY WITH NO FURTHER INCIDENTS.				1	L	7	2 	3T	4	T	RT	A8EA    	E4EA				 
2001040500168	20010405	00168	EA  	2001	4	5	CA010314024      	1	20010121	G	2730	22D1174A	CONTROL CABLE   			SCWZER	SG2   	SGS233A     	8051606	EA  										ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  BEARING ASSEMBLY AFT END OF TORQUE TUBE ASSEMBLY, LT MOUNT NUTCONTACTING CABLE. SUSPECT ANGLE BLOCK (FAIRLEAD) AF	T END OF TORQUE TUBE  ASSEMBLY AMPLIFIED DAMAGE TO CAUSE CABLE WEAR IN EXCESS OF 50 PERCENT. FURTHER INVESTIGATION ONGOI	NG BY SCHWEIZER.				1	K	0	0 	  			 	G2EA    					 
2001040500169	20010405	00169	EU  	2001	4	5	CA010314026      	1	20010227	G	2133	9599091131	REGULATOR       			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	CABIN PRESSURE	CONTAMINATED    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2649 								(CAN) SAFETY VALVE FAILED TON OPEN WHEN CARRYING OUT 1500 HOUR PRESSURIZATION CHECK. FAILED SAFETY VALVE WAS REMOVED AND	 VALVE AND SENSE LINE WERE FOUND CONTAMINATED WITH JET FUEL. FUEL APPEARED TO HAVE COME FROM A PREVIOUSLY SEEPING FUEL F	ILTER BOWL SEAL AND HAD ENETRED THE OUTFLOW VALVE WHERE THE AMBIENT PRESSURE SENSE LINE PROTRUDES THROUGH THE PRESSURE B	ULKHEAD (APPROX 12 -14 INCHES AFT OF THE FUEL BOWL).			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001040500170	20010405	00170	SW  	2001	4	5	CA010314027      	1	20010223	G	3222		STRUT           			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360C1D6   	41514	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	NLG	CONTAMINATED    	W				O	 	 	 	OTHER                   				J		 	WARNING INDICATION        			LD	LANDING        	1			CA			1711 	1711 							(CAN) A/C HAD UNCOMMANDED NOSE GEAR RETRACTION UPON LDG. IT NOTICED DURING POWER PACK PRESSURE TEST THAT 700PSI ON UP SI	DE WHEN GEAR EXTENDING & THAT PRESSURE WOULD NOT DECREASE BELOW 50-100 PSI WHEN GEAR WAS  FULLY EXTENDED.RESIDUAL PRESSU	RE PREVENTING DETENT PINS FROM ENGAGING. HYDRAULIC POWER PACK REMOVED & DISASSEMBLED.  FOUND ONE 8 OF INCH OF BLACK SLUD	GE & 1 X 5 INCH PIECE OF PAPER IN RESERVOIR.VALVE BODY ALSO DISSASSEMBLED. FOUND GEAR UP CHECK VALVE O-RING HARD & BRITT	LE & SEATS OF MOST OF VALVES COVERED WITH SLIMY GOO. NOSE GEAR ACTUATOR DISASSEMBLED.  MAIN PRESSURE O-RING MS28775-117 	NOTICED TO BE ROLLED.	1	L	7	1 	3O	3	O	 	A12SO   	1E10	5	C	P9EA	 
2001040500221	20010405	00221	EA  	2001	4	5	CA010320010      	1	20010308	G	5610	NP1393212	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) RT WINDSHIELD INNER PLY FOUND CRACKED, UNIT REPLACED AND AIRCRAFT BACK IN SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500222	20010405	00222	EA  	2001	4	5	CA010320013      	1	20010308	G	3234		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					MLG SELECTOR	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT LANDING GEAR WOULD NOT RETRACT, ANTI-SKID FAIL MESSAGE SHOW ON EICAS. MAINTENANCE REPLACED LANDING	 GEAR HANDLE AND AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500223	20010405	00223		2001	4	5	CA010320014      	4	20010308	G	3417	8220371140	ADC             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					E/E BAY	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE STABILIZER TRIM CH2 AND MACH TRIM FAILED. MAINTENANCE REPLACED ADC AND AIRCRAFT BACK IN SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001040500224	20010405	00224	CE  	2001	4	5	CA010320018      	1	20010228	G	2820	120010679	LINE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					FUEL DISTRIBUT	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1970 								(CAN) LINE ASSEMBLY - FUEL, STRAINER TO ELBOW FOUND CHAFING AGAINST RT NOSE GEAR STEERING BOOT.1.50 INCH X 0/032 INCH TU	BING FOUND WORN BY 0/018 INCH ON ONE SIDE. PART HAS BEEN REPLACED WITH A NEW LINE ASSEMBLY - FUEL AND PROTECTED WITH NYL	ON SPIRAL WRAP.				1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2001040500227	20010405	00227	EU  	2001	4	5	CA010320021      	1	20010214	G	2910		LINE            			AIRBUS	310   	A310304     	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					HYDRAULIC SYS	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN)  PILOT OBSERVED GREEN SYSTEM HYDRAULICS WAS LOOSING FLUID. AIRCRAFT DIVERTED TO YYT. HYDRAULIC LINE IN NR 1 ENGINE	 PYLONFOUND LOOSE. LINE TIGHTENED AND LEAK CHECK CARRIED OUT SERVICEABLE.					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2001040500233	20010405	00233	SO  	2001	4	5	CA010322002      	1	20010208	G	3242		LINER           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					BRAKES	DESTROYED       	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			43   								(CAN) WHILE CONDUCTING A GENERAL WALK AROUND FOR A PRE-PURCHASE, THE INBOARD PRESSURE PLATE SIDE OF THE BRAKE CALIPERS, 	THE BRAKE LINERS WERE TOTALLY DESTROYED, RESULTING IN THE STEEL PRESSURE PLATE TO COME IN FULL CONTACT WITH THE BRAKE DI	SC WHICH CREATED DEEP GROOVES AND SIGNIFICANT AMOUNT OF HEAT TO DISCOLOR THE PRESSURE PLATES AND DISCS.				1	L	7	2 	3O	3	O	 	A7SO    	E9CE				 
2001040500239	20010405	00239	NM  	2001	4	5	CA010322012      	1	20010317	G	4920		COMPRESSOR      			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					APU	MAKING METAL    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			41944	881  							(CAN) THE AIRCRAFT WAS CLIMBING OUT OF VANCOUVER WHEN THE APU DID AN AUTO SHUT DOWN AND THE APU FIRE HANDLE ILLUMINATED.	 THE FIRE HANDLE WAS PULLED BUT THE BOTTLE WAS NOT DISCHARGED DUE TO THE FIRE INDICATION GOING OUT. THE AIRCRAFT RETURNE	D TO VANCOUVER WHERE THE APU AREA WAS INSPECTED AND NO EVIDENCE OF A FIRE WAS DISCOVERED. THE APU WAS PLACED ON MEL AND 	THE AIRCRAFT WAS RELEASED TO SERVICE. FURTHER INVESTIGATION LATER IN THE DAY FOUND THAT THERE WAS METAL FRAGMENTS FOUND 	IN THE INTAKE OF THE APU AND THE APU WAS REMOVED FROMTHE AIRCRAFT. IT WILL BE RETURNED TO THE OVERHAUL FACILITY FOR DISA	SSEMBLY AND REPAIR.	2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001040500240	20010405	00240	EU  	2001	4	5	CA010323002      	1	20010217	G	2701	AS2219	CONTROL CABLE   	SIREN       	S1609       	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					CARGO HOOK	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA						876					(CAN) MANUAL / EMERGENCY RELEASE CABLE SHEATH BROKEN AWAY FROM FERRULE / SLEEVE WHERE CABLE ASSEMBLY ATTACHES TO THE CAR	GO HOOK.THE CARGO SUSPENSION SYSTEM (SWING) ALLOWS FOR A LOT OF MOVEMENT OF THE CARGO HOOK. THERE APPEARS TO BE A LOT OF	 FLEXING OF THE CABLE ASSY WHERE IT ATTACHES TO THE CARGO HOOK LEADING TO FAILURE OF THE CABLE SHEATH.THIS FAILURE RESUL	TED IN AN UNCOMMANDED LOAD RELEASE.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040500241	20010405	00241	NE  	2001	4	5	CA010323003      	2	20010309	G	7530	2496722	WASHER          	BENDIX      	153212A     	DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	120   	PW120       	 	NE  					VALVE SEALS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						RF4252					(CAN) COMPRESSION WASHER CRACKED AND JAMMED BETWEEN THE VALVE SEAL AND SEALING SURFACE PREVENTING THE A SIDE FROM COLOSI	NG.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001040500243	20010405	00243	EA  	2001	4	5	CA010323005      	1	20010314	G	5530	C6TFM102529	ADAPTER         			DHAV  	DHC6  	DHC6        	2802606	EA  										VERTICAL STAB	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOWER LT MOUNTING / MATING SURFACE INCORRECTLY MACHINED. SURFACE WAS MACHINED CYLINDRICALLY INSTEAD OF SPHERICAL C	ONVEX. IF INSTALLED THE MATING SURFACES WOULD NOT MATCH CAUSING STRESS AND POSSIBLE FAILURE OF THE MOUNT. CONCERNED THAT	 MORE WERE PRODUCED AND INSTALLED FROM THE SAME BATCH.				1	H	7	2 	3T			RT	A9EA    					 
2001040500244	20010405	00244	SO  	2001	4	5	CA010323006      	1	20010307	G	7721	LW16740	EXHAUST VALVE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 5 CYLINDER	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1724 								(CAN) PILOT REPORTED HIGH OIL TEMP VERNATHERN REPLACED AND ON GROUND RUN ENGINE RAN ROUGH. LARGE AMOUNT OF OIL NOTED COM	ING FROM SNIFFLE VALVE MIXED WITH FUEL. SPARK PLUGS REMOVED AND FOUND THOSE REMOVED FROM NR 5 CYLINDER WERE DAMAGED. REM	OVED CYLINDER AND FOUND 1/3 OF VALVE FACE (EXHAUST) MISSING. REPLACED CYLINDER AND CHECKED ALL SCREENS AND FILTERS.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001040500246	20010405	00246	CE  	2001	4	5	CA010323008      	1	20010302	G	5751	991300003	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					RT AILERON	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13438								(CAN) WHEN CHECKING SB 57-3148 IT WAS NOTICED THAT THIS AILERON WAS ALSO CRACKED AS PER SB 57-3148. KIT 109-4011-1 INSTA	LLED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001040500249	20010405	00249	CE  	2001	4	5	CA010323011      	1	20010313	G	5610	11450431S	WINDSHIELD      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	COCKPIT	CRACKED         	W				O		 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA			7057 								(CAN) ON DESCENT IN YWG PILOT HEARD SNAPING AND CRACKING AS THE OUTER LAYER OF LT WINDSHIELD SHATTERED. THEY DESCENDED T	O YWG ASKING FOR PRIORITY LANDING WITHOUT INCIDENT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2001040500250	20010405	00250	CE  	2001	4	5	CA010323013      	1	20010315	G	7603	S351	CLAMP           	CESSNA      		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					THROTTLE CABLE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THROTTLE SHEAF HAD VIBRATED LOOSE FROM CONNECTING CLAMP WHICH LEFT NO CONTROL FOR THROTTLE ADJUSTMENT. THROTTLE CA	BLE WAS RE-POSITIONED IN THE SHEAF AND NEW HARDWARE WAS INSTALLED.AIRCRAFT WAS GROUND UN AND ALL PARAMETERS NORMAL.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001041600458	20010416	00458	SO  	2001	4	16	CA010402004      	1	20010306	G	7810	5005500	EXHAUST STACK   			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFTER A FLIGHT, THE PILOTS REPORTED A CRACK AT THE INNER WELD SEAM OF THE LE OUTBOARD EXHAUST STACK.						1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2001041600459	20010416	00459	CE  	2001	4	16	CA010402005      	1	20010310	G	5310	05121871	DOOR FRAME      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E3D     	41508	EA  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8970 								(CAN) LOWER AFT DOOR POSTS INSPECTED PER SEB 97-1 AND FOUND LT CRACKED. INSTALLED SERVICE KITS SK172-149-1 AND -2 TO COR	RECT.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2001041600460	20010416	00460	NM  	2001	4	16	CA010402006      	1	20010309	G	5720	82710038101	FITTING         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	RUDDER PEDAL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28935								(CAN) THE PART WAS CRACKED TWO-THIRDS OF THE CIRCUMFERENCE AROUND THE RAISED BOSS (CASTING) NEAR THE RADIUS. THE TOP END	 FITTING WAS REPLACED IN ACCORDANCE WITH THE MAINTENANCE MANUAL AND CHECKED - SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001041600466	20010416	00466	EA  	2001	4	16	CA010403003      	1	20010313	G	5340	601350061	BEAM            		60135006    	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF341A      	 	NE  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK A CRACK WAS FOUND IN THE ENGINE SUPPORT BEAM LOWER WEB BETWEEN FS 625.30 AND FS 640.00 NEAR LBL 36.	20. THE CRACK WAS LOCATED IN THE CORNER OF ACCESS PANEL (P/N 601-35006-39) LANDING AND ENDED NEAR THE PANEL EDGE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041600467	20010416	00467	EA  	2001	4	16	CA010403004      	1	20010313	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA											(CAN) PILOT REPORT LT WINDSHIELD INNER PLY BOTTOM LOWER CORNER CRACKED. WINDSHIELD REMOVED AND REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041600468	20010416	00468	EA  	2001	4	16	CA010403006      	1	20010314	G	4920		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	FIRE            	W				F	 	 	 	ACTIVATE FIRE EXT.      				A	 	 	FLAME/FIRE                			TX	TAXI/GRND HDL  	1			CA											(CAN) APU CAUGHT FIRE ON THE GROUND AFTER LANDING.FIRE WAS EXTINGUISHED BUT RELIT. FIRE DEPARTMENT EXTINGUISHED IT FOR G	OOD. APU WAS REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041600469	20010416	00469	EA  	2001	4	16	CA010403007      	1	20010314	G	5730		PANEL           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					LT WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT WING PLANK CRACKED AT WS 148.019 FOR ABOUT 1.2 INCHES LONG. THE RT HAS NO CRACK. THEY WILL PERFORM THE REO 601R	-57-21-130.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700098	20010417	00098	EA  	2001	4	17	CA010403011      	1	20010306	G	7603	C3CE12	CABLE           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  					THROTTLE	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING THE PRE-FLIGHT RUN-UP, THE THROTTLE CONTROL WAS NOT RESPONDING PROPERLY. INVESTIGATION FOUND THAT THE FLEX 	CABLE WAS BROKEN INSIDE THE TUBING.					1	H	7	1 	3R	3	R	 	A815    	5E2				 
2001041700099	20010417	00099	EA  	2001	4	17	CA010403012      	1	20010305	G	7721	357285	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					NR 3	CRACKED         	W				O	 	 	 	OTHER                   				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA				1184 							(CAN) DURING A FLIGHT THE PILOT WAS FEELING AN ENGINE VIBRATION. HE REDUCED POWER AND CONTINUED HIS FLIGHT. ON MAINTENAN	CE THE NR 3 CYLINDER WAS FOUND CRACK FROM FRONT SPARK PLUG HOLE TO THE REAR.					1	H	7	1 	3R	3	R	 	A815    	E142				 
2001041700130	20010417	00130	NE  	2001	4	17	CA010403013      	2	20010312	G	8530	357285	HOUSING         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					ROCKER	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA				1199 							(CAN) DURING A FLIGHT, THE PILOT FELT AN ENGINE VIBRATION AND POWER REDUCTION.  HE LANDED ON A LAKE. MAINTENANCE FOUND A	 CYLINDER WITH ROCKER HOUSING BROKEN.					1	H	7	1 	3R	3	R	 	A815    	E142				 
2001041700131	20010417	00131	CE  	2001	4	17	CA010403014      	1	20010312	G	5520	50350055	FITTING         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					LT ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			12195								(CAN) - LEFT ELEVATOR FITTING FOUND CRACKED AT UPPER HOLE.  NEW FITTING P/N 5035005-3 INSTALLED.						1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001041700132	20010417	00132	SO  	2001	4	17	CA010403015      	1	20010219	G	3242	492152	VALVE           			PIPER 	PA44  	PA44180     	7104402	SO  										PARKING BRAKE	BENT            	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA			3818 								(CAN) PILOT REPORTED PARK BRAKE APPLYING ITSELF. NOTICED ONCE ON TAKEOFF ONCE ON LANDING.  CONFIRMED BY APPLYING SLIGHT 	PRESSURE TO PARK BRAKE SELECTOR TO THE OFF POSITION. UNIT REPLACED WITH SERVICEABLE UNIT, WHICH WAS SERVICED WITH NEW  O	-RINGS AND SYSTEM BLED GROUND CHECKED OK.				1	L	7	2 	3O			 	A19S0   					 
2001041700133	20010417	00133	EA  	2001	4	17	CA010404002      	1	20010305	G	3231	83231014003	ROD             			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	LT MLG DOOR	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			22260								(CAN) ON WALKAROUND INSPECTION, THE LT AFT OUTBOARD MLG DOOR ACTUATING ROD WAS FOUND TO BE BROKEN. THE DOOR OPENING ASSI	ST SPRING PN 83231020-003VP WAS ALSO FOUND BROKEN. THE SPRING HAD FRACTURED IN THE MID COIL AREA AND SPECULATION IS THAT	 THE BROKEN SPRING FOULED THE DOOR ACTUATING ROD DURING THE LAST LANDING GEAR EXTENSION, KINKING AND BREAKING THE ROD. R	OD AND SPRING WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001041700134	20010417	00134	EA  	2001	4	17	CA010404003      	1	20010308	G	2820	DSC33810D	FITTING         			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	FUEL SYSTEM	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW REPORTED THE NR 1  -FUEL LOW PRESS-  CAUTION LIGHT WOULD ILLUMINATE AS SOON AS THE AUXILIARY FUEL 	PUMP WAS SELECTED OFF, BUT THE LIGHT WOULD GO OUT AT LOW POWER SETTINGS. MAINTENANCE INVESTIGATION REVEALED THAT A  FITT	ING ON THE MOTIVE FLOW LINE INSIDE THE FUEL TANK COLLECTOR BAY WAS LEAKING AND LIMITING THE OUTPUT FROM THE EJECTOR PUMP	S IN THE FUEL TANK. THE O-RINGS INSIDE THE FITTING WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TTAF 22,271 T	CAF 32,957.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001041700136	20010417	00136	EA  	2001	4	17	CA010404005      	1	20010313	G	2130	7G959	PRESSURE SWITCH 			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 1 ENGINE	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE FLIGHT CREW REPORTED THAT THEY HAD NO HIGH BLEED ON EITHER ENGINE. MAINTENANCE INVESTIGATION REVEALED THAT THE	 NR 1 ENGINE HIGH PRESSURE >65 PSI SWITCH WAS OUT OF TOLERANCE AND REPLACED IT. THE AIRCRAFT WAS RETURNED TO SERVICE. TH	E NR 1 & 2 ENGINE HIGH BLEED SWITCHES OPERATE IN SERIES THROUGH A COMMON DELAY RELAY, THUS FAILURE OF ONE SWITCH WILL IN	HIBIT SWITCHING ON BOTH ENGINES.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001041700137	20010417	00137	NM  	2001	4	17	CA010404006      	1	20010319	G	3231	83232086001	ROD END         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG DOOR	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA											(CAN) THE FLIGHT CREW REPORTED AN AIRFRAME HOWL AFTER TAKEOFF AND LANDING GEAR RETRACTION. MAINTENANCE INVESTIGATION REV	EALED A BROKEN ACTUATING ROD FOR THE RT AFT NOSE LANDING GEAR DOOR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001041700138	20010417	00138	NE  	2001	4	17	CA010404007      	2	20010312	G	7200		ENGINE          			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					NR 2	VIBRATION       	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA			47894	930  							(CAN) A/C 722, MAR 12/2001, YQX, LOG SEQUENCE 0295200. TOP OF DESCENT WHEN THRUST LEVERS RETARDED, NR 2 ENGINE VIBRATION	 WAS INDICATING 2 MILS ON INLET AND 3.5 ON TURBINE. NR 2 START LEVER WAS VIBRATING. TRIED ENGINE ANTI-ICE AND THROTTLE M	OVEMENT, WITH NO CHANGE IN VIBRATIONS. ENGINE NR 2 THRUST LEVER RETARDED AND VIBS THEN REDUCED, BUT REMAINED RUMBLING UN	TIL ENGINE WAS SHUTDOWN. AIRCRAFT DIVERTED TO GANDER. NR 2 ENGINE WAS REPLACED AS PER WORK CARD 1125-2.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041700143	20010417	00143	WP  	2001	4	17	CA010405002      	1	20010328	G	6210	369D21100523	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2269 								(CAN) UPPER AND LOWER SKIN CRACKED AT STN 36.5. CRACKED FROM TRAILING EDGE TOWARDS LEADING EDGE 4.25 INCHES.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041700024	20010417	00024	CE  	2001	4	17	CA010405005      	1	20010302	G	3000	1143800465	HOSE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT BRAKE ASSY	BLOWN           	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED LT BRAKE DEICE FAIL LIGHT CAME ON IN FLIGHT. DEICE SYSTEM WAS TURNED OFF AND AIRCRAFT CONTINUED TO 	DESTINATION. UPON MAINTENANCE INVESTIGATION, THE FLEXIBLE BLEED AIR HOSE ASSY CARRYING HOT AIR TO BRAKE ASSY WAS FOUND B	LOWN. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001041700029	20010417	00029	SO  	2001	4	17	CA010406008      	2	20010321	G	8500		ENGINE          			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				95   							(CAN) PILOT/OWNER REPORTED NORMAL PRE-TAKEOFF START/RUN-UP PROCEDURES. NORMAL TAKEOFF WABASCA, ALBERTA,  IN ROUTE, EXPER	IENCED A SURGE (OVERBOOST) RT ENGINE. ADJUSTED POWER BACK TO CRUISE, LT AND RT. WHILE ADJUSTING MIXTURE - RIGHT ENGINE '	'THE ENGINE BLEW UP''. ENGINE SHUT DOWN AND PROPELLER FEATHERING PROCEDURES CARRIED OUT. PILOT ELECTED TO CONTINUE FLIGH	T TO CYEG. ENGINE TO BE REMOVED AND SENT FOR INVESTIGATION/REPAIR - FURTHER REPORT PENDING.			1	L	7	2 	3O	3	O	 	A7CE    	E7CE				 
2001041700031	20010417	00031	EA  	2001	4	17	CA010406010      	2	20010316	G	8520	11F20022D3	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4946 	1340 							(CAN) DURING ROUTINE 50 HR INSP, BROKEN CYLINDER HOLD DOWN STUD FOUND SITTING IN BOTTOM OF ENGINE COWLING. LATER INVEST.	, BROKEN STUDS ORIG LOCATION LOCATED ON FRONT INNER CYLINDER OF RT ENGINE. UPON CONSULTATION WITH AERO RECIP ENGINES OF 	WINNIPEG, MANBITOBA, REMOVAL OF CYLINDER COMPLETED FOR FURTHER INVEST. ONCE REMOVED, IT FOUND THAT BROKEN STUD NOT THROU	GH BOLT BUT NORMAL SHORT STUD. ANY FURTHER DISCUSSION ABAUG FURTHER REPAIRS OF HOLD DOWN STUD HALTED ONCE LARGE CRACK OF	 AT LEAST 6 IN FOUND AHEAD OF AFFECTED CYLINDER ON CRANK CASE. CRACK WOULD POSSIBLY NOT HAVE BEEN DETECTED AS IT NOT AL 	ALL CLEARLY VISIBLE UNTIL REMOVAL OF CYLINDER.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001041700032	20010417	00032	CE  	2001	4	17	CA010406011      	1	20010316	G	2435	23085001	STARTER GEN     			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					RIGHT	FAILED          	W				O	 	 	 	OTHER                   				H	J	 	ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA				288  		2518					(CAN) WHILE IN CRUISE FLIGHT THE RT GENERATOR FELL OFF LINE AND WOULD NOT RESET. AIRCRAFT CONTINUED TO FUEL STOP AIRPORT	. MAINTENANCE DISCOVERED FAULTY STARTER/GENERATOR WITH OBVIOUS DAMAGE TO FORWARD (DRIVE SPLINE END) BEARING. GENERATOR S	ENT FOR OVERHAUL WITH REQUEST FOR BEARING EVALUATION.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001041700044	20010417	00044	SO  	2001	4	17	CA010409010      	2	20010329	G	7314	64621011A3	PUMP            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE FUEL	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				J	 	 	WARNING INDICATION        			TO	TAKEOFF        	1			CA				445  							(CAN) LT ENGINE WOULD NOT RUN WITHOUT AUXILIARY ELECTRIC FUEL PUMP ON HIGH. FUEL PUMP AT DRIVE REPLACED, GROUND CHECKED 	OK.					1	L	7	2 	3O	3	O	 	3A25    	E8CE				 
2001041700045	20010417	00045	CE  	2001	4	17	CA010409017      	1	20010227	G	3240	AE2463509GO150	HOSE            			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					MLG BRAKES	LEAKING         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA			1214 								(CAN) FLIGHT CREW REPORTED RT BRAKE SOFT, AND BRAKE PRESSURE LOW WARNING ON, CREW LANDED AIRCRAFT NORMALLY USING THRUST 	REV. AND BRAKES. MAINTENANCE FOUND LEAKING BRAKE HOSE, HOSE REPLACED, BRAKE SYSTEM BLEED.HOSE DATE: AEROQUIP TELFLON HOS	E (FOR SKYDROL BRAKE FLUID)  A/PT 04-98, 3000 PSI.				2	L	7	2 	4F	4	F	RT	A22CE   	E25EA				 
2001041700046	20010417	00046	CE  	2001	4	17	CA010409018      	1	20010326	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9135 								(CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS, ALSO  TRANSPORT CANADA SDA AV-2000-06.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001041700047	20010417	00047	CE  	2001	4	17	CA010409019      	1	20010321	G	5510	04320041	BRACKET         			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  					HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5116 								(CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS. ALSO SDA AV-2000-06. AFFTER REMOVAL OF BRACKET ALSO FOU	ND REAR SPAR REINFORCEMENT P/N 0432001-15 CRACKED (HOLES ARE ALSO ELONGATED) ALONG TOPSIDE, AFTER REMOVAL OF REAR SPAR. 	REINFORCEMENT BOTH L/H AND R/H SPARS P/N 0432001-56.				1	H	7	1 	3O	3	O	 	3A19    	E252				 
2001041700048	20010417	00048	CE  	2001	4	17	CA010409020      	1	20010326	G	5510	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13221								(CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS, ALSO  TRANSPORT CANADA SDA AV-2000-06.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001041700049	20010417	00049		2001	4	17	CA010410006      	4	20010322	G	3418		COMPUTER        			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					STALL WARNING	FAILED          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) STALL FAIL MESSAGE AFTER GEAR UP. MAINTENANCE CARRY LRU DIAGNOSTICS AND OPERATIONAL CHECK, NO FAULT FOUND AT THIS 	TIME AND AIRCRAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700050	20010417	00050	EA  	2001	4	17	CA010410008      	1	20010322	G	5610		WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING CRUISE SIDE WINDOW SHATTERED, CREW DIVERTED AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REMOVED AND REPLACE	D SIDE WINDOW.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700051	20010417	00051	EA  	2001	4	17	CA010410009      	1	20010322	G	4920		APU             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					APU BAY	FAILED          	W				F	 	 	 	ACTIVATE FIRE EXT.      				A	 	 	FLAME/FIRE                			IN	INSP/MAINT     	1			CA											(CAN) APU SELECTED DURING DESCENT, FIRST TIME DID NOT START, PILOT RESELECT APU START. SECOND TIME APU START WITHOUT ANY	 INCIDENT. AIRCRAFT PULLED UP TO THE GATE, MAINTENANCE MET PILOT AT THE AIRCRAFT, ENGINE HAD BEEN SHUTDOWN WITH THE APU 	RUNNING. MAINTENANCE FOUND FIRE COMING OUT OF THE EXHAUST, PILOT EXECUTED THE FIRE EMERGENCY MEMORY ITEMS AND CONTACTED 	THE FIRE DEPARTMENT. FIRE DEPARTMENT SHOWED UP AND SPRAYED THE APU COMPARTMENT WITH EXTINGUISHANT.APU AND APU FIRE SYSTE	M DEFERRED AND AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700052	20010417	00052	EA  	2001	4	17	CA010410010      	1	20010322	G	3040	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			1353 								(CAN) AFTER LANDING CREW REPORT LT WINDSHIELD SHATTERED. MAINTENANCE REMOVED AND REPLACED WINDSHIELD AND AIRCRAFT BACK I	N SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700053	20010417	00053	EA  	2001	4	17	CA010410012      	1	20010322	G	2421	755469B	IDG             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1	DAMAGED         	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			13233	13233							(CAN) DURING CRUISE, CREW NOTED AN IDG NR 1 FAULT MESSAGE, FOLLOWED BY OIL PRESSURE FLUCTUATIONS, OIL PRESSURE WARNING. 	THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT MADE AN UNEVENTFUL SINGLE ENGINE LANDING. MAINTENANCE INVSTIGATION SUGGEST THA	T IDG DISCONNECT DID NOT ACTIVE. IDG, ACCESSARY GEAR BOX AND LUBE/SCAVENGE PUMP WERE REMOVED AND REPLACED. OIL FILTER AN	D OIL SAMPLE WERE SENT FOR ANALYSIS.AIRCRAFT HAS RETURNED IN SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700054	20010417	00054	EA  	2001	4	17	CA010410014      	1	20010324	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			2877 								(CAN) ENROUTE ATLANTA TO COLUMBIA SC, FIRST OFFICERS WINDSHIELD SHATTERED. CREW LANDED UNEVENTFULLY IN COLUMBIA.THE DAMA	GE TO THE WINDSHIELD IS ON THE INNER SURFACE AND GLASS FRAGMENTS WERE FOUND ON THE GLARESHIELD BY MAINTENANCE. WINDSHIEL	D WAS REPLACED AND TESTED I.A.W. AMM.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700055	20010417	00055	EA  	2001	4	17	CA010410023      	1	20010330	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA			40   								(CAN) ON DESCENT INTO WICHITA THE LT WINDSHIELD CRACKED. AIRCRAFT WAS FERRIED TO MEMPHIS AND THE WINDSHIELD WAS REPLACED	.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700056	20010417	00056	EA  	2001	4	17	CA010410025      	1	20010402	G	5610	NP1393212	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE RT WINDSHIELD MIDDLE PLY WAS FOUND CARACKED AIRCRAFT ON PARKING. THE AIRCRAFT DID A FERRY FLIGHT TO MORLAIX. T	HE WINDSHIELD WAS REPLACED AT THE MAINTENANCE BASE AS PER AMM 56-11-01.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700057	20010417	00057	EA  	2001	4	17	CA010410027      	1	20010402	G	5210	601R3189233	ROD             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) IN PITT DURING TURN AROUND, FLT ATTENDANT & CREW WERE UNABLE TO CLOSE MAIN PASSENGER DOOR.  AFTER MULTIPLE ATTEMPT	S CREW WERE ABLE TO CLOSE DOOR BUT WERE UNABLE TO RE-OPEN FROM INSIDE. NORTHWEST AIRLINK MAINT,  ENGINEERING & BOMBARDIE	R FSR WERE SENT TO PITT TO VERIFY REPORTED EVENT. IT NOTICED THAT WHEN ATTEMPTING TO SLOWLY CLOSE DOOR FROM INSIDE HANDL	E WOULD JAM HALF WAY.  WHILE HAVING HANDLE HALF WAY,  TORQUE TUBES GREEN  LINES WERE ALIGNED, WITH SECONDARY LOCK ALIGNM	ENT LINE OFF BY APPROX 3/4 OF AN INCH. FLAPPER DOOR ALSO NOT FULLY CLOSED. LATCH BOX ASSY & ACTUATING RODS HAD NO VISUAL	 DEFECTS.THE RIG PINS WERE INST PER AMM. THE CNTL ROD ASSY	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700058	20010417	00058	EA  	2001	4	17	CA010410030      	1	20010403	G	5610	601R2303310	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA											(CAN) THE RT WINDSHIELD INNER PLY CRACKED WHILE THE AIRCRAFT WAS IN DESCENT. THE WINDSHIELD WAS REPLACED AND THE AIRCRAF	T RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001041700059	20010417	00059	SO  	2001	4	17	CA010411003      	1	20010315	G	5341	4A0021001	TAPER PIN       			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					WING	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT TT: 18965.4 HRS CYC: 24946 PART TT: APP. 7200 HRS. IF REPLACED AT LAST C12 INSP.  TAPER PIN CONE BUSHINGS	 ALSO AFFECTED. PIN DID NOT COME OUT WITH MANUFACTURERS SPECIAL TOOL PRESS. NEW PINS AND CONES REQUIRED. PIN HAD TO BE D	RILLED AND CUT BY MACHINIST.IT APPEARS ITL P/N 1027251T2, MASTINOK 6856K JOINTING COMPOUND MADE BY PRC PESOTO INTERNATIO	NAL HAS NOT BEEN UTILIZED AT INSTALLATION AS SPECIFIED.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2001041700060	20010417	00060	EA  	2001	4	17	CA010411004      	1	20010312	G	5300		SKIN            			FRCHLD	F27   	F27F        	3373008	EA  	RROYCE	DART  	DART5297E   	54507	EU  					FUSELAGE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			36671								(CAN) CRACK FOUND AT TOP REAR CORNER OF FRONT CARGO DOOR FRAME (FUSELAGE). THE PROBLEM IS ONE BAD FLUSH RIVET CRACK FROM	 RIVET TO SKIN EDGE.  CRACK FOUND ON DAILY INSPECTION.REPAIR DONE AT STATION 181.102 AND 14 INCH ABOVE W.L. 0 LINE.					2	H	7	2 	4T	4	T	 	7A1     	E297				 
2001041700061	20010417	00061	CE  	2001	4	17	CA010411008      	1	20010316	G	2822	RG34720A	PUMP            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL BOOST	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA				853  							(CAN) CARRYING OUT A DAILY INSPECTION ON MARCH 16, AFTER RETURNING FROM A TRAINING FLIGHT. FOUND THAT THE ENGINE DRIVEN 	FUEL BOOST PUMP P/N 91-38003 THAT IS MOUNTED ON THE REAR OF ENGINE S/N PCE-81053 WAS LEAKING FUEL AROUND THE BASE OF THE	 VALVE THAT IS INSTALLED ON THE FUEL BOOST PUMP.ORDERED A NEW FUEL PUMP FROM TC STORES IN OTTAWA INSTALLED ON AIRCRAFT A	ND FOUND IT TO BE SERVICEABLE FOR FLIGHT, NO LEAK FOUND.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2001041700062	20010417	00062	EA  	2001	4	17	CA010411011      	2	20010326	G	7230		COMPRESSOR      								PWA   	PT6   	PT6A28      	 	EA  					ENGINE	FAILED          	W				K	 	 	 	NONE                    				C	 	 	F.O.D.                    			IN	INSP/MAINT     	1			CA											(CAN) THE COMPRESSOR HAD SUSTAINED FOD. AFTER REPAIR, PT AND CT VANE AREA ADJUSTMENT, THE ENGINE WAS RELEASED WITH SIMIL	AR TO NEW PERFORMANCE.										4	T			E4EA				 
2001050700356	20010507	00356	NE  	2001	5	7	CA010411013      	2	20010316	G	7260	311196801	TOWERSHAFT      								PWA   	120   	PW120A      	 	NE  					SPIRAL GEAR	FRACTURED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CAUSE OF THE IN FLIGHT SHUTDOWN WAS A FRACTURED TOWERSHAFT, RESULTING IN A LOSS OF DRIVE TO THE FUEL AND OIL P	UMPS. FAILURE ANALYSIS OF THE TOWERSHAFT INDICATES THAT THE FRACTURE RESULTED FROM FATIGUE AT THE OUTER SURFACE, LEADING	 TO A TWISTED DUCTILE FRACTURE WITH THE CENTRE OF THE SHAFT FAILING IN TENSILE MODE.THERE WERE NO IDENTIFIED WORKMANSHIP	 ERRORS RELATED TO THE FAILURE OF THE TOWERSHAFT. 2001-04-12 TC: NO DEFINITE RESULT OF FAILURE WAS DETERMINED.								4	T			E20NE				 
2001050700360	20010507	00360	SW  	2001	5	7	CA010423005      	1	20010328	G	6420		BEARING         		212010704107	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TRUNNION	FAILED          	W				K	 	 	 	NONE                    				S	 	 	AFFECT SYSTEMS            			IN	INSP/MAINT     	1			CA			185  			AFS3682FM					(CAN) BAD BRINNELLING, TEFLON WORN AWAY.(FLAPPING BEARINGS)						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001050700361	20010507	00361	SW  	2001	5	7	CA010423006      	1	20010406	G	6220	206010189001	BEARING         	BELL        	206011100021	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				980  		JILM11164					(CAN) FAILURE OF ROLLER BEARING CAGE CAUSED ROLLERS TO BUNCH UP AND MISALIGN WITH RACES, SCORING RACES, ROLLERS AND HUB.	FAILURE WAS DETECTED BY AN ENGINEER OBSERVING PIECES OF METAL IN THE PURGED GREASE. PRIOR TO DISASSEMBLY NO RESTRICTED M	OTION WAS DETECTED, HOWEVER, PIECES OF FAILED CAGE SHOWED EVIDENCE OF BEING SQUASHED BETWEEN ROLLERS AND RACES. THIS COU	LD POTENTIALLY CAUSE A SEIZURE OF THE GRIP FEATHERING MOTION.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050700362	20010507	00362	CE  	2001	5	7	CA010423007      	1	20010315	G	5610	10138402521	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6*        	52043	EA  					COCKPIT	BROKEN          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) AIRCRAFT IN CRUISE FLIGHT 29,000 FEET ALTITUTE OAT 45 WEATHER CLEAR NO TURBULENCE. SIMULTANEOUS LOUD BANG AND LT (	PILOTS) WINDSHIELD (INNER PANE)INSTANT SPIDER WEB CRACKS.					2	L	7	2 	4T	3	T	RT	A24CE   	E2NE				 
2001050700363	20010507	00363	WP  	2001	5	7	CA010423009      	1	20010316	G	6320	269D2512311	GEAR            	DOUG        	369D25100505	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R TRANSMISSION	BROKEN          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			CA				2214 		U0312					(CAN) MAIN ROTOR TRANSMISSION REMOVED FOR MAKING METAL. UPON DISASSEMBLY IT WAS DISCOVERED THAT ON INPUT GEAR TOOTH HAD 	BROKEN OFF. THE TOOTH WAS FOUND IN THE SCAVENGE PUMP INTAKE.REMNANTS OF THE TOOTH WERE FOUND IN THE SCAVANGE SPRAY TUBE.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001050700364	20010507	00364	NM  	2001	5	7	CA010423011      	1	20010322	G	6210	A1561	BOOT            	ROBSIN      	A0052       	ROBSIN	R22   	R22BETA     	       	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR BLADE	LEAKING         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			393  								(CAN) AIRCRAFT PARKED OVERNIGHT WITH COVERS AND HEATERS ON THE ENGINE. OVERNIGHT TEMP -35C. PILOT HAD LEFT PRINCE GEORGE	, B.C., THE PREVIOUS DAY AND TEMP WAS ABOUT +5C AT CYXS. PILOT NOTED NO DEFECTS THE MORNING OF DEPARTURE ON HIS PRE-FLIG	HT AND AS HE REMOVED THE COVERS AND HEATERS. HE NOTED THAT OAT GAUGE READ -27 WHEN HE STARTED THE AIRCRAFT ON A WALK ARO	UND AFTER ARRIVING BACK TO PRINCE GEORGE, HE NOTED OIL ON THE ROTOR HEAD AND THE PYLON. REMOVED THE ROTOR BLADES AND FOU	ND THE INNER CLAMPS FOR THE BOOT LOOSE, TIGHTENED THEM AND REPLACED THE OIL. SUSPECT THAT WITH THE COLD WEATHER, THE BOO	TS GOT STIFF AND THEN SLIPPED ON THE SPINDLE. AIRCRAFT HAD BEEN OPERATED OUT OF WARM HANGAR PRIOR.	1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2001050700365	20010507	00365	EU  	2001	5	7	CA010423012      	1	20010329	G	2910	3408360821	HARNESS         			BAG   	JETSTM	JETSTM4112  	       	EU  	GARRTT	TPE331	TPE33110    	01514	WP  	ROTOL	R333	R333482F12  	GL  	OVERRIDE SWITCH	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) DURING CLIMB, THE FLAPS WOULD NOT OPERATE WITH THE CONTROL SWITCH. THE HYDRAULIC OVERRIDE HANDLE HAD TO BE USED TO	 FUNCTION THE FLAPS UP AND DOWN.THE OVERRIDE SWITCH WIRING HARNESS (P/N 340-4263110) WAS FOUND TO BE AT FAULT, ONE WIRE 	WAS BROKEN, THE RECOIL SPRING WAS BROKEN WHICH PROBABLY CAUSED THE WIRE TO BREAK DUE TO A LACK OF SUPPORT FROM THE SPRIN	G.			1	L	7	2 	4T	4	T	RT	A196    	E4WE	6	C	P61GL	 
2001050700367	20010507	00367	WP  	2001	5	7	CA010423018      	1	20010401	G	6210	500P2100101	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1711 			A393					(CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT TO FAA DATED 24 APR 01 EXPRESSING TRANSPORT CANADA CONCERN	S.(CADIS PROJECT REPORT 20010079. (CROSS REFER TO SDR 20010423019)					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001050700368	20010507	00368	WP  	2001	5	7	CA010423019      	1	20010409	G	6210	500P2100101	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2120 			A048					(CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT FAA DATED 24 APR 01 EXPRESSING TC CONCERNS. (CADIS PROJECT	 REPORT20010079). CROSS REFER TO SDR 20010423018.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001050700369	20010507	00369	EA  	2001	5	7	CA010424002      	2	20010316	G	7314		SHAFT           	SUNDSTRANDAI	02527730007 	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					FUEL PUMP	FAILED          	W				O	 	 	 	OTHER                   				X	J	 	ENGINE FLAMEOUT           	WARNING INDICATION        		CR	CRUISE         	1			CA				4463 		PE3224					(CAN) THE NR 2 ENGINE FLAMED OUT. AFTER THE PILOT LANDED THE AIRCRAFT SUCCESSFULLY, REMOVE THE AFCU, MFCU AND ENGINE DRI	VEN FUEL PUMP. I FOUND THE FUEL PUMP SPLINES WITH NO LUBRICATION AND WORN WELL BEYOND LIMITS. (NOTE: THE SPLINED ADAPTER	 WAS SPINNING FREELY ON PUMP INPUT SPLINES.)				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001050700370	20010507	00370	CE  	2001	5	7	CA010424003      	1	20010409	G	5510	043200146	RIB             			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					STABILIZER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION STABILIZER RIB 0432001-46 LT, CRACKED.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001050700372	20010507	00372	SW  	2001	5	7	CA010425004      	1	20010405	G	2435	230321380	BRUSHES         	LEARSIEGLER 	23032018    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					STARTER GEN	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				324  		4666					(CAN) STARTER-GENERATOR WAS INSPECTED BECAUSE OF PREVIOUS HISTORY OF PROBLEMS IN THIS AR4A. UPON INSPECTION FOUND 3 BRUS	H LEADS BROKEN OFF BRUSHES AND 3 SPRINGS BROKEN. THE STARTER GENERATOR HAS BEEN REMOVED FOR OVERHAUL. STARTER-GENERATOR 	LAST OVERHAULED AT CANADIAN AERO ACCESS, CALGARY AND INSTALLED ON AIRCRAFT AT 12445.8 BRUSHES HAD BEEN REPLACED AT 12653	.3STARTER-GENERATOR REMOVED AT 12769.8			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050700374	20010507	00374	EU  	2001	5	7	CA010426002      	1	20010327	G	2750	B001	SHAFT           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	SHEARED         	W				C	B	 	 	ABORTED TAKEOFF         	EMER. DESCENT           			B	A	 	SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                		AP	APPROACH       	1			CA			1898 								(CAN) ON SELECTION OF FLAPS DOWN, FLAPS CAUTION ON C.A.W.S. PANEL CAME ON. FLAPS WERE RESET & TRIED AGAIN. FLAPS CAUTION	 CAME ON AGAIN. A/C LANDED W/O FLAP. MULTIPLE RESETS WERE THEN TRIED ON GROUND WHICH WOULD CAUSE F LAP CCT BREAKER ON  B	ATTERY BUS TO POP. TROUBLE SHOOTING REVEALED 2 INIT E203 CODES (MORE THAT 20 TURNS DIFFERENCE BETWEEN L/H & R/H ROTATION	 SENSORS, THEN MULTIPLE E208 CODES (OVERLOAD CB POPPED), & E203 CODES AGAIN. AS AIRCRAF T WASHED SHORTLY BEFORE DEPTR, I	T IS FELT THAT R/H FLAP FROZE IN FLT CAUSING INIT E203 CODE. SUBSEQUENT RESETS CAUSED R/H INBOARD FLEX SHAFT TO SWELL & 	JAM IN ITS HOUSING CAUSING E208 CODES. DURING TROUBLE SHOOTING AFTER MORE RESETS, FLEX SHAFT EVENTUALLY BROKE CAU	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001050700375	20010507	00375	EU  	2001	5	7	CA010426003      	1	20010328	G	3252	5322012262	STRAP           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			495  								(CAN) NOSE GEAR BONDING STRAP P/N 532.20.12.262 WAS WRAPPED AROUND SHOCK STRUT P/N 571.10.12.353 AND HAD BENT THE STRUT 	SOME 70 DEGREES UP FROM ITS NORMAL POSITION. THE STRUT COULD NO LONGER OPEN AND CLOSE THE OIL COOLER DOOR UPON GEAR RETR	ACTION. BONDING STRAP REQUIRED REPLACEMENT AS WELL AS THE STRUT. BONDING STRAP APPEARS TO BE A BIT LONGER THAN REQUIRED 	TO ALLOW FOR THE NOSE WHEEL ASSEMBLE TO TURN, THEREFORE CAUTION IS ADVISED WHEN INSTALLING BONDING STRAP TO ENSURE THAT 	THE BONDING STRAP WILL NOT SAG ONTO THE SHCOK STRUT ASSEMBLE. FIVE GEAR CYCLES COMPLETED AND AIRCRAFT WAS RETURNED TO SE	RVICE. NO FURTHER ACTION WAS REQUIRED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001050700378	20010507	00378	NM  	2001	5	7	CA010426010      	1	20010303	G	5230	85230480104	SUPPORT         			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	COUNTER BALANCE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WE HAD AN INSPECTION OF THE BAGGAGE DOOR ON ONE OF OUR DASH 8S, S/N 357, PER TASK 5230/51 AND  DURING THAT INSPECT	ION, WE FOUND THE AFT COUNTER BALANCE SUPPORT P/N 85230480-104 WAS CRACKED. I AM SUBMITING A STRUCTURAL DEFECT REPORT FO	R S/N 257. AIRCRAFT S/N 357 WAS DONE ON 3-3-01 AND HAD A TAT 16.286.6 AND TCY 26, 179. PART REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001050700379	20010507	00379	NM  	2001	5	7	CA010426019      	1	20010403	G	3251	89923	LINK            		8900115     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	STEERING ACTU	SPLIT           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			22097	1081 		DCL2388900					(CAN) DURING AN INSPECTION, THE NOSEWHEEL STEERING ACTUATOR TELESCOPING ADJUSTABLE LINK WAS FOUND SPLIT (PULLED APART) A	ND THE ATTACH LOCKING BOLT FOR THE LINK WAS MISSING (P/N NAS 1304-7D).THE STEERING ACTUATOR ASSEMBLY WAS REPLACED AND AL	L FURTHER CHECKS COMPLETED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001050700380	20010507	00380	EA  	2001	5	7	CA010426025      	2	20010320	G	8520	LW16812	LIFTER          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			651  								(CAN) PILOT REPORTED VIBRATION ON LT & RT ENGINE ON RUN-UP. INSPECTED BOTH ENGINES, FOUND GOOD COMPRESSION, NO BROKEN EN	GINE MOUNT (COMMON ON THIS AIRCRAFT). REMOVED LIFTERS FOUND BADLY DAMAGED, DAMAGE ON CAMSHAFT AS WELL. FRONT SURFACE MIS	SING PIECES ON LIFTERS. BOTH ENGINES REMOVED (& PROP FOR FLUSHING) SEND TO LEAVENS AVIATION FOR REPAIR. NOTE: LIFTERS IN	SPECTED ON 500 HOUR SINCE OVERHAUL, NO DAMAGE AT THAT TIME. DAMAGE OCCUR WITHIN 150 HR SINCE THAT INSPECTION.			1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2001050700381	20010507	00381	EA  	2001	5	7	CA010426026      	1	20010403	G	3244	0276970	TIRE            			CNDAIR	CL604 	CL604       	       	EA  										MLG	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			534  			9181P00282					(CAN) A/C DEPARTED TOLUCA, MENCO & LANDED AT TORONTO. UPON ARRIVAL IT NOTED THAT NR 3 MAIN WHEEL TIRE MISSING ITS TREAD.	 GTAA OPS STAFF RPTED NO DEBRIS ON LDG RWY. THEREFORE SEPARATION, MOST LIKELY OCCURRED ON TAKEOFF FROM TOLUCA. BASED ON 	ATMOSPHERIC CONDITION AT TIME OF DEPTR, IT CALCULATED THAT ACTUAL SPEED SEEN BY WHEELS 162 KNOTS. IS WELL BELOW RATED SP	EED FOR TIRE: TIRE SHOWED NO SIGNS OF DAMAGE THAT WOULD HAVE LED TO SEPARATION. ALSO, TIRES ARE REGULARLY CHECKED FOR CO	RRECT TIRE PXS. AS RESULT OF SEPARATION, INBOARD RT FLAP INBD RT FLAP VANE&LOWER FWD SECTION OF RT PYLON, SUFFERED MINOR	 DENTS. ALSO RT MLG W.O.W. HARNESS BRACKET THAT AFFIXES TO CEILING OF GEAR BAY BECAME DISBONDED AS RESULT OF IMPACT.	2	L	7	2 	4F			RT	A21EA   					 
2001050700382	20010507	00382	WP  	2001	5	7	CA010426031      	2	20010330	G	7412	103784005	EXCITER         			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					IGNITION SYS	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA				893  							(CAN) ENGINE WOULD NOT START. FOUND IGNITION EXCITER UNSERVICEABLE. REPLACED UNIT.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE				 
2001050700385	20010507	00385	NE  	2001	5	7	CA010430008      	2	20010307	G	7200		ENGINE          			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					RIGHT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE HAD A RUMBLE SOUND AND WAS THROWING FLAMES OUT THE EXHAUST. CREW REPORTED COMPRESSOR STALL.ENGINE REMOVE	D FOR INVESTIGATION. REPLACED ENGINE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001050700389	20010507	00389	NE  	2001	5	7	CA010430016      	2	20010407	G	7200		ENGINE          			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					NR 1	FAILED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			49254								(CAN) DRUING FLIGHT ENGINE NR 1 EXPERIENCED A SUDDEN VIBS INCREASE TO 3.5 UNITS ON BOTH CHANNELS A & B, WARNING LIGHTS C	AME ON, ENGINE SHUT DOWN WAS ACCOMPLISHED.MCD CHECKS WAS C/O NOT DAMAGED, ENGINE BORESCOPE WAS C/O NO DAMAGE FOUND. FAN 	BLADES REMOVED CLEANED AND RE-INSTALLED, FAN CLAPPERS LUB.FAN TRIM BALANCE TO BE ACCOMPLISHED.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001050700391	20010507	00391	WP  	2001	5	7	CA010430018      	1	20010321	G	5230	1586301113	HANDLE          			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					CARGO DOOR	OUT OF ADJ      	W				A	 	 	 	UNSCHED LANDING         				N	 	 	FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AT 9,000 FEET, DURING CLIMB, ON F/E ANNUNICATOR PANEL CARGO DOOR LIGHTS ILLUMINATE, AIRCRAFT RETURNED TO MAIN BASE	. FOUND T HANDLE ADJUSTMENT OUT OF RIG, ADJUSTED IN ACCORDANCE WITH MAINTENANCE MANUAL 52-35-01 AND PROXIMITY SENSOR IN 	ACCORDANCE WITH 52-71-03.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001050700392	20010507	00392	EA  	2001	5	7	CA010430022      	1	20010406	G	5210		LOCK            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	OUT OF ADJ      	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) FLIGHT ATTENDANT REPORTED THAT SHE WAS UNABLE TO CLOSE AND LOCK THE PASSENGER DOOR. MAINTENANCE FOUND THE SECONDAR	Y LOCK PAWL TO BE FOULING AGAINST THE TORQUE TUBE, TORQUE TUBE AND SECONDARY LOCK PAWL OUT OF ADJUSTMENT. THEY DID A PAS	SENGER DOOR ADJUSTMENT PER THE AMM. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700393	20010507	00393	EA  	2001	5	7	CA010430024      	1	20010407	G	5210		HANDLE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	JAMMED          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE AT THE GATE, AFTER BOARDING, THE FLIGHT ATTENDANT REPORTED THAT SHE WAS UNABLE TO CLOSE THE PASSENGER DOOR. 	THE FLIGHT ATTENDANT REPORTED THAT THE HANDLE WOULD JAM HALF WAY WHEN CLOSING.THE AIRCRAFT WAS BROUGHT TO THE HANGAR AND	 MAINTENANCE WERE UNABLE TO INSTALL THE RIG PINS. THE DOOR WAS RIGGED PER THE AMM AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700394	20010507	00394	EA  	2001	5	7	CA010430025      	1	20010407	G	5610	601R3303310	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA						00165H9933					(CAN) FIRST OFFICERS WINDSHIELD SHATTERED. CABIN DIFFERENTIAL PRESSURE 7.3. NO PRESSURE LOSS. REPLACED WINDSHIELD.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700395	20010507	00395	EA  	2001	5	7	CA010501002      	1	20010412	G	5210		BUSHING         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					PAX DOOR	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHEN THE AIRCRAFT ARRIVED IN THE HANGAR THE MECHANICS WERE UNABLE TO OPEN THE PASSENGER DOOR. THE BUSHING FROM THE	 CASTING FOR THE TORQUE TUBE WERE FOUND TO BE MIGRATED. THE BUSHING WERE RE-INSTALLED AND THE DOOR RIGGING C/OUT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700396	20010507	00396	EA  	2001	5	7	CA010501005      	1	20010412	G	5610	NP1393216	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA											(CAN) FIRST OFFICERS WINDSHIELD SHATTERED IN FLIGHT, NO CABIN PRESSURIZATION LOSS.WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700397	20010507	00397	NE  	2001	5	7	CA010501006      	2	20010412	G	7200	4121T03G01	ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF34*       	 	NE  					NR 2	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ON TAXI WITH THE THROTTLE ON IDLE POSITION THE ITT ON ENGINE NR 2 INCREASED SUDDENLY UP TO 1093 CELSIUS. THE ENGIN	E SHUT DOWN BY ITSELF.BASE ON THE INSPECTION RESULTS GE RECOMMANDS TO REPLACE THE FMU AND ENGINE RUN IN ORDER TO CONTINU	E TO OPERATE THE ENGINE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001050700398	20010507	00398	EA  	2001	5	7	CA010501008      	1	20010416	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002A12   	1900304	EA  										COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA											(CAN) R/H WINDSHIELD CRACKED WHILE ON APPROACH. MAINTENANCE REMOVED AND REPLACED RT WINDSHIELD WITH NEW UNIT. AIRCRFT BA	CK IN SERVICE.					2	L	7	2 	4F			RT	A21EA   					 
2001050700399	20010507	00399	EA  	2001	5	7	CA010501015      	1	20010417	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA											(CAN) UPON TOUCH DOWN, CAPTAINS WINDSHIELD INNER PLY CRACKED. WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051000067	20010510	00067	EA  	2001	5	10	CA010501017      	1	20010129	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  										COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA			11   								(CAN) AT 17,000 FEET, 280 KTS - LT WINDSHIELD STARTED TO CRACK AND THEN SHATTERED.						2	L	7	2 	4F			RT	A21EA   					 
2001051000068	20010510	00068	EA  	2001	5	10	CA010501021      	1	20010205	G	5610	601R330339	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			CL	CLIMB          	1			CA			7    								(CAN) CLIMBING THROUGH 31,000 FEET - 7 MACH, 8.2 P.S.I. LT WINDSHIELD SHATTERED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500334	20010515	00334	NM  	2001	5	15	CA010502004      	1	20010405	G	2750	655280726	MODULE          			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAPS	DEFECTIVE       	W				D	 	 	 	RETURN TO BLOCK         				N	 	 	FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA				1264 							(CAN) AS THE POWER LEVERS WERE ADVANCED FOR TAKEOFF AT 1.2 EPR A WARNING HORN SOUNDED. THE TAKEOFF WAS REJECTED AND THE 	AIRCRAFT PROCEEDED BACK TO THE GATE WITHOUT INCIDENT. MAINTENANCE REPLACED THE FLAP/SLAT POSITION ACCESSORY UNIT P/N 65-	52807-26 S/N D00235.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001051500344	20010515	00344	CE  	2001	5	15	CA010503011      	1	20010427	G	2810		FUEL CELL       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RT WING	LEAKING         	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			CL	CLIMB          	1			CA			17749								(CAN) A/C DEPARTED SMITHERS, BC ENROUTE TO VANCOUVER. AT APPROX 15 MIN. OUT A PASSENGER NOTED TO CREW THAT RT WING HAD A	 SMALL LEAK OF FUEL COMING FROM A RIVET HEAD JUST O/B OF ENGINE NACELLE. THE  CREW HAD NO IND.S OUT OF ORDINARY BUT AFTE	R CONFERRING WITH MAINT OVER RADIO THEY ELECTED TO RETURN TO SMITHERS AS A PRECAUTIOINARY MEASURE: EMERG SRVCS WHERE STA	NDING BY & THE  A/C MADE AN UNEVENTFUL LDG. LEAK WAS ONLY EVIDENT BY SOME WEEPING ON R/H WING & MUST HAVE BEEN GREATER W	ITH WING LOADING & AIRPRESSURES IN FLT.MAINT DEFUELED A/C ANDINVESTIGATED INTERNAL AREAS OF WING. SOME RIVETS WHERE SEAL	ED IN AREA OF WEEPING & A LEAK CHECK CARRIED OUT.	2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001051500345	20010515	00345	CE  	2001	5	15	CA010503012      	1	20010416	G	3222	12434262	TORQUE LINK     			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					NOSE GEAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER NOSE GEAR TORQUE LINK FOUND CRACKED HALF WAY UP PART AS SHOW. CRACK WAS IN TWO LOCATIONS ABOUT 1/4 INCH LONG	. PART HAD NOT FAILED.THIS IS THE SECOND PART FOUND CRACKED ON CESSNA 210 AIRCRAFT, BOTH IN THE SAME LOCATION.					1	H	7	1 	3O	3	O	 	3A21    	E5CE				 
2001051500346	20010515	00346	CE  	2001	5	15	CA010503013      	1	20010418	G	3222	12434262	TORQUE LINK     			CESSNA	210   	T210K       	2073447	CE  	CONT  	O520  	TSIO520H    	17040	SO  	MCAULY	3A32C	D3A32C88    	GL  	NOSE GEAR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER NOSE GEAR TORQUE LINK FOUND CRACKED AS SHOWN. CRACK WAS IN TWO LOCATIONS ABOUT 1/8 INCH LONG. PART HAD NOT F	AILED.THIS IS THE SECOND PART FOUND CRACKED ON CESSNA 210 AIRCRAFT, BOTH IN THE SAME LOCATION.					1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P21EA	 
2001051500347	20010515	00347	NE  	2001	5	15	CA010503015      	1	20010323	G	2421	31176002	SHAFT           			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					GENERATOR	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						237					(CAN) AIRCRAFT GENERATOR TURNS AT 12,000 RPM IS DRIVEN BY THE MAIN TRANSMISSION OF HELICOPTER & FAN CAME LOOSE ON SHAFT,	 RETENTION NUT MS21042-4 HAD SELF LOCKING FRICTION STILL WITHIN LIMITS. FAN IS A FIT ON SHAFT BY NUT TORQUE ONLY, NUT MU	ST NOT HAVE BEEN ON TIGHT ENOUGH, EVEN THOUGH NUT FRICTION WAS WITHIN LIMITS. FAN BEGAN TO VIBRATE AND A HIGH FREQUENCY 	VIBRATION WAS FELT. FAN COST IS US$4,900.00 FOR A SIMPLE FAN BLADE WITH REQUIRED AN EXCHANGE GENERATOR COST US$13,000.			1	G	7	2 	3U	3	U	NC	H1NE    	E00054EN				 
2001051500348	20010515	00348	NM  	2001	5	15	CA010503016      	1	20010414	G	2920	231840	POWER UNIT      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						MX467234					(CAN) WHILE USING STANDBY POWER UNIT DURING ROUTINE MAINTENANCE, IT WAS DISCOVERED THAT UNIT WAS NOT PRODUCING PRESSURE.	 UNIT REPLACED WITH SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001051500349	20010515	00349	NE  	2001	5	15	CA010503017      	1	20010418	G	6320	SB3151A1	BEARING         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR GB	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INPUT BEARING FAILED DURING THE INITIAL RUN IN PROCEDURE. INVESTIGATION SHOWED THAT BEARING PUSHER TOOL WAS IMPROP	ERLY USED CAUSING DEFORMATION OF BEARING CAGE AT OVERHAUL. TOOL WAS REMOVED FROM SHOP TO PREVENT POSSIBLE REOCCURRENCE.					2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001051500350	20010515	00350	EA  	2001	5	15	CA010504002      	3	20010411	G	6110		PROPELLER       			PIPER 	PA22  	PA22135     	7102206	SO  	LYC   	O320  	O320B2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2480 	336  							(CAN) HEAVY CORROSION THRU-OUT INTER PROPELLER, .040TH OFF MATERIAL. REMOVED TO REMOVE CORROSION.						1	H	7	1 	3O	3	O	 	1A6     	E274	5	N	P88614	 
2001051500351	20010515	00351	EU  	2001	5	15	CA010504004      	1	20010419	G	6520	369D25434	SHAFT           		369D25400   	HUGHES	369   	369FF       	       	EU  	ALLSN 	250C  	250C30      	03013	GL  					T/R GEARBOX	BROKEN          	W				K		 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2673 			1076					(CAN) - METAL GENERATION, SCHEDULED 100 HOUR INSPECTION.- GEARBOX REMOVED AND SENT FOR REPAIR. - TEARDOWN INSPECTION FOU	ND THAT THE INPUT GEARSHAFT HAD FAILED INBOARD OF THE INPUT GEAR.- THIS GEARBOX HAD BEEN REPAIRED ON 3 PREVIOUS OCCASION	S FOR CLOUDY OIL/SLUDGE IN OIL.- THE FAILED SHAFT HAS BEEN SENT FOR METALLURGICAL INSPECTIONS.				1	G	7	1 	3U	3	U	 	H3WE    	E1GL				 
2001060400001	20010604	00001	EU  	2001	6	4	CA010504007      	1	20010323	G	5530	SD3316384XAA	FITTING         	STBROS      	SD360       	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  					VERTCAL STAB	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			28800			SH3633					(CAN) DURING MID-LIFE STRUCTURAL INSPECTION THE ABOVE CLEAT WAS FOUND TO BE EXFOLIATED IN VARIOUS SPOTS BETWEEN THE WEBS	. IT IS LIKELY THAT STANDING WATER COULD SIT IN THE WEB AREAS AND SPEED UP THE CORROSION PROCESS. THE VERTICAL STAB WAS 	REMOVED TO OBTAIN ACCESS TO THE CLEAT. THE CLEAT WAS REPLACED AND THE VERTICAL STAB REINSTALLED.				2	H	7	2 	4T	4	T	 	A41EU   	E4EA				 
2001051500355	20010515	00355	CE  	2001	5	15	CA010504009      	1	20010405	G	5552	MS20253P25120	PIN             	CESSNA      	550         	CESSNA	500   	550         	2076604	CE  										LT ELEVATOR HING	MISMANUFACTURED 	W				K	 	 	 	NONE                    				W	 	 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			2339 	2339 		5500807					(CAN) FOUND ELEVATOR TRIM TAB HING PIN SHORT IN LENGTH ON LEFT SIDE ELEVATOR.						1	L	7	2 	4F			 	A22CE   					 
2001051500356	20010515	00356	CE  	2001	5	15	CA010504010      	1	20010408	G	2720	03101965	SPRING          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER	DISCONNECTED    	W				A	 	 	 	UNSCHED LANDING         				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) LT RUDDER AND BRAKE PEDAL RETURN SPRING P/N 0310196-5 BECAME DISLODGED FROM FRONT ANCHOR POINT BRACKET P/N 510128 	IN FORWARD CENTRE TUNNEL ASSEMBLY P/N 0591301-11.THIS ALLOWED THE LEFT BRAKE & RUDDER PEDAL TO MOVE FULL FWD. THE PEDALS	 WOULD NOT RETURN TO NEUTRAL POSITION. ALSO NO LEFT BRAKE WAS AVAILABLE DUE TO ANGLE OF PEDALS.BY ROLLING THE SPRING P/N	 0310196-5, ONE EIGHTY DEGREES & HOOKING IT OUT THROUGH BRACKET P/N 0510128 INSTEAD OF IN THROUGH THE BRACKET WOULD PREV	ENT THE SPRINGS P/N 0310196-3 L/H AND P/N 0310196-12 FROM BECOMING DISLODGED. BY DOING THIS THE GEOMENTRY OF THE SPRINGS	 ARE NOT ALTERED.NO EVIDENCE OF WEAR WAS VISIBLE ON ANY OF THE ABOVE MENTIONED PARTS.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001051500357	20010515	00357	EU  	2001	5	15	CA010504012      	1	20010420	G	2550	AS2219	CABLE           			SNIAS 	350   	AS350B2     	8680813	EU  										CARGO HOOK	BROKEN          	W				K	 	 	 	NONE                    				P	 	 	NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA											(CAN) THE METAL SHEATH THAT FORMS THE OUTER COVER OF THE MANUAL EMERGENCY RELEASE CABLE FOUND BROKEN. THE SHEATH WAS BRO	KEN WHERE THE RELEASE CABLE ATTACHES TO THE CARGO HOOK. THIS IS A CARGO SWING INSTALLATIION WHERE THE CARGO HOOK IS ATTA	CHED TO A FRAME THAT IS SUSPENDED FROM THE HELICOPTER BY FOUR CABLES. THERE IS A SUBSTANTIAL AMOUNT OF MOTION/MOVEMENT O	F THE CARGO HOOK RELATIVE TO THE HELICOPTER. THE RELEASE CABLE UNDERGOES A LOT OF FLEXING, LEADING TO FATIGUE FAILURE AT	 CABLE ATTACHMENT.		1	G	7	1 	3U			 	H9EU    					 
2001051500361	20010515	00361	EU  	2001	5	15	CA010504018      	1	20010409	G	6510	BB1B649781A	BEARING         		11731521    	BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					TAIL ROTOR DRIVE	ROUGH           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4574 			443					(CAN) HEARD CLICKING NOISE DURING DAILY INSPECTION WHILE TURNING MAIN ROTOR.DISCOVERED ROUGH NR 3 TAIL ROTOR DRIVESHAFT 	BEARING, BEARING CAUSED RUBBER SLEEVE ON SHAFT TO SPIN. DAMAGE TO SHAFT BEYONG LIMITS. SUSPECT INTERNAL CORROSION DUE TO	 HISTORY OF THIS PART SITTING IN STORAGE FOR A LONG TIME.				1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001051500362	20010515	00362	EU  	2001	5	15	CA010504020      	1	20010415	G	6510	350A236534451	BRACKET         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					T/R BEARING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4216 								(CAN) UPON INSPECTION, THE EIGINEER NOTICED A CRACK ON THE NR 5 T/R HANGAR BEARING SUPPORT BRACKET.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001051500363	20010515	00363	EU  	2001	5	15	CA010504021      	1	20010415	G	2913	350A35107000	BRACKET         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					HYD PUMP MOUNT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4216 								(CAN) UPON INSPECTION THE ENGINEER NOTICED A CRACK ON THE HYDRAULIC PUMP MOUNTING BRACKET. THE CRACK SEEMS TO ORIGINATE 	FROM TOOL MARKS CAUSED BY MAINTENANCE.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001051500370	20010515	00370	SO  	2001	5	15	CA010507006      	1	20010213	G	3245	600X6	TUBE            	MICHEL      	6006        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG TIRE	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			68   								(CAN) NOSE TIRE DEFLATED. TUBE FOUND DEFECTIVE WITH HOLE IN SIDEWALL. MANUFACTURE NOTIFIED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001051500371	20010515	00371	SO  	2001	5	15	CA010507007      	1	20010227	G	3245	600X6	TUBE            	MCCREARY    	6006        	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NLG TIRE	FAILED          	W				D	 	 	 	RETURN TO BLOCK         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			20   								(CAN) NOSE WHEEL DEFLATED.TUBE WAS FOUND DEFECTIVE WITH PIN HOLE IN SIDEWALL. MANUFACTURE NTIFIED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001051500372	20010515	00372	SW  	2001	5	15	CA010507008      	1	20010409	G	6320	F506A	OIL CAP         	BELL        	F506A       	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					LOCKING PINS	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LOCKING PINS IN TRANSMISSION OIL FILTER CAP ASSEMBLY CAME LOOSE AND FELL OUT OF TRANSMISSION OIL FILLER CAP ASSEMB	LY. REPLACED WITH NEW OIL FILTER CAP ASSEMBLY					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001051500377	20010515	00377	EA  	2001	5	15	CA010507015      	1	20010507	G	2731	M3414	ROD END         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					BEARING	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND ROD END WORN EXCESSIVELY ON INSPECTION 200 HOURS AFTER STC SA99-219/ST01243NY WAS INSTALLED.						1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001051500388	20010515	00388	CE  	2001	5	15	CA010508007      	1	20010418	G	2612	302157	FIRE DETECTOR   			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NR 1 ENGINE	SHORTED         	W				O	 	 	 	OTHER                   				N	 	 	FALSE WARNING             			DE	DESCENT        	1			CA						69428					(CAN) DURING DESCENT NR 1 ENG FIRE INDICATION ILLUMINATED. ENGINE WAS SHUT DOWN. INSPECTION DETERMINED NO ACTUAL FIRE. T	HE ERRONEOUS FIRE INDICATION COULD NOT BE DUPLICATED ON GROUND. BASED ON PREVIOUS TROUBLE SHOOTING ALL THE WIRING FOR TH	E FIRE DETECTIONS WAS SPRAYED WITH WATER. WHEN THE WIRING WAS MOVED, OR THE WIRE BUNDLE SQUEEZED, THE FIRE INDICATION IL	LUMINATED. INVESTIGATION REVEALED THAT THE WIRING FOR THESE DETECTIONS ARE SUSCEPTABLE TO MOISTURE AND SUBSEQUENTLY WILL	 SHORT OUT BRINGING ON THE FALSE INDICATION.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001051500389	20010515	00389	SO  	2001	5	15	CA010508008      	1	20010405	G	5730	62061804	SKIN            			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					WING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION ON SCHEDULED #50, FOUND REAR WALK SKIN FLEX TOO MUCH ON ONE SPOT. OPEN INSPECTION PANEL, FOUND CRA	CK DOUBLER, ON ENFORCED SKIN (THAT IS SANDWICH SKIN). CRACK LENGTH 5 INCHES.SKIN ORDERED, TO BE REPLACE.					1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001051500390	20010515	00390		2001	5	15	CA010508009      	4	20010424	G	2562	E0109	BRACKET         			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ELT	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			401  			029168					(CAN) MOUNTING BRACKET FOR PORTABLE ANTENNA HAS LOOSE FIT AND ALLOWS ANTENNA TO FALL OUT. MS 28775-009 O-RING USED TO RE	TAIN ANTENNA.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001051500392	20010515	00392	NM  	2001	5	15	CA010508011      	1	20010420	G	5730		SKIN            			BOEING	727   	72725C      	138400H	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					WINGLET	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3840 	3840 							(CAN) DURING ROUTING C CHECK INSPECTION , FOUND EVIDENCE OF DELAMINATION AT UPPER CHORD, 8 INCHES LONG, 6 1/2 INCHES FOR	WARD OF AFT MOUNT FITTING. WINGLET REMOVED AND RETURNED TO WINGLET SYSTEM FOR EVALUATION AND POSSIBLE RECTIFICATION. WIN	GLET SYSTEMS PROVIDED REPLACEMENT WINGLET FOR INSTALLATIOIN TO AIRCRAFT.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001051500393	20010515	00393	EA  	2001	5	15	CA010508013      	1	20010212	G	7120	C2EM4A	MOUNT           			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8689 								(CAN) THE ENGINE WAS CHANGED IN THE AIRCRAFT. UPON INSPECTION, THE ENGINE MOUNT WAS FOUND TO BE CRACKED AROUND THE LORD 	MOUNT PADS. THE MOUNT ASSEMBLY P/N C2EM4-A WAS REPLACED WITH A REPAIRED PART.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001051500394	20010515	00394	EA  	2001	5	15	CA010508014      	1	20010508	G	5312	C2FS533	FORMER          			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					BULKHEAD	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9689 								(CAN) THE INSPECTION REQUIRED BY CF-98-38 BULKHEAD CRACKS STA. 288 WAS CARRIED OUT ON THE AIRCRAFT. THE BULKHEAD AND THE	 CHANNEL ASSEMBLY WERE FOUND TO BE CRACKED. P/N C2FS533 FORMER WAS REPLACED WITH A NEW PART. P/N C2FS4045A CHANNEL ASSEM	BLY WAS REPLACED WITH A NEW PART.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001051500396	20010515	00396	EA  	2001	5	15	CA010509002      	1	20010423	G	5711	75710099	SPAR CAP        	DHAV        		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	LT & RT WING	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			24387								(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING 	IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THEE EARLIER MAINTENANCE PROJECTS, ON THE FOLL	OWING AIRCRAFT: (1) DHC-7 S/N 037 (GFOF) TSN: 30142.1 CSN: 42908(2) DHC-7 S/N  63 (GCEV) TSN: 33390.4 CSN: 32682(3) DHC-	7 S/N  81 (KWZV) TSN: 32198.4 CSN: 30818IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL	AND.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001051500397	20010515	00397	EA  	2001	5	15	CA010509003      	1	20010423	G	5711	75710099	SPAR CAP        	DHAV        		DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	LT & RT WING	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			30142								(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING 	IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL	LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24386.6 CSN: 43093(2) DHC-7 S/N  63 (GCEV) TSN: 33390.4 CSN: 32682(3) DHC-	7 S/N  81 (KWZV) TSN: 32198.4 CSN: 30818IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL	AND.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001051500398	20010515	00398	EA  	2001	5	15	CA010509004      	1	20010423	G	5711	75710099	SPAR CAP        	DHAV        		DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	LT & RT WING	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			33390								(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING 	IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL	LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24386.6  CSN: 43093 (2) DHC-7 S/N 037 (GFOF) TSN: 30142.1  CSN: 42908 (3) 	DHC-7 S/N  81 (KWZV) TSN: 32198.4  CSN: 30818 IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DE	HAVILLAND.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001051500399	20010515	00399	EA  	2001	5	15	CA010509005      	1	20010423	G	5711	75710099	SPAR CAP        	DHAV        		DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	LT & RT WING	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			32198								(CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING 	IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL	LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24486.6 CSN: 43093(2) DHC-7 S/N 037 (GFOF) TSN: 30142.1 CSN: 42908(3) DHC-	7 S/N  63 (GCEV) TSN: 33390.4 CSN: 32682IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL	AND.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001051500405	20010515	00405	CE  	2001	5	15	CA010509015      	1	20010417	G	2720	04115261	TORQUE TUBE     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CABLE ARM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9133 								(CAN) CRACK FOUND IN WELD FROM TORQUE TUBE TO CABLE ARM. THE CRACK WAS APPROXIMATELY 1/8 INCH LONG AT THE END OF THE WEL	D.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001051500407	20010515	00407	SW  	2001	5	15	CA010510003      	1	20010403	G	6710	206010355003	TUBE            		206010355001	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					PITCH LINK ASSY	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			14068			DI035					(CAN) CRACK WAS VISIBLE TO NAKED EYE EMINATING FROM LOWER INSERT FAYING SURFACE AND EXTENDING VERTICALLY UPWARD 0.4 INCH	ES. SOME CORROSION PRESENT. REPLACED BOTH PITCH LINK ASSEMBLY WITH LINK ASSY P/N 206-010-360-005. SUSPECT THEY ARE ORIGI	NAL WHICH MEANS 14,068 HOURS.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001051500408	20010515	00408	CE  	2001	5	15	CA010510004      	1	20010417	G	2400	2050421	CONNECTOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELECTRICAL	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			193  								(CAN) THIS CONNECTOR HAS BEEN FOUND TO BE EASILY DAMAGED WHEN IT IS REQUIRED TO REMOVE OR INSERT A CONTACT IN IT. NEW RE	PLACEMENT PARTS OFTEN ARRIVE DAMAGED AS WELL. WHILE NOT A PROBLEM IN TYPICAL OPERATION IT DOES ALLOW FOR THE POSSIBILITY	 AT THE TERMINAL BEING HELD IN PLACE ONLY BY THE SEALING COMPOUND. THERE IS A SPECIFIC TOOL FOR INSERTING THESE CONTACTS	 BUT EVEN WITH EXTREME CARE, IT IS VERY EASY TO DAMAGE THE CONNECTOR. CONNECTOR P/N 205042-1, 205043-1			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001051500409	20010515	00409	EA  	2001	5	15	CA010510005      	1	20010420	G	5315	60035031159	FLOORBEAM       			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF34*       	 	NE  					FUSELAGE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5393 								(CAN) DURING A CORROSION INSPECTION EXCESSIVE CORROSION AND EXFOLIATION WAS FOUND ON THE TOP SURFACE OF TWO FLOOR BEAMS 	IN THE AREA UNDER THE LAVATORY AND WATER SYSTEMS FILL CANISTERS. FS 559 TO FS 621.					2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001051500411	20010515	00411	EU  	2001	5	15	CA010510007      	1	20010412	G	7830	9055M20P272	CLAMP           		9118M85G02  	AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					THRUST REVERSER	BROKEN          	W				C	 	 	 	ABORTED TAKEOFF         				M	 	 	OVER TEMP                 			TO	TAKEOFF        	1			CA											(CAN) - ON TAKEOFF REW NOTICED 3/4 KNOB THROTTLE STAGGER. - DURING CLIMB NR 2 ENGINE LOOP B LIGHT ON. - IN CRUISE NOTICE	D NACELLE TEMP RISING.- UPON LANDING FOUND NR 2 ENGINE T/R BLOW OUT PANEL HANGING DOWN. - NR 2 CORE COWLS OPENED, FOUND 	REMAINS OF CLAMP IN T/R RT COWL. - CLAMP REPLACED WITHOUT FURTHER INCIDENT.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2001051500412	20010515	00412	CE  	2001	5	15	CA010510008      	1	20010417	G	5541	04330106	SPAR            	CESSNA      	04330101    	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9133 								(CAN) 4 CRACKS WERE FOUND ORIGINATING FROM A 1.0 INCH DIA. LIGHTENING HOLE, 1.50 INCH BELOW UPPER RUDDER HINGE BRACKET. 	NOTE: REPLACEMENT SPAR WITH THE SAME P/N FROM CESSNA DOES NOT HAVE THIS LIGHTENING HOLE.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001051500413	20010515	00413	CE  	2001	5	15	CA010510009      	1	20010416	G	5510	04320049	BRACKET         	CESSNA      	043200159   	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			9133 								(CAN) 2 CRACKS FOUND AT WELDED EDGE.2 CRACKS FOUND AT ANCHOR NUT HOLE.1 CRACK WELD CRACKED. 1 CORNER NOT WELDED.						1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001051500414	20010515	00414	CE  	2001	5	15	CA010510010      	1	20010417	G	2720	04115261	TORQUE TUBE     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CABLE ARM	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN WELD FROM TORQUE TUBE TO CABLE ARM. CRACK WAS APPROXIMATELY 0.125 INCH LONG AT THE END OF WELD.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001051500422	20010515	00422	NE  	2001	5	15	CA010511002      	2	20010330	G	7321	6078T55P18	FUEL CONTROL    	WOODWARD    		CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					RT ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			485  			WYG99820					(CAN) CREW REPORTED THAT THEY HAD 3 UNCOMMANDED OVERSPEEDS OF RIGHT ENGINE N1 DURING FLT. 1ST 104.5 PERCENT N1 FOR 5.7 S	EC ICAS N1 ICON TURNED RED. PILOT PULLED THROTTLE BACK & ENGINE DID NOT COME BACK FOR 3 TO 4 SEC. PILOT ADVANCED THROTTL	E BACK TO CRUISE POWER & 2ND OVERSPEED HAPPENED.  IT 103.3 PERCENT N1 FOR 6.1 SEC N1 ICON TURNED RED. THROTTLE PULLED BA	CK & WITH 2 TO 3 2ND DELAY BEFORE ENGINE CAME BACK IN SPEED. N1 SPEED SWITCH TURNED OFF&ENGINE SPEED ADVANCED BACK TO CR	UISE POWER. 3RD OVERSPEED THEN HAPPENED AT 99.1 PERCENT FOR 0.7 SEC. PILOT REDUCED THROTTLE & TURNED A/C BACK TO DEPTR A	IRPORT.MAIN FUEL CNTL REPLACED & A/C RT-SRV.2001-05-11 TC: INVESTIGATING	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500423	20010515	00423	EA  	2001	5	15	CA010511005      	1	20010419	G	5400	A33721	ROD             			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NACELLE DOOR	LOOSE           	W				A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			CR	CRUISE         	1			CA											(CAN) AIRCRAFT ENROUTE TO MONTERREY, THE CREW WERE UNABLE TO RETARD THE LEFT HAND THROTTLE LOWER THAN 95 PERCENT. THE CR	EW RETURNED TO MEMPHIS AND CARRIED OUT QRH ABNORMAL 1-14.  MECHANICS FOUND THE HOLD OPEN STRUT OF THE LT ENGINES UPPER C	ORE COWL JAMMED BETWEEN THE FUEL CONTROL UNIT INPUT SHAFT AND THE COWLING. THE STRUT WAS REMOVED (DMI) AND THE AIRCRAFT 	RETURNED TO SERVICE.DURING THE PRELIMINARY INVESTIGATION THE BALL WITHIN THE PIN BLC38C11SL5C4 WAS FOUND TO BE MISSING. 	THE STRUT STOWING END, BRACKET 228-50182-585 AND THE CLIP 228-50583-101 WILL BE VERIFIED UPON INSTALLATION OF NEW ROD TO	 CONCLUDE THE INVESTIGATION.	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500424	20010515	00424	EA  	2001	5	15	CA010511008      	1	20010419	G	2910	AE2460010H0264	LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	CHAFED          	W				A	 	 	 	UNSCHED LANDING         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) UPON CLIMBING, CREW RECEIVED A HYDRAULIC NR 1 LOW PRESSURE MESSAGE, ASSOCIATED WITH A NR 1 SYSTEM, QUANTITY INDICA	TING ZERO PERCENT. AIRCRAFT DIVERTED TO BIRMINGHAM. MAINTENANCE FOUND A CHAFED STEEL BRAIDE HYDRAULIC LINE IN AFT FUSE. 	THE LINE IS THE PESSURE LINE AT THE BULKHEAD. THE RUBBER HAD WORN OFF CLAMP P/N M85052-2-8. LINE REPLACE, ADP NR 1 REPLA	CED, OPS CHECK GOOD, AIRCRAFT RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500425	20010515	00425	NE  	2001	5	15	CA010511012      	2	20010425	G	7260		GEAR            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2 ENGINE	FAILED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE OIL PRESSURE DROPPED TO APPROXIMATELY 18 PSI WITH LOW OIL PRESSURE WARNING. ENGINE SHUTDOWN PER QRH. N	R 2 ENGINE REPLACED DUE TO GEAR MATERIAL ON THE CHIP DETECTOR.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500426	20010515	00426	EA  	2001	5	15	CA010511014      	1	20010426	G	5610	NP1393215	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA											(CAN) LT WINDSHIELD CRACKED DURING THE APPROACH. WINDSHIELD REPLACED AND RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500427	20010515	00427	EA  	2001	5	15	CA010511016      	1	20010426	G	5610	NP1393219	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FRACTURED       	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			DE	DESCENT        	1			CA											(CAN) CAPTAINS WINDSHIELD EXPERIENCED A PLY FRACTURE DURING DESCENT. WINDSHIELD REPLACE, AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500428	20010515	00428	EA  	2001	5	15	CA010511018      	1	20010429	G	7120		BEAM            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE SUPPORT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C-CHECK SEVEN CRACKS WERE FOUND IN THE ENGINE SUPPORT BEAM. TWO CRACKS WERE LOCATED ON THE LOWER WEB AT FS 	640.0 NAR LBL9.0. FIVE CRACKS WERE LOCATED ON THE UPPER WEB AT FS640.0 BETWEEN LBL9.0 AND RB122.0.REPAIR ONGOING IAW REO	 601R-53-61-340.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500429	20010515	00429	EA  	2001	5	15	CA010511019      	1	20010429	G	5610	NP1393226	WINDOW          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	CRACKED         	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			LD	LANDING        	1			CA											(CAN) ON LANDING COPILOTS SIDE WINDOW CRACKED.REPLACED COPILOTS SIDE WINDOW. AIRCRAFT RETURNED TO SERVICE.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500430	20010515	00430	EA  	2001	5	15	CA010511020      	1	20010429	G	7603	2100140007	GEARBOX         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE CONTROLS	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			3961 	3217 							(CAN) RIGHT ENGINE WILL NOT SHUT DOWN USING POWER LEVER.REPLACED THE THROTTLE CONTROL GEAR BOX ASSEMBLY. ENGINE RUNS CAR	RIED OUT, NO FAULTS FOUND.AIRCRAFT RETURNED TO SERVICE. 2001-05-11 TC: REQUESTING DETAILED INFORMATION FROM ORIGINATOR.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500431	20010515	00431	EA  	2001	5	15	CA010511021      	1	20010429	G	7720	6030T40P01	HARNESS         			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ITT INDICATOR	INOPERATIVE     	W				C	 	 	 	ABORTED TAKEOFF         				N		 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) CREW ABORTED TAKEOFF DUE TO NR 2 ENGINE OVER TEMPERATURE. MAINTENANCE FOUND ITT THERMOCOUPLE HARNESS PARTIALLY INO	PERATIVE. REPLACED HARNESS. NO FURTHER FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001051500432	20010515	00432	NE  	2001	5	15	CA010511023      	2	20010416	G	7230	BRR17740	BLADE           	RROYCE      	M33119      	BOEING	717   	717200      	1383700	NM  	RROYCE	BR700 	BR700715A130	 	NE  					HP COMPRESSOR	BROKEN          	W				A		 	 	UNSCHED LANDING         				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA			2821 	1797 							(CAN) AIRTRAN A/C 702, NR 1 ENGINE S/N 13121 EXPERIENCED SHUTDOWN ON CLIMB OUT OF RALIEGH DURHAM AT 9,000 FT. ENGINE RPT	EDLY MADE RMBLING NOISE&LOST POWER & RAN DOWN, ENGINE SUB-IDLE BEFORE SHUTDOWN, VIBRATION HIGH BUT NOT AMBER, SURGE LIGH	T  CAME ON. GROUND INSP REVEALED NO METAL IN TAIL PIPE&NO EVIDENCE OF EXTERNAL DAMAGE OR BIRDSTRIKE. WEATHER AT TIME OF 	EVENT CLEAR&SUNNY. ON GROUND, PRELIM GROUND-RUN PERFORMED&EVM ROSE TO 4.0 UNITS N2 BY 72% N2. PHYSICAL VIBRATION FELT,&R	UN STOPPED. BORESCOPE PERFORMED&HP1 COMPRESSOR BLADE FOUND BROKEN OFF MID SPAN, PLUS EXCESSIVE HP1 COMPRESSOR DAMAGE. EN	GINE CHANGE HAS BEEN CALLED FOR. DETAILS OF TROUBLE SHOOTING:ENGINE  BORESCOPE PERFORMED IN RALIEGH DURHAM ON 16/04	2	L	7	2 	4F	4	F	TR	A6WE    	E00061EN				 
2001061400002	20010614	00002	SO  	2001	6	14	CA010511025      	1	20010402	G	5712		SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					BOLT ATTACHMENT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CRACK IS CAUSED BY THE ATTACHMENT OF THE SUPPORT ON THE EDGE WITH AN AN3-4A BOLT.						1	L	7	1 	3O	3	O	 	2A13    	E274				 
2001061400003	20010614	00003	EA  	2001	6	14	CA010511026      	1	20010421	G	7500		ACTUATOR        			CNDAIR	CL604 	CL604       	       	EA  	GE    	CF34  	CF343B1     	 	NE  					BLEED AIR SYSTEM	FAILED          	W				K				NONE                    				M	J		OVER TEMP                 	WARNING INDICATION        		IN	INSP/MAINT     	1			CA			2683 								(CAN) OVERHEAT OF THE ACCUMULATOR, THE ELECTRIC WIING, LOWER ENGINE FAIRING AND THE LOWER CENTRAL PART OF THE NACELLE DU	E TO DE-COUPLING OF THE COMPRESSED AIR INTAKE AND THE 10TH STAGE HOT AIR PORTION. THIS COUPLING IS IN A HARD TO READ ARE	A AND IS HARD TO TIGHT AND HAS NO RETAINING WIRE. THIS IS THE 3RD INCIDENT THAT I NOTICE OF THIS SORT.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001061400004	20010614	00004	SW  	2001	6	14	CA010511027      	1	20010115	G	6220		HUB             	BELL        	64A         	BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1543 	192  		CH116					(CAN) FOUND CRACKED IN THREADED AREA AFTER EDDY CURRENT INSPECTION WHILE CARRYING OUT AD, CF-1988-08R1.						1	G	7	1 	3O	3	O	 	2H3     	E304				 
2001061400010	20010614	00010	NM  	2001	6	14	CA010515004      	1	20010420	G	3240		ISOLATION VALVE 			BOEING	737   	7372Q9      	138448M	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA				1731 		0575					(CAN) AIRCRAFT LOST A SYSTEM HYDRAULIC FLUID UPON TAXIING TO THE TERMINAL. CREW HAD TO USE DIFFERENTIAL BRAKING TO GET T	O GATE. AFTER INVESTIGATION IT WAS DETERMINED THAT THE MAIN GEAR ISOLATION VALVE P/N 65-44581-6, S/N 0575 WAS LEAKING.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001061400011	20010614	00011	EA  	2001	6	14	CA010515005      	1	20010410	G	3510		RHEOSTAT        			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					COCKPIT	OVERHEATED      	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			9250 	9250 							(CAN) OXYGEN REGULATOR IN COPILOT POSITION WAS REPLACED WITH OVERHAULED UNIT. INTERNAL LIGHTING WIRES FOR THIS UNIT WERE	 CONNECTED IMPROPERLY (POLARITY REVERSED).AS A RESULT THE RHEOSTAT WHICH CONTROLS LIGHT INTENSITY FOR THE COPILOTS INSTR	UMENT LIGHTING WAS SHORTED TO GROUND. THE 5 AMP CIRCUIT BREAKER THAT PROTECTS THIS LIGHTING RHEOSTAT DID NOT POP AND CAU	SED THIS RHEOSTAT (RATED AT 2.7 AMPS MAX .7 MIN.) TO OVERHEAT AND CAUSE SOME SMOKE IN THE COCKPIT AREA.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2001061400012	20010614	00012	EU  	2001	6	14	CA010515008      	1	20010419	G	2910		SOLENOID VALVE  			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					HYD SYSTEM	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA											(CAN) HYD BLOCK LIGHT CAME ON IN FLIGHT. PILOT RETURNED TO BASE AND CALLED OUT RESCUE CREW. LANDED WITHOUT DIFFICULTY. S	OLENOID VALVE REPLACED AND AIRCRAFT RETURNED TO SERVICE ON APRIL 20. AIRCRAFT TEST FLOWN FOR 30 MINUTES AND NO FURTHER L	IGHT REPORTS.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001061400013	20010614	00013	SW  	2001	6	14	CA010515009      	1	20010327	G	6700		TUBE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TUBE ASSY (XMSN) FOUND CHAFED IN VERTICAL TUNNEL. ONE OF THE CONTROL TUBES CHAFED THE TUBE WITH EVERY CONTROLLED I	NPUT. TUBE ASSY REPLACED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001061400014	20010614	00014	SW  	2001	6	14	CA010515010      	1	20010327	G	6510		BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R DRIVESHAFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 2 TAIL ROTOR DRIVESHAFT BEARINGS HAVE GREASE HOUSINGS CRACKED. BOTH BEARINGS ROUGH, EXCESSIVE GREASE SQUEEZE OUT. 	BOTH BEARINGS REPLACED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001061400015	20010614	00015	EU  	2001	6	14	CA010515011      	1	20010413	G	6310		ENGINE          			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					NACELLE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6349 	1876 		878					(CAN) AIRCRAFT LANDED AND SHUTDOWN. AFTER APPROXIMATELY 10 MIN WHEN ATTEMPTING A RESTART AT APPROXIMATELY 15 PERCENT NG 	AND T4 -400 DEGREES C A LOUD RINGING NOISE WAS HEARD FROM THE ENGINE COMPARTMENT AND START STALLED - START WAS ABORTED. 	AFTER SOME TROUBLESHOOTING THE ENGINE WAS REMOVED AND RETURNED TO THE MANUFACTURER FOR FURTHER EVALUATION.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001061400016	20010614	00016		2001	6	14	CA010515013      	4	20010412	G	2312		POWERPACK       	NARCO       	661         	GRUMAV	TBM   	TBM3EAIRTRD 	3950310	EA  	WRIGHT	R2600 	R260020     	67050	EA  	HAMSTD	23E	23E50       	NE  	VHF COMM	BURNED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) SHORTLY AFTER TAKEOFF THE PILOT DETECTED THE SMELL OF SMOKE IN THE COCKPIT. HE ELECTED TO RETURN TO Fredericton AI	RPORT AND DID A NORDO APPROACH AND LANDED SAFELY. MAINTENANCE FOUND THAT THE POWERPACK RESISTOR HAD BURNED AND THEREBY C	UTOUT NR 1 RADIO. THE BURNED MP-10 POWER PACK RESISTOR WAS CAUSED BY A FAILED VOLTAGE REGULATOR (BENDIX P/N TYPE 1589) W	HICH RESULTED IN AN UNCONTROLLED VOLTAGE SITUATION.			1	L	7	1 	4R	4	R	 	L82     	TC176	6	C	P603	 
2001061400017	20010614	00017	CE  	2001	6	14	CA010515014      	1	20010404	G	6310		ENGINE          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					R GEARBOX	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25153	1475 							(CAN) ENGINE SPOOL DOWN NOTED TO BE VERY SHORT HIGH RESISTANCE TO TURNING REDUCTION GEAR BOX THROUGH PROP BLADES AND INT	ERNAL RUBBING DETECTED INDICATING INTERNAL PROBLEMS. - CAUSE TO BE DETERMINED UPON ENGINE TEAR DOWN. - ENGINE WAS INVOLV	ED IN A PROP STRIKE 10 DAYS (64 FLIGHT HOURS) EARLIER AND HAD JUST BEEN RETURNED TO REGULAR MAINTENANCE INTERVALS AFTER 	COMPLETING THE REQUIRED INCREASED INSPECTIONS REQUIRED BY THE ENGINE MANUFACTURER. - ENGINE TEAR DOWN SHOULD INDICATE TH	AT THE PROP STRIKE WAS THE CAUSE.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001061400018	20010614	00018	EU  	2001	6	14	CA010518002      	1	20010126	G	6210		BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2100 								(CAN) DURING ROUTINE DAILY INSPECTION, MAIN ROTOR BLADE WAS FOUND TO HAVE TWO CRACKS ON THE UPPER SKIN AT STA 1177 AND S	TA 1182, RUNNING IN A CORD WISE DIRECTION. UPON REMOVED OF PART AND FURTHER INSPECTION, IT WAS DETERMINED THAT BLADE WAS	 NOT REPAIRABLE AS PER EUROCOPTER INSTRUCTION.				1	G	7	1 	3U			 	H9EU    					 
2001061400020	20010614	00020	EU  	2001	6	14	CA010518003      	1	20010430	G	2822		PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				216  		23455					(CAN) NR 2 FUEL BOOST PUMP WAS FOUND TO BE EXCESSIVELY NOISY DURING POST FLIGHT INSPECTION. PUMP WAS REMOVED FOR REPAIR 	AS THIS NOISE IS A SIGN OF IMPENDING FAILURE. REPLACEMENT PUMP INSTALLED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001061400027	20010614	00027	EU  	2001	6	14	CA010518009      	1	20010326	G	2822		PUMP            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL BOOST	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				670  							(CAN) PILOT NOTED FUEL PRESSURE INTERMITTENT/FLUCTUATING, NORMAL LANDING WAS CARRIED OUT. FUEL PUMP WAS REPLACED TO CORR	ECT PROBLEM.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001073000006	20010730	00006		2001	7	30	CA010518010      	4	20010503	G	6113		PLATE           	MOONEY      	SA8659SW    	MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			100  								(CAN) CRACK & FAILURE OF FLANGE OF BACKING PLATE THAT HAS BLADE ROOT CLOSING FAIRING ATTACHED.A PORTION OF FAIRING REMAI	NED ATTACHED TO SPINNER WHICH SEVERELY DAMAGED NOSE BOWL FAIING LEAVING BACKING PLATE&FAIRING DEBRIS INSIDE ENGINE COWL.	THERE WAS SOME MINOR DAMAGE TO PROP BLADES ABOUT FOOT FROM ROOT. SPINNER REMAINED ATTACHED&SECURE: CRACK APPEARED TO BEG	IN NEAR FWD EDGE OF FLANGE OF BOTH BACKING PLATE&FAIRING ATTACHMENT. PERHAPS ABOUT 1/2 INCH&REST OF FAILURE APPEARED TO 	HAVE BEEN EXTREMELY RAPID.		1	L	7	1 	3O	3	O	 	2A3     	1E10	5	C	P920	 
2001061400033	20010614	00033		2001	6	14	CA010522010      	4	20010427	G	2213		CONTROL CABLE   			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22429								(CAN) THE FLIGHT CREW REPORTED THAT THE ROLL CONTROL FELT HEAVIER THAN STANDARD FOR TYPE. MAINTENANCE INVESTIGATION REVE	ALED THAT THE R/H UPPER AILERON CONTROL CABLE WAS FRAYED AT THE STEEL PULLEY, WING STATION YW 256.0, JUST OUTBOARD OF TH	E ENGINE NACELLE. THE CABLE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TTAF 22,429 HOURS, TCAF 33,043.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001061400034	20010614	00034	EU  	2001	6	14	CA010522011      	1	20010429	G	3200		PROXIMITY SENSOR			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			15239	13602							(CAN) THE FLIGHT CREW REPORTED THE L/H RED "GEAR UNSAFE" LIGHT ILLUMINATED ACCOMPANIED BY GEAR HORN, STICK SHAKER, AND M	ANUAL SPOILER FAULT WHILE AT THE GATE AFTER SWITCHING FROM GROUND POWER TO APU. MAINTENANCE INVESTIGATION REVEALED AN OP	EN CIRCUIT IN THE L/H MAIN GEAR SIDESTAY PROXIMITY SENSOR. THE SIDESTAY ASSEMBLY WAS REPLACED AND THE AIRCRAFT WAS RETUR	NED TO SERVICE.			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001061400035	20010614	00035	NM  	2001	6	14	CA010522013      	1	20010506	G	2420		CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 GENERATOR	LEAKING         	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			6070 	161  							(CAN) THE FLIGHT CREW REPORTED ILLUMINATION OF THE NR 2  A/C. GENERATOR LIGHT ON TAKEOFF.  AN UNSCHEDULED LANDING WAS AC	COMPLISHED AND THE GENERATOR WAS REPLACED. OIL WAS FOUND IN THE MAIN ELECTRICAL CONNECTOR OF THE UNSERVICEABLE GENERATOR	. THIS UNIT HAD BEEN REPAIRED 161 HOURS PREVIOUS TO THIS OCCURRENCE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001061400036	20010614	00036	NE  	2001	6	14	CA010522016      	1	20010501	G	6220		PLATE           	SKRSKY      	S61102000304	SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14100	1508 		A9835					(CAN) ON POST FLIGHT INSPECTION A CRACK WAS FOUND EXTENDING UPWARD FROM BIFILAR ATTACH BOLT HOLE ON MAIN ROTOR HUB UPPER	 PLATE. MAIN ROTOR HEAD REMOVED FROM SERVICE. ON DISASSEMBLY, SHIM CHECK WAS CARRIED AS PER SB 61B10-46, AND FOUND TO BE	 WITHIN ACCEPTABLE TOLERANCE. NO NOTABLE CORROSION WAS FOUND IN THE PLATE BOLT. SIKORSKY HAS BEEN NOTIFIED.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001061400038	20010614	00038	CE  	2001	6	14	CA010522019      	1	20010508	G	7721		CYLINDER        			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300B       	17022	SO  					NR 1	SEPARATED       	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA				2103 							(CAN) NR 1 CYLINDER BARREL BROKE LEAVING CYLINDER BAS ATTACHED TO CRANKCASE AND CYLINDER ATACHED BY EXHAUST AND INTAKE. 	APPROXIMATELY 1" OF CYLINDER IS STILL ATTACHED TO CRANKCASE. PISTON AND CONNECTING ROD ARE DESTROYED. BOTH CASE HAVES AN	D REAR CASE IS DESTROYED. A SUCCESSFUL FORCED LANDING WAS MADE AT PRINCE GEORGE AIRPORT.				1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2001061400040	20010614	00040	SW  	2001	6	14	CA010522025      	1	20010501	G	3210		CROSSTUBE       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) HELICOPTER WAS ON A HELI SKIING JOB. THE JOB DESCRIPTION IS LOW HOURS BUT LOTS OF LANDINGS IN SNOW. THE PILOT HAD 	A RATHER ABRUPT LANDING ON ONE OF THE LANDING SITES (NOT HARD BUT NOT SMOOTH). AT THE NEXT LANDING THE PILOT HEARD A LOU	D BANG AND IT WAS NOTED THAT THE SKID TUBE ON THE LEFT SIDE OF THE AIRCRAFT WAS NO LONGER PARALLEL WITH THE AIRCRAFT, TH	E SKID TUBE WAS DETACHED FROM THE REAR CROSS TUBE BUT STILL ATTACHED TO THE FRONT CROSS TUBE, A CRIB OR SUPPORT WAS BUIL	T TO ALLOW THE AIRCRAFT TO LAND AND SHUT DOWN WITH NO INCIDENT. THE HELICOPTER HAD BROKEN THE LOW AFT CROSS TUBE NEAR TH	E SKID TUBE ATTACHMENT SADDLE ON THE LEFT SIDE.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001061400042	20010614	00042	SW  	2001	6	14	CA010523004      	1	20010410	G	3040		WINDSHIELD      			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UHR 	 	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1790 								(CAN) DURING CRUISE FLIGHT AT 24,000 FEET, WITH CABIN PRESSURE APPROXIMATELY 6 PSI, THE LT WINDSHIELD OUTER PANEL CRACKE	D. THE CREW ELECTED TO DIVERT TO THE NEAREST AIRFIELD, REDUCE ALTITUDE TO 10,000 FEET, AND DEPRESSURIZE THE CABIN AS A P	RECAUTION.IT WAS NOTED THAT THE FAIRCHILD 227 FLIGHT MANUAL DOES NOT GIVE ANY DIRECTIVES FOR ACTION IN THE CASE OF A CRA	CKED WINDSHIELD, THEREFORE THE CREW TOOK ACTION BASED ON EXPERIENCE ON OTHER SIMILAR TYPES OF AIRCRAFT.FAIRCHILD WILL BE	 CONTACTED TO REQUEST AN AMENDMENT TO THE FLIGHT MANUAL PROCEEDURES SECTION TO COVER THIS SITUATION.		2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE	 
2001061400043	20010614	00043	CE  	2001	6	14	CA010523006      	1	20010514	G	1100		PLACARD         			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					COCKPIT	REVERSED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE DECAL ON THE ELEVATOR TRIM WHEEL APPEARS TO HAVE BEEN FABRICATED. WHEN IT WAS INSTALLED, THE "NOSE UP" AND "NO	SE DOWN" DECALS WERE REVERSED. WHEN THE PILOT THOUGHT HE WAS TRIMMING THE NOSE DOWN, HE WAS ACTUALLY TRIMMING IT UP. THE	 LOCATION OF THE DECALS WAS CORRECTED.				1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2001072600023	20010726	00023	EU  	2001	7	26	CA010523010      	1	20010502	G	2913	704A33690004	BELT            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD PUMP	FAILED          	W				A				UNSCHED LANDING         				J	F		WARNING INDICATION        	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			190  								(CAN) WHILE IN CRUISE FLIGHT THE PILOT LOST HYDRAULIC PRESSURE. SLOWED THE A/C AND LANDED. HYDRAULIC PUMP BELT BROKEN.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001073000007	20010730	00007	EU  	2001	7	30	CA010523011      	1	20010430	G	6320	1171206301	BEVEL GEAR      	KAWSKI      	1171201001  	BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TRANSMISSION	MAKING METAL    	W				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA			3733 			KA0225					(CAN) MINOR "PEPPER" METAL, SHINY, WITHIN OPERATIONAL LIMITS WOULD OCCASIONALLY ACTIVATE OR FLICKER CAUTION LIGHT."PEPPE	R" FOUND IN BOTH FILTERS, MAINLY NR 1 SIDE. REMOVAL OF INSPECTION COVER REVEALED DEGENERATION OF SURACE OF BEVEL GEAR.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2001073000008	20010730	00008	SO  	2001	7	30	CA010523012      	1	20010420	G	5320	1712124	CHANNEL         			PIPER 	PA23  	PA23        	7102302	SO  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4221 								(CAN) DURING ANNUAL 100 HOUR INSPECTION OF THE TAIL AREA, NOTICED THAT THE CHANNEL THAT SUPPORTS THE LOWER RUDDER SUPPOR	T AND RUDDER STOP BRACKET WAS CRACKED. THIS WAS THE RESULT OF THE RUDDER BEING FORCED HARD AGAINST THE RUDDER STOPS BY W	IND.				1	L	7	2 	3O			 	1A10    					 
2001073000009	20010730	00009	SO  	2001	7	30	CA010523013      	1	20010420	G	3220	1904600	DRAG LINK       			PIPER 	PA23  	PA23        	7102302	SO  										NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL 100 HOUR INSPECTION FOUND NOSE GEAR LOWER DRAG LINK BROKEN IN THE DOWN LOCK AREA.						1	L	7	2 	3O			 	1A10    					 
2001072600024	20010726	00024	WP  	2001	7	26	CA010523015      	1	20010426	G	6210	369D21100517	BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DAMAGED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			2111 								(CAN) DURING HIS DI, THE PILOT NOTICED ADHESIVE MISSING FROM ONE MAIN ROTOR BLADE ROOT FITTING. MAINTENANCE WAS ADVISED.	 THE BLADE WAS REMOVED AND CHECKED AS PER DN188. THE ROOT FITTING FAILED THAT INSPECTION. THE REST OF THE BLADES WERE AL	SO INSPECTED AND FOUND SERVICEABLE. THE BLADE WAS RETURNED TO THE MANUFACTURER. A SERVICEABLE BLADE WAS INSTALLED AND TH	E AIRCRAFT RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001073000011	20010730	00011	SO  	2001	7	30	CA010523017      	1	20010427	G	3230	455180	RELEASE CABLE   			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					MLG	STIFF           	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) - LANDING GEAR FAILED TO RETRACT ON CLIMB OUT & BREAKERS POPPED.- GEAR FAILED TO EXTEND WHEN BREAKER RESET & SELEC	TED DOWN, NO GREEN LIGHT TO INDICATE GEAR DOWN AND LOCKED.- PILOT COULD NOT RELEASE EMERGENCY GEAR EXTENSION HANDLE.- RT	 GEAR COLLAPSED ON ROLL OUT. - TELEFLEX CABLES FOUND TO BE VERY STIFF IN CONDUIT/SLEEVE, LUBRICATION FREED UP ACTION CON	SIDERABLY.			1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2001072600026	20010726	00026	GL  	2001	7	26	CA010523019      	2	20010329	G	7230	6890550	COMPRESSOR      			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE COMPRESSOR WAS FRESHLY OVERHAUL WITH A TSO OF 1.1, CSO .3 AIRCRAFT FAILED TO START. PROBLEM FOUND TO BE COMPRE	SSOR LOCKED UP. MANUFACTURE CALLED AND INDICATED PROBLEM TO BE POSSIBLE REAR BEARING DIFFUSOR DUE TO THE TIGHT TOLERANCE	S.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001072600030	20010726	00030	WP  	2001	7	26	CA010523020      	1	20010424	G	5511	369D23623	SPAR            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5657 								(CAN) UPON SHOP REPAIR OF THIS STABILIZER FOR SKIN CRACKS, DOUBLER CRACKS AND LOOSE RIVETS. IT WAS OBSERVED, THAT THE AF	T SPAR IS CRACKED ALMOST ALL THE WAY THROUGH, 2.5 INCHES FROM THE INBOARD END. WE ALSO SUSPECT ANOTHER CRACK AT ANOTHER 	LOCATION ON THE SAME SPAR, BUT HAVE NOT CONFIRMED IT. THESE STABILIZERS HAVE JUST HAD THEIR RETIREMENT LIFE EXTENDED. TH	IS STABILIZER HAS BEEN REMOVED FROM SERVICE.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001073000012	20010730	00012	EA  	2001	7	30	CA010523024      	2	20010427	G	7414	66M19385	CLAMP           	BENDIX      	1068291018  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				207  		825199					(CAN) DURING A ROUTINE INSPECTION, IT WAS NOTED THAT EXCESSIVE OIL WAS LEAKING AROUND THE MAGNETO GASKET. UPON REMOVAL O	F THE MAGNETO, IT WAS NOTED THAT THE MAGNETO HAD ABNORMAL AMOUNT OF WEAR IN THE MAGNETO CLAMP AREA. FURTHER INVESTIGATIO	N REVEALED ONE OF THE HOLD DOWN CLAMPS WAS GROUND AWAY IN THE FACE CONTACT AREA, RESULTING IN THE MAGNETO HANGING ON THE	 CASE BY ONE CLAMP. BOTH THE MAGNETO AND CLAMPS WERE REMOVED AND SENT TO THE OVERHAUL FACILITY FOR REPLACEMENT.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001073000013	20010730	00013	EA  	2001	7	30	CA010523030      	1	20010425	G	2760	3310961	BELLCRANK       			SCWZER	SG2   	SGS233A     	8051606	EA  										DRAG CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4155 								(CAN) AN INSPECTION WAS CALLED FOR AS INSRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUBJ	ECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND RETURNED TO 	SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS.				1	K	0	0 	  			 	G2EA    					 
2001073000014	20010730	00014	EA  	2001	7	30	CA010523031      	1	20010425	G	2760	3313661	BELLCRANK       			SCWZER	SG2   	SGS233A     	8051606	EA  										DRAG CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2897 								(CAN) AN INSPECTION WAS CALLED FOR AS INSTRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUB	JECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND ETURNED TO 	SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS.				1	K	0	0 	  			 	G2EA    					 
2001073000015	20010730	00015	EA  	2001	7	30	CA010523032      	1	20010425	G	2760	3310961	BELLCRANK       			SCWZER	SG2   	SGS233A     	8051606	EA  										DRAG CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3142 								(CAN) AN INSPECTION WAS CALLED FOR AS INSTRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUB	JECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND RETURNED TO	 SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS.				1	K	0	0 	  			 	G2EA    					 
2001073000019	20010730	00019	EA  	2001	7	30	CA010529003      	1	20010505	G	2910	C3CF6139	LINE            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYD SYSTEM	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA											(CAN) ON LANDING THE PILOT PUMPED THE FLAPS DOWN, WHEN THE FLAPS REACHED THE DOWN POSITION THE HYDRAULIC LINE TO THE FLA	P SELECTOR BROKE, LEAKING HYDRAULIC FLUID ON TO THE FLOOR. THE PILOT LANDED THE AIRCRAFT WITHOUT INCIDENT. UPON INVESTIG	ATION THE AME FOUND THAT THE HYDRAULIC LINE FROM THE HYDRAULIC FILTER TO THE FLAP SELECTOR HAD BROKEN OFF AT THE SELECTO	R. SUSPECT THAT THE PROBLEM WAS THAT THE HYDR AULIC LINE NUT WAS OVERTORQUED AT ONE TIME WHICH CAUSED THE FLAIR TO EVENT	FULLY BREAK OFF. THE LINE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE.. .		1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA	 
2001073000020	20010730	00020	EU  	2001	7	30	CA010529004      	1	20010507	G	2822	MS345613273P	CONNECTOR       			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  	ROTOL	R4304	R2124304    	EU  	FUEL PRESS SYS	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			664  								(CAN) THE PORT FUEL PRESSURE WARNING LIGHT WAS INITY RPTED FLICKERING IN FLT, LATER CAME ON STEADY. LIGHT REMAINED ON WH	EN CREW SELECTED POWER OFF DURING POST FLT SHUTDOWN ON RAMP.INVEST. REVEALED THAT PORT FWD WING ROOT BREAK CONNECTOR PL3	 HAD DEVELOPED AN INTERNAL SHORT BETWEEN PINS 4, 5 & 24 (NOTE: THIS A/C HAS AERO CONSULTING SRVCS "CONNECTOR MOD" NOC38 	550 INCORPORATED). THIS ALLOWED 24 VDC PORT BATTERY BUS BAR C/B 5 (5 AMP) THROUGH PIN 24 TO FEED PINS 4 & 5 (PORT FUEL L	OW PRESSURE SWITCH/WARNING LIGHT CCT) PIN 5 BEING F103 (3 AMP) CENTRE BUSS BAR NORMAL FEED TO PORT FUEL LOW PRESSURE SWI	TCH & PIN 4 BIENG LOAD SIDE OF PORT FUEL LOW PRESSURE SWITCH ALSO CONNECTED TO PORT LOW FUEL PRESSURE IND. LIGHT. PL3 W	2	L	7	2 	3T	4	T	 	A24EU   	A196	6	C	P899	 
2001070500005	20010705	00005	EU  	2001	7	5	CA010529005      	1	20010429	G	2421	740119G	IDG             	            	            	AIRBUS	320   	A320212     	       	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  	 		            		IDG	OVERSERVICED    	W			    	A	 	 	 	UNSCHED LANDING         				H	 	 	ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			CA		 				1970					(CAN) 35,000 CLIMBING - LOSS GEN #2 LOSS GEN #2 AND AC #2 RETURNED TO AIRPORT FOUND IDG (INTERGRATED DRIVE GENERATOR) #2	 OVERSERVICED.IDG #2 REPLACED. . LEAK CHECKED AND OPS CHECKED SERVICEABLE. ALL BUS TRANSFERS NORMAL, SERVICEABLE.. .. . 	. .				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001073000021	20010730	00021	EU  	2001	7	30	CA010529006      	1	20010426	G	2910	S43500272	MANIFOLD        			AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					HYD SYSTEM	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			DE	DESCENT        	1			CA			23300			1588					(CAN) YELLOW SYSTEM LOW LEVEL ECAM ON DESCENT INTO YYC - MAJOR HYDRAULIC LEAK EVIDENT AT BLOCK IN ON RAMP. FOUND YELLOW 	LEAK MEASUREMENT MANIFOLD LEAKING. REPLACED HYDRAULIC LEAK MEASUREMENT MANIFOLD. SYSTEM CHECKS SERVICEABLE IAW 29-19-41-	401.. . . .				2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2001073000036	20010730	00036	NE  	2001	7	30	CA010529007      	2	20010327	G	8550	12345	TUBE            			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	S3H1        	52016	NE  	HAMSTD	12D	12D40       	NE  	OIL TRANSFER	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				378  							(CAN) ENGINE SUMP WAS REQD TO BE REMVD FROM ENGINE TO FACILITATE CYLINDER REMOVAL. UPON REMOVAL OF SUMP, IT WAS DISCOVER	ED THAT DAMAGE HAD OCCURRED TO OIL TRANSFER TUBES FROM SUMP TO CRANKCASE. THIS HAD BEEN CAUSED BY IMPROPER ASSY OF ENGIN	E AT AN EARLIER REPAIR.				1	L	7	1 	3R	3	R	 	EXPA1L71	E143	5	C	P257	 
2001073000038	20010730	00038	GL  	2001	7	30	CA010529009      	1	20010327	G	5741		ATTACH FITTING  			NAMER 	T6    	HARVARDMK4  	1922828	GL  										WING	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			8496 								(CAN) OUTER WING ATTACHMENT HARDWARE CONSISTS OF 224 NUTS AND BOLTS FOR BOTH WINGS. APPROXIMATELY 40% OF THE NUTS USEDWE	RE OF A TYPE USED IN SHEAR APPLICATIONS (NAS679). CORRECT HARDWARE SHOULD HAVE BEEN AN365-428 AND AN365-524 NUTS AS CALL	ED FOR IN THE HARVARD PART LIST. HARDWARE WAS REPLACED AS REQUIRED.				1	L	7	1 	3R			 	EXPA1L71					 
2001073000041	20010730	00041	GL  	2001	7	30	CA010529010      	1	20010327	G	5522	662200110	SKIN            			NAMER 	T6    	HARVARDMK4  	1922828	GL  										ELEVATOR	MISREPAIRED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			84960								(CAN) ELEVATOR COVERING WAS OBSERVED DURING NORMAL INSPECTION TO HAVE CRACKING OF THE DOPE FINISH. FURTHER INVESTIGATION	 DISCOVERED BODY FILLER BETWEEN TWO SEPARATE DOPING AND PAINTING PROCESSES. UPON REMOVAL OF ELEVATOR, THE BALANCE CHECK 	CONFIRMED AN EXTREME TAIL HEAVINESS (IN EXCESS OF TWO POUNDS BEYOND ALLOWABLE LIMITS) OF BOTH ELEVATORS. ELEVATORS WERE 	REPLACED WITH SERVICEABLE SPARES. . .			1	L	7	1 	3R			 	EXPA1L71					 
2001073000045	20010730	00045	EU  	2001	7	30	CA010529013      	1	20010515	G	5532	202473	SKIN            			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4528 	4528 							(CAN) SMOKING WAS NOTICED AT THE ETOP R/H VERTICAL STAB SKIN. FURTHER INSPECTION REVEALED THAT THE REPAIR PATCH PREVIOUS	LY INSTALLED IAW PILATUS TECH MEMO EC-12-TM-540 WAS CRACKED AT APPROXIMATELY THE SAME LOCATION AS THE ORIGINAL SKIN CRAC	KED. THE FIRST REPAIR WAS CARRIED OUT AT 880.8 HOURS AND 1103 CYCLES. THE SECOND REPAIR CARRIED OUT AT 4528.4 HOURS AND 	5315 CYCLES UNDER TECH MEMO EC-12TM-939.. .			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073000048	20010730	00048	GL  	2001	7	30	CA010529015      	3	20010515	G	6114	7724981	PLATE           			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				5000 							(CAN) DURING LPI OF BARREL PLATE IT FOUND TO HAVE A CRACK THAT GOES ACROSS PACKING GROOVE FOR PACKING THAT SEALS BARREL 	PLATE TO BARREL. THIS PACKING SEALS BARREL LUBRICATING OIL INTO BARREL.THE BARREL PLATE IS ITEM #682.IPL FIGURE #1A, CMM	 61-13-01,REVISION 10.AFTER WE FOUND THIS BARREL PLATE CRACKED WE EXAMINED ANOTHER PROP FROM A DIFFERENT OPERATOR THAT &	 IT WAS ALSO FOUNDWITH A CRACKED BARREL PLATE.WE THEN CHECKED A 2ND BARREL PLATE FROM 2ND OPERATOR & IT ALSO HAD A VERY 	SMALL CRACK STARTING.THE 1ST OPERATOR THEN SENT 2 MORE BARREL ASSY TO TRY & SALVAGE THE BARREL PLATES FROM THEM & BARREL	 PLATES WERE ALSO FOUND CRACKED.THE 2ND REPL BARREL ASSY WAS REMVD FROM SERVICE WITH TIME SINCE LAST MAJOR INSP OF 6,32	2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001073000051	20010730	00051	SO  	2001	7	30	CA010529016      	1	20010427	G	7120	V961312	ISOLATOR        	PIPER       	1607305     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	ENGINE MOUNT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			665  			274721					(CAN) TO KEEP FRONT OF ENGINE FROM CONTACTING COWL, ADDITIONAL P/N 85012-101 WASHERS WERE FOUND UNDER LOWER CORD MOUNTS 	TO RAISE FRONT OF ENGINE. . . .					1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2001073000053	20010730	00053	SW  	2001	7	30	CA010529017      	1	20010427	G	1100		PLACARD         			RKWELL	700   	700         	7630520	SW  	LYC   	O540  	TIO540R2AD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE OIL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN ADDING OIL TO ENGINE WE NOTICED THAT EXTERNAL MARKING ON LITRE CONTAINER SAID "EXXON AVIATION OIL 100". WE CH	ECKED THE CARTON CONTAINING 12 LITRES AND IT READ "EXXON AVIATION OIL EE100". ONE INDICATED ASHLESS DISPERSANT OIL AND O	NE INDICATED STRAIGHT MINERAL OIL. DISTRIBUTOR FOR OIL CONFIRMED PROBLEM AND TOOK BACK ALL PRODUCT IN QUESTION. . . . .				1	L	7	2 	3O	3	O	 	A12SW   	E14EA	5	C	P33EA	 
2001073000056	20010730	00056	EU  	2001	7	30	CA010529020      	1	20010430	G	2550	S160919	SPACER          	SIREN       	S16096      	SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					CARGO HOOK	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			843  	843  		898					(CAN) WHEN THE HOOK ARRIVED AT E.C.L., THE SCREW AND NUT WHICH TIGHTEN THE SPACER (P/N S1609-19) HAD BEEN LOOSENED. IT W	AS TIGHTENED TO PERFORM INCOMING TESTS. THE CAM WHICH RELEASES THE LOAD BEAM WOULD NOT FUNCTION UNDER LIGHT LOAD (12 LBS	). AS THE LOAD WAS INCAREASED THE CAM WOULD BE PUSHED OUT OF THE PATH OF THE LOAD BEAM, BUT THE CAM WOULD NOT RETURN. WH	EN THIS OCCURES THE HOOK WILL NO LONGER HOLD A LOAD..			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001073000058	20010730	00058	NM  	2001	7	30	CA010529021      	1	20010415	G	3320	BA080061	BALLAST         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	LIGHTS	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA			3403 								(CAN) WHEN THE FLIGHT CREW ARRIVED AT THE AIRCRAFT (ON GATE WITH EXTERNAL POWER ON) THEY REPORTED A BURNING SMELL IN THE	 CABIN. THEY IMMEDIATELY TURNED OFF THE AIRCRAFT POWER. MAINTENANCE FOUND THE OVERHEADLIGHTING BALLAST FOR ROW 1 - R/H, 	HAD OVERHEATED AND BURNED OUT. THE BALLAST AND BULB WERE REPLACED AND CHECKED - SERVICEABLE. . .. .				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073000060	20010730	00060	NM  	2001	7	30	CA010529022      	1	20010423	G	2910	82950010271	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			25945								(CAN) DURING A WALK-AROUND, THE FLIGHT CREW NOTED FLUID LEAKING FROM THE R/H WING. MAINTENANCE FOUND THE HYDRAULIC TUBE 	(PRESSURE) TO THE R/H INBOARD ROLL SPOILER ACTUATOR LEAKING (PIN HOLE). THE HYDRAULIC TUBE WAS REPLACED AND ALL CHECKS C	OMPLETED. . . . .				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073000061	20010730	00061	SO  	2001	7	30	CA010529023      	2	20010425	G	8530	646605	NUT             	CONT        	646742      	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360D      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	CYLINDER SECTION	DAMAGED         	W				E				ENGINE SHUTDOWN         				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		TX	TAXI/GRND HDL  	1			CA				1432 							(CAN) AFTER LANDING PILOT WAS TAXIING FOR SHUTDOWN WHEN HE HEARD A BANKING NOISE AND REAR ENGINE ROUGHNESS. INSPECTION R	EVEALED A DENT IN VALVE COVER. COVER REMOVED AND FOUND BOTH ROCKER SHAFT HOLD DOWN STUDS SHEARED. IT HAS BEEN NOTED BEFO	RE ON OTHER AIRCRAFT THAT ROCKER SHAFT HOLD DOWN NUTS HAVE BEEN STRIPING EASILY EVEN WITH TELEDYNE CONTINENTAL NEW ROCKE	R SHAFT HOLD DOWN NUTS TORQUE VALVES. . .			1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2001073000073	20010730	00073	SW  	2001	7	30	CA010530009      	1	20010510	G	2550	9307U	BEARING         		52800200    	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					CARGO HOOK	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAL909					(CAN) DURING AN OPS CHECK IT WAS DISCOVERED THAT THE UPPER HOUSING NR 76 TO LOWER HOUSING NR 100, LOCK NR 79 WAS DISLODG	ED. FURTHER INVESTIGATION FOUND THAT THE BEARING NR 98 (WHICH ALLOWS THE CARGO HOOK TO ROTATE UNDER LOAD) WAS SEIZED DUE	 TO CORROSION. THERE ARE SEVERAL POSSIBLE AREAS THAT MOISTURE COULD ENTER THIS AREA. ONE WAS THE MANUAL RELEASE CABLE AN	D THE SEALANT AROUND IT WAS IN POOR CONDITION. THIS HOLE THROUGH THE UPPER HOUSING IN DETAILED IN THE PICTURE PROVIDED. 	THE HOOK ASSEMBLY IS BIENG REPLACED. TSO OF HOOK ASSY IS 9 MONTHS..		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001073000081	20010730	00081	EA  	2001	7	30	CA010531003      	1	20010422	G	2750	865D1007	DRIVE UNIT      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAPS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLAP FAIL CAUTION MESSAGE DISPLAY ON EICAS (ENGINE INDICATIONS AND CREW AL ERT SYSTEM), QRH PERFORM WITH A NORMAL 	LANDING. RESET DONE AND FOUND SERVICEABLE BUT DEFECT RE-OCCURRED. FECU (FLAP ELECTRONIC CONTROL UNIT) CHANGED AS A PREVE	NTIVE MEASURE WITHOUT ANY SUCCESS, THE DEFECT RE-OCCURRED, AFTER FURTHER INVESTIGATION, MAINTENANCE FOUND TO BE THE PDU 	(POWER DRIVE UNIT) TO BE AT FAULT. REPLACED POWER DRIVE UNIT AND ALSO ADJUSTED #6 & 7 POTENTIOMETERS FECU AND PDU WIRING	 CHECK (NIL FAULT DETECTED). FLAP RIGGED AND OPERATIONAL CHECK CARRIED OUT...		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001070500006	20010705	00006	EU  	2001	7	5	CA010531004      	1	20010428	G	5210	D5311253800000	BEARING         	AIRBUS      	            	AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  	 		            		DOOR HINGE	SEIZED          	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			DE	DESCENT        	1			CA		 									(CAN) PASSENGER DOOR L1 NOISEY DURING DECENT, WHEN DOOR OPENED ON ARRIVAL, , DOOR JAMMED. FOUND DOOR HINGE BEARING TO FR	AM, SEIZING. REPLD UPP ER & LOWER HINGE BEARINGS, OP CHECKED NORMAL.. . . . . .					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001073000083	20010730	00083	NM  	2001	7	30	CA010531005      	1	20010414	G	2150	EO390DD03S2B11B	RECEPTACLE      			AIRBUS	A319  	A319114     	       	NM  										FUSLEAGE	FAULTY          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) FORWARD CABIN CONDITION TRIM AIR VALVE SYSTEM AT FAULT, ECAM MESSAGE, LONG HISTORY, MINIMUM EQUIPMENT LIST 21-63-0	2 APPLIED. ON TROUBLESHOOTING, FOUND TRIM AIR VALVE CONNECTOR 1941VC RECEPTACLE & 1941VCA PLUG FOR ZONE CONTROLLER DAMAG	ED, BURNT PINS. ON TROUBLESHOOTING FOUND SHORT BETWEEN PIN 11A OF CONNECTOR AB AN PIN 5A OF AA CONNECTOR OF 8HK ZONE TEM	PERATURE CONTROLLER. PULLING ON CONNECTOR 1941VC CAUSED ARCING AND DAMAGE TO CONNECTOR 1941VC AND VCA. THE FAULTY RECEPT	ACLE AND PLUG IS LOCATED BELOW CABIN FLOOR AT STATION 1290. REPLACED CONNECTOR 1941VC AND 1941 VCA, FORWARD CABIN CONDIT	ION TRIM AIR SYSTEM TESTED, OPERATION NORMAL.	2	L	7	2 	4F			RT	A28NM   					 
2001073000084	20010730	00084	WP  	2001	7	30	CA010531006      	1	20010428	G	3320		TERMINAL BLOCK  			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					ROW 23	OVERHEATED      	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) ON ARRIVAL CREW REPORTE SMOKE AT ROW 23 LT CEILING. FOUND LUMINARE TERMINAL BLOCK OVERHEATED. LUMINARE ASSY REPLAC	ED AND TERMINAL BLOCK REPLACED AIRCRAFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001073000086	20010730	00086	WP  	2001	7	30	CA010531007      	1	20010508	G	4900	74275	FUEL BOWL       	PWC         	ST6         	LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					FUEL FILTER	CRACKED         	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA						74275					(CAN) DURING THE TAXI IN THE AIRCRAFT LOST APPROXIMATELY 600 LBS OF FUEL. MAINTENANCE FOUND FUELLEAK FROM APU. UPON INSP	ECTION FOUND THAT THE FUEL WAS COMING FROM THE LOW PRESSURE FUEL FILTER BOWL CRACKED AT MOUNTING FLANGE. BOWL REPLACED A	ND AIRCRAFT RETURNED TO SERVICE. BOWL MUST HAVE BEEN INSTALLED COCKED EYED AND THE BOLT WAS USED TO OVER TORQUE THE FLAN	GE TO SEAT THE BOWL PROPERLY. . . . .			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001070500007	20010705	00007	WP  	2001	7	5	CA010531008      	1	20010428	G	2400	2621TB9	TERMINAL BLOCK  	            	            	LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  	 		            		317 BB	FAILED          	W			    	K	 	 	 	NONE                    				P	 	 	NO WARNING INDICATION     			IN	INSP/MAINT     	1			CA		 									(CAN) FOLLOWING APU WARNING HORN RCCB TRIPPED OFF FOUND 5 WIRES WHERE THE INSULATION WAS BROKEN AND RELATED TERMINAL BUS	 CHEMICALLY DESTROYED BY SKYDROLL. APU FIRE-EX BOTTLE SQUIB WS INTERMITTENT DUE TO DAMAGE. REPLACED TERMINAL BLOCK AND R	EPAIRED WIRING AND AREA CLEAN FROM SKYDROLL AND INSPECTED FOR LEAKS. NO LEAKS WERE NOTED, AIRCRAFT RETURNED TO SERVICE. 	. . . .			2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001073000088	20010730	00088	CE  	2001	7	30	CA010621003      	1	20010524	G	2421	7565T	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	ENGINE	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			6    								(CAN) ALTERNATOR WS REMOVE TO CHECK FOR INSTALLATION OF NUT AND SPLINE DRIVE. COTTER PINE WAS BROKEN AND NUT WAS BACKED 	OFF ON SPLINE. BOTH THE NUT AND COTTER PIN WS FOUND INSIDE THE ENGINE SPLINE GEAR. ALTERNATOR WAS SENT TO MANUFACTURER F	OR OBSERVATIONS.				1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2001073000089	20010730	00089	CE  	2001	7	30	CA010621004      	1	20010518	G	2421	7565T	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	ENGINE	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			32   								(CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WAS REMOVED FOR REPLACEMENT. THE ALTERNA	TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONDSIDERATION. THE MANUFACTURER 9SKYTRONICS) CONTACTED ME AND INFORME	D ME THAT THE ROTORS AND STATORS WERE FRIED. THE REASON WAS UNKNOWN. RAM AIR WAS CONNECTED AND FUNCTIONING.				1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2001073000091	20010730	00091	CE  	2001	7	30	CA010621005      	1	20010420	G	2421	7565T	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			32   								(CAN) ALTERNATOR WAS REMOVED TO CHECK FOR INSTALLATION OF NUT ON SPLINE DRIVE. COTTOR PIN WAS BROKEN AND NUT WAS BACKED 	OFF THE SPLINE. BOTH THE NUT AND COTTER PIN WAS FOUND INSIDE THE ENGINE SPLINE GEAR. ALTERNATOR WAS SENT TO MANUFACTURER	 FOR OBSERVATIONS.				1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2001073000093	20010730	00093	CE  	2001	7	30	CA010621006      	1	20010425	G	2421	7565T	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	ENGINE	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			4    								(CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WAS REMOVED FOR REPLACEMENT. IT WAS NOTE	D THAT THE ALTERATOR DID HAVE A NUT INSTALLED ON THE SPLINE DRIVE. THE SPLINE DRIVE WAS NOTED TO BE SHEARED. THE ALTERNA	TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONSIDERATION.				1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2001073000094	20010730	00094	CE  	2001	7	30	CA010621007      	1	20010419	G	2421	7565T	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  	MCAULY	1A200	1A200FM     	GL  	DRIVE GEAR	FAILED          	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			295  								(CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WS REMOVED FOR REPLACEMENT. IT WAS NOTED	 THAT THE ALTERNATOR DID NOT HAVE A NUT INSTALLED ON SPLINE DRIVE. THE SPLINE DRIVE WAS NOTED TO BE SHEARED. THE ALTERNA	TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONSIDERATIONS.				1	H	7	1 	3O	3	O	 	5A5     	E269	5	N	P874	 
2001073000110	20010730	00110	EA  	2001	7	30	CA010621016      	1	20010601	G	7603	3011094	PIN             			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	POWER LEVER	MAKING METAL    	W				O				OTHER                   				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			16   	16   							(CAN) AT T/O POWER LEVER GOT NOTICIABLY DIFFICULT TO MOVE, EVENTUALLY SEIZING COMPLETELY AT LANDING. APPEARS TO BE MATER	IAL FAILURE OF PIN					1	H	7	1 	3R	4	T	 	A815    	E4EA	6	C	P15EA	 
2001073000119	20010730	00119	CE  	2001	7	30	CA010621018      	1	20010515	G	3242	1338932	STATOR          	BFGOODRICH  	215286      	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					RT BRAKE	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			637  			0534					(CAN) WHEN AIRCRAFT WAS TAXING FOR TAKE-OFF PILOTS REPORTED A LOUD NOISE AND THE AIRCRAFT BECAME DIFFICULT TO TAXI. THE 	PILOTS MADE AN ATTEMPT TO RETURN TO THE HANGAR BUT WERE UNABLE TO DO SO. MAINTENANCE PERSONNEL WERE CALLED, ANDUPON INSP	ECTION OF THE R/H BRAKE, DISCOVERED THAT A STATOR DISC HAD FAILED AND JAMMED THE MAIN WHEEL. THE BROKEN STATOR WAS REMOV	ED AND THE AIRCRAFT WAS TOWED BACK TO THE HANGAR AND REPAIRED AS REQUIRED.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001073000120	20010730	00120	EA  	2001	7	30	CA010621020      	1	20010515	G	3246	31279	WHEEL           			CNDAIR	CL215 	CL2151A10   	       	EA  										NLG	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON DISASSEMBLY OF NOSE WHEELS A SHARP DEEP GOUGE WAS FOUND IN THE VICINITY OF THE ONE WHEEL HALF. AFTER BLENDING	 THE DAMAGE WAS BEYOND THE LIMITS STATED IN THE B.F.G MANUAL. THE GAUGE APPEARED TO HAVE BEEN MADE DURING THE PREVIOUS D	ISASSEMBLY SUBSEQUENTLY FOUR OTHER WHEELS HAVE BEEN FOUND WITH THE SAME DAMAGE. THE WHEELS WERE REPLACED WITH SERVICEABL	E UNITS.			2	H	7	2 	4R			 	A14EA   					 
2001073000122	20010730	00122	SO  	2001	7	30	CA010621024      	1	20010508	G	3242	1107252132	HOSE            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	BRACK ASSY	BLOCKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRAKES ON 4TH SIDE WERE REPORTED GRABBING AND OCCASSIONALLY NOT RELEASING PROPERLY. BRAKE UNIT, SHUTTLE VALVE AND 	BRAKE PRESSURE REDUCER WERE ALL REPLACED WITH NO SUCCESSFUL RESULT. IT WAS DISCOVERED THAT THE ABOVE BRAKE HOSE HAD DETE	RIORATED INSIDE AND A SMALL PIECE OF RUBBER WAS ACTING LIKE A FLAPPER/CHECK VALUVE, RESTRICTING THE PROPER FLOW OF FLUID	 IN BOTH DIRECTIONS. 4 BRAKES WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001073000123	20010730	00123	WP  	2001	7	30	CA010621026      	1	20010524	G	7921	369H5656	PULLEY          	DOUG        	369H5656    	HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20      	03013	GL  					OIL COOLER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						HL9936					(CAN) OIL COOLER PULLEY IS MADE UP OF A SPLINE BELT PULLEY WITH A METAL RING THAT IS "STAKED" ONTO THE PULLEY. THE RING 	WAS FOUND AROUND THE ENGINE OUTPUT DRIVE SHAFT AFTER GROUND RUNNING THE A/C. A NEW PART WAS USED TO COMPARE THE STAKING 	MARKS ON THE OLD PULLEY. THE NEW PULLEY HAS 4 LARGE STAKE MARKS COMPARED TO 8 SMALLER STAKE MARKS ON THE OLD PULLEY.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001073000125	20010730	00125	CE  	2001	7	30	CA010621027      	1	20010526	G	3242	1338932	STATOR          	BFGOODRICH  	215286      	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE ASSY	CRACKED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA				670  		2164					(CAN) UPON LANDING IN QUESNEL B.C, WHEN THE PILOT APPLIED BRAKE HE FELT THE AIRCRAFT VIBRATE AND SHUTTER WHEN LH BRAKE A	PPLIED. THEY TAXIED TO THE RAMP AND NOTIFIED MAINTENANCE AFTER SHUTDOWN. INVESTIGATIONBY MAINTENANCE FOUND THAT THE BRAK	E WEAR PINS STILL INDICATED THERE WAS LIFE REMAINING ON THE BRAKES, HOWEVER THE BRAKE WAS WORN TO THE LIMITS AND THE INB	D STATOR WAS CRACKED THROUGH. THE BRAKE ASSEMBLY WAS REPLACED WITH AN OVERHAUL UNIT AND THE A IRCRAFT WAS RETURNED TO SE	RVICE.		1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001073000127	20010730	00127	CE  	2001	7	30	CA010621028      	1	20010520	G	3213	5081032017	AXLE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			1583 	1583 							(CAN) CREW REPORTED A HARD LANDING ON MAY 20/01 DURING LANDINGT. THE A/C WS INSPECTED WHERE THE MAINTENANCE STAFF NOTED 	WHAT WERE POSSIBLY CRACKS IN THE MAIN LANDING GEAR AXLE HOUSING. NDT WAS PERFORMED AND CONFIRMED THE PRESENCE OF CRACKS 	ONBOTH THE LEFT HAND AND RT SIDE. THE LOWER OLD AXLE ASSEMBLIES ARE CURRENTLY BEING REPLACED				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2001073000129	20010730	00129	EA  	2001	7	30	CA010621034      	1	20010606	G	7921	1893013	REGULATOR       		21563113805 	CNDAIR	CL215 	CL2151A10   	       	EA  										OIL COOLER	STUCK           	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) #2 ENGINE SHUT DOWN IN FLIGHT DUE TO HIGH OIL TEMPERATURE AND DECREASING OIL PRESSURE. MAIN OIL SCREEN INSPECTED A	ND NO CONTAMINATS WERE PRESENT. THE OIL COOLER REGULATOR WAS STUCK IN THE CLOSED POISITION. THE OIL COOLER REGULATOR WAS	 REPLACED, AIRCRAFT WAS GROUND RUN AND LEAK CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.				2	H	7	2 	4R			 	A14EA   					 
2001073000147	20010730	00147	CE  	2001	7	30	CA010622003      	1	20010529	G	3240	114800851143880	BRAKE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) PILOT DEPARTED CALGARY ON ROUTE TO PENTICTON. AT SOME POIN WHILE AIRBOURNE THE PARKING BRAKE WAS ENGAGED. DURING T	OUCHDOWN IN PENTICTON NR 2,3,& 4 MAIN TIRES BLEW. THE A/C VEERED TO THE RIGHT, THE PILOTS MAINTAINED CONTROL AND THE A/C	 STOPPED AT SOME POINT ON THE RUNWAY. AS A RESULT OF THE TIRES BLOWING NR 3 & 4 MAIN WHEELS AND BRAKES WERE DAMAGED BEYO	ND REPAIR. A MAINTENANCE CREW WAS FLOWN TO PENTICTON WHERE THE A/C WA JACKED UP, TIRES AND BRAKES REMOVED, NR 1 & 2 BRAK	E ASSEWMBLIES WERE FOUND SERVICABLE. NR 3 & 4 BRAKE ASSEMBLIES WERE REPLACED. ALL FOUR MAIN WHEEL ASSY'S WERE REPLACED. 	THE A/C WAS THEN RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2001073000148	20010730	00148	EA  	2001	7	30	CA010622004      	2	20010531	G	7261		GARLOCK SEAL    			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CL	CLIMB          	1			CA											(CAN) LT ENGINE LOST OIL PRESSURE DURING CLIMB OUT OF AFTER APPROX. 20 MINUTES. PILOT SECURED ENGINE WHEN OIL PRESSURE W	AS IN YELLOW ARC OF OIL GAUGE. AIRCRAFT LANDED UNEVENTUALLY ATER RETURNING TO YUR. MAINTENANCE FOUND THAT MOST OF THE OI	L HAD BEEN EJECTED OVERBOARD THROUGH THE FUEL PUMP CASE DRAIN. GARLOCK SEAL AND CARRIER SEAL WERE REPLACED TWICE WITHOUT	 RESULTS. IVESTIGATION STILL IN PROGRESS. LT ENGINE POWER SECTION AND OIL COOLER WERE REPLACED THE 2 DAYS BEFORE. OIL LE	AK WAS ALSO REPORTED 1 DAY BEFORE AND THE THRMAL BYPASS VALCE WAS REPLACED. GROUND RUS CHECKED SERVICEABLE.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2001073000177	20010730	00177	SW  	2001	7	30	CA010622018      	1	20010528	G	3310	60647	POTENTIOMETER   			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	COCKPIT	SPARKS          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			545  								(CAN) IN FLT, A/C EXPERIENCED "SHOWER OF SPARKS" EMINATING FROM L OWER INSTRUMENT LIGHTING DIMMER POTENTIMETER. DURING A	PPROACH PILOT TRIED TO ADJUST THELOWER INSTRUMENT DIMMER THESPAR KS FLEW UPON LDG.THE INST WAS INSP/IT WAS NOTED THAT SO	LDERED CONNECTION OF BOTH UPPER & LOWER INSTRUMENT DIMMER POTTS WERE CONTACTING EACHOTHER. SINC E THERE IS NO POSITIVE E	NGAGEMENT  OF POTENTIOMETER TO INSTRUMNET PANEL. IF ATTACH NUT ON POTENTIOMETER BECOMES SLIGHT LOOSE, POT ROTATE & CONTA	CT ADJACENT POT. BOTH POTENTIOMETERS WERE RE-SECURED IN ASAFE POS AND  CHECKED FOR CORRECT OP/OTHER DAMAGE TO SYS. FLEET	 CHECK. ONLY ONE OTHER A/C HAD A LOOSE POTENTIOMETER.	1	L	7	1 	3T	4	T	NC	A19SW   	E26NE	6	C	P44GL	 
2001073000179	20010730	00179	EA  	2001	7	30	CA010622019      	1	20010522	G	2752	MS28775142	SEAL            		215750108   	CNDAIR	CL215 	CL2151A10   	       	EA  										FLAP ACTUATOR	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						H358					(CAN) A/C HAD BEEN ON GROUND 45 MINS WIHT NO SIGN OF FLUID LEAK. SUDDEN HYDRAULIC FLUID STARTED TO LEAK FROM R/H FLAP AC	TUATOR & FLAPS DROOPED TO APPROX. 10 DEGS. FLUID WAS COMING F ROM LOWER END SEAL. ACTUATOR WAS CLEANED & FLAPS WERE CYCL	ED 20 TIMES WITH NO FURTHER SIGNS OF LEAKAGE. A/C WAS RT-SRV. A/C WAS PARKED FOR NIGHT WITH NO S IGNS O F LEAKS. UPON DA	ILY INSPS NEXT MORNING FLAPS WERE FOUND SAGGED TO APPROX. 10 DEGS/ PUDDLE OF HYD. FLUID FOUND BELOW R/H FLAP ACTUATOR. F	LAPS WERE CYCLED WITH THEAUX FLUID PU MP/ A STREAM OF FLUID EMITTED FROM LOWER END OF ACTUATOR ON 1ST CYCLE ONLY.NO SIGN	S OF LEAKAGE FOLLOWING 10 CYCLES.	2	H	7	2 	4R			 	A14EA   					 
2001073000181	20010730	00181	CE  	2001	7	30	CA010622021      	1	20010608	G	5347	50150193	CHANNEL         	CESSNA      	501509797   	CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C87    	GL  	SEAT SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5890 	5890 							(CAN) BROUGHT THE A/C IN TO ADJUST THE LOW FUEL PRESS ON THE AUX FUEL PUMP. TO D0SO YOU MUST REMOVE THE PILOT SEAT & ADJ	UST A RESISTOR UNDER THE PILOT SEAT SUPPORT ASSY. THAT IS WHEN NOTICED THE CRACKIN THE LOWER R/H SEAT SUPPORT ASSY BOTTO	M CHANNEL				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001073000183	20010730	00183	EA  	2001	7	30	CA010622024      	2	20010421	G	8530	75838	VALVE GUIDE     	LYC         	LW12966     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			41   								(CAN) ON THE 1ST EVENT INSPECTION AFTER ENGINE WAS INSTALLED FOUND NR 5 CYLINDER FAILED COMPRESSION CHECK WITH 15/80. PR	OGRESSIVE AIR IN KAMLOOPS SUSPECTS GUIDE WORN. RETURNED CYLIDER TO THEM FOR WARRANTY CONSIDERATION.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2001073000185	20010730	00185	CE  	2001	7	30	CA010622025      	1	20010605	G	3213	504100036	ATTACH FITTING  			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION, THE LOWER SCISSOR ATTACH LUG WAS FOUND CRACKED. THE CRACK WAS FOUNDONLY AROUND THE SMALLER L	UG. THE RT LANDING GEAR AXLE ASSE MBLY WAS REPLACED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001073000188	20010730	00188	CE  	2001	7	30	CA010622028      	1	20010605	G	5743	52920048	DOUBLER         			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE COMPLETING AN INSPECTION A CRACK WAS FOUND ON THE RT MAIN LANDING GEAR DOUBLER. A WING RIB IMPROVEMENT KIT (	SK414-8E) WAS PREVIOUSLY INSTALLED. DOUBLER P/N 5292004-8 WAS PART OF THE KIT. IT WAS THIS DOUBLER THAT WAS AGA IN FOUND	 CRACKED. THE DOUBLER WAS REPLACED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2001073000196	20010730	00196	EA  	2001	7	30	CA010622029      	1	20010512	G	7810	311178001	EXHAUST STACK   			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A34      	52043	EA  					LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			870  	870  							(CAN) ON A 100 HOUR INSPECTION A CRACK WAS FOUND ON THE LT EXHAUST STACK MOUNTI NG FLANG OF THE TURBINE_EXHAUST DUCT. DU	E TO THE FACT THAT THERE WAS SO LITTLE TIME ON THE ENGINE I CALLED P&W AND THEY SENT A REP. & A NEW PART FOR OUR AIRCRAF	T. THE REP DID NOT KNOW WAY OUR EXHAUST WOULD CRACK. WE ARE NOW LOOKING AT THE EXHAUST AT 50 HOURS INTERVALS FOR THE NEX	T LITLE WHILE TO SEE IF WE GET ANY MORE CRACKS.			1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001073000198	20010730	00198	EU  	2001	7	30	CA010622032      	1	20010530	G	2560	AFG0314294	SEAT BELT       			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INERTIA REELS, EACH 2 WERE RE-WEBBED BY AN UNAUTHORIZED REPAIR FACILITY IN CANADA. IT IS UNKNOWN IF WEBBING / THRE	AD MEETS REQUIRMENT SPECIFICATIONS / IF THE HARNESS ASSY WOULD TENSUKE TEST TO PROPER FOR MATERIAL / STITCH PATTERN. PAR	TS WERE RE-WEBBED AND CERTIFIED WITH PROPER MATERIALS AND TC24-0045 CONFORMITY CERTIFICATIONS ISSUED PARTS RETURNED TO S	ERVICE.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001073000199	20010730	00199	SO  	2001	7	30	CA010622033      	2	20010604	G	7314	6462121	PUMP            			CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			570  								(CAN) THE PILOT NOTED FUEL DRIPPING FROM THE OVERBOARD DRAIN TUBE. MAINTENANCE DISCOVERED FUEL COMING FROM THE FUEL PUMP	 SEAL DRAIN. THERE IS A CRITICAL SERVICE BULLETIN C53 01-01. ALTHOUGH THE PART NUMBER DID NOT MATCH THE BASIC FUEL PUMP 	WAS IDENTIFIED BY THE PRESENCE OF TWO ROUND BOSSES LOCATED ON OPPOSITE SIDES OF THE FUEL PUMP HOUSING OWNER /AME SHOULD 	BE ALERT TO ANY FUEL LEAKAGE IN THIS AREA.			1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2001073000200	20010730	00200	EA  	2001	7	30	CA010622034      	1	20010515	G	2510	FDC2700	SEAT BELT       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 10 PAX LAP BELT ASSY'S WERE REPAIRED AND CERTIFIED BY UNAUTHORIZED REPAIR FACILITY. UNKNOWN IF WEBBING MATERIAL AN	D THREAD MEETS SPECIFICATION. UNKNOWN IF STITCH PATTERN WILL TENSILE TEST TO REQUIRED LIMIT. LAP BELTS WERE RE-WEBBED TO	 PROPER 1500 LB CINFIGURATION WITH CERTIFIED MATERIALS. TENSILE TEST TO 1500 LSB CARRIED OUT. PROPER TAGS WERE INSTALLED	 ON BELTS AND 24-0045 CONFORMITY CERTIFICATIONISSUED. PARTS RETURNED TO SERVICE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA	 
2001073000201	20010730	00201	EU  	2001	7	30	CA010622035      	1	20010606	G	5280	137414B416	DOOR            			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	MLG	BENT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE GEAR WAS SELECTED DOWN FOR LANDING. A VIBRATION WAS FELT AND THE AIRCRAFT DELVELOPED A SLIGHT YAW TO THE RIGHT	. THE YAW WAS TRIMMED OUTAND THE LA NDING CONTINUED. AFTER LANDING IT WAS DISCOVERED THAT THE RT GEAR DOOR WAS HANGING L	OOSE. ON INSPECTION IT WAS FOUND THAT THE ROD CONNECTINGTHE DOOR TO THE GEAR HAD FAILED IN COMPRESSION AND THE AFT HINGE	 WAS BROKEN. THE DOOR WAS BENT OUTWARD FROM A POINT ABOUT 7 INCHES INBOARD OF THE HINGE LINE. IT APPEARS THAT THE DOOR H	UNG UP ON THE EDGE OF THE LANDING GEAR BAY. THE ACTION OF THE GEAR LOWERING PUSHED DOWN ON THE DOOR CAUSING IT TO BEND O	UTWARDS AND EVENTUALLY BREAK THE OPERATING ROD.	2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	3PNE	 
2001073000202	20010730	00202	SO  	2001	7	30	CA010622036      	2	20010507	G	8520	6419311075	BOLT            			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	LT ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				973  							(CAN) UPON INSPECTION (EVENT 1 & 2), TAKING THE COWLING OFF ON LEFT ENGINE, A NUT WITH PART OF THE THRU BOLT HIT THE FLO	OR, FURTHER INSPECTION FOUND THE LEFT THRU BOLT HAS SNAPPED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA	 
2001073000203	20010730	00203	SO  	2001	7	30	CA010622037      	1	20010705	G	3320	10002719	LIGHT           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	CABIN	SPARKS          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) CUSTOMER REPORTED SPARKS FROM LOOSE OVERHEAD LIGHT IN 7TH ROW, LEFT SIDE.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA	 
2001073000204	20010730	00204	EU  	2001	7	30	CA010625001      	1	20010613	G	3210	200877664	PIN             			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			28020	7342 							(CAN) LARGE SECTION OF CHROME MISSING FROM DIAMETER "A" PIN (PARENT METAL CORRODED UNDER AREA OF MISSING CHROME) DEFECT 	FOUND REMOVAL OF PIN WHEN RETRACTION ACTUATOR REPLACEMENT WAS REQUIRED. PIN REPLACED. ADDITIONAL INFORMATION & PICTURES 	E-MAILED TO STEVE DUDKA AT TRANSPORT CANADA.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001073000206	20010730	00206	NM  	2001	7	30	CA010625002      	1	20010611	G	5330		SKIN            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			51026								(CAN) CRACKED FUSELAGE SKIN LEFT SIDE, BETWEEN FUSELAGE STATIONS 747 ABD 767, STRINGER 17L. REPAIRED AS PER SRM 53-30-3,	 TABLE 1, METHOD 1 PAGES 87,88 & 88A.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073000208	20010730	00208	NM  	2001	7	30	CA010625004      	1	20010611	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			52471								(CAN) CRACK IN FUSELAGE SKIN LEFT SIDE, BETWEEN FUSELAGE STATIONS 747 AND 767, STRINGER 17L. REPAIRED AS PER SRM 53-30-3	, TABLE 1, METHOD 1, PAGES 87,88 & 88A.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001073000228	20010730	00228	CE  	2001	7	30	CA010625005      	1	20010616	G	6120	11538900215	CONTROL CABLE   	HARTZL      	HCB3TN3G    	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						BUA20464					(CAN) WHILE OPERATING IN CRUISE FLIGHT, A SELECTION OF THE PROPELLOR LEVER CONTROL FOR THE RIGHT ENGINE WAS MADE WITH NO	 CHANGE IN PROP RPM. ANOTHER SETTING WAS TRIED WITH NO RESPONSE. THE RPM REAMINED AT 1900. THE FLIGHT ROUTIG WAS CANCELL	ED AND TH AIRCRAFT RETURNED FOR MAINTENANCE INSPECTION. MAI NTENANCE DETERMINED THAT THE PROPELLER CONTROL PUSH/PULL CAB	LE ASSEMBLY HAD BROKEN ABOUT 3 INCHES INSIDE OF THE HOUSING AT THE COCKPIT LEVER END. THERE WERE NO PREVIOUS INDICATIONS	 OR REPORTS OF A STIFF OR ROUGH PROP LEVER CONTROL. THE BROKEN CABLE ASSY WAS REMOVED FOR REPLACEMENT WITH A NEW ASSEMBL	Y.	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001073000277	20010730	00277	CE  	2001	7	30	CA010625010      	1	20010531	G	5610	10138402522	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1241 								(CAN) A/C WAS ENROUTE AT FL. 310, WINDHIELD ANTI-ICE WAS SE LECTED ON.SUDDENLY A LOUD CRACK WAS HEARD AND THE CO-PILOTS 	WINDHIELD SHATTERED AND THE INNER PANE INTO MANY SMALL PIECES. CR EW FOLOWED CHECKLIST FOR CRAKED WIND AND A/C DESENDED 	TO 12,000 FT ASL AND LANDED. CO-PILOTS WINDSHIELD ASSYWAS REPALACED AND IT WAS CONFIRM ED THAT THE H.P AND L.P HEAT ELEM	ENTS AND CONTROL SENSOR ON THE FAILED WINDSHIELD PANEL WERE SERVICEABLE. LATEST WINDSHIELD AVAILABLE P/N 101-384025-2 4 	INCORPORATING NEW INTERLAYER MATERIAL (PPG-12) INSTALLED, TO REPLACE FAILED WINDSHIELD.		2	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P56GL	 
2001073000278	20010730	00278	SW  	2001	7	30	CA010625011      	1	20010516	G	5311		FRAME           			AIRTRC	AT802 	AT802       	0390305	SW  										FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50   								(CAN) ON INSPECTION THE RUDDER CABLE AND RUDER TRIM CABLE WERE FOUND TO BE RUBBING ON THE CUT-OUT IN THE BULKHEAD AT THE	 FS 180.					1	L	7	1 	3T			NC	A19SW   					 
2001073000306	20010730	00306	SO  	2001	7	30	CA010625013      	1	20010605	G	5751	6237601	DOUBLER         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION CRACKS WERE NOTED ALONG THE BEND RADIUS OF PARTS (REFER PHOTOS ATTACHED). SUSPECT DAMAGE 	WAS CAUSED FROM CONTROLS NOT BEING PROPERLY SECURED ALLOWING AILERONS TO WORK UP ANDDOWN DURING WINDY CONDITION S._P/N'S	 66767-00 & 66767-01.				1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2001073000307	20010730	00307	SW  	2001	7	30	CA010625014      	1	20010607	G	3246	40279	WHEEL           			AIRTRC	AT802 	AT802       	0390305	SW  										MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25   								(CAN) UPON DISASSEMBLY OF WHEEL MAINTENANCE DISCOVERED SERIOUS CORROSION AT THE TOP AND BOTTOM OF THE OUTER BEARING RACE	.					1	L	7	1 	3T			NC	A19SW   					 
2001073000308	20010730	00308	SO  	2001	7	30	CA010625015      	1	20010525	G	2140		COMBUSTION LINER	JANITROL    	90D381      	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	HEATER	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			O			OTHER                     			CL	CLIMB          	1			CA				283  		4791851					(CAN) PILOT SMELLED A STRANGE BURING SMELL IN COCKPIT WHICH LAST APPROX. 30 SEC AND DISAPPEARED. SHORTLY FOLLOWING SHE S	TARTED FEELING A FLOATING SENSATION /TRANSFERRED CONTROL TO STUDENT/WITHIN 30 SEC THE STUDENT FEELING SAME EFFECTS.THE P	ILOT THAN DECLARED EMERGENCY AND REGAINED CONTROL FLIGHT WAS IMC. WE OPENED THE STORM WINDOW SHUT OFF HEATER/CHECKED THE	 CO DETECTIR WHICH INDICATED NORMAL. WITHIN 30SEC WE FELT BETTER WITH THE FRESH AIR AND LANDED WIT HOUT INCIDENT. INSPEC	TION SHOWED AIRCRAFT HEATING SYSTEM REVEALED A 2.5-3 INCH CRACK IN THE COMBUSTION HEATER CAN, IN THE AFT WELDED LID. HEA	TER W AS REPLACED. NEXT DUE FOR PRESSURE DECAY TEST AT 500HR. HEATER HOBBS TIME.	1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2001073000309	20010730	00309	CE  	2001	7	30	CA010625016      	1	20010530	G	5751	50130016	HINGE BRACKET   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	RT AILERON	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT FOUND AILERON SECURED ONLY BY OUTBOARD HINGE AND PUSHROD DURING WALK AROUND INSPECTION. THE SCREWS FOR THE I	NBOARD AND MIDDLE HINGE BRACKETS WERE IN PLACE, BUT NOT THROUGH THE BRACKETS. THE AILERON WAS REMOVED IN NOV 98 FOR PAIN	T. THE A/C WENT THROUGH A FULL PHASE 1-4 INSPECTION IN OCT. 99. THE A/C WENT THROUGH ANOTHER FULLPHASE 1-4 INSPECTION IN	 FEB 2001 WHO ALSO CONDUCTED THE EXPORT C OFA.CANADIAN APPROVAL WAS THEN CARRIED OUT IN TORONTO. P/N'S 50-130016 & 50-13	0021.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	5	C	STC	 
2001073000310	20010730	00310	SO  	2001	7	30	CA010625017      	1	20010605	G	5740	62102000	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AILERON SUPPORT BRACKET AT BOLT HOLE WERE FOUND CRACKED WITH THE RIGHT HAN D PART COMPLETLY BROKEN AS PER PHOTO. S	USPECT CAUSE-CONTROLS NOT SECURED BUT ALLOWED TOFLOP AROUND DURING WINDY CONDITIONS, PROBABLY OVER A PERIOD OF TIME._P/N	'S 62102-000(LEFT) 62102-001(RIGHT)				1	L	7	1 	3O	3	O	 	2A13    	E274	5	N	P88614	 
2001073000311	20010730	00311	NE  	2001	7	30	CA010625019      	3	20010509	G	6114	78230101	BEARING         		14SF7       	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	PROP HUB	GOUGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10500			8992					(CAN) SUSPECT ELECTRICAL ARCING OR DELAMINATION OF CHROME COATING FROM SUB SURFACE STRUCTURE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073000312	20010730	00312	EA  	2001	7	30	CA010625024      	2	20010509	G	7200	PT6A41	ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RIGHT	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			8808 	980  							(CAN) ABOUT 1 HR INTO FLT CREW NOTED A SLIGHT FLUNCTUATION IN RT ENGINE TORQUE ALONG WITH A REDUCTION IN ENGINE NG SPEED	. ITT ALSO INCREASED 50 DEGS HIGHER THAN NORMAL FOR CRUISE POWER.THE CREW MONITORE ENGINE PARAMETERS & NOTED A FURTHER D	ECREASE IN NG TO BELOW NORMAL OP LIMITS WITH INCREASES IN ITT. REW ELECTED TO SHUTDOWN ENGINE IN ACCORD WITH AFM AND SOP	'S & RETURNED TO MAIN BASE FOR FURTHER INVEST.. A/C LANDED W/O FURTHER INCID..MAINT INSP OF ENGINE REVEALED THAT ACCESSO	RY SECTION /GAS GEN GROUP HAVE SIGNS OF INTERNAL DAMAGED AS INDICATED BY INABILITY TO ROTATE SEVERAL OF DRIVES. NO FURTH	ER TEAR DOWN OF ENGINE WILL TAKE	1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001073000313	20010730	00313	SW  	2001	7	30	CA010625025      	1	20010430	G	2150		BEARING         			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	COOLING TURBINE	SEIZED          	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) AFTER LDG /DURING TAXI TO TERMINAL BLDG CREW NOTICED A SMOKY HAZE IN FWD CABIN& COCKPIT AREA. THEY IMMEDIATELY TUR	NED OFF LEFT & RIGHT BLEED AIR SWITCHES & THEN ELECTED TO SHUTDOWN ENGINES WHEN THEY DIDN'T SEE ANY NOTICEABLE CHANGE WI	TH SWITCHES SELECTED OFF.THE CREW & PASSENGERS DEPLANED A/C W/O FURTHER INCID.. MAINT RETURNED A/C TO TH HANGAR & BEGAN 	AN INSP INTO CAUES OF INCID.. IT WAS DETERMINED THAT LEFT AIR-COND, COOLING TURBINE WAS INOPERATIVE & HAD SEIZED. IT APP	EARS THAT BEARING IN THEUNIT IS AT FAULT, RESULTING IN AN IMBALANCE IN ROTATING IMPELLER. THIS RESULTED IN IMPELLER RUBB	ING ON SHROUD CAUSING IT TO FAIL	2	L	7	2 	4T			RT	A8SW    		6	C	P61GL	 
2001073000314	20010730	00314	CE  	2001	7	30	CA010625026      	1	20010529	G	7120		MOUNT           			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	LT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3199 								(CAN) ENG MOUNT FOUND CRACKED ON UPPER LT STRUT.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2001073000315	20010730	00315	NM  	2001	7	30	CA010625028      	1	20010614	G	3241		CONNECTOR       			BOEING	737   	737281      	138448P	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG BRAKE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				187  							(CAN) IN TROUBLE SHOOTING A HISTORY OF INTERMITTENT ANTI-SKID PROBLEMS IT WAS DISCOVERED THAT THE HYDRAULIC BRAKE PRESSU	RE LINES FROM THE AIRFRAME TO THE TOP OF THE R.H LANDING GEAR SWIVELS THE CONNECTORSTOTHE WHEEL SPEED TRANSDUCERS WERE S	WAPPED TO THE OPPOSITE WHEEL. THE A/C WAS RESTORED TO NORMAL. NO FURTHER PROBLEMS OCCURRED. THE FAULT HISTORY INDICATED 	ON GEAR INSTALLATION AT T THIRD PARTY A.M.O.THE OVER HAULER WAS ADVISED AND IS IMPLEMENTING CHANGES IN THEIR PROCEDURES.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073000316	20010730	00316	EU  	2001	7	30	CA010625029      	1	20010613	G	7110	5711012367	HINGE           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6560 								(CAN) DURING AN INSPECTION OF THE FLAP ASSY FOR THE OIL COOLER DOR A 1" CRACK WASFOUND DBETWEEN THE MOUNTING HOLES AND T	HE HINGE. NEW PART WAS INSTALLED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073000318	20010730	00318	GL  	2001	7	30	CA010625031      	2	20010606	G	7230	6890550	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			6228 	2980 							(CAN) PILOT FELT ENGINE VIBRATION, 30 MINUTES INTO THE FLIGHT, WITH CLIMB OF T.O.O. TURN BACK FOR LANDING. ENGINE OIL PR	ESS FLACTUATE. 6FT ABOVE GROUND THE ENGINE QUIT. THE PILOT DID LOWER AUTOROTATION, NO DAMAGE TO AIRCRAFT AND NO ONE GOT 	INJURED. INITIAL INSPECTATION WAS DONE AND FOUND THAT COMPRESSOR BLADES WERE DAMAGED AND NR  1 BEARING AND SEAT FAILED. 	ENGINE ASSY REMOVE /REPLACED /SENT FOR EVALUATION.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001073000319	20010730	00319	CE  	2001	7	30	CA010625033      	1	20010518	G	3234	998100753	BRACKET         		11581102011 	BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					SWITCH MOUNT	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SWITCH MOUNT FLANGE NOT BENT PROPERLY PER DRAWING TO OBTAIN 90 DEGREE RELATIONSHIP WITH PIVOT POINT. THIS RESULTS 	IN A SMALLER RANGE OF ADJUSTMENT. SWITCH P/N 622EN51 (HONEYWELL) INTERNAL SPRING IS SOSTIFF(3-6LBS) THE BRACKET FLEXES E	XCESSIVELY AS THE SWITCH IS BEING ACTIVATED. THIS ALSO RESULTS IN REDUCING RANGE OF ADJUSTMENT. HAVE TALKED TO RAYTHEON 	TECH SUPPORT.			1	L	7	2 	4T	4	T	 	A31CE   	E4EA				 
2001073000320	20010730	00320	EA  	2001	7	30	CA010625034      	2	20010518	G	7414	10682056	DISTRIBUTOR BLK 	BENDIX      	D6LN3200    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	DUAL MAGNETO	WORN            	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA				1335 		4072013					(CAN) PILOT EXPERIENCED ROUGH RUNNING ENGINE SHORTLY AFTER TAKEOFF. INSPECTION OF THE MAGNETO REVEALED A SEVERLY WORN BR	ONZE BUSHING ON THE DISTRIBUTOR BLOCK. ROUGH RUNNING WAS ATTRIBUTED TO INTERNAL CONTAMINATION OF THE MAGNETO WITH FINE B	RONZE FILINGS, PARTIALLY SHORTING THE CONTACTS.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2001073000321	20010730	00321	NM  	2001	7	30	CA010625035      	1	20010625	G	3246	2601450	WHEEL           			BOEING	737   	737200      	1384453	NM  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				467  							(CAN) DURING TEAR DOWN FOR OVERHAUL CRACK WERE DISCOVERED EMANTAING FROM THE BEARING CUP BORE AND EXTENDING INTO THE SPO	KE WEBS ABD REACHING TO WITHIN 1" OF SPLITTING THE HUB. THE PART WAS BER'D THE LAST OVERHAUL INCLUDED LIQUID PENETRANT I	NSPECTION AND HIGH FREQUENCY EDDY CURRENT INSPECTION AT WHICH TIMENO ANOMALIES WERE INDICATED.				2	L	7	2 	4F			 	A16WE   					 
2001073000322	20010730	00322	CE  	2001	7	30	CA010625037      	1	20010514	G	3213	14504A20100J	WASHER          	CESSNA      	208B        	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TRUNNION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2255 			26410081					(CAN) DURING INSPECTION, MAINTENANCE FOUND THE PIN SECURING THE MAIN LANDING GEAR SPRING (LEG) HAD MOVED AFT APPROXIMATE	LY 3/4 OF AN INCH.MAINTENANCE CONCLUDED WASHER (ITEM 28-FORWARD) WAS DISHED AND FRACTUR ED DUE TO OVERTORQUING OF BOLT (	ITEM 30) AND NUT.T HE TWO WASHERS (ITEM28) ARE FOR THE PURPOSE OF RETAINING PIN (ITEM 27) WITHIN ITS BORE. REF:FIGURE 01	,32-10-00 OF THE 208 IPC			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001073000323	20010730	00323	CE  	2001	7	30	CA010625038      	1	20010522	G	5521	115610010169	RIB             	BEECH       	115610010347	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8742 								(CAN) WHEN REMOVING RH ELEVATOR FOR INSTALLATION OF UPDATE KIT # 100-4005-1SWAS FOUND INBOARD RIB CRACKED TWO PLACES AT 	FORWARD END. RIB REPLACED WITH FACTORY NEW.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001073000324	20010730	00324	CE  	2001	7	30	CA010625039      	1	20010606	G	2750	12602442	TUBE            	CESSNA      	12602441    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	TE FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6441 								(CAN) FOUND DURING A SCHEDULED 200 HOUR INSPECTATION. TUBE ASSY BROKE AT A POINT OF APPROX. 3/8" OUTBOARD OF THE INBOARD	 ROD END. (AT THE BASE OF THE THREADS). TUBE THEN RESTED ON TOP OF THE FLAP MOTOR AND BELLCRANK.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2001073000325	20010730	00325	EA  	2001	7	30	CA010625043      	2	20010515	G	8530	16T19468	EXHAUST VALVE   		LW12966     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						J3151					(CAN) ON GROUND RUN PILOT REPORTED R/H ENGINE RUNNING ROUGH. MAINTENANCE FOUND #2CYLINDER, EXHAUST VALVE SEAT DISLODGED,	 DAMAGING THE PISTON. ENGINE HAD METAL CONTAMINATION. ENGINE FIREWALL FORWARD REPLACEDWITH O/H UNIT AND COMPONENTS AND H	OSES. CYLINDER ASSY HAD 596.4 HOURS SINCE REPAIR.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001073000326	20010730	00326	EA  	2001	7	30	CA010625044      	2	20010611	G	8520	T10540J2BD	CONNECTING ROD  	CONT        	TIO540J2BD  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA				2418 		L798161A					(CAN) ON TAKEOFF FROM YVG (VERMILION) THE PILOT NOTICED THE LH ENGINE STARTED TO RUN ROUGH AND LOSE POWER. THE ENGINE TH	EN STARTED TO VIBRATE BADLY AT WHICH POINT THE PILOT STOPPED AND FEATHERED THE # 1 ENGINE. THE AIRCRAFT RETURNED TO VERM	ILION WHERE MAINTENANCE CHANGED THE #1 ENGINE. UPON INSPECTION, MAINTENANCE FOUND THE # 6 CYLINDER CONNECTING ROD DETATC	HED FROM PISTON. SUBSEQUENT ROTATION OF ENGINEAND CONNECTING ROD CAUSED SEVERE DAMAGE TO CRANKCASE AND CAMSHAFT VISIBLE 	THROUGH HOLE IN CRANKCASE ABOVE # 5 CYLINDER CASUING ENGINE STOPPAGE. THE ABOVE ENGINE WAS RUNNING ON CONDITION. WE ARE 	PRESENTLY REVIEWING OUR ON CONDITION PROCEDURES.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001073000327	20010730	00327	NM  	2001	7	30	CA010625046      	1	20010530	G	2612		FIRE DETECTOR   			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					APU	SHORTED         	W				F				ACTIVATE FIRE EXT.      				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) IN CRUISE 15 MIN AFTER APU SHUT DOWN. APU FIRE WARNING OCCURED. FIRE HANDLED PULLED AND BOTTLE DISCHARED. FIRE IND	ICATION TERMINATED. AFTER APPROX. 30 SEC. FIRE TEST CARRIED OUT, ALL INDICATIONS NORMAL. FLIGHT CONTINUED NO FURTHER PRO	BLEM. INVESTIGATION ON GROUND FOUND NO EVIDENCE OF FIRE OR OVER HEATING DAMAGE TROUBLE SHOOTING OF LOOPS AND WIRING FOUN	D NO FAULTS. A/C DISPATCH WITH MEL ON DISCHARGED BOTTLE AND MEL ON FIRE DETECTION SYSTEM..			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073000328	20010730	00328	SW  	2001	7	30	CA010625047      	1	20010525	G	5302	205030899009	SKIN            	BELL        		BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK IN SKIN DUE TO BROKEN STIFFENER INSIDE FIN. APPROX LOCATION IS FSTA 444.75, WATERINE 85 RIGHT BUTTLINE 3.0. 	STIFFENER P/N 205-030-899-036 ALSO RIB P/N 204-030-827-015 WAS DAMAGED BY BROKEN STIFFENER.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001073000330	20010730	00330	NE  	2001	7	30	CA010625051      	2	20010622	G	7323	4301121204	GOVERNOR        			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					POWER TURBINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1005 							(CAN) TORQUE SPLITS COULD NOT BE BROUGHT INTO SPLE WITH ALLOWABLE AIRFRAME ADJUSTMENTS AND PERCENTAGE OF SPLITTING WOULD	 VARY AT EACH CYCLE.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE				 
2001073000331	20010730	00331	CE  	2001	7	30	CA010625052      	1	20010614	G	2710	35524238124	RETAINER        			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	AILERON	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE IT WAS FOUND THAT THE LOWER CONTROL ARM RETAINER WAS MISSING. UPON FURTHER INVESTIGAT	ION, IT WAS FOUND LYING IN THE BELLY OF THE AIRPLANE. IT WAS ALSO NOTED THAT THE UPPERCONTROL ARM RETAINER WAS ATTACHED 	WITH ONLY ONE OF TWO SCREWS WAS THE INCORRECT STYLE.				1	L	7	2 	3O	3	O	 	3A16    	3E1	5	C	P911	 
2001073000335	20010730	00335	CE  	2001	7	30	CA010626006      	1	20010524	G	3212	5801	SWITCH          			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FLOAT	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON GEAR EXTENSIONFOR LANDING IN PRINCE ALBERT SASK. THE RH MAIN GEAR DOWN INDICATOR LIGHT DID NOT ILLUMINATE. AFTE	R TESTING THE SYSTEM AND HAVING THE SAME RESULTS, THE PILOT ELECTED TO LAND AND DID SOWITHOUT INCIDENT. ON THE GROUND, T	ESTING REVEALED THAT THE PROXIMITY SWITCH FOR THE RH MAIN GEAR WOULD FAIL INTERMITTANTLY. AS A PRECAUTION THE OTHER SWIT	CHES WERE ALSO TESTED AND THE LH NOSE WHEEL A LSO FAILEDINTERMITTANTLY. NEW SWITCHES HAVE BEEN ORDERED TO REPLACE THE FA	ULTY ONES. BOTH SWITCHES ARE THE SAME PART NUMBER. AS A MATTER OF INTEREST THE LANDING GEAR HAD BEEN SWUNG AS MANY AS TH	IRTY TIMES THAT DAY BEFORE WITHOUT FAILURE WHILE TROUBLE SHOOTING A DIFFERENT DISCREPENCY.	1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001073000336	20010730	00336	NM  	2001	7	30	CA010626007      	1	20010527	G	6210	369D21102523	BLADE           			DOUG  	600N  	600N        	3027377	NM  	ALLSN 	250C  	250C47M     	03013	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			642  								(CAN) A/C STOPPED FOR REFUELING, DUE TO THE TQ EVENTS THAT HAD BEEN ACCUMULATED, (160) THE PILOTS CARRIED OUT A BLADE TO	RQUE EVENT INSPECTION I.A.W. SB600N-031. THEY FOUND THE WHITE BLADE TO BE CRACKED, BOTTOM SIDE, 12.5" O/B OF THE LAST BO	LT ON THE BLADE GRIP, 2.25" I/B OF THE SERIAL # DATA PLATE, MID WAY IN THE BLADE, CRACK WAS MEASURED TO BE .75" LONG, BU	T THE PILOTS CONFIRMED THAT THE CRACK WAS LONGER WITH THE BLADE SUPPORTED OFF THE DROOP STOP RING, AND WAS SAID TO RUN T	O .25" FROM THE TRAILING EDGE, ESTIMATING THE CRACK TO BE 2.5" TO 3.0" LONG IN LENGTH.		1	G	7	1 	3U	3	U	NC	H3WE    	E1GL				 
2001073000337	20010730	00337	NM  	2001	7	30	CA010626008      	1	20010612	G	2520	2A0590174	TUBE            			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TORQUE TUBE CRACKED WHERE THE CUTOUT HAS BEEN MADE FOR THE WIRING TO GO THROUGHT. THIS IS THE SECOND SEAT WE FIND 	WITH THE SAME PROBLEM.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001073100040	20010731	00040	EA  	2001	7	31	CA010626019      	1	20010530	G	3610	320207231	CHECK VALVE     			CNDAIR	CL600 	CL6002B16   	1900305	EA  	GE    	CF34  	CF343B1     	 	NE  					APU	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING APU BLEED TRANSITION TO ENGINES THE APU LCV FAIL LIGHT CAME ON AND OPEN LIGHT REMAINED ON. ABOUT 15 SECONDS	 THE RT FIRE INDICATION APPEARED, CREW THROTTLED BACK JUST BELOW 70 PERCENT N1 AND THE FIRE WENT OUT. CREW SHUTDOWN ENGI	NE AND DECLARED EMERGENCY AND LANDED UNEVENTUALLY AT LAX. FOLLOW UP: FOUND LCV AND FIRE LOOP BAD. ALSO FOUND THE FLAPPER	S FOR THE CHECK VALVE ABOVE THE LCV MISSING. FOUND BOTH FLAPPERS OF CHECK VALVE, ALSO FOUND RT STATER DAMAGE POSSIBLE FR	OM CHECK VALVE PIECES. PARTS REPLACED AND RETURNED TO SERVICE.		2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100041	20010731	00041	EA  	2001	7	31	CA010626020      	1	20010417	G	7110		ACCESS DOOR     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NOSE COWL	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) AFTER AIRCRAFT LANDED AT CHICAGO O'HARE, IT WAS NOTICED T HAT THE NOSE COWL LOWER ACCESS PANEL (228-50081-142) WAS	 ON THE RUNWAY. OTHER DAMAGED PARTS WERE NOSE COWL UPPER ACCESS PANEL 228-50080-158 AND COVER ASSEMBLY 228-50793-120. PR	IOR TO THIS EVENT THE AIRCRAFT WAS DOWN FOR ROUTINE MAINTENANCEAN D WORK WAS PERFORMED ON THE THRUST REVERSER SYST EM DU	E TO A MMEL.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100043	20010731	00043	EA  	2001	7	31	CA010626022      	1	20010528	G	2421		GENERATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 1	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA				9014 							(CAN) SHORTLY AFTER TAKEOFF, NR 1 AC GENERATOR FAILURE WARNING CAME UP. THE GENERATOR SYSTEM WAS RESETED IAW THE FMP, WI	THOUT SUCCESS. THE GENERATOR WAS THEN DEACTIVATED AND ISOLATED IAW THE FMP.THE GENERATOR WS REPALCED AN THE AIRCRAFT WS 	RELEASED FOR SERVICE WITHOUT FURTHER INCIDENTS.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001070500013	20010705	00013	NM  	2001	7	5	CA010626024      	1	20010430	G	7830	312N53217	DUCT            	BOEING      	LJ76579     	BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  	 		            		JOINT SLEEVE	LEAKING         	W			    	H	 	 	 	DEACTIVATE SYST/CIRCUITS				J	 	 	WARNING INDICATION        			NR	NOT REPORTED   	1			CA		 									(CAN) #1 ENG THRUST REVERSER DEACTIVATED AS PER MEL. INVESTIGATION FOUND THE PYLON MOUNTED FAN THRUSR REVERSER ELECTRICA	L HARNESS PN LJ6579 AND LJ 76580 MELTED AND HEAVELY DAMAGED. HOT AIR LEAK FROM HP2 ANDHP7 BLEED AIR DUCT PN 312N5321-7 A	ND 312N5306-1 ALSO CAUSED LH THRUST REVERSER HYD LINES AND PROTECTION SLEEVE TO OVERHEAT. #1 THRUST REVERSER UPPER FEEDB	ACK CABLE FOUND DAMAGED AND SEIZED AND FAILED THE STIFFNESS CHECK, PARTS REPLACED.			2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001073100044	20010731	00044	CE  	2001	7	31	CA010626026      	1	20010502	G	2823	M83248110111	O-RING          			CESSNA	206   	T206H       	       	CE  	LYC   	O540  	TIO540AJ1A  	 	EA  					FUEL SELECTOR	LEAKING         	W				O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		LD	LANDING        	1			CA			104  								(CAN) DURING APPROACH AND LANDING A FUEL ODOR WAS APPARENT. INVESTIGATION OF THE REPORTED SNAG REVEALED THAT THE FUEL SE	LECTOR WAS LEAKING AND SOME FUEL HAD ACCUMULATED IN THE FUSELAGE, UNDER THE CABIN F LOOR.					1	H	7	1 	3O	3	O	 	A4CE    	E14EA				 
2001073100045	20010731	00045	NM  	2001	7	31	CA010626027      	1	20010607	G	2400	FCC4008	RELAY           			BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING CLIMB OUT, ALL LIGHTS ON FORWARD PANEL, AND GLARESHIELD ILLUMINATED. AIRCRAFT RETURNED WITHOUT INCIDENT. WH	ILE TROUBLE SHOOTING THE R33 RELAY WAS INTERCHARGED WITH THE R41 AND THIS SOLVED THEUNSERVICEABILITY. A NE W R33 RELAY W	AS INSTALLED AND SYSTEM WAS TESTED SERVICEABLE. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100046	20010731	00046	EA  	2001	7	31	CA010626028      	1	20010612	G	3244		TIRE            			CNDAIR	CL601 	CL6012A12   	1900303	EA  	GE    	CF34  	CF343A      	30015	NE  					MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) THREAD SEPARATION ON TAKEOFF WHICH INDUCED DAMAGE TO WHEEL WELL AREA.						2	L	7	2 	4F	4	F	RT	A21AE   	E15NE				 
2001073100047	20010731	00047	EA  	2001	7	31	CA010626029      	1	20010613	G	5246	215310326	WEB             			CNDAIR	CL215 	CL2151A10   	       	EA  	PWA   	R2800 	CA3         	52026	NE  					WATER DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING THE INCIDENT REPORTED ON A/C CL215-1A10 S/N 1076 (SDR DATED 00-08-24) BOMBARDIER AMO 35-95 DECIDED TO CA	RRY OUT A SPECIAL INSPECTION ON HIS FLEET. THE WEB P/N 215-31032-6 HAS BEEN FOUND CRACKED BEHIND RH AND LH UPLOCK SPIGOT	S AND WATER DOOR ACTUATOR SPIGOTS IN WATER SYSTEM APPROX. FS368.5 ON VARIOUS A/C AND VARIOUS DEGREE. BOMBARDIER ENGINEER	ING HAS PRODUCED DIFFERNET REPAIR ENGINEERING ORDERS AND TWO GENERAL REAPIR APPLICABLE TO ALL CL215. REO 215-53-10-75 (W	ATER DOOR ACTUATOR MOUNTING LUGS) AND 215-53-10-093 (UPLOCK ACTUATOR MOUNTING LUGS. THE FOLLOWING A/C HAVE BEEN INSPECTE	D AND REPAIRED	2	H	7	2 	4R	4	R	 	A14EA   	E231				 
2001073100056	20010731	00056	NE  	2001	7	31	CA010626043      	2	20010520	G	7261		SUMP            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	COKED           	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN). NR 2 ENGINE SHUT WITHOUT PILOT'S INPUT DURING THE APPROACH PHASE OF THE FLIGHT, APPROX 3500 FEET. UPON INSPECTION	, MAINTNANCE NOTED: OIL DETECTED IN THE TAILPIPE, ENGINE QUANTITY CHECKED AND FOUND DEPLETED, AND SUMP B SCREEN COKED UP	. ENGINE REPLACED AND A/C RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100057	20010731	00057	NM  	2001	7	31	CA010626044      	1	20010617	G	3260		DOWNLOCK SENSOR 			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) NOSE GEAR TRANSIT LIGHT ILLUMINATED WHEN GEAR SELECTED DOWN. CREW CYCLED GEAR A COUPLE OF TIMES WITH NO RESULTS. A	 VISUAL CHECK THROUGH FLOOR HOLE VIEWER ATTEMPTED. NOSE GEAR VIEWER HARD TO DETERMINE VISUAL ON RED LINES FOR A LOCKED C	ONDITION.THE CREW OPTED TO RETURN TO STATION OF ORIGIN WITH AN UNEVENTFUL LANDING. THE A/C WAS FERRIED TO THE MAIN BASE 	FOR MAINTENANCE. MAINTTENANCE TESTED AND CONSEQUENTLY REPLACED THE NLG DOWN LOCK SENSOR. AS A PRECAUTION THE NLG VIEWER 	WAS CLEANED AND THE DOWNLOCK INDICATOR ARROWS WERE REPAINTED.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100058	20010731	00058	EA  	2001	7	31	CA010626045      	1	20010619	G	3244	299K631	TIRE            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKE OFF AT GEAR RETRACTION, THE CREW NOTED A LEFT MAIN LANDING GEAR DISAGREEMENT. THE AIRCRAFT RETURNED AND	 LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL INSPECTED ANDFOUND THAT THE TREADHAD SEPARATED FROM THE LEFT INBOARD MAI	N GEAR TIRE DURING THE TAKE OFF ROLL. COLLATERAL DAMAGE TO THE LEFT INBOARD FLAP AND MAIN GEAR DOOR BELL CRANK WERE ALSO	 OTED. THE FLAP ASSEMBLY P/N 601R14002-1 AND THE LEFT MAIN GEAR DOOR BELL CRANK P/N 601R31185-15 WERE ALSO REPLACED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001070500014	20010705	00014	EA  	2001	7	5	CA010626046      	1	20010619	G	5610		WINDSHIELD      	PPG         	NP1393219   	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		WINDSHIELD	CRACKED         	W			    	A	 	 	 	UNSCHED LANDING         				O	 	 	OTHER                     			CL	CLIMB          	1			CA		 	5572 			98343H4828					(CAN) PASSING THROUGH 8,000 FT. THE WINDSHIELD DEVELOPED A CRACK AND SHATTERED. AFTER THE EVENT THE AIRCRAFTIMMEDIATELY 	RETURNED FORA WINDSHIELD REMOVAL AND REPLACEMENT.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100060	20010731	00060	EA  	2001	7	31	CA010626049      	1	20010524	G	5720		STRUCTURE       			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF34*       	 	NE  					RT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING PREFLIGHT INSPECTION MECHANIC OBSERVED THAT THE RT WING TIP HAD BEEN DAMAGED BY CONTACT WITH A HARD OBJECT 	9LIKE A RUNWAY) THE WINGTIP FAIRING HAD BEEN GROUND DOWN TO THE UNDERLYING STRUCTURE AND ALSO DAMAGE THE WING EXTENSION 	LOWER SKIN. WING EXTENSION LOWER SKIN AND WING TIP FAIRING REPLACED WITH NEW PARTS. SKIN DOUBLER REPAIRED PER REO 601R-5	7-31-279.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100061	20010731	00061	EA  	2001	7	31	CA010626050      	1	20010524	G	2751		TRANSMITTER     			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					TE FLAP	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON APPROACH AFTER SELECTING FLAP DOWN, CREW NOTICED THAT THE FLAP INDICATION WAS DIFFERENT FROM LEFT TO RIGHT. MAI	NTENANCE INSPECTED FLAP SYSTEM AMD FOUND FUNCTIONING NORMALLY. RT FLAP POSITION TRANSMITTER WAS DEFERRED PER MEL.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100063	20010731	00063		2001	7	31	CA010627008      	4	20010612	G	3416	215T5100876	NIPPLE          	BOMBDR      		CNDAIR	CL215 	CL2156B11215	       	EA  										STATIC PORT	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) A NIPPLE FITTING INSTALLED AT THE STATIC PORT OF THE ALTIMETER WAS FOUND TO BE THE WRONG TYPE HAVING AN OPENING OF	 .032 INCH INSTEAD OF THE RECOMMENDED .008 INCH. THIS COULD HAVE CAUSED PROBLEMS IN CALIBRATING THE ALTIMETER ABD FURTHE	R MORE , SHOULD FITTINGS DIFFER FROM PILOT TO CO-PILOT SIDE, THE INDICATIONS WILL LAG IN CLIMB ABD DESCENT BUT WILL BE C	ORRECT AT LEVEL FLIGHT. A BOMBARDIER SERVICE PROBLEM 34-12-00-001 WAS OPENED UP IN ORDER TO CORRECT THIS DISCREPENCY.			2	H	7	2 	4T			RT	A14EA   					 
2001073100066	20010731	00066	NM  	2001	7	31	CA010627010      	1	20010527	G	2612		CONNECTOR       			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	DIRTY           	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) WHIE ENROUTE TO YYC, NR 2 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. NO EVERHEAT LIGHT CAME ON. ENGINE SECURED AN	D AIRCRAFT LANDED IN YYC WITHOUT INCIDENT. ALL CONNECTOR PLUGS CHECKED AND CLEANED. MEL 26-2 RAISED. DMI 29776. FIRE BOT	TLES REPLACED IAW MM 26-21-11. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100068	20010731	00068	NM  	2001	7	31	CA010627011      	1	20010507	G	5242		SWITCH          			BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					E/E BAY DOOR	OBSTRUCTED      	W				O				OTHER                   				D			INFLIGHT SEPARATION       			DE	DESCENT        	1			CA											(CAN) DURING FLIGHT, E& E BAY DOOR OPENED AND AIRCRAFT LANDED WITHOUT INCIDENT. E& E BAY DOOR SWITCH STICKER WAS JAMMING	 THE SWITCH IN THE DEPRESSED MODE. THE OBSTRUCTION WAS REMOVED AND THE DOOR CLOSED. INDICATION TESTED IAW MM 2-71-00 AND	 CHECKED SERVICEABLE. NO FURTHER INCIDENT SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100069	20010731	00069	NM  	2001	7	31	CA010627012      	1	20010515	G	5414		PANEL           			BOEING	737   	7372E1      	138448F	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					RT NACELLE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A MAINTENANCE CHECK, IT WAS OBSERVED THAT THE RT AFT NACELLE PANEL WAS MISSING. SERVICEABLE PANEL WAS INSTA	LLED. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100070	20010731	00070		2001	7	31	CA010627013      	4	20010501	G	2312		STATIC WICK     			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COMM SYSTEM	WORN            	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DECEND AND FLYING THROUGH PRECIPITATION, BOTH VHF RADIOS HAD HEAVY STATIC. AIRCRAFT LANDED WITHOUT INCIDENT	. 5 STATIC DISCHARGERS WERE FOUND OUT OF LIMITS. ALL REPLACED IAW MM 23-61-00. NO FU RTHER INCIDENT DURING SUBSEQUENT FL	IGHT.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001070500015	20010705	00015	NM  	2001	7	5	CA010627014      	1	20010509	G	3700	BACH30BC060332	LINE            	            	            	BOEING	737   	7372A9C     	1384495	NM  	PWA   	JT8   	JT8D9A      	52048	NE  	 		            		RH PITOT STATIC	WORN            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 									(CAN) AT CRUISE, FIRST OFFIER'S AIRSPEED INDICATION WASERRATIC, AIRCRAFT LANDED WITHOUT INCIDENT. FOUND PITOT STATIC LIN	ES WORN. LINES REPLACED AND TESTED SERICEABLE IAW MM34-11-0. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001073100071	20010731	00071	WP  	2001	7	31	CA010627015      	1	20010528	G	5610		WINDSHIELD      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COCKIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT F5890 FROM MADRID TO LYON, INCRUISE CO-PILOT WINDSHIELD INNER PLY CRACKED, UNSCHEDULED LANDING IN BI	ARRITZ. RT WINDSHIELD REPLACED. A/C RETURNED TO SERVICE.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001073100073	20010731	00073	EA  	2001	7	31	CA010627021      	1	20010529	G	7120		WEB             	BOMBDR      	60135006    	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19301								(CAN) DURING "C" CHECK, SIX CRACKS WERE FOUND INTHE ENGINE SUPPORT BEAM. TWO CRACKS WERE LOCATED ON THE LOWER WEB AT FS 	640.0 BETWEEN LBL 9.5 AND RBL 9.5. FOUR CRACKS WERE LOCATED ON THE UPPER WEB AT FS 640 BETWEEN LBL 9.5 REPAIR PERFORMED 	PER REO 601R-53-61-345.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100075	20010731	00075	NE  	2001	7	31	CA010627025      	2	20010612	G	7261		PUMP            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE OIL	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE OIL PRESSRE BEGAN TO FLUCTATE DURING CRUISE. THE PRESSURE DROP FOLLOWED BY AN INCFREASE IN OIL TEMP. T	HE PILOT INITIATED AN IN FLIGHT SHUTDOWN. ENGINE OIL PUMP REPLACED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100077	20010731	00077	NE  	2001	7	31	CA010627032      	2	20010517	G	7261		ENGINE          			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					OIL SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT CREW REPORTED LOW OIL PRESSURE AND ASSOCIATED WITH HIGH OIL TEMPERATURE. ENGINE REPLACED AND 	A/C RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100078	20010731	00078	NE  	2001	7	31	CA010627034      	2	20010619	G	7261		OIL SYSTEM      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	FLUCTUATES      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) A/C IN CRUISE AT FL.310, CREW NOTICED FLUCTATION IN OIL PRESSURE WITH A LOSS OF OIL PRESSURE. ENGINE SHUT DOWN BY 	THE FLIGHT CREW AND LANDED IN PHOENIX. INVESTIGATING AT THIS POINT SHOWS OIL TANK AS GOOD. OIL LEVEL IN GEARBOX IS GOOD.	 GE ON WING SUPPORT IS ON SITE TO HELP WITH INVESTIGATION. FSR HAS REQUESTED THAT THE MDC BE DOWNLOADED AND THE DFDR BE 	DOWNLOADED.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100080	20010731	00080	SW  	2001	7	31	CA010627040      	1	20010627	G	5302	206031418005	SUPPORT BRACKET 	BELL        	206031004   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL BOOM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE FLANGE FOR THE VERTICAL FIN UPPER ATTACHMENT BOLT IS SEPARATED FROM SUPPORT DUE TO CRACK.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001073100082	20010731	00082	CE  	2001	7	31	CA010627042      	1	20010622	G	2434	7565T1	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011B     	17026	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6    								(CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. AFTER MAKING	 A FEW TEST, IT WAS DETERINED THAT THE ALTERNATOR WAS FAULTY. THIS NEW ALTERNATOR WAS INSTALLED ON THE AIRCRAFT AS A REP	LACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY NO EXTERIOR DAMAGES WAS FOUND THA	T COULD HAVE LEAD TO THE FAILURE.  SOMETHING INSIDE THE ALTERNATOR HAD FAILED BUT SINCE THE ALTERNATOR IS PARTIALLY SEAL	ED AND IS ON WARRANTY COVERAGE NO FURTHER ACTION WAS TAKEN TO INVESTIGATE TH FAILED ASSEMBLY.		1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100084	20010731	00084	CE  	2001	7	31	CA010627043      	1	20010621	G	2434	7565T1	ALTERNATOR      			CESSNA	305   	305C        	2074014	CE  	CONT  	O470  	O47011B     	17026	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1    								(CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. AFTER MAKING	 A FEW TEST, IT WAS DETERMINED THAT THE ALTERNATOR WAS FAULTY. THIS NEW ALTERNATOR WAS INSTALLED ON THE AIRCRAFT AS A RE	PLACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY, A SMALL PIECE FELL OFF BY VENT 	DUCT OF THE SHROUD OF THE ALTERNATOR. LOOKING CLOSELY AT THE PIECE IT WAS DETERMINED THAT THIS SMALL PIECE WAS A DIODE. 	THE DIODE SEEMED NOT DAMAGED OTHER THAN BEING UNSOLDERED FROM THE INTERNAL PART OF THE ALTERNATOR. IT WAS CERTAINLY NOT 	SOLDERED PROPERLY AND FAILED WITH THE VIBRATIONS OF THE AIRCRAFT. THE P/N OF THE DIODE COULD BE SEEN EASILY.PN. MR2504W0	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100099	20010731	00099	CE  	2001	7	31	CA010627044      	1	20010622	G	2434	7565T1	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4    								(CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAT LANDING. AFTER MAKING 	A FEW TESTS, IT WAS DETERMINED THAT THE ALTERNATOR WAS FAULTY. THIS OVERHAULED ALTERNATOR WS INSTALLED ON THE AIRCRAFT A	S A REPLACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY, SMALL PIECES COULD BE HEA	RD MOVING INSIDE THE ALTERNATOR. THE ALTERNATOR WAS SHAKEN TO TRY AND REMOVE THESE PIECES BY THE SHROUD AIR VENT BUT NON	E FELL OUT. SINCE THE ALTERNATOR IS PARTIALLY SEALED AND IS ON WARRANTY COVERAGE NO FURTHER ACTION WAS TAKEN TO INVESTIG	ATE THE FAILED PIECES.	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100101	20010731	00101	EA  	2001	7	31	CA010627046      	1	20010626	G	7120		SUPPORT BRACKET 	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00					(CAN) BOMBARDIER AEROSPACE HAS JUST RECEIVED A REPORTALE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON. DURING INSPECTION	 OF ENGINE SUPPORT BEAM IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER PROGRESS, SHOULD BE PROV	IDED TO THE OPERATOR SOON.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100102	20010731	00102	EA  	2001	7	31	CA010627047      	1	20010622	G	7120		SUPPORT BRACKET 	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00					(CAN) DURING INSPECTION OF ENGINE SUPPORT BEA IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER PR	OVIDED, REPAIR IN PROGRESS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100103	20010731	00103	EA  	2001	7	31	CA010627048      	1	20010622	G	7120		SUPPORT BRACKET 	GE          	CF343A1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						00					(CAN) DURING INSPECTION OF ENGINE SUPPORT BEAM IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER P	ROVIDED, REPAIR IN PROGRESS.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100105	20010731	00105	SW  	2001	7	31	CA010627051      	1	20010627	G	2121	21036012	BLOWER          			GULSTM	690TP 	690         	0141720	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  	HARTZL	HCB3T	HCB3TN5     	GL  	AIR DISTRIBUTION	SEIZED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA				40   							(CAN) SMOKE ENTERED COCKPIT AFTER ORBITING FIRE FOR 20 MINUTES. GROUND BLOWER RESET CIRCUIT BREAKER TRIPPED OFF. COCKPIT	 CHECKED FOR DAMAGED WIRING. ENGINE BLEED AIR SUPPLY WAS INSPECTED FOR OIL CONTAMINATION NO DEFECTS NOTED. GROUND BLOWER	 INTAKE WAS INSPECTED NO OBSTRUCTION WAS NOTED. GROUND BLOWER UNIT REPLACED FUNCTION TESTED. THE AIRCRAFT WAS RETURNED T	O SERVICE.			1	H	7	2 	3T	4	T	 	2A4     	E2WE	6	C	P15EA	 
2001073100107	20010731	00107	SW  	2001	7	31	CA010627052      	1	20010519	G	6320	212040233001	TUBE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6   	PT6A34      	52043	EA  					TRANSMISSION OIL	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE 300 FT AGL, MAIN TRANSMISSION OIL PRESS WAS NOTICED FLUCTUATING. AN IMMEDIATE PRECAUTIONARY LANDING 	WAS CARRIED OUT. A/C WAS INTERMEDIATELY SHUT DOWN. UPON INVESTIGATION TUBE ASSY P/N 212-040-233-001 IN HELL HOLE WAS FOU	ND LEAKING. TUBE REPLACED TRANSMISSION FILTER WAS INSPECTED NO CONTAMINATION WAS FOUND. 6 LITRES OF OIL WAS ADDED. (12 L	 MAX CAPACITY) AIRCRAFT GROUND RUN & RETURNED TO SERVICE.			1	G	7	1 	4U	4	T	 	H4SW    	E4EA				 
2001073100109	20010731	00109	CE  	2001	7	31	CA010627053      	1	20010625	G	5720	MS2001426	BOLT            			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF36C	2AF36C39    	GL  	WING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			630  								(CAN) UPON MPI IT WAS FOUND THAT 2 OF 4 WING BOLTS FAILED INSPECTION. IT WAS THANDETERMINED TO CHANGE ALL THE BOLTS. LOG	 ENTRY INDICATES BOLTS WERE LAST CHANGED IN 1992. THER IS NO RECORD OF BOLT INSPECTION SINCE THAT TIME ALTHOUGH INSPECTI	ON IS CALLED FOR AFTER 5 YEARS.				1	L	7	2 	3O	3	O	 	3A16    	3E1	5	C	P911	 
2001073100110	20010731	00110	SO  	2001	7	31	CA010627054      	1	20010608	G	3222	6705403	TRUNNION        			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  	HARTZL	HCC3Y	PHCC3YF1    	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2474 								(CAN) WHILE INSPECTING SHIMMEY DAMPENER AS PART OF 100 HOUR INSPECTION. IT WAS DISCOVERED THAT THE NLG TRUNNION ASSEMBLY	 WAS CRACKED AT SHIMMEY DAMPENE R ATTACH POINT.					1	L	7	1 	3O	3	O	 	2A13    	E9CE	5	C	P25EA	 
2001073100111	20010731	00111	CE  	2001	7	31	CA010627055      	1	20010615	G	3234	1013841379	SWITCH          			BEECH 	200   	B200        	1152922	CE  	PWA   	PT6   	PT6A42      	52043	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			6147 								(CAN) WHEN LANDING GEAR SELECTED UP AFTER TAKE OFF, GEAR DID NOT RETRACT. GEAR SELECTED BACK DOWN WITH NORMAL DOWN AND L	OCKED INDICATION ON ALL GEAR. NORMAL LANDING CARRIED OUT WITHOUT INCIDENT. TROUBLESHOOTING FOUND INTERMITTENT MIRCOSWITC	H CONTACTS IN LANDING GEAR SELECTOR SWITCH ASSEMBLY WHEN HANDLE SELECTED UP. ASSEMBLY REPLACED AND GEAR SWINGS COMPLETED	. NO FURTHER FAULTS.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001073100112	20010731	00112	CE  	2001	7	31	CA010627056      	1	20010626	G	5610	10138402515	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	FAILED          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA			3218 								(CAN) AIRCRAFT WAS IN LEVEL FLIGHT AT 24000 FEET ON AUTOPILOT WHEN LT WINDSHIELD SHATTERED. FLIGHT CREW DEPRESSURIZED AN	D DESCENDED. AIRCRAFT RETURNED WITHOUR FURTHER INCIDENT.					1	L	7	2 	4T	4	T	 	A24CE   	E4EA	6	C	P15EA	 
2001073100114	20010731	00114	CE  	2001	7	31	CA010627057      	1	20010529	G	5510	2332051	GUSSET          	LEAR        	263200032   	LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14818			35002					(CAN) WHILE CARRYING OUT A ROUTINE INSPECTION (PHASE C6-1200HRS) ON THE HORIZONTAL STABILIZER "GUSSET" A CRACK WAS DISCO	VERED IN THE GUSSET ERNINATING FROM THE EDGE OF THE LIGHTENING HOLE. THE INSPECTION SPECIFIES SCRUTINY OF THESEGUSSETS F	OR CRACKS ON AIRCRAFT THAT DID NOT INCORPORATE AN EXTRA DOUBLER INSTALLED PER SSK 954. THIS AIRCRAFT DID NOT INCORPORATE	 THE DOUBLER. THE CRACK IS SMALL (.141 INCH LONG AND DIFFICULT TO SEE. IT WAS CONFIRMED USING HIGH FREQUENCY EDDY CURREN	T. THERE IS A SMALL SCRATCH ON THE WEB OF THE GUSSET AT THE CRACK SITE. THE STABILIZER WAS REMOVED TO INSTALL LEAR SPECI	AL SERVICES KIT 954 IN PLACE OF THE CRACKED GUSSET.	2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2001073100116	20010731	00116	NM  	2001	7	31	CA010627059      	1	20010627	G	3213		STABILIZER      			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) PORT MAIN LANDING GEAR FAILED TO LOCK DOWN WHEN SELECTED DOWN FOR LANDING. GEAR WAS CYCLED AND LOCKED DOWN ON SECO	ND ATTEMPT. ON INSPECTION, THE LEFT SPRING ON THE PORT MLG STABILIZER STRUT WAS FOUND BROKEN. AS THIS IS NOT AN LRU, PER	MISSION WAS OBTAINED TO FERRY AIRCRAFT TO MAIN BASE WITH GEAR LOCKED DOWN. AIRCRAFT FERRIED TO BASE FOR REPAIRS. PORT MA	IN LANDING GEAR STABILIZER ASSY CHANGED IAW 32-10-26 GEAR RETRACTION CHECK CARRIED OUT SATISFACTORY.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100117	20010731	00117	CE  	2001	7	31	CA010627060      	1	20010615	G	7120	075100125	MOUNT           			CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			6950 								(CAN) UPPER LT VERTICAL TUBING CRACKED AT LOWER GUSSET						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2001073100120	20010731	00120	CE  	2001	7	31	CA010627061      	1	20010614	G	3260	1303640489	CIRCUIT BOARD   			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  	HARTZL	HCB4M	HCB4MP3     	GL  	MLG INDICATOR	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			LD	LANDING        	1			CA			5106 								(CAN) ON APPROACH AIRCRAFT LOSS ALL GREEN ADVISORY LIGHTS AIRCRAFT MADE 3 FLY BY'S TO VERIFY GEAR DOWN & LOCKED. AIRCRAF	T LANDED WITHOUT INCIDENT. THE LANDING GEAR LIGHTS ARE DIMMED THROUGH THE ABOVE P.C. BOARD.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL	 
2001070500016	20010705	00016	SO  	2001	7	5	CA010627062      	2	20010618	G	8530	648049	PISTON          	CONT        	I0360       	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	PISTON	BROKEN          	W			    	O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA		 		1350 		352436					(CAN) ON A GROUND RUN-UP PRIOR TO A SCHEDULED INSPECTION A PARTIAL POWER LOSS WAS DETECTED. A MOTO-STAT WAS CARRIED OUT 	AND #6 CYL. HAD VERY LOW COMPRESSION. A FILTER CHECK WAS CARRIED OUT AND SUBSTANIAL METAL PARTS, ALM, CHROME AND STEEL W	ERE FOUND THAT ARE CONSISTANT WITH A PISTON FAILURE. THE ENGINE HAS BEEN REMOVED FROM SERVICE. STRIP REPORT TO FOLLOW.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA	 
2001073100121	20010731	00121	EA  	2001	7	31	CA010627063      	2	20010621	G	7310	76778	MANIFOLD        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				2407 							(CAN) ON INSPECTION OF AD 93-02-05 FUEL INJECTOR LINES AND CLAMPS IT WAS NOTED THAT FUEL WAS LEAKING WITH BASE OF FITTIN	G IN MANIFOLD. UPON REMOVAL OF MANIFOLD IT WAS TOWED TO BE CRACKED BETWEEN BOTH LT & TOP FITTING.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001073100122	20010731	00122	CE  	2001	7	31	CA010628002      	1	20010614	G	2510	041405410	RELEASE SYSTEM  	CESSNA      	04140711    	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	SEAT	SHEARED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			11600			80173					(CAN) 3 OF 4 LATCH PINS CONTROLLING SEAT NIGHT FOUND SHEARED AT ENGAGEMENT HOLE ALLOWING SEAT TO DROP AND TILT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001073100135	20010731	00135	EA  	2001	7	31	CA010628012      	1	20010511	G	6120	12350	TUBE            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  	HAMSTD	23D	23D40       	NE  	PROPELLER OIL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			274  								(CAN) COULD NOT CYCLE PROPELLER. FOUND OIL TRANSFER TUBE IN NOSE CASE BROKEN AT ATTACH POINT IN CENTRE OF TUBE. ONE TUBE	 REPLACED AT 274 HOURS SINCE OVERHAUL AND ANOTHER TUBE WAS REPLACED WITH 243 HOURS SINCE REPLACEMENT. THESE ARE 2 SEPARA	TE OCCURANCES.				1	H	7	1 	3R	3	R	 	A815    	5E2	6	C	P719	 
2001073100138	20010731	00138	SO  	2001	7	31	CA010628014      	1	20010522	G	3097		WIRE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COCKPIT	MELTED          	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			9259 								(CAN) DURING CRUISE, WITH ENGINE AND WINDSHIELD HEAT SELECTED. SMOKE WAS OBSERVED COMING FROM THE RIGHT FORWARD CIRCUIT 	BREAKER PANEL. AT THIS POINT THE RIGHT ENGINE AND WINDSHIELD DEICE SYSTEMS WERE TURNED OFF AND THE SMOKE DISSAPPEARED. T	HE AIRCRAFT LANDED SAFELY AT ITS DESTINATION. MAINTENANCE THEN DISCOVERED THAT 2 WIRES, BEHIND THE CIRCUIT BREAKER PANEL	 WERE MELTED : ONE BEING RIGHT INLET DEICE ANDTHE OTHER RIGHT WINDSHIELD HEAT. CORROSION WAS FOUND AT THE SPLICES, WHICH	 CAUSED EXCESSIVE HEAT.		1	L	7	2 	3T	4	T	 	A8EA    	E4EA	6	C	P15EA	 
2001073100139	20010731	00139	SW  	2001	7	31	CA010628016      	1	20010606	G	2750	12395	PULLEY          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  	MCAULY	1A200	1A200*      	GL  	FLAP SYSTEM	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT AND RT PULLEYS FOUND SEIZED AT WING ROOT(100 HOUR INSP.) BOTH CABLES FREYED AND UNSERVICEABLE. (LT/RT) AT POSIT	ION OF PULLEY.SOLID ALUMINUM PULLEYS, NO BEARING , DIFFICULT TO KEEP LUBRICATED. HIGH POTENTIAL FOR INFLIGHT FLAP CABLE 	FAILURE.				1	H	7	1 	3O	3	O	 	A21CE   	E286	5	N	P874	 
2001073100144	20010731	00144	CE  	2001	7	31	CA010628023      	1	20010524	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FUEL SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) FAILED.PILOTS CHECK FOR LEAKING SHUTOFF VALVE AS PER FLT. MANUAL PROCEDURES. NEW VALVE INSTALLED CHECKED OK.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2001073100181	20010731	00181	CE  	2001	7	31	CA010628029      	1	20010511	G	5511	07321014	SPAR            			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			2572 								(CAN) DURING ANNUAL INSPECTION FOUND PLAY IN HORIZONTAL STABILIZER TO ELINMINATE PLAY REPLACE ALL HARDWARE AND BUSHING I	N ASS. DURING LUBRICATING OF ELEVATOR HINGES DISCOVERED CRACK ON STABILIZER HINGE REINFORCEMENT. THIS REINFORCEMENT IS R	IVETED ON MAIN SPARE. STABILIZER HINGE IS BOLTED THROUGH MAIN SPARE AND REINFORCEMENT. A/C CONFIGURATION: SEAPLANE STRAI	GHT FLOATS			1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2001073100184	20010731	00184	SO  	2001	7	31	CA010628037      	1	20010525	G	3246	16205700	WHEEL           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5266 								(CAN) FLANGE OF OUTER WHEEL HALFFOUND CRACKED (4 INCHES) ALONG FLANGE WHERE TIRE BEAD SEATS.						1	L	7	2 	3O	3	O	 	A19S0   	E286	5	C	P920	 
2001073100205	20010731	00205	EU  	2001	7	31	CA010628038      	1	20010520	G	2612	6493950730	FIRE LOOP       			AIRBUS	320   	A320212     	       	EU  	CFMINT	CFM56 	CFM565A3    	 	NE  					NR 2 ENGINE	DAMAGED         	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA											(CAN) PRF MESSAGE CHECK ENGINE NR 2 FIRE LOOP "B". THIS DEFECT WAS UNDER INVESTIGATION BY MAINTENANCE PERSONNEL AND ALSO	 DEFFERED UNDER MEL 26-12-01 CATEGORY "C" AS A RESULT OF THIS PFR MESSAGE. FIRE LOOP "B" REPLACEMENT WAS SCHEDULED WHILE	 OPERATING THE "C" DUCT FOR LOOP REPLACEMENT IT WAS NOTICED FOR DAMAGE TO THE NR 2 ENGINE RT "C" DUCT HEAT SHIELD. THE D	AMAGE HAS BEEN CAUSE BY A MISSING "PISTON RING" (P/N336-510-710-0 OR 649-395-073-0 POST SB).MAINTENANCE PERSONNEL INSTAL	LED NEW PISTON RING, BUT AIRCRAFT WAS GROUNDED DUE TO THE EXTENSIVE DAMAGE TO THE 32 ENGINE RT "C" DUCT HEAT SHIELD. A T	EMPORARY RE PAIR HAS BEEN ACCOMPLISHED TO THE HEAT SHIELD WITH A REPETITIVE INSPECTION EVERY "A" CHECK GRANTED BY BF GOO	2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001073100213	20010731	00213	EA  	2001	7	31	CA010628039      	2	20010628	G	8530	LW19340	CAMSHAFT        			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	ENGINE	WORN            	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				1440 							(CAN) ENGINE HAD BEEN HARD TO START, LOW STATIC RPM AND HIGH MANIFOLD PRESSURE. ENGINE INSP. REVEALED THAT THE CAMSHAFT 	LOBE THAT DRIVES NR 5&6 CYL INTAKE VALVES WERE WORN. FURTHER TEAR DOWN OF ENGINE REVEALED NO FURTHER ABNORMAL WEAR OR CO	RROSION.				1	H	7	2 	3O	3	O	 	6A1     	1E4	5	C	P6EA	 
2001073100215	20010731	00215	SO  	2001	7	31	CA010628042      	1	20010527	G	2910	3036	HOSE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	HYD SYSTEM	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC HOSE RUPTURE AT FITTING P/N MS24590-4. FITTING M524590-4 HAD WORN INTERNAL THREADS WHEN HOSE WAS MANUFAC	TURED. HOSE AND FITTING SEPARATED ON GEAR CYCLE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2001073100217	20010731	00217	SW  	2001	7	31	CA010628043      	1	20010520	G	5711		SPAR            			BBAVIA	7     	7CCM        	21101MW	SW  	CONT  	C90   	C9012F      	17009	SO  	SNSNCH	76AK	M76AK       	EA  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TO CARRY OUT AD 2000-25-02, ADDITIONAL HOLES WERE CUT IN EACH LOWER WING PANEL. NO PROBLEMS WERE FOUND. REMOVED WI	NG ROOT FAIRINGS AND FABRIC ON TOP OF BOTH WINGS JUST TO BE SURE IN WING ROOT AREA. FOUND BOTH FWD SPAR ROOT ATTACH POIN	TS CRACKED AT THE ENDS. ALSO ONE LONG CRACK APPROX. 1 INCH DOWN FROM TOP TO BOTTOM OF SPAR APPROX. 4 FT LONG BETWEEN ROO	T /STRUT WHICH WAS NOT SEEN UNTIL FABRIC WAS COMPLETELY REMOVED. THE OTTAWA AIRWORTHINESS OFFICE WAS CONTACTED.			1	H	7	1 	3O	3	O	 	A759    	E252	5	N	1P210	 
2001073100220	20010731	00220	SO  	2001	7	31	CA010628045      	1	20010520	G	7603	2489403	CONTROL CABLE   			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	THROTTLE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA			5141 	5141 							(CAN) THROTTLE CONTROL CABLE BROKE AT ENGINE END RESULTING IN LOSS OF ENGINE POWER SELECTION CAPABILITY. SUBSEQUENTLY, A	LL ENGINE CONTROL /CABLES ON BOTH ENGINES WERE REPLACED.					1	L	7	2 	3O	3	O	 	A1EA    	1E12	5	C	P9EA	 
2001073100244	20010731	00244	NM  	2001	7	31	CA010628062      	1	20010528	G	3260	189915	UPLOCK SENSOR   			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) RED LEFT GEAR ANNUNCIATOR ON FORWARD PANEL ILLUMINATED IN FLIGHT WITH LANDING GEAR SELECTOR UP AND OFF. ALL OTHER 	LANDING GEAR ANNUNICATION (INCLUDING DOOR ANNUNICATORS) EXTINGUISHED. RED LEFT GEAR ANNUNICATOR EXTINGUISHED WITH ILLUMI	NATION OF GREEN LEFT GEAR LIGHT WHEN LANDING GEAR SELECTED DOWN. LEFT MAIN LANDING GEAR UP-LOCK SENSOR REPLACED IN ACCOR	DANCE WITH MAINTENANCE MANUAL AND TESTED SERVICEABLE. NO FURTHER DEFECTS NOTED IN THE LAST TWO FLIGHT LEGS.			2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001070500020	20010705	00020	NM  	2001	7	5	CA010628064      	1	20010322	G	3040		WINDSHIELD      	TRIPLEX     	0780306     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	WINDSHIELD	CRACKED         	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 	13748			TH2078					(CAN) BOMBARDIER AEROSPACE REGIONAL AIRCRAFT HAS JUST RECEIVED A REPORTABLE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON	 MARCH 22/01. IN CRUISE FLIGHT AT 15,000FT. THE FIRST OFFICERS WINDSCREEN CRACKED AND BECAME TOTALLY DISTORTED. EMERGENC	Y DECLARED AND FLIGHT DIVERTED TO BASE LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED FIRST OFFICERS WINDSHIELD IN ACCORD	ANCE WITH DEHAVILLAND DASH 8 MAINTENANCE MANUAL OPERATIONAL CHECK OF WINDSHIELD GOOD. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100249	20010731	00249	EU  	2001	7	31	CA010629006      	3	20010514	G	6110	697071003	BLADE           	ROTOL       	697071003   	DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  	ROTOL	R4304	R4304*      	EU  	PROPELLER	BURNED          	W				O				OTHER                   				C			F.O.D.                    			AP	APPROACH       	1			CA											(CAN) BOMBARDIER AEROSPACE REGIONAL AIRCRAFT HAS JUST RECEIVED A REPORTABLE SDR WEVENT WHICH WE ARE REQUIRED TO REPORT O	N MAY 5/01. DURING APPROACH, THE PILOT REPORTED THAT THE R/H PROPELLER SUSTAINED A LIGHTENING STRIKE. INSPECTION OF THE 	PROPELLER UPON LANDING SHOWED A BURN MARK ON ONE BLADE APPROX 3MM IN WIDTH FROM TIP, CENTRE OF BLADE. IAW THE AMM THE PR	OPELLER ASSY, HUB ANDBETA TUBE HAVE TO BE REMOVED AND SENT TO DOWTY FOR INVESTIGATION. NEW ASSY, INSTALLED AND AIRCRAFT 	RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN	6	C	P890	 
2001073100251	20010731	00251	EA  	2001	7	31	CA010629009      	1	20010522	G	2710		SERVO           	COLLINS     	6222366001  	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6*        	52043	EA  					AILERON	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, AILERON CONTROL LOST DUE TO AILERON SERVO SERVO PRIMARY JAMMED. AIRCRAFT RETURNED TO BASE. SERVO WA	S REPLACED. AIRCRAFT RETURNED TO SERVICE.					1	H	7	2 	3T	3	T	RT	A9EA    	E2NE				 
2001073100254	20010731	00254		2001	7	31	CA010629017      	4	20010323	G	3417		ADC             			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	E/E BAY	FAILED          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  DURING CLIMB, AT APPROX. 6000FT, RDADC FAIL. BOTH ADVISORY DISPLAYS RESE T LIGHT WAS ON. SAT 2 WAS SHOWING DASHES	. ALTITUDE SELECT BLANK. BASIC PITCH MESSAGE ON. VSI 2 SHOWED 0. ALT PRESELECT BLANK. YAW DAMPER FAIL. AP DISCONNECTED E	GPWS FAIL. RNAV MESSAGE "ADC FAIL" TRUE AIRSPEED INOP. ON ECP, "NR 2 ENG ECU FLAGGED. NO CHANGE WHEN L DADC WAS MADE MAS	TER. FLT ABORTED. A/C RETURNED TO BASE.ON GROUND: NO FAULT CODES IN FLT FAULT SUMMARY. UNABLE TO DUPLICATE THEFAULT ON G	ROU ND #2 AIR DATA COMPUTER REPLD. CHECKED WATER DRAINS..OK PITOT/STATIC LEAK TESTOK/PURGED PITOT/STATIS LINES...OK A/C 	RETURN TO SERVI	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100256	20010731	00256	EA  	2001	7	31	CA010629019      	2	20010426	G	7321	25244405	FUEL CONTROL    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA				3514 							(CAN) RT POWER LEVER IS VERY DIFFICULT TO SCHEDULE SUBTLE POWER CHANGES. IE. WHEN ATTEPTING TO SELECT A CHANGE OF 100 FT	/LBS RESULTING TORQUE CHANGE COULD BE AS MUCH AS 400FT/LBS. THIS RESULTS IN AN OSCILLATION OF POWER LEVER MOVEMENT TO GE	T DESIRED POWER OUTPUT. THIS IS ESPECIALLY APPARENT WHEN LANDING WITH GUSTING WINDS. R/H FUEL CONTROL UNIT REPLACED. S/N	 OFF A7414.S/N ON A7968. TEARDOWN REPORT INDICATED GOVERNOR HYSTERESIS WAS 180 RPM. MAX ALLOWABLE IS 50 RPM. DRIVE BODY 	ALSO FOUND TO BE DIRTY/SOOTY. THIS WOULD CAUSE FCU TO RESPOND SLOWLY AND INTERMITTENTLY.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC	 
2001073100259	20010731	00259	EA  	2001	7	31	CA010629020      	2	20010604	G	7230		SEAL            			SOCATA	TBM   	TBM700      	8682000	EU  	PWA   	PT6   	PT6A6A      	52043	EA  	HARTZL	HCE4N	HCE4N3      	NE  	ACTUATOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29   								(CAN) INERTIA ACTUATOR MOTOR P/N 200N6071017220 WAS REPLD 29.9 HRS PRIOR TO FAILURE . NEW ACTUATOR WAS BEING INST WHEN N	OTICES INERTIA APOATOR DEFLECTOR BEING CUT WHILE MANU MOVING. UNIT WAS REMOVED FROM HC & WHILE INVESTIGATING NOTICED SEA	L THAT HAD UNEVEN MASHINGS FROM WEAR. WHEN DISLOCATED CREATED SAME PROBLEM OF DEFLECTOR BEING CAUGHT & REQ A LOT OF FORC	E TO MOVE. THAT COND ITION TOOK OUT NEW MOTOR. EMPIRE PERFORMANCE DROPPED IN FLT & A/C ALTITUDE LIMITED. INCORRECT INST 	OF INERTIA SEPARATOR SEAL DISCLOSED CAUSING PROC FAILURE OF MOTOR DUE TO EXCESSIVE PRESSURE SUGGESTED CONNECTIVE ACTION-	AFTER REMOVAL & REINSTATIN OF INERTIA SEPARATOR DISCONNECT WATER FROM ASSY & MANU CHECK.	1	L	7	1 	3T	3	T	RT	A60EU   	E4EA	5	C	P10NE	 
2001073100261	20010731	00261	EU  	2001	7	31	CA010629023      	1	20010511	G	2434	HED60CR132200	BRUSHES         	BOSCH       	5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			222  			100037					(CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON THE CAWS PANEL. THE PILOT NOTED THAT THE NR 2 GENERATOR OUTPUT WAS	 FLUCTUATING BETWEEN A 60AMP DISCHARGE AND A 20 AMP POSITIVE CHARGE. HE TURNED THE GENERATOR OFF, THEN RE-SELECTED IT TO	 THE ON POSITION.THE RESET WAS SCESSFUL FOR APPROX. 20 MINUTES AT WHICH TIME FOR APPROX 20 MINUTES, THE PROBLEM REOCCURR	ED. MAINTENANCE FOUND THAT THE BRUSHES WERE WORN WELL BEYOND A SERVICEABLE LIMIT. A NEW SET OF BRUSHES WAS INSTALED AND 	THE AIRCRAFT GROUND RUN. NO FURTHER PROBLEMS NOTED.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100263	20010731	00263	EU  	2001	7	31	CA010629024      	1	20010518	G	2434	HED60CR132200	BRUSHES         	BOSCH       	5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			12   			100037					(CAN) THE NR 2 GEN CAUTION LIGHT ILLUMINATED ON CAWS PANEL. PILOT ALSO NOTED THAT A VERY LOUD SQUEALING SOUND COULD BE H	EARD IN HEADSET. CAUTION LIGHT THEN ILLUMINATED & PILOT THEN SELECTED NR 2 GEN SWITCH TO OFF POS. GEN WAS THEN RE-SELECT	ED TO ON POS, WITH SAME RESULT AS NOTED ABOVE. GEN #2 WAS THEN SELECTED TO OFF POS, & THEAIRCRA FT RETURNED TO BASE. ONC	E AGAIN MAINTENACE FOUND THAT POST SB- "24-016" BRUSHES HAD FAILED WELL BEFORE THEIR LIFE LIMIT WAS REACHED. A EW SET OF	 POST S/B BRUSHES WAS INSTAND AIRCRAFT GROUND RUN, WITH NO FURTHER DEFECTS BEING NOTED. AS MENTION IN OUR PREVIOUS SDR 1	1-05-2001. MAINT HAS INSTITUED A VOLUNTARY	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100264	20010731	00264	NE  	2001	7	31	CA010629025      	2	20010522	G	7321	8063041	FUEL CONTROL    			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	FAILED          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1215 								(CAN) WHEN TRYING TO START ENGINE, THE ENGINE WOULD NOT ACCELERATE ABOVE APPROXIMATELY 35-39 PERCENT THE FUEL CONTROL UN	IT WAS REPLACED, AND THE AIRCRAFT WAS RETURNED TO SERVICE					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100265	20010731	00265	EU  	2001	7	31	CA010629026      	1	20010528	G	2434	9789601090	BRUSHES         		5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			94   			100318					(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN 	EXCESSIVELY AND HAS BEEN REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100267	20010731	00267	EU  	2001	7	31	CA010629027      	1	20010518	G	5270	9733024202	ARM             			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DOOR SWITCH	BROKEN          	W				D				RETURN TO BLOCK         				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CA			1572 								(CAN) ON CLOSING THE CARGO DOOR THE UNLOCKED WARNING LIGHT IN THE COCKPIT FAILED TO EXTINGUISH. ON INVESTIGATION THE ROL	LER SPRING ON THE MICRO SWITCH WAS BROKEN.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100268	20010731	00268	EU  	2001	7	31	CA010629029      	1	20010518	G	2434	9789601090	BRUSHES         		5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			370  			100092					(CAN) #2 GENERATOR FAIL LIGHT CAME ON DURING FLIGHT. AN INSPECTION OF THE BRUSHES SHOWED ONE TO HAVE SUFFERED SIGNS OF A	RCING.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100271	20010731	00271	EU  	2001	7	31	CA010629032      	1	20010514	G	2710	5271012115	CONTROL CABLE   			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AILERON	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1993 								(CAN) WHEN INSPECTING CONTROL CABLES AS PER 2000HR/5YR. INSPECTION REQUIREMENT, SOME ABNORMALITIES WERE NOTED ON THE 2 F	ORWARD AILERON CONTROL CABLES. ON ONE OF THE BUNDLES OF STRANDS IT APPEARED AS IF 2 OR 3 OF THE INDIVIDAL STRANDS WERE S	EPARATED FROM EACHOTHER WITH A SLIGHT KINK. THIS PATTERN REPEATED ITSELF EVERY 4 OR 5 INCHES. THIS ABNORMALITY IS ONLY A	 FEW MILLIMETERS IN LENGTH. THE 115 CABLE HASSEVERVAL OF THESE SUSPICIOUS SPOTS AND THE 116 HAS ONLY A FEW. THE CABLES H	AVE BEEN REPLACED WITH NEW PILATUS PARTS AND THE SUSPECT CABLES HAVE BEEN FORWARDED TO OUR REGIONAL SUPERVISOR FOR FURTH	ER EVALUATION.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100272	20010731	00272		2001	7	31	CA010629033      	4	20010514	G	3425	071014393100	CONTROL PANEL   			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			1993 								(CAN) HDG CONTROL KNOB FEELS SCRATCHY, CAUSING INTERMITTENT RED FLAG ON HDG SYMBOL ON EFIS.PANEL REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100274	20010731	00274		2001	7	31	CA010629036      	4	20010530	G	2210		SERVO           	HONEYWELL   	7002260922  	DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	AUTOPILOT	FAILED          	W				C				ABORTED TAKEOFF         				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA						00105873					(CAN) ELEVATOR HEAVY OPERATION AFTER TAKE OFF. FLIGHT WAS ABORTED. LANDING WAS UNEVENTFUL. MAINTENANCE TESTS REVEALED TH	AT THE AUTO PILOT ELEVATOR SERVO MOTOR'S CLUTCH WAS STILL ENGAGED. ELEVATOR ACTUATOR SERVO MOTOR IS BEING REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100277	20010731	00277	NE  	2001	7	31	CA010629038      	2	20010517	G	7261	3033990	LINE            			DHAV  	DHC8  	DHC8101     	2809002	NM  	PWA   	120   	PW120       	 	NE  	HAMSTD	14SF	14SF7       	NE  	OIL SUPPLY	FRACTURED       	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			A	J		FLAME/FIRE                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN)  AN INCID. OCCURRED ON CLIMB OUT. PILOTS RPT THAT NR 1 ENGINE TRQ DROPPED TO 30 PERCENT, PILOTS PULLED & RESET CCT	 BREAKER. 30 2NDS AFTER TRQ DROP WAS NOTICED NR 1 OIL PX DROPPED TO 0 PSI & FIRE IND. FOR NR 1 ENG. ILLUMINATED. PILOTS 	BLEW 1 FIRE BOTTLE AFTER ENGINE SHUTDO WN 28 SEC LATER FIRE IND. EXTINGUISHED A/C RETURNED TO BASE W/O INCID.. NR 1 ENGI	NE IS SEIZED WITH PROP UNFEATHERED. UPON INSP OF ENGINE, OIL SUPPLY LINE TO NR 6 BEARI NG FOUND FRACTURED. FIRE WAS CONT	AINED WITHIN NACELLE FIREWALL, HOWEVER THERE HAS BEEN HEAT DAMAGE TO STRUCTURE:		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100279	20010731	00279	EU  	2001	7	31	CA010629039      	1	20010629	G	2913	501310000	PRESSURE SWITCH 	VICKERS     	887673      	AIRBUS	320   	A320232     	3930326	EU  	IAE   	V2527 	V2527A5     	 	NE  					HYD PUMP	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			528  	528  		MX632028					(CAN)  DEPARTED YUL FOR KEF. WHILE IN CLIMB THE ENGINE NR 2 YELLOW HYDRAULIC PUMP FAULT LIGHT ILLUMINATED. THE PUMP WAS 	DE-ACTIVATED AND THE AIRCRAFT DIVERTED TO YHZ. MAINTENANCE TROUBLESHOOTING LOCATED A HYDRAULIC LEAK FROM THE HYDRAULIC P	UMP NR 2 PRESSURE SWITCH. THE SWITCH ASSY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4F	4	F	RT	A28NM   	E40NE				 
2001073100281	20010731	00281	WP  	2001	7	31	CA010629040      	1	20010608	G	3231	28B4028	TORQUE TUBE     			CVAC  	PBY5  	PBY5A       	2421208	WP  	PWA   	R1830 	R183092     	52020	NE  					MLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6960 								(CAN) NOSE GEAR DOOR TORQUE TUBES REMOVED FOR INSPECTION DUE TO THE PROMPTING OF A SERVICE DIFFICULTY ADVISORY. THE COND	ITION PREDICTED IN THE ADVISORY (CORROSION) WAS FOUND TO EXIST IN A FAIRLY ADVANCED STAGE, PARTICULARLY AROUND THE TAPER	 PINS AND HOLES. THESE TUBES HAVE BEEN MODIFIED WITH GREASE FITTINGS TO FACILITATE FILLING THE TUBES WITH GREASE, HOWEVE	R, AN INCOMPLETE FIL HAD IN FACT MADE THE PROBLEM WORSE. THE PLUGS OF GREASE HAD IN FACT CREATED POCKETS WHERE MOSITURE 	WAS TRAPPED, WORSENING THE PROBLEM. NEW TUBES WERE FABRICATED AND INSTALLED WITH NEW HARDWARE. AS THE ADVISORY POINTS OU	T, FAILURE DURING WATER LANDING COULD HAVE FATAL CONSEQUENCES IF THE DOOR COLLAPSE.	2	H	7	2 	4R	4	R	 	2548    	5E4				 
2001073100282	20010731	00282	NE  	2001	7	31	CA010629043      	2	20010317	G	7321	324485318	FUEL CONTROL    			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	RT ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA			30   								(CAN) THE NR 2 ENGINE POWER COULD NOT BE ADJUSTED AFTER TAKEOFF TO SET POWER. THEAIRCRAFT EXPERIENCED MODERATE TURBULENC	E BETWEEN 20 TO 21 THOUSAND FEET. THE ENGINE WAS STUCK AT ABOUT 88 PERCENT TORQUE AND FUEL FLOW WAS ABOUT 610 TO 640 LBS	 PER HOUR. AT ENGINE SHUTDOWN AN OVER TORQUE WA S NOTED BUT IT IS NOT KNOWN HOW MUCH OVER. WITH THE POWER LEVER AT FLIGH	T IDLE THE FUEL FLOW WAS STILL NOTED TO BE 610 TO 640LB			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001073100285	20010731	00285	NM  	2001	7	31	CA010703002      	1	20010611	G	5330		SKIN            			BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				52471							(CAN) CRACK IN FUSELAGE SKIN LEFT SIDE BETWEEN FUSELAGE STATIONS 747 AND 767, STRINGER 17L REPAIRED AS PER SRM 53-30-3, 	TABLE 1, METHOD 1, PAGES 87,88 & 88A.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001073100302	20010731	00302	NM  	2001	7	31	CA010703007      	1	20010612	G	5610		WINDSHIELD      			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN)  CO-PILOTS WINDSHIELD CRACKED IN CRUISE. A/C THEN DESCENDED, SLOWED AND REDUCED PRESSURIZATION. A/C LANDED UNEVENT	FUL. WINDSHIELD REPLACED.					2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2001073100308	20010731	00308	EU  	2001	7	31	CA010703013      	1	20010614	G	6410	355A12005004	BLADE           	SNIAS       	355A12005004	SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	FAILED          	W				A				UNSCHED LANDING         				C			F.O.D.                    			CL	CLIMB          	1			CA			1528 			6964					(CAN) T/R BLADES WERE SUBJECTED TO A MINOR CONTACT ON THE OUTBOARD SKIN AREA WITH A PINE BOUGHT IN SLOW FORWARD FLIGHT, 	A/C THEN LANDED TO INSPECT THE BLADES. BLADES WERE REMOVED TO HAVE CRACKS IN THE FILLER AROUND THE EDGE OF THE TABS REPA	IRED ( WARRANTY WORK) AND ALSO TO FURTHER INSPECT AND REPAIR MINOR BLADE DAMAGE.				1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2001073100309	20010731	00309	EU  	2001	7	31	CA010703015      	1	20010628	G	2560	504202201	BUCKLE          	AMSAFTYEQUIP	504202403   	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	SEAT BELT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1240 			AFG0598790					(CAN) CO-PILOTS SEAT BELT BUCKLE WOULD NOT UNLATCH WHEN OPERATED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001073100319	20010731	00319	SO  	2001	7	31	CA010703026      	1	20010614	G	2730	71056003	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ELEVATOR	BROKEN          	W				D				RETURN TO BLOCK         				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			632  								(CAN) AFTER LANDING, THE PILOT NOTED UNUSUALY LIGHT ELEVATOR.UPON SHUTDOWN, THE ELEVATOR WAS INSPECTED AND IT WAS NOTED 	THAT THE SPRING WAS BROKEN. UPON INSPECTION OF RECORDS, THE PART WAS FOUND TO HAVE 632HOURS SINCE REPLACEMENT AS PER AWD	 98-08-18. THE PART HAS BEEN RETAINED IF FUTURE INSPECTION IS REQUIRED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001073100325	20010731	00325	CE  	2001	7	31	CA010703032      	1	20010622	G	8011	654472	BUSHING         			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	STARTER SHAFT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				375  							(CAN) DURING SCHEDULED COMPLIANCE WITH CSB-94-4C THE STARTER SHAFT BUSHING WAS FOUND TO BE LOOSE IN THE ENGINE CASE.						1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL	 
2001070500021	20010705	00021	NE  	2001	7	5	CA010703034      	2	20010617	G	7210	130000405	BEARING         	HONEYWELL   	T5313B      	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  	 		            		BEARING	BROKEN          	W			    	A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA		 		1413 		LE07592					(CAN) ENGINE CHIP LT CAME ON. METAL CHIPS WERE FOUND IN CHIP PLUG & FILTER. REPLACED ENGINE. INVESTIGATION SHOWS BEARING	 P/N 1-300-004-05 CAGE WAS BROKEN & INNER/ OUTER RACE BEARING SURFACE HAD FLAKE DAMAGE.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001073100327	20010731	00327	CE  	2001	7	31	CA010703035      	1	20010615	G	2434	6682	RETAINER        	SKYTRONICS  	7565T1      	CESSNA	305   	305C        	2074014	CE  	CONT  	O470  	O47011      	17026	SO  					ALTERNATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			113  			0201123					(CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INVEST. & TO SEE IF RETAINER CUP WS DAMAGED. SMALL PIECES OF METAL & RUBBER	 FELL OFF ACCESSORIES CASE UPON REMOVAL OF ALTNR. LOOKING AT ALTERNATOR SPLINE GEAR & DRIVE SHAFT, EVIDENCE OF DAMAGES W	ERE FOUND. RETAINING CUP WAS SHREDDED IN PIECES & ONLY ONE RUBBER BUSHING LEFT IN PLACE. AT TIME OF REMOVAL ALTNR WAS CH	ARGING PRO PERLY INDICATING THAT SHAFT OF ROTOR WAS STILL TURNING. RETAINING CUP & RUBBER BUSHINGS ARE MOUNTED BETWEEN S	PLINE GEAR DRIVING SHAFT & ROTOR SHAFT OF ALTNR. THIS INSTATION IS DESIGNED TO SHEAR OFF & PREVENT DAMAGES TO ENGINE IN 	CASE WHERE AN ALTNR. THIS INST IS DESIGNED TO SHEAR OFF	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100328	20010731	00328	CE  	2001	7	31	CA010703036      	1	20010615	G	2434	6682	RETAINER        	SKYTRONICS  	7564T1      	CESSNA	305   	305C        	2074014	CE  	CONT  	O470  	O47011B     	17026	SO  					ALTERNATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			44   			0201124					(CAN) ALTERNATOR REMOVED FROM AIRCRAFT ENGINE FOR INVESTIGATION AND TO SEE F RETAINER CUP WAS DAMAGED. LOOKING AT THE AL	TERNATOR SPLINE EAR AMD DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUPWAS CRACKED WHERE THE RUBBER BUSHI	NGS ARE SEATED. THE RETAINING CUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT AND THE ROTOR SH	AFT OF THE ALTERNATOR. THE INSTALLATION IS DE SIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN THE CASE WHERE AN	 ALTERNATOR SHAFT WOULD SEIZE UP. IN THIS CASE, A FE WMORE HOUR FLIGHT WOULD HAD CERTAINLY CAUSED THE TOTAL BREAK OF THE	 CRACKED RETAINER CUP AND FAILURE OF THE ALTERNATOR.	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100330	20010731	00330	CE  	2001	7	31	CA010703037      	1	20010615	G	2434	6682	RETAINER        	SKYTRONICS  	7565T1      	CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					ALTERNATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			50   			0201120					(CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INVESTIGATION AND TO SEE IF RETAINER CUP WAS DAMAGED. LOOKING AT THE ALTERN	ATOR SPLINE GEAR AND DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUP WAS CRACKED WHERE THE RUBBER BUSHING	S ARE SEATED. THE RETAINING CUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT AND THE ROTOR SHAF	T OF THE ALTERNATOR. THE INSTALLATION IS DESIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN THE CASE WHERE AN AL	TERNATOR SHAFT WOULD SEIZE UP. IN THIS CASE, A FEW MORE HOU OF FLIGHT WOULD HAD CERTAINLY CAUSED THE TOTAL BREAK OF THE 	CRACKED RETAINER CUP AND THE FAILURE OF THE ALTERNATOR.	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100336	20010731	00336	CE  	2001	7	31	CA010703038      	1	20010614	G	2434	6682	RETAINER        	SKYTRONICS  	7565T1      	CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011B     	17026	SO  					ALTERNATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			76   			0201121					(CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INST ON A NEW ENGINE FOR THIS A/C. NO PILOT RPTED LOSS OF CHARGE BEFORE ENG	INE WAS STOPPED FOR HIS TBO. SMALL PIECES OF METAL & RUBBER FELL OFF THE ACCESSORIES CASE UPON REMOVAL OF ALTNR. LOOKING	 CLOSELY TO ALTNR SPLINE GEAR & DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. RETAINING CUP & RUBBER BUSHINGS WERE COMPLE	TELY SHREDED. SPLINE GEAR LUGS WERE ALSO BROKEN OFF & THIS PARTICULAR ALTNR, ROTOR SHAFT SHEARED. RETAINING CUP & RUBBER	 BUSHINGS ARE MOUNTED BETWEEN SPLINE GEAR DRIING SHAFT & THEROTOR SHAFTOF ALTERNATOR. THIS INST IS DESIGNED TO SHEAR OFF	 & PREVENT DAMAGES TO ENGINE IN CASE WHERE AN ALTNR SHAFT	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100337	20010731	00337	CE  	2001	7	31	CA010703039      	1	20010613	G	2434	6682	RETAINER CUP    	SKYTRONICS  	7565T1      	CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011B     	17026	SO  					ALTERNATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			73   			0201126					(CAN) ALTERNATOR REMOVED FROM A/C AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. SMALL PIECES OF M	ETAL AND RUBBER FELL OFF THE ACCESSORIES CASE UPON REMOVAL OF ALTERNATOR. LOOKING CLOSELY TO THE ALTERNATOR SPLINE GEAR 	AND DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUP AND TH RUBBER BUSHINGS WERE COMPLETLY SHREDDED. THE S	PLINE GEAR LUGS WERE ALSO BROKEN.THE RETAININGCUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT 	AND THE ROTOR SHAFT OF THE ALTERNATOR. THIS INSTALLATION IS DESIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN T	HE CA S WHERE AN ALTERNAOTR SHAFT WOULD SEIZE UP. IN THIS CASE, THE ALTERNATOR SHAFT COULD BE TURNED FREEY	1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001073100340	20010731	00340	EA  	2001	7	31	CA010704011      	1	20010627	G	7120		BEAM            	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CRACKS WERE FOUND DURING ENGINE SUPPORT BEAM INSPECTION, AS PER SB601R-53-059.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001070500022	20010705	00022	NE  	2001	7	5	CA010704015      	2	20010627	G	7200		CARBON SEAL     	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		CARBON SEAL	FAILED          	W			    	G	 	 	 	O2 MASK DEPLOYED        				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA		 									(CAN) BOMBARDIER AEEROSPACE HAS JUST RECEIVED A REPORTABLE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON. WHILE IN CRUISE	 FLIGHT THE CREW COULD SMELL AND SEE SMOKE.OXYGEN MASKS WERE DONNED BY THE CREW ANDTHEPAX MASKS WERE DEPLOYED. FLIGHT WA	S DIVERTED. UPON INVESTIGATION THE ENGINE #1 CARBON SEAL WAS FOUND TO HAVE COME APART.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100345	20010731	00345	EA  	2001	7	31	CA010704024      	1	20010629	G	5320		PLATE           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING C CHECK, MAINTENANCE FOUND A CRACK LOCATED IN THE PLATE ASSY. RBL 45.00 AT THE JOINT WITH THE FLOOR BEAM SU	PPORT ANGLE AT PRESSURE BULKHEAD FS 621.00 THE CRACK WAS CONFIRMED USING NDT INSPECTION.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100348	20010731	00348		2001	7	31	CA010704028      	4	20010629	G	3160		CONTROL UNIT    			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					NR 2	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMB PILOT REPORTED EICAS MESSAGE DCU NR 2 AUR AL FAIL, APR FAIL AND FLUCTATION OF ENGINE PARAMET ERS 9N1,	N2 & ITT) ON BOTH ENGINES. THEY SELECTED THE APR SWITCH OFF AND THE FLUCTUATIONS WENT AWAY, FLIGHT CONTINUED TO NICE. IT	 CAME BACK AT 40 NM OF MONTPELLIER. BASED ON MDC CODES MAINTENANCE FOUN DCU NR  2 DEFECTIVE. REPLACED DCU NR 2, AIRCRAFT	 BACK IN SERVICE.			2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001072500555	20010725	00555	WP  	2001	7	25	CA010706004      	1	20010429	G	3200	1523153115	SWITCH          	            	            	LKHEED	1011  	10113851    	5265010	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  	 		            		SWITCH	FAILED          	W			    	A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA		 									(CAN) AFTER DEPARTURE FROM YMX, THE TRUCK LIGHT CAME ON, NORMAL PROCEDURES WHERE NOT TO RETRACT THE GEAR, CREW DUMPED FU	EL AND RETURNED TO BASE. FOUND TRUCK SWITCH AT FAULT, COMPLETE ACTUATOR REP LACED AND AIRCRAFT RELEASED FOR A FLIGHT TES	T, SYSTEM CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001073100352	20010731	00352	WP  	2001	7	31	CA010706006      	1	20010428	G	4970	2621TB9	TERMINAL BLOCK  			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					APU	DESTROYED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOLLOWING APU WARNING HORN RCCB TRIPPED OFF FOUND 5 WIRES WHEE THE INSOLATION WAS BROKEN AND RELATED TERMINAL BUS 	CHEMICALLY DESTROYED BY SKYDROLL. APU FIRE-EX BOTTLE SQUIB WAS INTERMITTENT DUE TO DAMAGE. REPLACED TB AND REPAIRED WIRI	NG AND AREA CLEAN FROM SKYDROL AND INSPECTED FOR LEAKS. NO LEAKS WERE NOTED, AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001072500556	20010725	00556	WP  	2001	7	25	CA010706007      	1	20010428	G	3320		TERMINAL BLOCK  	            	            	LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  	 		            		ROW 23 L/H CEILI	OVERHEATED      	W			    	K	 	 	 	NONE                    				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA		 									(CAN) ON ARRIVAL CREW REPORTED SMOKE AT ROW 23 L/H CEILING. FOUND LUMINARE TERMINAL BLOCK OVERHEATED. LUMINARE ASSEMBLY 	REPLACED AND TERMINAL BLOCK REPLACED. AIRCRAFT RETURNED TO SERVICE.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001073100353	20010731	00353	EU  	2001	7	31	CA010706008      	1	20010508	G	7120	S5411020001000	MOUNT           			AEROSP	ATR42 	ATR42320    	8680930	EU  	PWA   	PW121 	PW121       	52124	NE  	HAMSTD	14SF	14SF5       	NE  	LT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18491								(CAN) LEFT ATACHMENT FOR LOWER NACELLE IS WORN AND HOLE ARE ELONGATED. ENGINE MOUNT TO BE REPLACED BEFORE FURTHER FLIGHT	.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE	 
2001073100354	20010731	00354	CE  	2001	7	31	CA010706009      	1	20010505	G	5310	50430043865	DOOR FRAME      			BEECH 	100   	B100        	1152919	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DOOR FRAME AFT FOUND CRACKED AROUND REAR BAYONET.						1	L	7	2 	4T			 	A14CE   					 
2001073100355	20010731	00355	SW  	2001	7	31	CA010706014      	1	20010430	G	6410	206011809109	PITCH HORN      			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				730  							(CAN) DURING A DAILY INSPECTION, WE DISCOVERED THAT THE TORQUE OF THE BOLTS HOLDING THE PITCH HORN TO THE TAIL ROTOR BLA	DE WAS LOOSE. THE LOCKWIRE WAS STILLIN PLACE BUT THE 2 BOLTS WERE NO LONGER TORQUED.DURING THE DISMANTLING NO OTHER ANOR	MALITIES. THE PITCH HORN AND THE TAIL ROTOR BLADE WERE DISMANTLED, CLEANED, CHECKED AND REASSEMBLED IN ACCORDANCE TO THE	 (BELL HELICOPTER T EXTRON) COMPONENT REPAIR& OVERHAUL MANUAL CHAPTER 4. IF THIS DISCREPANCY HAD NOT BEEN FOUND, IT MIGH	T HAVE RESULTED IN A TAIL ROTOR CONTROL LOSS.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001073100356	20010731	00356	EA  	2001	7	31	CA010706015      	1	20010305	G	2910		LINE            			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					HYD SYSTEM	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) PILOT REPORT: HYDRAULIC SYSTEM NR 2 LOW PRESSURE MESSAGE DURING CRUISE. FOUND HYDRAULIC SYSTEM NR 2 EMPTY OF FLUID	. MAINTENANCE FINDING: FOUND FITTING OF FILL LINE LEAKING (REF IPC 29-11-00-5-270). FOUND FITTING ADAPTER WRONG INSTALLE	D ON FILL LINE. INSTALLED SWAGE ADAPTER. REFILLED HYDRAULIC AND REPLACED UNSERVICEABLE EDP.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100357	20010731	00357	EA  	2001	7	31	CA010706016      	1	20010505	G	5610		WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND THE CAPTAIN WINDSHIELD INNER PLY CRACKED ON AN UNSCHEDULED MAINTENANCE INSPECTION. WINDSHIELD REPLACED, AIRC	RAFT BACK IN SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001072500557	20010725	00557	EA  	2001	7	25	CA010706017      	1	20010513	G	7732		ENGINE          	GE          	CF343B1     	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  	 		            		R/H ENGINE	FAILED          	W			    	A	 	 	 	UNSCHED LANDING         				E	 	 	VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA		 				EBU7114					(CAN) ON TAKEOFF R/H ENGINE N2 VIBRATION EXCEEDED LIMITS, IN FLIGH T ENGINE SHUT DOWN CARRIED OUT AND AIRCRAFT RETURNED 	FOR TROUBLSHOOTING					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001072500558	20010725	00558	EA  	2001	7	25	CA010706018      	1	20010513	G	5610	601R330333	WINDSHIELD      	CNDAIR      	            	CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  	 		            		L/H WINDSHIELD	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				95039H2892					(CAN) LEFT WINDSHIELD CRACKED. WINDSHIELD REPLACED.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100358	20010731	00358	EA  	2001	7	31	CA010706019      	1	20010513	G	5610	601R33033	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FL330 THE CAPTAIN'S WINDSHIELD SHATTERED. NO CONFIRMATION IF PIECES OF WINDOW DEPARTED AIRCRAFT. REMOVED AND RE	PLACED CAPTAIN'S WINDSHIELD IN ACCORDANCE WITH AMM 54-11-01.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001073100360	20010731	00360	EA  	2001	7	31	CA010706020      	1	20010326	G	2460	M81381	HARNESS         			CNDAIR	CL601 	CL6012A12   	1900303	EA  										ELECTRICAL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7194 								(CAN) A TECHNICIAN WAS WORKING IN AFT FUSELAGE SECTION,PAINTING AROUND APU EXHAUST OUTLET WHEN HE 1ST SMELLED SMOKE.HE T	HEN SAW A WIRE BUNDLE ERUPTING INTO SPARKS & FIRE EVEN THOUGH THERE WAS NO CONTACT WITH WIRE BUNDLE WHEN EVENT OCCURRED.	THE BATTERY WAS CONNECTED BUT A/C POWER WAS OFF.IT IS ASSUMED THAT THERE WAS AN EXISTING CHAFING CONDITION & THAT WIRE B	UNDLE HAD BEEN DISTURBEDDURING APU EXHAUST REMOVAL.ONE CCT BREAKER POPPED ON JB-4 & IT WAS NOT NOTED BY TECH.17 WIRES HA	VE BEEN DAMAGED WHERE SOME WERE POWERED BY BATTERY DIRECT BUS.SOME OTHER A/C INSP FOR CHAF ING CONDITIO N & A/C 3025 WIR	ING WAS ROUTED SLIGHTLY DIFFERENT.THE CUSTOMER MADE SOME TEMP SPLICES & WILL REPL ALL DAMAGED WIRES SHORTLY.	2	L	7	2 	4F			RT	A21AE   					 
2001073100362	20010731	00362	SW  	2001	7	31	CA010711002      	1	20010625	G	6230	20601033217	MAST            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9863 	2715 							(CAN) WHEN REASSEMBLED 1/2 OF THE SPLIT CONE ASSEMBLY HAD NOT SEATED PROPERLY IN THE GROVE IN THE MAST. MAIN ROTOR MAST 	NUT TORQUE CHECK WAS CARRIED OUT AFTER 1.3 HOURS OF OPERATION AND TORQUE LOSS WAS NOTED. WHEN DISASSEMBLED AGAIN DAMAGE 	TO THE SPLINE WAS FOUND. MAIN ROTOR MAST AND SPLIT CONES WERE REPLACED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001073100365	20010731	00365	EU  	2001	7	31	CA010711008      	1	20010627	G	2910	HTE400005	CHECK VALVE     			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	HYD SYSTEM	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA											(CAN) PILOTS WERE NOT ABLE TO EXTEND LANDING GEAR. GEAR WAS PUMPED DOWN (EMERGENCY EXTENSION). AIRCRAFT LANDED WITHOUT I	NCIDENT. CHECK VALVE WAS FOUND CRACKED, ALLOWING FLUID TO EXCAPE SYSTEM. NO PHYSICAL DAMAGE THAT COULD CAUSE CRACK WAS E	VIDENT. PART REPLACED. SYSTEM CHECKED AND SERVICED AND AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2001080100031	20010801	00031	NM  	2001	8	1	CA010711014      	1	20010622	G	5310	85310776111	WINDOW POST     			DHAV  	DHC8  	DHC8103     	1386005	NM  										COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25978								(CAN) L/H AND R/H FLIGHT COMPARTMENT WINDSHIELD FRAMS P/N 85310776-111 AND P/N 85310776-112 ARE CORRODED AT THE BOTTM OF	 THE FRAMES. THIS CORROSION WAS FOUND DURING THE SCHEDULED MAINTENANCE GROUND RUNS, PRESSURIZATION LEAK CHECK. A STREAM 	OF WATER SPOUTED FROM THE L/H WINDSHIELD CORNER. WINDSHIELDS WERE REMOVED AND DURING FURTHER CLEANING AND INSPECTION COR	ROSION WAS FOUND ON THE LOWER PORTION OF THE FRAMES.			2	H	7	2 	4T			RT	A13NM   					 
2001080100062	20010801	00062	EA  	2001	8	1	CA010711015      	1	20010628	G	2460	CE934641	TERMINAL BLOCK  			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  					ELECTRICAL	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TERMINAL BLOCK 2449-TB3 SHOWS SIGN OF OVERHEATING DUE TO CORROSION ON AFT SIDE OF REAR PRESSURE BULKHEAD. THE OVER	HEATING OF THE TERMINAL BLOCK RESULTED IN IGNITION OF THE INSULATION ON THE TERMINAL LUG OF FEEDER CABLE 2449-37A0-1. TH	E OVERHEATING AND CORROSION WERE FOUND WHEN COMPLYNG WITH DASH 8 SERVICE BULLETIN 8-24-48.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE				 
2001080100065	20010801	00065	EA  	2001	8	1	CA010713003      	1	20010629	G	8011		NUT             			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	STARTER GEN	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, FOUND THAT THE NR 4 STARTER/GENERATOR COULD ROTATE 1/4 TURN ON IT'S MOUNT. THE SELF 	LOCKING NUT ON THE CLAMP HAD NO FRICTION AND BACKED OFF. THE CLAMP WAS LOOSE. THE STARTER HAD SHEARED THE ALIGNMENT PIN.	 WE REPLACED THE NUT, THE STARTER/GENERATOR AND THE MOUNT.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2001080100067	20010801	00067		2001	8	1	CA010713011      	4	20010704	G	2562	MX1300	BATTERY         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN1     	52008	NE  					ELT	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING BATTERY DUE DATE INSPECTION IT WAS FOUND THAT THE ELT HAD INCORRECT BATTERIES INSTALLED. INSTALLED CORRECT 	BATTERIES.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001080100077	20010801	00077	EU  	2001	8	1	CA010723001      	1	20010621	G	3020	21175789	COMPUTER        	HONEYWELL   		BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE ANTI-ICE	MALFUNCTIONED   	W				O				OTHER                   				J	W		WARNING INDICATION        	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			22539			45209					(CAN) DURING A MAINTENANCE ENGINE RUN, THE NR 1 ANTI-ICE VALVE CIRCUIT BREAKER POPPED AND WOULD NOT RESET. MAINTENANCE R	EPLACED THE JUST INSTALLED THRUST MODULATION SYSTEM (TMS) COMPUTER, AND THE PROBLEM WENT AWAY. APPARENTLY, A FAULT IN TH	E TMS COMPUTER BLEW THE CIRCUIT BREAKER IN THE OTHER SYSTEM.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001072500560	20010725	00560	NM  	2001	7	25	CA010723003      	1	20010626	G	2910	AN937D6	FITTING         	BOMBDR      	AN937D6     	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	FITTING	CRACKED         	W			    	O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA		 									(CAN) THE FLIGHT CREW REPORTED A FLUID LEAK FROM THE R/H WING ROOT DURING WALKAROUND. MAINTENANCE INVESTIGATION REVEALED	 A CRACKED HYDRAULIC "CROSS" FITTING, P/N AN 937 D6. THE FITTING WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080100080	20010801	00080	NM  	2001	8	1	CA010723004      	1	20010704	G	2910	DSX252B4012	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											(CAN) THE FLIGHT CREW REPORTED FLUID LEAKING FROM THE NOSEGEAR AREA DURING WALK AROUND. MAINTENANCE INVESTIGATION REVEAL	ED THAT THE HYDRAULIC FLEX LINE FOR THE NLG DRAG LINK ACTUATOR "UP" SELECTION WAS LEAKING AT THE AREA OF MAXIMUM FLEX, A	DJUCENT TO THE FITTING. THE LINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001080100082	20010801	00082	NE  	2001	8	1	CA010723041      	2	20010714	G	7200		ENGINE          			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					NR 1	DAMAGED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA											(CAN) NR 1 ENGINE STALLED ON TOP OF DESCENT INTO YYZ DURING DECELERATION, ENGINE WAS SHUT DOWN. STALL INSPECTION, ENGINE	 BOROSCOPE DISCOVERED THAT 1 HP COMPRESSOR BLADE BROKEN OFF AND DAMAGED REMAINING HP COMPRESSOR.					2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001080100110	20010801	00110	EU  	2001	8	1	CA010723043      	1	20010716	G	2824		VALVE           			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					FUEL TRANSFER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ETOP REQUIRED REPORTING. AIRCRAFT COULD NOT TRANSFER ALL THE FUEL FROM CENTER TANK. FQIS RESET AND BITE CHECKED SE	RVICEABLE. THIS IS A RECURRING DEFECT WHERE THE FQIS IS REST AND THE DEFECT RETURND A COUPLE OF FLIGHTS LATER ADDITIONAL	 TROUBLE SHOOTING REQUIRED.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2001080900101	20010809	00101	NE  	2001	8	9	CA010724004      	2	20010708	G	7260	4002TO2P03	BEARING         			SKRSKY	S61   	S61N        	8142104	NE  	GE    	CT58  	CT581401    	30011	NE  					ACCESSORY DRIVE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			265  								(CAN) INVESTIGATION OF A CHIP LIGHT ON FORWARD CHIP PLUG SHOULD A BUILD UP OF BLACK FUZZY PASTE WITH SOME INDICATION OF 	FERROUS MATERIAL. ENGINE WAS REMOVED AND DISASSEMBLED. SUBSTANCIAL WEAR WAS FOUND ON ACCESSORY DRIVE GEAR BOX IMPUT PIST	ON BEARINGS. PARTS WERE ROUTED TO LAB FOR FURTHER INVESTIGATION.				2	G	7	2 	4U	4	U	 	1H15    	1E3				 
2001080900103	20010809	00103	NE  	2001	8	9	CA010724008      	2	20010705	G	7210	214040214001	LINER           	BELL        	212040005005	BELL  	214   	214B1       	1182105	SW  	LYC   	T55   	T5508D      	41555	NE  					GEARBOX	UNSERVICEABLE   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			HO	HOVERING       	1			CA			7151 	1476 		AMG28031					(CAN) AFTER RECEIVING CHIP IND. FROM REDUCTION GEARBOX FILTER REMVD FOR INSP. OIL IN FILTER & BOWL FOUND TO BE BLACK WIT	H FERROUS MATERIAL PRESENT. REDUCTION GEARBOX THEN REMOVED & INIT INSP REVEALED  THAT GEARBOX INPUT GEAR NUT P/N 214-040	-236-001 HAD LOST TORQUE & BACKED OFF OF IMPUT GEAR&INTO SIX ENGINE OUTPUT SHAFT SEAL HOUSING BOLTS P/N MS9566-12. BOTH 	INPUT GEAR NUT & SIX SEAL HOUSING BOLTS WERE FOUND TO BE SCRAP. IT WAS NOTED THAT APPROX ONE HR EARLIER REDUCTION GEARBO	X REMVD TO FACILITATE REPL OF ENGINE OUTPUT SHAFT SEAL HOUSING RE-SHIMMED TO ACCOMMODATE NEW OUTPUT SHAFT (PART OF TORQU	E KIT).	2	G	7	1 	4U	4	U	 	H6SW    	E4NE				 
2001080900109	20010809	00109	NE  	2001	8	9	CA010724009      	2	20010716	G	8530	399356	ROCKER BOSS     			AIRTRC	AT400 	AT401B      	0370207	SW  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	23D	23D40       	NE  	EXHAUST VALVE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA				538  							(CAN) THE EXHAUST VALVE ROCKER ARM BOSS CRACKED THROUGH THE PIVOT BOLT HOLES WHICH ALLOWED THE ROCKER ARM TO MOVE WITHOU	T OPENING THE EXHAUST VALVE, SEVERLY REDUCING ENGINE POWER. FROM DISCUSSIONS WITH SEVERAL AME'S THE CONSENSUS IS THAT OV	ERTORQUING OF THE PIVOT BOLT, AT SOME TIME IN THE PAST, COULD CAUSE FATIQUE IN THIS AREA. THIS CYLINDER HAS HAD NO REPAI	RS SINCE LAST OVERHAUL.			1	L	7	1 	3R	3	R	NC	A17SW   	5E2	6	C	P719	 
2001080900111	20010809	00111		2001	8	9	CA010724011      	4	20010710	G	6113	05503671	SPINNER         			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9127 								(CAN) CRACK IN PROPELLER CUTOUT OPENING IN SPINNER NOTED DURING PREFLIGHT INSPECTION. AIRCRAFT WAS GROUNED FOR REPAIRS.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001080900112	20010809	00112	SW  	2001	8	9	CA010724012      	1	20010712	G	5320	206031200118	STRAP           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSTALLING ELECTRICAL EQUIPMENT, A CRACK WAS FOUND ON THE AFT OUTBOARD RADIUS, STATION 100.8. THE CRACK STAR	TED FROM THE EDGE OF THE STRAP AT A TOOLING MARK MADE EITHER DURING MANUFACTURE OR PREVIOUS INSTALLATION. THE CRACK IS A	PPROXIMATELY 2 1/2 INCHS LONG, MOVING FORWARD AND OUTBOARD. THE STRAP WAS REPLACED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900114	20010809	00114	SW  	2001	8	9	CA010724015      	1	20010708	G	6220		BEARING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R ROD END	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING REGULAR MAINTENANCE (DAILY INSPECTION) EXCESSIVE PLAY WAS OBSERVED IN THE M/R DAMPER RODEND ON ON	E OF THE DAMPER ASSEBLIES. FURTHER INVESTIGATION REVEALED THAT THE TEFLON LINER (APPROX. 50%) WAS EXTRUDING FROM THE BEA	RING. THE BEARING WAS REPLACED AND THE A/C RETURNED TO SERVICE.				1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001080900116	20010809	00116	CE  	2001	8	9	CA010724023      	1	20010710	G	2720		ARM             			CESSNA	188   	A188        	2073004	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C98    	GL  	RUDDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4200 								(CAN) RUDDER PEDAL PEDASTAL BROKEN ON LANDING. FOUND THE PEDAL ARM BROKEN DUE TO CORROSION						1	L	7	1 	3O	3	O	 	A9CE    	E5CE	5	C	P3EA	 
2001080900118	20010809	00118	NM  	2001	8	9	CA010724026      	1	20010714	G	3246	26045641	WHEEL           			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				59   							(CAN) DURING SERVICE CHECK, NR 1 MAIN WHEEL TIRE PRESSURE FOUND TO BE 40 PSI PRESSURE DETECTED TO BE LEAKING AT WHEEL HU	B. NR 1 AND 2 MAIN WHEEL ASSEMBLIES REPLACED, NO FURTHER FAULTS AFTER 8 FLIGHT SEGMENTS.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA				 
2001080900120	20010809	00120	NM  	2001	8	9	CA010724027      	1	20010718	G	3244	26045611	TIRE            			BOEING	727   	727223      	1384074	NM  	PWA   	JT8   	JT8D15      	52051	NE  					MAIN WHEEL ASSY	FLAT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				366  							(CAN) NR 3 MAIN WHEEL TIRE FOUND FLAT ON WALKAROUND INSPECTION. MAIN WHEEL REPLACED. NO FURTHER FAULTS ON NEXT FIVE FLIG	HT SEGMENTS.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001080900121	20010809	00121	SW  	2001	8	9	CA010724031      	1	20010607	G	5302	206032400027	BULKHEAD        	BELL        	206031004FM 	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13108			AOKP00649					(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PA	RT  206-032-400-117, WHEN THE BULK HEAD WAS REMOVED CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BU	LK HEAD AND BOLT ATTACH FITTING PART  206-032-409-001 AND THE RADIUS WHERE THE BULK HEAD ATTACHED TO THE SKIN. THE BULK 	HEAD WAS REPLACED WITH NEW BELL HELICOPTER PART AS PER THE STRUCTURAL REPAIR MANUAL.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900123	20010809	00123	SW  	2001	8	9	CA010724032      	1	20010607	G	5340	206030111003	FITTING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13109								(CAN) THE FITTING WAS FOUND CORRODED ON 1200 HOUR INSPECTION AND NEW PART  206-033-173-001 WAS INSTALLED. THE ORIGINAL P	ART IS MANUFACTURED FROM MAGNESIUM WHERE THE NEW PART IS ALUMINUM SO AFTER 13109 OF FLYING ON A AIRCRAFT MANUFACTURED IN	 1978 THIS WOULD NOT BE UNUSUAL. WE SHOULD GET MUCH BETTER SERVICE FROM THE ALUMINUM FITTING.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900125	20010809	00125	SW  	2001	8	9	CA010724033      	1	20010523	G	2140	46D36	SWITCH          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					HEATER CONTROL	MISSING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE IN CRUISE FLIGHT ALL EXPERIENCED A NO HEAT CONDITION. ON INSPECTION, FOR SWITCH WAS REMOVED AND RUDDER PAD O	N THE END OF THE PLUNGER WAS FANNED DEBONDED & LODGED IN ORIFICE CAUSING HEATER NOT TO WORK.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001080900126	20010809	00126	WP  	2001	8	9	CA010724034      	1	20010710	G	6410	269A603523	BLADE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3380 								(CAN) ON DAILY INSPECTION OUTBOARD PART OF BLADE SKIN WAS FOUND TO BE CRACKED. CRACK IS FORMED AROUND TIP BLOCK ON BLADE	. THE CRACK IS APPROX. 3 INCHES LONG, STARTING FROM BEHIND ABRASION STRIP TO ABOUT MIDDLE OF BLADE.					1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001080900127	20010809	00127	WP  	2001	8	9	CA010724035      	1	20010710	G	6410	269A603523	BLADE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2890 								(CAN) ON INSPECTION OF OPPOSITE TAIL ROTOR BLADE, THIS TAIL ROTOR BLADE WAS FOUND TO HAVE NO ABRAISON STRIP ON LEADING E	DGE OF BLADE. FURTHER INSPECTION REVEALED THAT FILLER WAS USED UNDER PAINT TO BUILD UP EDGE. BOTH BLADES WERE REMOVED AN	D SENT TO SCHWEIZER A/C CORP FOR FURTHER INVESTIGATION.				1	G	7	1 	3O	3	O	 	4H12    	1E10				 
2001080900129	20010809	00129	SW  	2001	8	9	CA010724036      	1	20010709	G	6510	206040272101	SEAL            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R DRIVE SHAFT	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) ON PRE-FLIGHT INSPECTION, GREASE LEAKAGE ON FORWARD COUPLING ON INPUT DRIVESHAFT WAS NOTED. FURTHER INSPECTION REV	EALED THATTHE FORWARD SEAL ASSY HAD FAILED AND ALL THE GREASE IN THE FORWARD COUPLING WAS THROWN OUT WHICH CAUSED AN OVE	RHEAT CONDITION. A MORE DETAILED PRE-FLIGHT INSPECTION OF FORWARD AND AFT SEAL ASSEMBLIES FOR RIPS, TEARS AND GREASE LEA	KAGE WILL HELP PREVENT AN OVERHEAT CONDITION OR TOTAL DRIVESHAFT FAILURE			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900130	20010809	00130	CE  	2001	8	9	CA010725005      	1	20010705	G	5540	04331401	RUDDER HORN     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	VERITICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON COMPLYING WITH AD CF-2000-20 RE. RUDDER INSPECTION, FOUND LOWER RIB P/N 0431004-24 CRACKED. LEVER RUDDER FAIR	ING HAD TO BE REMOVED IN ORDER TO REPAIR RIB. UPON FAIRING REMOVAL, FOUND RUDDER HORN CRACKED IN TWO PLACES AT RADIUS. I	 FEEL THIS DAMAGE WAS CAUSED FRIN WIND DAMAGE AND NO RUDDER LOCK INSTALLED.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL	 
2001080900137	20010809	00137	SW  	2001	8	9	CA010725006      	1	20010621	G	3020	8943822	TUBE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ANTI-ICE SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ENGINE CHANGE EGT AND FF WERE HIGH AND RIGGING WAS DIFFICULT. BLEED AIR LEAK WAS FOUND AND THE LINE REPLACE	D. ENGINE PARAMETERS WERE NOW NORMAL AND RIGGING WAS ACCOMPLISHED. THE CRACKED TUBE ALSO CAUSED THE ENGINE COWL TO HEAT 	UP, POSSIBLE FIRE CONSIDERATION.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE	 
2001080900138	20010809	00138	NE  	2001	8	9	CA010725007      	3	20010710	G	6111	78030S0CN8173881	SEAL            			CNDAIR	CL215 	CL2156B11415	       	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	PROP SEAL	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			4    	4    							(CAN) THE PROPELLER BLADE SEAL HAD SPRING INSIDE OF IT AND THE TWO ENDS ARE WELDED TOGETHER BY THE MANUFACTURE. THE SPRI	NG BROKE AT THE WELDED JOINT CAUSING OIL TO LEAK OUT OF THE HUB AT THE BLADE ROOT. IT WAS NOTICED DURING A D.I AFTER THE	 FLIGHT. THE SEAL AND SPRING ASSY WAS REPLACED AND THE A/C RETURNED TO SERVICE.				2	H	7	2 	4T	4	T	RT	A14EA   	E20NE	6	C	P7NE	 
2001080900162	20010809	00162	EU  	2001	8	9	CA010725008      	1	20010717	G	2910	9603001261	SELECTOR VALVE  			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			1713 			HG40288					(CAN) PILOTS REPORTED A INTERMITTENT PROBLEM WITH THE HYDRAULIC LIGHT COMING ON WHEN LANDING. THIS INDICATES THE HYDRAUL	IC PUMP CYCLED 6 TIMES IN 1 HOUR. AFTER SERVICING THE SYSTEM THE PROBLEM WOULD STILL OCCUR. IT WAS DECIDED TO CHANGE THE	 HYDRAULIC SERVICE SELECTOR VALVE. THE PROBLEM DID NOT RETURN AFTER THIS.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001080900164	20010809	00164	EU  	2001	8	9	CA010725010      	1	20010719	G	2822	9688411404	PUMP            			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL BOOST	UNSERVICEABLE   	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			1458 	1458 							(CAN) BOOST PUMP FAILED CAUSING FUEL IMBALANCE. AIRCRAFT LANDED AND PUMP REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001080900170	20010809	00170	EU  	2001	8	9	CA010725013      	1	20010710	G	2752	9787320001	DRIVE GEAR      			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA			2126 								(CAN) PILOTS REPORTED FLAP SYSTEM 1 AMP CIRCUIT BREAKER ON BATTERY BUS TRIPPED WHEN FLAP SELECTED DOWN. THE SYSTEM WOULD	 FUNCTION NORMAL IF THEY KEPT THE AIR SPEED BELOW 140 KNOTS. THE FAILURE COULD NOT BE DUPLICATED ON THE GROUND. THE FLAP	 POWER DRIVE UNIT WAS REPLACED. THE AIRCRAFT WAS FLOWN AND FLAPS EXTENDED AT MAX EXTENSION SPEED AND SYSTEM FUNTIONED NO	RMAL.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001080900171	20010809	00171	EU  	2001	8	9	CA010725014      	1	20010710	G	2510	9593001216	SEAT BACK       			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2135 								(CAN) THE SEAT WAS REMOVED TO REPAIR BROKEN UP/DOWN ADJUSTMENT AND THE SEAT BACK WAS FOUND CRACKED. THE CRACKS WERE FOUN	D TO BE ONLY IN THE PLASTIC PART OF THE ALUMINUM STRAPS WERE NOT CRACKED, THE PART WAS REPLACED WITH A NEW UNIT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001080900172	20010809	00172	EA  	2001	8	9	CA010725019      	1	20010705	G	7120		MOUNT           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SUPPORT BEAM INSPECTION, AS PER SB601R-53-059, CRACKS WERE FOUND AT BL0 AND LBL36.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001080900173	20010809	00173	EU  	2001	8	9	CA010725020      	1	20010704	G	6720		LINER           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R BEARING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BEARING LINER WAS FOUND CRACKED IN BOTH TAIL ROTOR PITCH LINKS. THE SAME PROBLEM HAS BEEN REPORTED IN THE PAST	.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080900175	20010809	00175	SW  	2001	8	9	CA010725021      	1	20010703	G	2550	204075157001	SLIP RING       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					CARGO HOOK	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED PROBLEMS WITH ELECTRICAL RELEASE ON CARGO HOOK ASSEMBLY. SUSPENSION ASSEMBLY LATER DISASSEMBLED AND	 FOUND THAT INNER RING ON SLIP RING ASSEMBLY HAD DISBONDED PREVENTING PROPER CONTACT. THE SLIP RING ASSEMBLY WAS REPLACE	D WITH NEW PART AND UNIT REASSEMBLED. THE SUSPENSION ASSEMBLY WAS REINSTALLED IN THE AIRCRAFT AND SYSTEMCHECKED SERVICEA	BLE. THE SLIP RING ASSEMBLY ( THAT IS; DEBONDING AND PITTING) IS A COMMON SOURCE OF PROBLEMS WITH THE SUSPENSION ASSEMBL	Y.		1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001080900178	20010809	00178	SW  	2001	8	9	CA010725022      	1	20010703	G	7500		ARM             			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FOUND NUT OF ACTUATOR ARM LOOSE IN ARM. UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER ADJUSTMENTS.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900179	20010809	00179	SW  	2001	8	9	CA010725023      	1	20010703	G	5302	206031329003	FITTING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE FITTING HAD TO BE REPLACED DUE TO CRACK. IT APPEARS TO HAVE CRACKED DUE TO INCORRECT INSTALLATION. THERE WAS A	 100 INCH GAP BETWEEN THE LONGERON AND THE FITTING AND THIS PLACED THE FITTING UNDER STRESS. THE FITTING WAS REPLACED BY	 A NEW PART WITH CARE TAKEN TO ENSURE NO GAP WAS PRESENT ON THE NEW PART INSTALLATION.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900181	20010809	00181	EU  	2001	8	9	CA010725024      	1	20010704	G	6710	350A371508	ROD END         			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					MAIN ROTOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING POST FLIGHT INSPECTION OF AIRCRAFT IT WAS NOTICED THAT THE MAIN ROTOR PITCH LINK ROD AND RETAINER HAD SEPAR	ATED FROM ROD END. PILOT CONFIRMED THAT ON PREVIOUS FLIGHT HE HAD STARTED TO EXPERIENCE A MAIN ROTOR VIBRATION. MAIN ROT	OR AND SWASHPLATE ASSEMBLIES INSPECTED BY MAINTENANCE. NO OTHER DAMAGE FOUND. THE MAIN AIRCRAFT WAS FLIGHT TESTED AND RE	TURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2001080900183	20010809	00183	NE  	2001	8	9	CA010725026      	2	20010626	G	8510	16475	CASE            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				562  							(CAN) SMALL OIL LEAK ON NOSE SECTION. REMOVED NOSE SECTION AND DISCOVERED CRACK RADIATING FROM BOLT HOLE IN BEARING BORE	 OF FRONT ENGINE CASE. REMOVED ENGINE FOR REPLACEMENT.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2001080900184	20010809	00184	SW  	2001	8	9	CA010725031      	1	20010703	G	2810	206063688001	HOSE            		206063600   	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20R2    	 	GL  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING REFUELING OPERATION, FUEL WAS OBSERVED LEAKING FROM TANK VENT HOSE ASSEMBLY WHEN TANK WAS FILLED TO CAPACIT	Y. HOSE APPEARS TO HAVE DETERIORATED WITH AGE ALLOWING FUEL TO LEAK. DUE TO THIS DEFECT ANOTHER AIRCRAFT WAS VERIFIED BY	 PRESSURE TESTING THE VENT HOSE ASSEMBLY. IT WAS ALSO FOUND TO BE LEAKING. BOTH AIRCRAFT HOSES WERE REPLACED AND SYSTEMS	 CHECKED SERVICEABLE. MANUFACTURER OF AIRCRAFT CURRENTLY DOES NOT HAVE A RETIREMENT OR TEST SCHEDULE FOR THESE FLEXIBLE 	HOSES.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900191	20010809	00191	NE  	2001	8	9	CA010725032      	1	20010705	G	3231	7625100702043	LINK            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MLG DOOR	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			1882 								(CAN) DURING MAIN LANDING GEAR RETRACTION AND EXTENSION PILOTS NOTED A SLIGHT YAW. THEY ASSUMED IT TO BE CASUED BY DIFFE	RNECE IN RETRACTION RATES OF LANDING GEAR. UPON LANDING AT BASE, THE ENGINEER NOTED THAT THE GEAR DOOR WAS LOWER THAN TH	E RIGHT. INVESTIGATION REVEALED THAT THE LANDING GEAR DOOR LINK WAS REPLACED WITH A NEW ONE AND THE SYSTEM WAS FUNCTION 	CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE.			1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001080900196	20010809	00196	NE  	2001	8	9	CA010725033      	1	20010705	G	2910	7665103004041	TUBE            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					HYD SYSTEM	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) APPROX. 10 MINS AFTER TAKEOFF UNUSUAL LOW WHISTLING SOUND NOTICED BY ONE OF PILOTS, FOLLOWED SHORTLY THEREAFTER BY	 NR 2 SERVO WARMING LIGHT ILLUMINATING & NR 2 HYDRAULIC PRESSURE CYCLING BETWEEN 1000 & 3000PSI. SWITCHED OFF #2 SERVO S	WITCH AT WHICH TIME HYDRAULIC PRESSURE IND. RETURNED TO NORMAL (INDICATIVE OF LEAK AFT OF SERVO SHUTOFF VALVE. EMERG CHE	CKLIST FOR "LOSS OF HYD. PRESSURE" PREFORMED. PILOTS REVERSED COURSE&CARRIED OUT PRECAUTIONARY LDG W/O INCID.. POST FLT 	INSP REVEALED FLUID LEAKING OUT OF BELLY AREA AFT OF BAGGAGE COMPT & NR 2 HYDRAULIC RESERVOIR BELOW MIN.LEVEL. MAINT INV	EST. FOUND FLUID LEAK FROM PINHOLE IN NR 2 TAIL ROTORPRESSURE TUBE.  TUBE REPL ALONG WITH HYDRAULIC PUMP DUE TO	1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001080900199	20010809	00199	EA  	2001	8	9	CA010726001      	1	20010715	G	7120	60135006	MOUNT           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			19370								(CAN) DURING AN OPPORTUNITY INSPECTION OF THE ENGINE BEAM, CRACKS WERE FOUND ON THE CENTER SECTION. (REF ASB 601R-53-069	.)					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001080900200	20010809	00200	EA  	2001	8	9	CA010726006      	1	20010705	G	7120		MOUNT           			CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343B1     	 	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN OPPORTUNITY INSPECTION OF THE ENGINE SUPPORT BEAM, CRACKS WERE FOUND ON THE CENTER SECTION. SEE ASB						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001080900206	20010809	00206	EU  	2001	8	9	CA010726008      	1	20010703	G	6220	350A37116200	YOKE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ONE OF THE THREE DROOP RESTRAINT STOP YOKES WERE FOUND BROKEN IN TWO PIECES. MAIN ROTOR HEAD AND BLADES INSPECTED 	AND NO ADDITIONAL DAMAGE FOUND. YOKE REPLACED.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080900207	20010809	00207	NE  	2001	8	9	CA010726012      	1	20010705	G	3200	7655200904046	HARNESS         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					MLG	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, RED LANDING GEAR UNSAFE LIGHT FLICKERING INTERNITTENTLY WITH A CORRESPONDING "CLUNKING" IN THE AIRF	RAME FELT THROUGH THE COLLECTIVE STICK. UPON RETURN FROM FLIGHT MAINTENACE PUT AIRCRAFT ON JACKS AND THE LANDING GEARWAS	 OPERATED TO SIMULATE THE CONDITION. THE FAULT WAS TRACED TO THE LEFT MAIN DOWN LOCK WIRING HARNESS. THE HARNESS WAS REP	LACED WITH A NEW ONE. THE SYSTEM WAS FUNCTION TESTED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001080900213	20010809	00213	CE  	2001	8	9	CA010726014      	1	20010620	G	7603	K30B22HT	WIRE            	GARRTT      	TFE73122B   	LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	FAILED          	W				C				ABORTED TAKEOFF         				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			CA						P74114C					(CAN) ON TAKE OFF ROLL, ENGINE SLUGGISH, R/H FUEL COMPUTER LIGHT ON (COMPUTER KICKED OFF), ABORT TAKEOFF, CAME BACK TO M	AINTENACE HANGAR (MAIN BASE). N2 MONOPOLE FAULT APPEARS, CODE 14 ON DITAL ENGINE COMPUTER DOWNLOAD. WIRE K30B22HT SUSPEC	TED TO CAUSE THE FAULT BETWEEN CONNECTORS P360 & P358. WIRE REPLACED WITH NEW ONE. GROUND RUN CARRIED OUT. HIGH SPEED TA	XIING CARRIED OUT. NO MORE FAULT FOUND. A/C RETURNED TO SERVICE.			2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2001080900217	20010809	00217	WP  	2001	8	9	CA010726024      	1	20010606	G	6310	369D25351	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			392  								(CAN) O/R CLUTCH ASSY WAS REMOVED FOR O/H. UPON O/H INSPECTION IT WAS FOUND THAT THE SPRAG ASSY HAD ONE BROKENSPRAG. THE	 BROKEN PIECE WAS RECOVERED FROM INSIDE THE ASSEMBLY.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001080900218	20010809	00218		2001	8	9	CA010726025      	4	20010726	G	3457	114DD26	RELAY           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	GPS	UNSERVICEABLE   	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) HSI LT/RT DEVIATION REAMINS CENTERED WHEN GPS IS SELECTED WITH NO FAILURE WARNING/INDICATION GPS LAMP REMAINED ON,	 GPS & TO FROM FLAGS REMAINED VALID). RELAY K2 IN AVIONICS J-BOX #1 FAILED TO ENERGIZE WHEN GPS WAS SELECTED. REPLACED K	2. NOTE: TC ENGINEERING REQUIRES THAT THE GPS LAMP BE INTERLOCKED THROUGH ALL RELAYS. IF A SINGLE RELAY WERE TO FAIL, TH	E GPS LAMP WOULD EXTINGUISH. TH 208/B SWITCHING SYSTEM WAS APPROVED IN THE USA WITHOUT SUCH INTERLOCKS. HSI (GS) VERTICA	L DEVIATION POINTER IS DRIVEN DURING GPS SELF TEST. FOUND GPS VERTICAL DEVIATION WIRES CONNECTED TO CESSNA J-BOX. CAPPED	 AND STOWED GPS VERTICAL DEVIATION WIRES AT AVIONICS J-BOX #2.	1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001080900219	20010809	00219	EU  	2001	8	9	CA010726026      	1	20010724	G	3411	0851HL	PROBE           			AIRBUS	330   	A330322     	3930325	EU  	PWA   	4168  	PW4168      	 	NE  					PITOT SYSTEM	BLOCKED         	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) A/C ARRIVED WITH CAPTS. AIRSPEED READING INCORRECTLY. MTCE SWAPPED ADIRU #1 INTO #3 POSITION TO DEFER WITH LEAST A	MOUNT OF IMPACT. A/C DEPARTED AND REJECTED T/O. ADM WAS OBTAINED FROM AIR CANADA AND INSTALLED IN A/C SSV. AVIONICS WAS 	CALLED IN TO C/O PITOT STATIC CHECK. FAULT STILL PRESENT. PITOT LINE REMOVED BETWEEN CAPT. PITOT PROBES AND ADM AND FOUN	D BLOCKED. DEBRIS REMOVED FROM LINE AND PROBE SYST. TESTED SERVICEABLE WITH PITOT STATIC TEST SET. A/C DECLARED SERVICEA	BLE 7:30 HOURS.		2	L	7	2 	4F	4	F	RT	A46NM   	E36NE				 
2001080900221	20010809	00221	SW  	2001	8	9	CA010726027      	1	20010726	G	6510	407340339103	BEARING         		4070403031  	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					FAN SHAFT	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1256 								(CAN) AFTER NORMAL UNEVENTFUL FLT, PILOT SHUTDOWN A/C&NOTICED NOISE COMING FROM TAIL ROTOR DRIVE TRAINN DURING COAST DOW	N. SUBSEQUENT INSP REVEALED THATT HE GREASE EMANATING FROM AFT FAN SHAFT BEARING BLACK WITH METALLICPARTICLES, BEARING R	OUGH WHEN ROTATED USING DRIVE TRAIN BY HAND&MORE PLAY IN BEARING THAN IS NORMALLY FELT WHEN LOADED IN LATERAL&FORE&AFT D	IRECTION BY HAND. NO ANCILLARY DAMAGE. BEARING WS REPL WITH NEW BEFOREFURTHER FLT. HAVE BEEN OTHER FAILURES OF TYPE ON B	ELL 407 RESULTING IN TC AD CF-2000-02 REQ 25 HR INSP&LUBE OF THESE BEARINGS. PLEASE NOTE THAT BEARING FAILED 13.7 HRS AF	TER SUCH INSP.THE INSP AT THAT TIME DID NOT REVEAL ANY PAR	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080900222	20010809	00222	SW  	2001	8	9	CA010726028      	1	20010724	G	6510	407340339103	BEARING         		407040303101	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					FAN SHAFT	DISINTEGRATED   	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			1233 								(CAN) SHORTLY AFTER TAKEOFF, ABOUT 400 FT ABOVE GROUND, A/C SOUND & VIBRATION LEVELS SUDDENLY CHANGED FROM NORMAL TO HEA	VY VIBRATION THROUGHOUT WHOLE A/C WITH OSCILLATING, DRONING NOSIE. AS WELL, PILOT NOTICED PULSING FEEDBACK SE NSATION FR	OM ANTITORQUE PEDALS. PILOT IMMEDIATELY ABORTED CLIMB&CARRIED OUT PRECAUTIONARY DESCENT&NORMAL LDG W/O INCID.. TAIL ROTO	R CNTL AUTH NEVER LOST. AFTER ENGINE SHUTDOWN, INSP REVEALED COMPLETELY FAILED FWD FAN SHAFT BEARING WITH DISINTIGRATED 	BEARING CAGES & BALLS EJECTED INTO IMPELLER. ANCILLARY DAMAGE TO IMPELLER, SHAFT&OIL COOLER BLOWER HOUSING. THER HAVE BE	EN OTHER FAILURES OF TYPE ON BELL 407 RES ULTING IN TC AD CF-2000-02 REQ	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080900223	20010809	00223	EU  	2001	8	9	CA010726034      	1	20010725	G	6520	350A33212900	PLATE           		350A33200403	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				428  		V231292					(CAN) BLACK PAINT INDEX MARKS MISALIGNED AND OUTBAOARD SPACER FREE TO ROTAT. UNIT IS POST MOD 07-6554 PART 2.B.3 AND POS	T MOD 07-6551. RECEIVED IN SHOP, DOUBLE LOCKING OF NUT VERIFIED ALL VISIBLE ELEMENTS INBOARD OF BEARING FELT TIGHT AND S	ECURE, NUT UNLOCKED AND TORQUE APPLIED. NUT ROTATED 30 DEGREES PRIOR TO ACHIEVING MINIMUM TORQUE LOAD. UNIT DISASSEMBLED	, ALL SPACERS AND BEARING INNER RACE EXHIBITED SIGNS OF ROTATION. BEARING INNER RACE HAS WORN THROUGH THE D148 VARISH AN	D INTO PARENT MATERIAL OF ROTATING PLATE (350A33-2129-00).		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080900224	20010809	00224	EU  	2001	8	9	CA010726035      	1	20010725	G	2400	350A61131201	CIRCUIT BOARD   			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BUCKET RELEASE	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) UNABLE TO PERFORM WATER BUCKET OPERATIONS (FIRE SUPPRESSION) DUE TO ELECTRICAL DEFECT. TROUBLESHOOTING CARRIED OUT	 ON SYSTEM AND PRINTED CIRCUIT BOARD 25 IDENTIFIED AS CAUSE DUE TO HAEAVY CORROSION ON CONTACT POINTS OF BOARD. BOARD WA	S REPLACED WITH NEW UNIT AND SYSTEM CHECKED SERVICEABLE. THIS BOARD ALSO CONTROLS OTHER AIRCRAFT SYSTEMS SUCH AS COMMUNI	CATIONS, CARGO HOOK OPERATIONS, ETC. IT IS CURRENTLY NOT PART OF THE MANUFACTURE'S INSPECTION PROGRAM AS A POINT OF INSP	ECTION.		1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080900226	20010809	00226	NM  	2001	8	9	CA010726036      	1	20010716	G	2720	401602728A	COMPUTER        			BOEING	727   	727172C     	1384058	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					FEEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) POST INSTALLATION DURING FUNCTIONAL TEST THE UNIT DISCOVERED TO BE LEAKING. AFTER REMOVAL OF THE FEEL COMPUTER IT 	WAS NOTICED THAT A CRACK APPROX. 3 INCHES IN LENGTH WAS WMITTING FROM THE ACTUATOR MOUNTING COVER. THE CRACK ITSELF IS L	OCATED ON THE CHAMBER. THIS UNIT WAS RECENTLY OVERHAULED BY AVBORNE ACCESSORY GROUP INC.				2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001080900227	20010809	00227	WP  	2001	8	9	CA010726038      	1	20010630	G	7920	6843698	INSULATOR       	ALLSN       	501D13D     	CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					INSULATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						705276					(CAN) FOUND INSULATOR MISSING ON SERVICE CHECK NEW PART INSTALLED. NO OTHER PROBLEM FOUND AND A/C RETURNED TO SERVICE. L	T ENGINE REAR SCAVENGE PUMP INSULATOR WAS MISSING IT HAD BEEN REPORTED BY GROUND PEOPLE THAT A PART FALL FROM AIRCRAFT O	N APPRAOCH TO LAND IN WINNIPEG. NORMAL INSPECTION CALL TO VERIFY PRESENCE OF INSULATOR.				2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001080900228	20010809	00228	SW  	2001	8	9	CA010727001      	1	20010704	G	6510	R34665	TURBINE         		2040625401  	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					COOLER BLOWER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9209 	322  		417					(CAN) VIBRATION ON BLOWER ASSY. EXAMINE BLOWER ASSY & FOUND TWO CRACKS ON THE ROOT OF TWO BLADE.						1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2001080900229	20010809	00229	EA  	2001	8	9	CA010727008      	1	20010607	G	6310	269A55593	SHAFT           		259A55593   	SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE ADAPTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4138 			5424					(CAN) BROKEN TEETH ON SHAFT ON ENGINE ADAPTER SIDE. REPLACE SHAFT.						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001080900230	20010809	00230	EA  	2001	8	9	CA010727009      	1	20010707	G	6320	CR3687	SEAL            			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					MAIN ROTOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OIL SEAL LEAKING IN RPM CABLE. REPLACE OIL SEAL PN CR 3687.						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001080900233	20010809	00233	EA  	2001	8	9	CA010727010      	1	20010607	G	6220	269A1227817	BEARING         			SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					MAIN ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING WORN INSIDE. REPLACE ALL 3 GRIP BEAR IN SET.						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001080900234	20010809	00234	EA  	2001	8	9	CA010727011      	1	20010707	G	6220	269A1231	BEARING         		269A12215   	SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					MAIN ROTOR	RATCHETING      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BEARING RACHET WHEN INSPECTION. REPLACE BEARING.						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001080900235	20010809	00235	EA  	2001	8	9	CA010727014      	1	20010707	G	2140	269A4799003	BRACKET         		269A4799001 	SCWZER	269   	269D        	8059501	EA  	LYC   	O360  	HIO360D1A   	41514	EA  					HEATER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BRACKET CRACK . REPLACE BRACKET.						1	G	7	1 	3U	3	O	0	4H12    	1E10				 
2001080900239	20010809	00239	SW  	2001	8	9	CA010727015      	1	20010607	G	5302	206032400027	BULKHEAD        		206032400177	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13108			AOKP00649					(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PA	RT # 206-032-400-117. WHEN THE BULKHEAD WAS REMOVED, CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE B	ULKHEAD AND BOLT ATTACHMENT FITTING #206-032-409-001, AND THE RADIUS WHERE THE BULKHEAD ATTACHES TO THE SKIN. THE BULKHE	AD WAS REPLACED WITH NEW BHTC PART AS PER THE SRM.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080900241	20010809	00241	NM  	2001	8	9	CA010727016      	1	20010718	G	3244		TIRE            			BOEING	727   	727227      	1384078	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) THE NR  1 TIRE THREAS SEPARATED FROM THE CARCASS DURING T/O ROTATION. DAMAGE ON EXTERIOR OF THE WING DOOR. THE NR 	2 TIRE FAILED ON TAXI INTO RAMP IN YYC.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001080900242	20010809	00242	GL  	2001	8	9	CA010727017      	2	20010720	G	7210		GEARBOX         			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D22      	03005	GL  					ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THROUGH FL170 AFTER DEPARTURE NOTICED NR 2 GEAR BOX OIL PRESSURE FLICKERING. OIL PRESSURE WAS STILL I	N THE GREEN RANGE AND THE POWER SECTION OIL PRESSURE WAS NORMAL. ENGINE SHUT DOWN AND AIRCRAFT DIVERTED INTO YYZ.					2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001080700223	20010807	00223	NM  	2001	8	7	CA010727020      	1	20010718	G	2910	271N61191	HYDRAULIC LINE  	            	273N20025   	BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E437	54555	NE  	 		            		RUPTURED @ MIDPT	LEAKING         	W			    	D	 	 	 	RETURN TO BLOCK         				K	 	 	FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA		 									(CAN) AIRCRAAFT RETURNED TO THE GATE, AFTER  PUSH BACK, DUE TO A HYDRAULIC LEAK AT THE L/H MAIN LANDING GEAR DOWNLOCK AC	TUATOR SUPPLY FLEX LINE. LINE WAS FOUND RUPTURED AT MID POINT. LINE WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001080900243	20010809	00243	NM  	2001	8	9	CA010727023      	1	20010727	G	2730		BUSHING         		2827001011  	BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					ACTUATOR	LOOSE           	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) BUFFETING FELT THROUGH THE FLIGHT AND INCREASE IN FREQUENCY DURING CLIMB OUT. THE LEFT ELEVATOR WAS INDICATING LOW	ER THAN THE RIGHT AND WOULD FLUCTUATE UPWARD. INVESTIGATION REVEALED LEFT END OUTBOARD POWER ACTUATOR (P.C.A.) EYE END B	USHING LOOSE AND SUPPORT TRUNNION LOOSE. REPLACED ACTUATOR AND TRUNNION.				2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001080700224	20010807	00224	WP  	2001	8	7	CA010727026      	1	20010711	G	2751	0070J	TRANSMITTER     	            	            	DOUG  	DC9   	DC932       	3022066	WP  	PWA   	JT8   	JT8D7       	52053	NE  	 		            		TRANSMITTER	FAILED          	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			AP	APPROACH       	1			CA		 									(CAN) STALL WARNING OCCURRED SEVERAL TIMES DURING APPROACH WITH SPEED ABOVE 220 KTS. REPLACED FLAP POSITION TRANSMITTER.						2	L	7	2 	4F	4	F	 	A6WE    	E2EA				 
2001080700225	20010807	00225	NM  	2001	8	7	CA010727027      	1	20010705	G	2912	2705579	CLAMP           	            	            	BOEING	737   	737296      	1384486	NM  	PWA   	JT8   	JT8D9A      	52048	NE  	 		            		CLAMP	                	W			    	D	 	 	 	RETURN TO BLOCK         				K	 	 	FLUID LOSS                			TO	TAKEOFF        	1			CA		 									(CAN) HYDRAULIC LOSS OF SYSTEM A AFTER TAKE OFF, AIRCRAFT RETURNED. BROKEN CLAMP ON THE RETURN FILTER BOWL. NEW CLAMP IN	STALLED, AND FILTER ELEMENT CHANGED.					2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001080700226	20010807	00226	NM  	2001	8	7	CA010727029      	1	20010704	G	4910	732138701	ACTUATOR        	            	732138701   	BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  	 		            		ACTUATOR	                	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 									(CAN) BUFFETING FELT THROUGH THE FLIGHT AND INCREASED IN FREQUENCY DURING CLIMB OUT. FOUND TO BE THE APU DOOR ACTUATOR A	T FAULT. HALF INCH PLAY IN ACTUATOR BEARING AND SEAL DAMAGE. REPLACED THE APU DOOR ACTUATOR.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001080900244	20010809	00244	CE  	2001	8	9	CA010727034      	1	20010719	G	3310	041312610	RHEOSTAT        			CESSNA	172   	172D        	2072410	CE  	CONT  	O300  	O300D       	17022	SO  					COCKPIT	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING THE ANNUAL INSPECTION OF THE ELCTRICAL SYSTEM THE RHEOSTAT BEGAN SMOKING.						1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2001080900245	20010809	00245	NE  	2001	8	9	CA010727035      	2	20010727	G	7532		SWITCH          		3192100     	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					BLEED VALVE	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			2831 	283  		670					(CAN) LOST SIGNAL FROM BLEED VALVE WHICH WORKS CORRECTLY. FOUND SWITCH LEAF AND ROLLER WAS BROKEN.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001080900246	20010809	00246	CE  	2001	8	9	CA010727036      	1	20010723	G	3230	244110010	PIVOT           			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			CA			6300 								(CAN) DURING INSPECTION CARRIED OUT IAW AD 2001-06-06, BOTH PIVOT ASSMEBLIES WERE FOUND CRACKED						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001080900247	20010809	00247	CE  	2001	8	9	CA010730001      	1	20010723	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6300 								(CAN) DURING INSPECTION REQUIRED BY CESSNA SEB 01-2 BOTH ACTUATORS WERE FOUND CRACKED						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001080900249	20010809	00249	CE  	2001	8	9	CA010730002      	1	20010723	G	3233	99820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8600 								(CAN) DURING INSPECTION CARRIED OUT IAW CESSNA SEB01-2, BOTH LANDING GEAR ACTUATORS WERE FOUND CRACKED.						1	H	7	1 	3O	3	O	 	3A17    	E286	5	C	P7EA	 
2001082300087	20010823	00087	CE  	2001	8	23	CA010808002      	1	20010729	G	6310	105199	CARBURETOR      			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				650  							(CAN) ENGINE STARTED LOSING POWER WHILE IN CRUISE AT 2500 FT & 30 SEC LATER QUIT RUNNING. PILOT INSTRUCTOR MADE A FORCED	 LANDING IN HAY FIELD. ENGINE WOULD NOT START AGAIN. CARBURATOR WAS REPLACED AND ENGINE STARTED TO RUN NORMALLY AND AIRC	RAFT WAS FLOWN OFF FIELD. NOTE: LAST SUMMER A SIMILAR INCIDENT OCCURRED ON ANOTHER OF OUR C-152'S EXCEPT THAT THE ENGINE	 DID NOT QUIT COMPLETELY AND HE LANDED AT ON AIRPORT.			1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2001082300093	20010823	00093	SW  	2001	8	23	CA010808003      	1	20010706	G	6320	2060400321	BEARING         		20604000005 	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	SPALLED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99		7617 	2233 		B12150					(CAN) TRANSMISSON REMOVED FROM A/C DUE TO METAL CONTAMINATION AND EXCESSIVE NOISE. ON DISASSEMBLY, MAIN INPUT GEAR SHAFT	 P/N 206040040003 WAS FOUND TO HAVE VERTICAL PLAY. AFTER REMOVING THE SHAFT AND THE DUPLEX THRUST BEARING P/N 2060400321	 THE TOP BEARING OF THE THRUST BEARING WAS FOUND TO BE BADLY SPALLED ON ALL THE BALLS. THE VERTICAL MOVEMENT OF THE SHAF	T AND RING GEAR ALSO CAUSED EXCESSIVE WEAR OF THE PINON AND RING GEAR.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001082300095	20010823	00095	NM  	2001	8	23	CA010808032      	1	20010726	G	5246	LJ76872	DOOR            			BOEING	757   	757236      	       	NM  	RROYCE	RB211 	RB211535E437	54555	NE  					ENGINE OIL	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT ARRIVED ON STATION WITH NR 2 ENGINE OIL SERVICING DOOR MISSING. ROLLS ROYCE SERVICE BULLETIN RB 211-71-B5	92 WAS INCORPORATED ON THE DOOR. A NEW ACCESS DOOR WAS INSTALLED. NEW SPRING CLIP FROM GOODRICH WILL BE INSTALL WHEN MOD	IFICATION BECOME AVAILABLE AS PER FIELD TECHNICAL STATUS ISSUE 12.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU				 
2001082300100	20010823	00100	WP  	2001	8	23	CA010808060      	1	20010801	G	5280	1512449107	ROD             			LKHEED	1011  	1011385114  	       	WP  	RROYCE	RB211 	RB21122B02  	54555	NE  					MLG DOOR	STIFF           	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			SW	99										(CAN) AFTER TAKE OFF, LEFT HAND NOSE GEAR DOOR WOULD NOT RETRACT. AIRCRAFT RETURNED TO THE STATION. FOUND THE LEFT HAND 	GEAR DOOR ROD ACTUATOR VERY STIFF. UNIT WAS SERVICED AS PER MAINTENANCE MANUAL AND CHECKED SERVICEABLE AS PER OVERHAUL M	ANUAL. SYSTEM WAS VERIFIED AND FOUND SERVICEABLE DURING TEST FLIGHT.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001082300101	20010823	00101	GL  	2001	8	23	CA010809001      	2	20010725	G	7230	23033721	COMPRESSOR WHEEL		C20B6890550 	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		5069 	1695 		CAC35783					(CAN) DURING AN SCHEDULED INSP THE 1ST STAGE COMPRESSOR WAS NOTED TO HAVE F.O.D. AFTER REMOVING THE CASE HAVLES FOR FURT	HER INSPECTION. IT WAS FOUND NO DAMAGE WENT FURTHER DOWN THAN THE 1ST STAGE. THE DAMAGE WAS INSPECTED AND BLENDED OUT IA	W MAINTENANCE MANUAL. THIS F.O.D. WAS UNDETERMINED ON WHAT AND HOW, SINCE THERE WAS A PART SEP. INSTALLED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001082300103	20010823	00103	GL  	2001	8	23	CA010809002      	2	20010724	G	7323	1056058312	SPRING          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 2 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A POWER ASSURANCE CHECK NR 2 ENGINE HAD TOT AND TORQUE FLUCTUATIONS. ENGINE POWER RETURNED TO OPERATIVE LIM	ITS AND A/C LANDED AT MAINTENACE FACILITY. DURING POST FLIGHT INSPECTION, SPRING WAS FOUND TO BE CRACKED OFF FROM GOVERN	OR ARM. NEW ONE INSTALLED.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001082300104	20010823	00104	CE  	2001	8	23	CA010809003      	1	20010725	G	2150	1155550259	SHAFT           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					A/C PACK	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			593  								(CAN) QUILL SHAFT IN AIR CONDITIONING COMPRESSOR DRIVE SHEARED AT SHEAR POINT BEHIND SPLINE. SHAFT REPLACED & AIRCRAFT R	ETURNED TO SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA				 
2001082300105	20010823	00105	GL  	2001	8	23	CA010809005      	2	20010718	G	7250	23065833	TURBINE BLADES  								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA			373  	373  							(CAN) AFTER AN INFLIGHT SHUTDOWN, THE ENGINE WAS DISMANTLED AT THE VANCOUVER SERVICE CENTRE OF STANDARD AERO. THE LOCAL 	TSB, ROLLS ROYCE AND CUSTOMER WERE ALL PRESENT DURING THE TEARDOWN INVESTIGATION. IN THE DISMANTLING OF THE TURBINE ASSE	MBLY, THE 3RD STAGE TURBINE WHEEL WAS MISSING ONE ENTIRE BLADE. THE BLADE HAD SEPARATED AND CAUSED SIGNIFICANT DOWNSTREA	M DAMAGE. THE EXACT CAUSE OF THE FAILURE IS CONSIDERED UNKNOWN. IN CONJUNCTION WITH THE TSB IN VANCOUVER, THE FAILED PAR	TS WILL BE FORWARDED TO ROLL ROYCE IN INDIANAPOLIS FOR A FULL METALURGICAL INVESTIGATION.							3	U			E4CE				 
2001082300107	20010823	00107	WP  	2001	8	23	CA010809006      	1	20010725	G	2913	EA501828	PUMP            			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					HYD SYSTEM	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			DE	DESCENT        	1			CA				1297 							(CAN) EMERGENCY LANDING WITH SMOKE IN COCKPIT. FOUND ELECTRIC HYDRAULIC PUMP BYPASSING THRU CASE DRAIN AND PUMP DEVELOPI	NG 2,700 PSI ONLY. AFTER INSPECTION AIRCRAFT WAS FERRIED TO MAINTENANCE BASE WITH GEAR DOWN AND PUMP OFF. AC PUMP REPLAC	ED. MULTIPLE GEAR RETRACTION C/O AND FLAP MOVEMENT USING AC HYDRAULIC PUMP. PRESSURE AND TEMPERATURE WITHIN LIMIT. AIRCR	AFT RETURN TO SERVICE.			2	L	7	2 	4R	4	T	 	6A6     	E282				 
2001082300108	20010823	00108	SW  	2001	8	23	CA010809007      	1	20010724	G	6310	206040272101	SEAL            		206040015103	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					DRIVESHAFT	DETERIORATED    	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA						A2001964					(CAN) ON LANDING AN ABNORMAL NOISE WAS HEARD FROM ENGINE COMPARTMENT. ENGINE WAS SHUT DOWN AND IT WAS DISCOVER THAT THE 	FORWARD COUPLER OF THE ENGINE -TRANSMISSION X HAD HEATED UP. THE SEAL HAD RUPTURED ALLOWING THE GREASE TO EXIT HEAT UP T	HE COUPLER AND FURTHER MELT THE SEAL. ALL 4 TEMPLATES ON THE COUPLER HAD TURNED BLACK INDICATING AN OVERTEMP CONDITION. 	AT THE DAILY INSPECTION/PREFLIGHT THERE WERE NO SIGNS OF GREASE LACKING FROM THE COUPLER AND ALL 4 TEMPLATES WERE NORMAL	. THIS VISUAL INSPECTION WAS CARRIED OUT BY THE PILOT 1.6FLT LVS PRIOR TO DISCOVERY OF THE FAULT.		1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001082300109	20010823	00109	WP  	2001	8	23	CA010809008      	1	20010724	G	7921	A1855	BRACKET         	ROBSIN      	C2361       	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					SCROLL ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			841  								(CAN) UPON REMOVING THE SCROLL TO CORRECT A CLUTCH ACTUATOR SWITCH THAT WAS NOT FUNCTIONING, THE BROKEN A185-5 BRACKET W	AS DISCOVERED. SUSPECT FAN IMBALANCE TO BE THE CAUSE OF THIS DEFECT.					1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001082300110	20010823	00110	WP  	2001	8	23	CA010809009      	1	20010724	G	6200	V31001	SWITCH          	ROBSIN      	C0511       	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ACTUATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			841  			0312					(CAN) AT 100 HR INSPECTION, TEST OF ACTUATOR SWITCHES-ONE SWITCH FAILED THE TEST. INSPECTION OF THE SWITCH REVEALED THAT	 THE ACTUATOR BUTTON ON THE SWITCH WAS WORN TO ABOUT 1/2 OF IT'S ORIGINAL HEIGHT. INSTALLED A NEW SWITCH. SUSPECT FAN IM	BALANCE TO BE THE CAUSE OF THIS WEAR.				1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001082300111	20010823	00111	NM  	2001	8	23	CA010809014      	1	20010710	G	3211	NAS679A5	NUT             	BOEING      	B273201602  	BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					SUPPORT ASSY	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2031					(CAN) UPON SCHEDULED MLG REMOVAL FOUND NUT P/N NAS679A5 ON RT SUPPORT ASSY TRUNNION SPLIT ON ONE SIDE.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001082300137	20010823	00137	GL  	2001	8	23	CA010809016      	2	20010722	G	7230		CASE            		6890550     	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	DAMAGED         	W				O				OTHER                   				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			CA			4168 	982  		CAC41685					(CAN) ON WINDUP FROM GROUND IDLE TO FLIGHT IDLE, THE PILOT HEARD A POPPING NOISE AND A STEADY SOUND OF RUSHING AIR. THE 	TURBINE OUTLET TEMPERATURE (TOT) HAD CLIMBED INTO THE YELLOW ARC. DURING TROUBLLE SHOOTING THE COMPRESSOR CASE HALF WAS 	MISSING AND STATOR (NEXT TO THE SPLIT LINE) AT THE 4TH STAGE STATION LINE. THIS STATOR WENT BACK AND DAMAGED THE REMAINI	NG STATORS AND WHEELS. COMPRESSOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001092000047	20010920	00047	SO  	2001	9	20	CA010809018      	1	20010726	G	2133	1036383	OUTFLOW VALVE   			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					CABIN PRESSURE	DIRTY           	W				B				EMER. DESCENT           				W			INADEQUATE Q C            			CR	CRUISE         	1			CA				310  							(CAN) AT FLIGHT LEVEL 22000, CABIN LOST PRESSURE. AN EMERGENCY DESCENT WAS CARRIED OUT AND THE REMAINDER OF THE FLIGHT W	AS NORMAL. UPON INSPECTION THE OUTFLOW VALVE WAS FOUND TO BE LOOSE AND DIRTY. THE VALVE WAS CLEANED & TIGHTENED, THEN A 	SATISFACTORY TEST FLIGHT WAS CARRIED OUT.				1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2001081400013	20010814	00013	NE  	2001	8	14	CA010810001      	1	20010422	G	5320		BULKHEAD        	SKRSKY      	            	SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  	 		            		L/H SIDE ST.215	CRACKED         	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 	11668								(CAN) CRACKED FOUND AT ST.215 L/H SIDE BULKHEAD 7.5 INCHES BELOW WATERLINE 121. EXTENDING FROM M6B SUPPORT TO MAIN BULKH	EAD ELECTRICAL PLUG.					1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001092000048	20010920	00048	SW  	2001	9	20	CA010810005      	1	20010723	G	6410	206016201133	BLADE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL ROTOR	DENTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			106  								(CAN) DURING A DAILY INSPECTION THE PILOT NOTICED A DENT ON THE LEADING EDGE OF THE NOTED T/R BLADE. UPON INSPECTION THE	 DAMAGE WAS MEASURED AND FOUND TO BE IN LIMITS. FURTHER TO THE INVESTIGATION IT WAS FOUND THAT A SCREW HAD COME LOOSE FR	OM THE GEARBOX FAIRING INTO THE T/R BLADE PATH. NO OTHER DAMAGE WAS NOTED.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001092000049	20010920	00049	WP  	2001	9	20	CA010810006      	1	20010801	G	3246	C2411	CROSSTUBE       	ROBSIN      	C0148       	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MLG	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1355 								(CAN) 2 CHAFED MARKS APPROX 1/16" DEEP, 3/8" APART & 1/2" LONG, MADE BY THE WIRES OF THE SEAT HOSE THAT IS ATTACHED TO T	HE CABIN HEATER SHROUD ON THE OUTLET SIDE. HEATER SHROUD IS NOT A TIGHT FIT TO THE MUFFLER & I HAVE IN THE PAST NOTED WE	AR ON THE MUFFLER SUPPORT RINGS FOR THE SHROUD. THERE IS ROOM FOR THE SHROUD TO ROTATE UNTIL THE SEAT HOSE & CLAMP TOUCH	ES & WEARS THE AFT CROSS TUBE. AFT CROSS TUBE REPLACED.			1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2001092000050	20010920	00050	CE  	2001	9	20	CA010810007      	1	20010518	G	2612	302158	FIRE DETECTOR   			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LT ENGINE	INTERMITTENT    	W				E				ENGINE SHUTDOWN         				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) ON SHORT FINAL, THE FIRE DETECTION SYSTEM ON THE LEFT ENG ACTIVATED. THE PILOT ELECTED TO SHUTDOWN THE ENG & CONTI	NUED WITH THE LANDING. NO OTHER INDICATIONS, SUCH AS SMOKE OR FLAMES, WERE NOTICED. ON INSPECTION THE LOWER AFT FIRE DET	ECTOR (NR 3) WAS FOUND TO BE INTERMITTENTLY INDICATING A FIRE WHEN THERE WAS NO FIRE. THE DETECTOR WAS REPLACED WITH A S	ERVICEABLE UNIT & THE A/C WAS RETURNED TO SERVICE. THERE IS AN AD ON THIS UNIT, PYROTECTOR 78-14-09, WHICH INCLUDES TEST	ING THE SYSTEM EVERY 100 HOURS. THIS AD HAD BEEN CARRIED OUT ABOUT 25 HOURS AGO WITH NO INDICATION OF ANY PROBLEMS. THIS	 IS THE FIRST TIME WE HAVE HAD A FALSE FIRE INDICATION FROM ONE OF THESE UNITS.	1	L	7	2 	3T	3	T	 	A14CE   	E4EA				 
2001092000053	20010920	00053	SW  	2001	9	20	CA010810013      	1	20010625	G	5711		SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  	AMTR  	CUSHMN	O200        	05645	GL  	MCAULY	1A100	1A100ACM    	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH WINGS WERE STRIPPED OF FABRIC & L/E MATERIAL REMVD DURING INSP. BOTH WING TIPS WERE REMVD ALONG WITH FUEL TAN	KS & AILERON BELLCRANKS. SPARS WERE BLOWN WITH COMPRESSED AIR THEN WASHED DOWN WITH MILD SOAP & WARM WATER. THE INSP THE	N PROCEEDED USING HIGH INTENSITY LAMP & LARGE MAGNIFYING GLASS. AFTER REMOVING VARNISH IN LIFT STRUT ATTACHMENT POINT, I	 COULD IDENTIFY VERY SMALL CRACK IN GLUE JOINT ON REAR FACE OF RIGHT REAR WING SPAR. USING LIGHT & MAGNIFYING GLASS, I D	ETECTED ON UPPER EDGE OF RIGHT REAR SPAR, TOTAL OF 5 COMPRESSION TYPE CRACKS WHICH UNDER NORMAL LIGHTING CONDITIONS COUL	D NOT BE SEEN. 2 ACTUAL SPLITS WERE REVEALED STARTING AT REINFORCING PLYWOOD PLATE. THESE SPLITS FOLLOWED EDGE GRAIN OF	1	H	7	1 	3O	3	O	 	A759    	EXPA3O	5	N	P918	 
2001092000055	20010920	00055	EU  	2001	9	20	CA010813003      	1	20010731	G	2431	23491	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE731*     	01518	WP  					NR 2	OVERHEATED      	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				35   							(CAN) DURING CRUISE NR 2 BATTERY OVERHEAT INDICATED IN COCKPIT, CREW DIVERTED TO CYXU, BATTERY WAS REPLACED WITH SERVICA	BLE UNIT AND AIRCRAFT PROCEEDED WITH NO ADDITIONAL FAULTS. FAULTY BATTERY WAS FORWARDED FOR REPAIR/DEEP CYCLE.					2	L	7	2 	4F	4	F	RT	A3EU    	E6WE				 
2001092000057	20010920	00057	EA  	2001	9	20	CA010813005      	2	20010703	G	7230		BLADE           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB4T	HCB4TN3     	GL  	COMPRESSOR	SEPARATED       	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA											(CAN) ON TAKEOFF PARTIAL LOSS OF POWER EXPERIENCED ON RT ENGINE. TAKEOFF ABORTED. UPON SUBSEQENT TEAR DOWN WITH A PRATT 	& WHITNEY REPRESENTATIVE PRESENT, IT HAS BEEN DETERMINED THAT A COMPRESSOR TURBINE BLADE SEPARATED AND DAMAGED COMPONENT	S DOWNSTREAM IN ENGINE.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P40EA	 
2001092000059	20010920	00059	CE  	2001	9	20	CA010813009      	1	20010630	G	5310	50430043867	DOOR FRAME      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			21552								(CAN) DOOR FRAME FORWARD 50-430043-867 CRACKED ON LOWER BAYONNET HOLE TO SCREW HOLE AND 1/2" BEYOND. OTHER SCREW HOLE TO	 BAYONNET HOLE. DOOR FRAME AFT 50-430043-865 CRACKED ON UPPER BAYONNET HOLE TO SCREW HOLE ONE ONLY.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	5	C	STC	 
2001092000061	20010920	00061	EU  	2001	9	20	CA010813011      	1	20010716	G	2750	ONL3120146X77	BOLT            		Z4243430000 	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					FLAP CONTROL	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3046 								(CAN) DURING A 100/500 HOUR INSPECTION THE LT FLAP BELLCRANK BOLT WAS FOUND TO BE BENT. THE BOLT WAS REPLACED WITH A NEW	 ONE. IT IS SUSPECTED THAT A STUDENT PILOT EXTENDED THE FLAPS ABOVE THE MAXIMUM SPEED ALLOWED FOR FLAP EXTENSION. THE MA	INTENANCE SCHEDULE ALREADY HAS AN ADDITIONAL INSPECTION ON THE FLAP BOLTS AND THE INSTRUCTORS AND STUDENTS WERE AGAIN RE	MINDED OF THE PROPER PROCEDURE USING THE FLAPS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2001092000068	20010920	00068	NM  	2001	9	20	CA010813012      	1	20010721	G	5310		DOOR FRAME      			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FWD FRAME OF AFT CARGO DOOR CRACKED AT BS1057, STR.24. CRACK MEASURED 1.5 INCHES.						2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001092000073	20010920	00073	CE  	2001	9	20	CA010813013      	1	20010720	G	2800	57181061	HARNESS         			CESSNA	441   	441         	2076020	CE  										FUEL SYSTEM	CHAFED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING INVESTIGATION OF INTERMITTENT BOOST PUMP FOUND CHAFED SPOT ON WIRE HARNESS INSIDE FUEL TANK. MAGNIFIED VIEW	 SHOWED EVIDENCE OF ELECTRICAL CONTACT BETWEEN WIRE AND STRUCTURE OF FUEL TANK.					1	L	7	2 	3T			RT	A28CE   					 
2001092000075	20010920	00075	SO  	2001	9	20	CA010813014      	1	20010720	G	3244	10320400	BOLT            	CLEVELAND   	40106       	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			795  	795  							(CAN) ON AN EVENT NR 2 INSPECTION IT WAS FOUND THAT THE RIGHT MAIN WHEEL P/N 40-106 WAS MISSING 1 THROUGH BOLT ((P/N 103	.20400 (AN5-35A))AND ANOTHER BESIDE THE MISSING BOLT BROKEN IN TWO AND PROTRUDING FORWARD THE BRAKE CALIPER. THE ROTATIO	N OF THE WHEEL CAUSED THE HEAD OF THE BOLT TO CAUSE CONSIDERABLE DAMAGE TO THE TORQUE PLATE. (P/N 075-12800).				1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2001092000076	20010920	00076		2001	9	20	CA010813016      	4	20010715	G	3420	1242102011	INDICATOR       			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AHRU	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			462  			1545					(CAN) DURING STRAIGHT AND LEVEL FLIGHT THE PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE CIRCUIT BREAKERS, AND TH	E UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092000079	20010920	00079		2001	9	20	CA010813017      	4	20010724	G	3420	1242102011	INDICATOR       			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AHRU	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			476  								(CAN) DURING STRAIGHT AND LEVEL FLIGHT THE CO-PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE AVIONICS POWER, AND T	HE UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092000081	20010920	00081	EU  	2001	9	20	CA010813018      	1	20010724	G	2434	9789601090	BRUSH HOLDER    	BOSCH       	5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			102  			100318					(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN 	EXCESSIVELY, AND HAS BEEN REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092000086	20010920	00086	SW  	2001	9	20	CA010813021      	1	20010725	G	2810	71493	STRUCTURE       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FUEL CELL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) - FUEL TANK CRACKING. - POSSIBLY DUE TO TOO LIGHT GUAGE OF MATERIAL & NO INTERNAL BAFFLES INTANK. CRACKS USUALLY O	CCUR AT END OF STIFFENER INDENTS. - WE AVERAGE 2-3 FUEL TANK FAILURE DUE TO CRACKING PER FLYING SEASON.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001092000087	20010920	00087	SW  	2001	9	20	CA010813022      	1	20010801	G	2823	110660	SHUTOFF VALVE   			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FUEL SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				Y			ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA											(CAN) - THREADED COLLAR THAT SECURES VALVE SHAFT IN BODY CAME LOOSE AND DETACHED ITSELF FROM SHUTOFF BALL INSIDE VALVE. 	FOR SOME REASON THE VALVE WAS OR WENT INTO THE CLOSED POSITION & STARVED THE ENGINE FOR FUEL DURING TAXI OUT FOR DEPARTU	RE. - THERE IS NOTHING PROVIDED TO SECURE THE COLLAR SO THAT IT WILL NOT LOOSEN.				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2001092000091	20010920	00091	CE  	2001	9	20	CA010813024      	1	20010809	G	3220	030A39313	BOLT            			MTSBSI	MU2   	MU2B36A     	5780413	CE  	GARRTT	TPE331	TPE3315     	01514	WP  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE NOSE LANDING GEAR DRAG STRUT ATTACH BOLT WAS FOUND CRACKED AT SCHEDULED NDT INSPECTION OF BOLT. THIS BOLT HAD 	BEEN MAGNETIC PARTICAL INSPECTED EVERY 2000 HOURS.					1	H	7	2 	3T	4	T	 	A10SW   	E4WE				 
2001092000093	20010920	00093	NM  	2001	9	20	CA010814003      	1	20010726	G	2900	TC125UK00ZY1	INDICATOR       			BOEING	767   	767333      	       	NM  	PWA   	4060  	PW4060      	52119	NE  					HYD PRESSURE	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) ENROUTE FROM TEL AVIV TO TORONTO AFTER THE LT SYSTEM WAS TOPPED OFF (IN TLV) LOSS OF HYDRAULIC FLUID OF THE L/H SY	STEM, THE A/C RE-ROUTED AND ASK FOR AN EMERGENCY LANDING. A/C LANDED SAFELY WITHOUT FURTHER INCIDENT. FOUND TO BE A LEAK	 AT THE DIFFERENTIAL INDICATOR PRESSURE DRAIN CASE MODULE FILTER (AROUND THE POP OUT). REPLACED THE PRESSURE CASE DRAIN 	FILTER MODULE DIFFERENTIAL PRESSURE INDICATOR.			2	L	7	2 	4F	4	F	RT	A1NM    	E24NE				 
2001092000094	20010920	00094	EU  	2001	9	20	CA010814005      	1	20010718	G	2740	47147400	ACTUATOR        			AIRBUS	A340  	A340313     	       	EU  	CFMINT	CFM56 	CFM565C4    	13802	NE  					HORIZONTAL STAB	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA											(CAN) ON MAINTENANCE CHECK FOUND TRIM HORIZONTAL STABILIZER ACTUATOR BALLNUT TRANSFER TUBE DISCONNECTED FROM BALLNUT. RE	PLACED TRIM HORIZONTAL STABILIZER ACTUATOR AND SYSTEM TESTED.					2	L	7	4 	4F	4	F	RT	A197    	E37NE				 
2001092000096	20010920	00096	EU  	2001	9	20	CA010814006      	1	20010718	G	3244		TIRE            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					MLG	SEPARATED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) #3 MAIN WHEEL TIRE CAP SEPARATION ON TAKEOFF. AIR TURN BACK TO AIRPORT. AIRCRAFT SUSTAINED DAMAGE TO #2 ENGINE FAN	 BLADES, ENGINE INTAKE ACOUSTIC PANELS, R/H INBOARD TRAILING EDGE FLAP. ONE LINE OF THE YELLOW HYDRAULIC SYSTEM BROKE IN	 AREA OF R/H MAIN LANDING GEAR AREA. THE R/H HORIZONTAL STABILIZER DENTED AND HOLE ON THE UPPER SURFACE OF THE R/H WING 	ABOVE THE MAIN LANDING GEAR (R/H).REPAIRS WILL BE ACCOMPLISHED AFTER ENGINEERING EVALUATION.FINAL REEPORT FOR FIXES WILL	 BE PRODUCED AT A LATER DATE.		2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001082800072	20010828	00072	CE  	2001	8	28	CA010814020      	1	20010615	G	2131	13035616	CONTROLLER      	            	13035616    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  	 		            		INTERNAL	                	W			    	B	G	 	 	EMER. DESCENT           	O2 MASK DEPLOYED        			W	 	 	INADEQUATE Q C            			DE	DESCENT        	1			CA		 		207  		79327					(CAN) PRESSURIZATION PROBLEMS OCCURRED SHORTLY AFTER TAKEOFF BACK TO OTTAWA (CONTROL). ON DESCENT THROUGH 23,000 FEET. C	REW EXPERIENCED RAPID DEPRESSURIZATION. MASKS WERE DONNED AND DESCENT ACCELERATED TO BELOW 10,000 FT. MAINTENANCE DETERM	INED THE CAUSE TO BE THE PRESSURIZATION CONTROLLER, CONTROLLER REPLACED. NO FURTHER ACTION REQUIRED.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001092000098	20010920	00098	CE  	2001	9	20	CA010814021      	1	20010807	G	2130	41EN496	SQUAT SWITCH    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN PRESSURE	WORN            	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			W			INADEQUATE Q C            			DE	DESCENT        	1			CA											(CAN) WHILE IN DESCENT FROM FL330, AND DESCENDING THROUGH 15,000 FT CABIN ALTITUDE STARTED TO INCREASE RAPIDLY. AIRCRAFT	 DIVERTED TO CYQM FOR MAINTENANCE. WHILE AT 10,000 FT CABIN ALTITUDE RECOVERED. WHEN THROTTLES REDUCED FROM 88  TO 70 PE	RCENT N1, CABIN PRESSURIZATION WAS LOST AGAIN. MAINTENANCE DETERMINED THAT THE L/H SQUAT SWITCH WAS AT FAULT UNIT REPLAC	ED, NO FURTHER ACTION.			1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001092000100	20010920	00100	CE  	2001	9	20	CA010814022      	1	20010802	G	2710	0510105217	CONTROL CABLE   	CESSNA      		CESSNA	172   	172I        	2072426	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C172	1C172MTM    	GL  	AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT DAMAGE ON LANDING AT PICTOU ISLAND. AIRCRAFT BEING STRIPPED FOR REPAIR WHEN THE CABLE, ABOVE WAS FOUND FR	AYED WHERE IT PASSES OVER THE PULLEY. LT SIDE TOP OF FUSELAGE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001092000104	20010920	00104	NM  	2001	9	20	CA010815001      	1	20010709	G	2433	2299	TRANSFORMER     			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					E&E BAY	FAULTY          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) AT CRUISE, A SNAPPING NOISE WAS HEARD. NR 1 TR CB POPPED. NR 1 MAIN FUEL TANK AFT FUEL BOOST PUMP CB POPPED ALONG 	WITH NUMEROUS C/P LIGHTS. #1 ENGINE OIL TEMP INDICATOR, CAPT'S AUX. PITOT STATIC AND NO SMOKING & FASTEN SEAT BELT SIGNS	 ALL NOT OPERATING. AS A PRECAUTION, ATC NOTIFIED FOR DIRECT DESTINATION IN CASE OF FURTHER ELECTICAL PROBLEMS. ON INITI	AL DESCENT, THE TR BUS SUDDENLY POWERED BACK UP AGAIN & AIRCRAFT LANDED WITHOUT INCIDENT #1 TR REPLACED IAW MM 24-21-0 A	ND CHECKED SERVICEABLE. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.		2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001092000105	20010920	00105	NM  	2001	9	20	CA010815002      	1	20010716	G	2822	2580003	PUMP            			BOEING	737   	737201      	1384454	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					FUEL BOOST	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) 1. EXTENGUISHED. NR 1 115 VAC TR BUS INOP. AIRCRAFT LANDED WITHOUT INCIDENT. MAIN FUEL TANK, AFT FUEL BOOST PUMP U	NSERVICEABLE. BOOST PUMP CHANGED IAW MM 28-22-41. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001092000106	20010920	00106	EU  	2001	9	20	CA010815003      	1	20010713	G	5240	A5247514700800	DOOR            			AIRBUS	310   	A310304     	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					LAV SERVICE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 1. DURING THE TURNAROUND IT WAS OBSERVED THAT THE MID LAV SERVICING PANEL DOOR WAS MISSING. 2. DMI 35881 WAS RAISE	D UNDER CDL 52-4. AIRCRAFRT RELEASED FOR FLIGHT.3. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT.					2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2001092000107	20010920	00107	EU  	2001	9	20	CA010815004      	1	20010720	G	5270		WARNING SYSTEM  			AIRBUS	310   	A310304     	       	EU  	GE    	CF6   	CF680C2B2   	30025	NE  					CARGO DOOR	FALSE ACTIVATION	W				O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) 1. DURING TAKEOFF, ECAM WARNING FOR BULK CARGO DOOR INDICATION. AIRCRAFT RETURNED TO GATE. SYSTEM CHECKED AND MEL 	52-7-0 APPLIED. AIRCRAFT RELEASED FOR FLIGHT. 2. NO PROBLEM DURING SUBSEQUENT FLIGHT. 3. UPON ARRIVAL TO HOME BASE, BULK	 CARGO DOOR INDICATION CHECKED SERVICEABLE AND MEL 52-7-0 CLEARED.4. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.				2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2001092000108	20010920	00108	EU  	2001	9	20	CA010815005      	1	20010620	G	3150	20662155	CONTROLLER      			AIRBUS	310   	A310304     	       	EU  	GE    	CF6   	CF680C2B2   	30025	NE  					ECAM	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA						1893					(CAN) 1. AT CRUISE, ECAM CONTROLLER SHOWED SIGNS OF BEING ERRATIC, FLASHING THEN TURNED BLACK. SMOKE STARTED FOR 10 SECO	NDS WITH ELECTRICAL SMELL. CB POPPED AND SMOKE STOPPED. NOT ENOUGH SMOKE TO DON O2 MASKS. 2. PHONE PATCH MADE TO DISPATC	H REGARDING PROBLEM. AIRCRAFT CONTINUED WITH FLIGHT WHILE MONITORING SITUATION. 3. ON ARRIVAL, #1 ECAM CONTROLLER REPLAC	ED AND CHECKED SERVICEABLE IAW MM 31-51-00. 4. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT.			2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2001092000110	20010920	00110	CE  	2001	9	20	CA010815012      	1	20010801	G	5540	1156400006	HINGE           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPPER RUDDER HINGE BRACKET RIVETS LOOSE DUE TO FLIGHT CONTROL FLUTTER.SCREWS WERE LOOSE IN THE CENTER HINGE ALSO. 	PC/TSO/TSN ARE UNKNOWN, NOT 0.0.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2001092000112	20010920	00112	CE  	2001	9	20	CA010817002      	1	20010814	G	5710	10140243S	BOLT            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11181	11181							(CAN) BOLT FOUND WITH MECHANICAL THREAD DAMAGE UPON INSPECTION						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2001092000113	20010920	00113	SO  	2001	9	20	CA010817003      	1	20010626	G	3260		INDICATOR       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MLG	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) WHILE LANDING THE LT WHEEL LIGHT DID NOT COME ON. AFTER VERIFICATION WITH THE MIRABLE TOWER WHO CONFIRMED 3 WHEELS	 OUT. THE AIRCRAFT RETURNED TO ST-HUBERT WITH THE LANDING GEAR DOWN. THE LIGHT CAME ON WHILE ONROUTE TO ST-HUBERT. 2 ELE	CTRICAL TERMINALS WERE REPLACED AND THE GROUND WAS CLEANED FOLLOWED BY MANY RETRACTIONS AND THE SYSTEM WAS CHECKED SERVI	CEABLE.			1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2001092000114	20010920	00114	NE  	2001	9	20	CA010820009      	2	20010619	G	8500	114651	CYLINDER HEAD   			CVAC  	PBY5  	PBY5A       	2421208	WP  	PWA   	R1830 	R183092     	52020	NE  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CL	CLIMB          	1			CA				248  							(CAN) NO. 11 CYLINDER HEAD CRACKED CYLINDER REPLACED. A/C RETURNED TO SERVICE. ON A TRAINING FLIGHT FLIGHT, ONE WATER PI	CK UP WAS CARRIED OUT, LOAD WAS DROPPED ON TARGET, WHILE GOING BACK FOR A SECOND LOAD, THE MAP SHOWED A SUBSTANTIAL SPEE	D. VISUAL CHECKS OF THE ENGINES WAS DONE AND A SUBSTANTAIL OIL LEAK ON THE RIGHT ENGINE WAS FOUND. ENGINE WAS SHUT DOWN,	 SOON AS POSSIBLE.			2	H	7	2 	4R	4	R	 	2548    	5E4				 
2001092000115	20010920	00115	CE  	2001	9	20	CA010820010      	1	20010807	G	2841	774000419	TRANSMITTER     			CESSNA	150   	150J        	2071820	CE  										FUEL QTY	STUCK           	W				D				RETURN TO BLOCK         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			116  								(CAN) TRANSMITTER LEVER PIVOT HAS BECOME SOMEWHAT STIFF, RESULTING IN INACCURATE FUEL LEVEL INDICATIONS. PART WAS REPLAC	ED. THIS PART IS PART OF CESSNA SERVICE KIT SK-150-65. THE KIT WAS MADE NECESSARY BY THE UNAVAILABILITY OF THE ORIGINAL 	STEWART- WARNER SYSTEM PARTS. THIS UNIT IS MADE BY ROCHESTER. HOLDING PARTS FOR 21 DAYS. AFTER WHICH IT WILL BE RETURNED	 FOR WARRANTY.			1	H	7	1 	3O			 	3A19    					 
2001092000116	20010920	00116	SO  	2001	9	20	CA010820012      	1	20010726	G	3297		WIRE            			PIPER 	PA44  	PA44180     	7104402	SO  										MLG	BROKEN          	W				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA											(CAN) AS PILOT SELECTED GEAR DOWN ON APPROACH "GEAR WARNING" CCT BREAKER TRIPPED&UNSAFE LIGHT DID NOT ILLUMINATE DURING 	GEAR EXTENSION. PILOT NOTICED THAT HE HAD 3 GREEN LIGHTS INDICATING GEAR DOWN&LOCKED. AIRCRAFT LANDED W/O INCID.. MANTEN	ANCE FOUND L.H. DOWNLOCK SWITCH WITH WIRES PULLED OUT OF SWITCH BODY. DOWNLOCK SWITCHES TURN OFF GEAR WARNING SYS WHEN A	LL 3 SWITCHES ARE ENGAGED. PULLED WIRES WERE SHORTING OUT&WHEN TH E GEAR SELECTED DOWN BREAKER WOULD TRIP.WHEN LDG GEAR 	RETRACTS WIRES RUB ON GEAR LEG,&IF SWITCH IS INST W/O ANY SLACK IN WIRES THEY CAN BE PULLED OUT OF SWITCH. WIRES WERE WR	APPED WITH SPIRAL WRAPAND SWITCH INST WITH ENOUGH SLACK IN THE	1	L	7	2 	3O			 	A19S0   					 
2001092000117	20010920	00117	SO  	2001	9	20	CA010820014      	1	20010727	G	2740	4296102	SCREW           	PIPER       	4269200     	PIPER 	PA18  	PA18        	7101802	SO  	LYC   	O320  	O320A2B     	41508	EA  					STABILIZER	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			2725 								(CAN) STABILIZER TRIM FOUND NOT WORKING ON PILOT'S WALK AROUND. DISASSEMBLE AND FOUND SCREW BROKEN IN HALF, JAMMED IN TH	E YOKE HOUSING.					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2001092000118	20010920	00118	EU  	2001	9	20	CA010821003      	1	20010807	G	3010	3D248526	TIMER           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	AIRFOIL DEICER	MALFUNCTIONED   	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA				471  							(CAN) ON THE SCHEDULED AIRFOIL DEICER SYSTEM INSPECTION, IT WAS DISCOVERED THAT THE NORMAL INFLATION SEQUENCE WOULD WORK	 PROPERLY ONLY 1 TIME OUT OF THREE. IT WAS DETERMINED THAT THE TIMER WAS FUNCTIONING IN AN INTERMITTENT MANNER. DEICER C	AUTION LIGHT WOULD COME ON INDICATING SEQUENCE MALFUNCTION. THE TIMER WAS REPLACED WITH A SERVICEABLE UNIT.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092000119	20010920	00119	CE  	2001	9	20	CA010821005      	1	20010811	G	2434	7565T1	ALTERNATOR      			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					ENGINE	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA			446  	151  							(CAN) ALTERNATOR WENT OFF LINE. UPON REMOVAL OF THE ALTERNATOR WAS NOTICED THAT THE SPLINE GEAR WAS SHEARED. THE DRIVE S	HAFT WAS ALSO SHEARED IN THE THREADED PORTION, JUST BELOW THE CASTLE NUT. THE CASTLE NUT WAS STILL INTACT ON THE TIP OF 	THE THREADED SHAFT WITH THE COTTER PIN INTACT. THIS PARTICULAR UNIT HAS BEEN SENT TO DND TEST FACILITIES TO DETERMINE TH	E EXACT CAUSE OF FAILURE.			1	H	7	1 	3O	3	O	 	5A5     	E269				 
2001092000120	20010920	00120	CE  	2001	9	20	CA010821010      	1	20010808	G	3221	NA5130514DH	BOLT            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	NLG	BROKEN          	W				E	C			ENGINE SHUTDOWN         	ABORTED TAKEOFF         			D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA			4347 								(CAN) ON TAKE OFF PILOT BEARD A BANG. THIS WAS FOLLOWED BY A NOTICEABLE LOSS OF NOSE WHEEL CONTROL (STREERING). TAKE OFF	 WAS ABORTED, INSPECTION REVEALED ONE OF THE NOSE GEAR FORK ATTACH BOLTS WAS BROKEN.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001092000121	20010920	00121	CE  	2001	9	20	CA010821011      	1	20010813	G	2720	0411307	ARM             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2965 								(CAN) DURING A 200 HOUR ANNUAL INSPECTION, THE PILOT R/H RUDDER PEDAL ARM FOUND LOOSE. THE ARM WAS CRACKED IN TWO PLACES	: FROM EACH OF THE ATTACH BOLT HOLES TO THE BOTTOM OF THE TUBE.					1	H	7	1 	3O	3	O	 	A4CE    	E3SO				 
2001092100008	20010921	00008	WP  	2001	9	21	CA010822013      	2	20010730	G	7250	TPE33110UG514H	ENGINE          			BAG   	JETSTM	JETSTM3101  	1500215	EU  	GARRTT	TPE331	TPE33110UG  	01514	WP  	ROTOL	R333	R333482F12  	GL  	NACELLE	DAMAGED         	W				E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			LD	LANDING        	1			CA				3319 							(CAN) ON LANDING IN FORT MCMURRAY ON THE MORNING OF 30 JULY, 01 AN UNCOMMANDED ENGINE SHUTDOWN OCCURRED. THE PILOT REPOR	TED THAT THE ENGINE SHUT DOWN WHEN THE WHEEL TOUCHED THE GROUND, OR SHORTLY THEREAFTER. HE PULLED THE STOP FEATHER LEVER	 FOR THAT ENGINE AND CONTINUED THE LANDING. ON INVESTIGATION OF THE ENGINE, WE COULD NOT FIND ANYTHING WRONG EXTERNALLY,	 BUT THE ENGINE WOULD NOT START. WE REMOVED THE ENGINE FROM THE AIRCRAFT AND FOUND EVIDENCE THAT INTERNAL DAMAGE HAD OCC	URRED. THE THIRD STAGE APPEARS TO HAVE BEEN RUBBING.		2	L	7	2 	4T	4	T	RT	A21EU   	E4WE	6	C	P61GL	 
2001092100011	20010921	00011	WP  	2001	9	21	CA010823003      	1	20010727	G	2120	LS11088B614	DUCT            			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					CABIN AIR	SPLIT           	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) AIRCRAFT REJECTED TAKE OFF AT 80 KTS DUE A LOUD NOISE IN COCKPIT. FOUND THE #2 ZONE TRIP MANIFOLD DUCT HOSE COUPLI	NG SPLIT. THE COUPLING WAS REPAIRED AS PER MAINTENANCE MANUAL AND SUBSEQUENTELY THE HOSE COUPLING WAS REPLACED AT THE NI	GHT LAYOVER.				2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2001092100016	20010921	00016	GL  	2001	9	21	CA010823015      	3	20010815	G	6110	A4643	SPACER          			TMPSON	NAVION	NAVIONA     	6150104	SW  						MCAULY	2A34C	D2A34C98    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				43   							(CAN) PART CORRODED AND INSTALLED UPSIDE DOWN.						1	L	7	1 	3O			 	A782    		5	C	P3EA	 
2001092100017	20010921	00017	SO  	2001	9	21	CA010827004      	2	20010809	G	7414	M3820	DISTRIBUTOR BLK 	SLICK       	6310        	CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  	MCAULY	2AF34C	D2AF34C*    	GL  	MAGNETO	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			106  			01012755					(CAN) BOTH MAGNETOS WERE REMOVED IN ERROR FOR 500 HR INSP ONLY LH WAS DUE WHEN RH MAGNETO WAS DISASSEMBLIED BY LEGGAT AV	IATION. THE BEARING BAR P/N M3004 WAS BURNED THROUGH AT HIGH TENSION BRUSH AREA OF DISTRIBUTER BLOCK NO PROBLEM WAS EVER	 FOUND ON MAGNETO CHECK.				1	H	7	1 	3O	3	O	 	A4CE    	E8CE	5	C	P5EA	 
2001092100018	20010921	00018	EU  	2001	9	21	CA010827008      	1	20010812	G	7930	1D1	CHIP DETECTOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	ACTIVATED       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ENGINE CHIP LIGHT IN FLIGHT. CHIPS FOUND ON UPPER ELECTRICAL CHIP PLUG, MO5 AND ENGINE OIL TANK PLUGS. ENGINE REMO	VED FOR EVALUATION.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001092100019	20010921	00019	SW  	2001	9	21	CA010827009      	1	20010814	G	6410		BLADE           	BELL        	206011810013	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TAIL ROTOR	TORN            	W				A				UNSCHED LANDING         				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		NR	NOT REPORTED   	1			CA			2585 			MOT3141					(CAN) WHILE IN FLIGHT THE T/R COULING FILLER COVER DEPARTED AND STRUCK THE TAIL ROTOR BLADE CAUSING A 2 CM TEAR OR HOLE 	IN ONE BLADE ABOUT 2/3 OF THE WAY DOWN. JUST AFT OF THE LEADING EDGE. THE A/C LANDED SAFELY. NO OTHER DAMAGES WAS FOUND.	 NEW COVER TO T/R ASSY INSTALLED A/C RETURNED TO SERVICE.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001092100025	20010921	00025	NE  	2001	9	21	CA010828021      	1	20010827	G	6510	76361040078101	COUPLER         	SKRSKY      	763610520104	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			171  								(CAN) DURING INSP OF TAIL ROTOR DRIVESHAFT ASSY IT NOTED THAT FLEX COUPLING BETWEEN INTERMEDIATE GEARBOX & NR 5 TAIL ROT	OR DRIVESHAFT HAD CRACKED LAMINATE. COUPLING REMOVED & INSP. IT HAD ONE CRACKED LAMINATE (OUTTER LAMINATE OF PACK) & CRA	CK LOCATED BETWEEN 2 OF FLANGE ATTACHEMNT BOLT HOLES. CRACK RUNS COMPLETLELY THROUGH LAMINATE IN STRAIGHT LINE FROM OUTT	ER EDGE TO INNER EDGE. IS NO APPARENT SURFACE DEFECT THAT WOULD APPEAR SURFACE DEFECT THAT WOULD APPEAR TO BE CAUSE IF C	RACK. PART HAS BEEN SENT TO SIKORSKY A/C PRODUCT SAFETY DEPARTMENT FOR EVALUATION. SIKORSKY A/C FIELD SERVICE REPRESENTA	TIVE STATED THAT HAS BEEN PREVIOUS CASES OF THESE COUPLINGS CRACKING.	1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001092100033	20010921	00033	CE  	2001	9	21	CA010828023      	1	20010814	G	2730		TORQUE TUBE     	BEECH       	1156100103  	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NA					(CAN) UPON PERFORMING THE SB2145 ON THE COMPONENT.FIRST INSPECTION FROM FACTORY, WE DO IT UPON ARRIVAL FOR QUALITY REASO	NS.  A CRACK WAS FOUND DURING THE LPI PROCESS.THE CRACK TRAVELS FROM INSIDE THE HOLE TO APROX. 4MM OUTSIDE THE HOLE RUNN	ING AXIAL ALONG THE TUBE.  TUBE WAS REJECTED.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2001092100035	20010921	00035	CE  	2001	9	21	CA010829009      	1	20010819	G	2810	052600750	FUEL TANK       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			4055 								(CAN) TANK WOULD ALWAYS POP OR OIL CAN AS IT WAS FILLED, LEAK WOULD ONLY OCCUR WHEN TANK WAS FUELLED RIGHT TO THE TOP. I	T IS BELIEVED THAT THE REPETITIVE OIL CANNING OF THE TANK CAUSED A FATIQUE CRACK TO START. THE TANK WAS REPAIRED AND THE	 UPPER SURFACE WAS CONTOURED BACK TO ITS ORIGINAL SHAPE SO IT WILL NOT OIL CAN ANY LONGER.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001092100047	20010921	00047	CE  	2001	9	21	CA010830007      	1	20010823	G	2435	23079004	STARTER GEN     			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT ENGINE	FAILED          	W				E	H			ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS			H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA				84   							(CAN) PILOT WAS TAXING WHEN  HE LOST TOTAL POWER TO NO. 2 BUS. INVESTIGATION FOUND THAT THE R/H GENERATOR COOLING FAN BL	ADES TOTALLY CRACKED OFF AND FLEW INTO THE GENERATOR WINDINGS, DESTROYING ALL WORKING CAPABLITY OF STARTER GENERATOR. TH	IS CAUSED A GCU FAILURE AND A NO. 2 BUS CURRENT LIMITER TO BLOW AS WELL.				1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA	 
2001092100048	20010921	00048	EU  	2001	9	21	CA010830009      	1	20010823	G	2160	9599020135	CONTROL VALVE   			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TEMP CONTROL	SEIZED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			3783 	3783 							(CAN) AFTER STARTUP THE PILOT SELECTED COOL SETTING ON THE ENVIRONMENTAL CONTROL SYSTEM (ECS). THE SYSTEM BLEW COOL AIR 	FOR APPROX 25 SECONDS, THEN BLEW HOT AIR. AFTER APPROX 1 MINUTE THE SYSTEM SHUTDOWN AND AN AMBER LIGHT INDICATING ECS FA	ILURE APPEARED ON THE CAWS DISPLAY. THE SYSTEM AND DETERMINED THAT THE TEMP CONTROL VALVE WAS NOT FUNCTIONING. AFTER REP	LACEMENT OF THE PART AND RUNUP, THE SYSTEM WORKED NORMALLY. AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100049	20010921	00049	EU  	2001	9	21	CA010830017      	1	20010713	G	3246	AHA1489	WHEEL           			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3234 	699  							(CAN) THE WHEEL HAD BEEN REMOVED DUE TO THE TIRE BEING WORN TO LIMITS. DURING THE CLEANING PROCESS, TWO CRACKS WERE DISC	OVERED VISUALLY. THEY RAN FROM THE LIGHTENING HOLES TO UNDER THE WHEEL BEARING OUTTER RACE. PICTURES ARE AVAILABLE. THE 	WHEEL HALF HAD BEEN N.D.T. INSPECTED AT LAST TIRE REPLACEMENT MAR 28/01.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE				 
2001092100055	20010921	00055	GL  	2001	9	21	CA010830020      	2	20010828	G	7313	2306045	NOZZLE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	WARPED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				535  							(CAN) THERE WERE INTERMITTENT START DELAYS ON A/C AT VARIOUS TIMES DURING OPAL SORTIES. IT DETERMINED THAT POOR FITTING 	1ST STAGE NOZZLE CAUSED START DELAY. TURBINE REPD WITH INST OF NEW 1ST STAGE NOZZLE P/N  23062753 S/N KD258711; NEW NOZZ	LE SHIELD P/N 23073533&2 NEW POSING PLUGS P/N 23009573. NOZZLE TBO 535.6 HRS, NOZZLE SHIELD TBO U/K 535.6 HRS SINCE INSP	. POS PLUG TSN U/K TBO U/K TIME SINCE INSP 535.6 HRS. FINDINGS PRIOR TO THE REPLACED OF AFOREMENTIONED PARTS; 1ST STAGE 	NOZZLE P/N 23060450, NOZZLE SHIELD P/N 6890040 APPEARED TO BE WARPED WHEN PLACED ON LEVELING PLATE THAT MAY HAVE CONTRIB	UTED TO POOR FIT OF BOTH ENGINE COMPONENTS. ONE ADDITIONAL OBSERVATIO N MODS TO LOWER POSING PL	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001092100059	20010921	00059	SO  	2001	9	21	CA010831004      	1	20010821	G	7120	3743701	FASTENER        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	FITTING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 1. FITTING, ASSY OUTBOARD LOWER ENGINE MOUNT. ONE MISSING FASTENER ON OUTBOARD LOWER SIDE FITTING (P/N: 37437-01).	2. FITTING, ASSY INBOARD LOWER ENGINE MOUNT. ONE MISSING FASTENER ON INBOARD LOWER SIDE OF FITTING (P/N: 37442-01)					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA	 
2001092100062	20010921	00062	EA  	2001	9	21	CA010831005      	2	20010815	G	7210		GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	DAMAGED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) ON RAMP AFTER M/R HEAD CHANGE MASTER CAUTION LIGHT ACTIVATED&ENGINE CHIP LIGHT ACTIVATED. ENGINEER FOUND ON REAR C	HIP DETECTOR FOR ENGINE MINOR FUZZ. ENGINER CLEANED CHIP DETECTOR & REINSTALLED ENGINEER INSPECTED FILTERS & FOUND NO DI	SCREPANCY. A/C GROUND RUN&NO CHIP LIGHTS OCCURRED. AFTER TRACK & BALANCE. COUPLE HRS LATER ANOTHER ENGINE CHIP LIGHT. TI	ME MASSIVE AMOUNTS OF METAL. A/C SHUTDOWN. METAL GENERATION MAYBE COMING FROM NR 2 POWER SECTION OR COMBINING GEARBOX. O	NCE POWER SECTION REMVD BEARING CAGE OF NR 5 DUPLEX BEARING IN TRANSITION AREA OF POWER SECTION&COMBINING GEARBOX. COMBI	NING GEARBOX REPLACED. TSO OF COMBINING GEARBOX 2126 HRS.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001092100065	20010921	00065	CE  	2001	9	21	CA010831006      	1	20010817	G	2820		TUBE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O550  	IO550F      	17042	SO  	MCAULY	D3A34	D3A34C402   	GL  	FUEL SYSTEM	LEAKING         	W				L				ABORTED APPROACH        				K	R	J	FLUID LOSS                	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) NR 5 CYLINDER FUEL DISTRIBUTION TUBE RUPTURED DURING CRUISE FLIGHT. TUBE BREAK IS AT THE CONNECTION TO FUEL DISTRI	BUTOR VALVE. CONNECTION POINT A CYLINDER REMAINED INTACT. FAILURE OCCURRED AT FLANGE END WHERE TUBE FLARE END IS BRAZED 	TO TUBE ASSY. NO POSITIVE CAUSE IDENTIFIED. VIBRATION AND CYCLES MAY HAVE CONTRIBUTED TO FAILURE. POSSIBLE FLAW WITH BRA	ZING OF TUBE ASSY.			1	H	7	1 	3O	3	O	 	A4CE    	E3SO	5	C	P47GL	 
2001092100068	20010921	00068	CE  	2001	9	21	CA010831007      	1	20010803	G	7120	NAS148A94	BOLT            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ENGINE MOUNT	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			3800 								(CAN) ON ENGINE REMOVAL, MAINTENACE FOUND ENGINE MOUNT BOLT PART NO. NAS 148A94 (S3461-64) AT LEFT, LOWER ENGINE MOUNT B	RACKET. (ITEM 27)- THREADBOUND DUE TO WASHER PART NO. MS20002C8 NOT INSTALLED AT FACTORY ASSEMBLY. MAINTENACE ALSO FOUND	 INCORRECT WASHERS PART NO. AN960-616L INSTALLED ON ENGINE MOUNT BOLTS AT RIGHT LOWER BRACKET (ITEM 28) AND TOP CENTER B	RACKET (ITEM 26)- INSTEAD OF WASHERS PART NO. MS20002C8. THE THREE REMAINING CESSNA 208B AIRCRAFT IN THE FLEET WERE INSP	ECTED FOR THE SAME CONDITION WITH NO DISCREPANCIES NOTED.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001091700030	20010917	00030	WP  	2001	9	17	CA010831010      	1	20010822	G	6210	369D21100523	MAIN ROTOR      	HUGHES      	369D21200503	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  	 		            		LWR SKIN ROOT	CRACKED         	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 	3340 			2544					(CAN) 1 1/2"- 2" CHORDWISE CRACKS IN LOWER ROOT DOUBLER ADJACENT TO OUTBOARD END OF ROOT END FITTING. TWO BLADES FROM SA	ME SET WITH SIMILAR CRACKS S/N'S 009999-K068,-K070. *TORQUE EVENTS CALCULATED BY TSNX20 (REF: BOEING SERVICE BULLETIN SB	 369D195R3)				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001092100074	20010921	00074	CE  	2001	9	21	CA010831012      	1	20010802	G	2434		BRUSHES         	CESSNA      	991059111   	CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	FAILED          	W				O				OTHER                   				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			CA			472  			A149997					(CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A 	INCORRECT INSTALLATION.					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001092100075	20010921	00075	CE  	2001	9	21	CA010831013      	1	20010816	G	2434	9910591111	BRUSHES         	CESSNA      	9910591111  	CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	BROKEN          	W				K				NONE                    				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		TX	TAXI/GRND HDL  	1			CA			445  			A150018					(CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A 	INCORRECT INSTALLATION					1	H	7	1 	3O	3	O	NT	3A12    	1E10				 
2001092100076	20010921	00076	EU  	2001	9	21	CA010831014      	1	20010824	G	5610	9598110108	WINDSHIELD      			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			132  								(CAN) ON TAKE-OFF AT FT ST. JOHN, CO-PILOTS WINDSHIELD SHATTERED JUST AT ROTATION, PILOT ABORTED TAKEOFF AND TAXIED BACK	 TO RAMP. WINDSHIELD WAS REPLACED 132 HRS PRIOR.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100077	20010921	00077	EU  	2001	9	21	CA010831016      	1	20010828	G	7712	5771112104	TUBE            			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GEARBOX OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PART TIME NOT KNOWN. METAL CLAMP ON LINE CHAFED THROUGH OIL LINE.TUBE WAS FOR TORQUE TRANSDUCER.  FIG 01, 77-10-00	 ITEM 10 MOST OF THESE LINES HAVE CLAMPS WITHOUT RUBBER INSERTS.  THEY ARE METAL ON METAL.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100079	20010921	00079	NE  	2001	9	21	CA010831018      	2	20010831	G	7314	RG9570R1M	COVER           			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FUEL PUMP	LOOSE           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2761 	2761 							(CAN) COVER SCREWS WERE FOUND WITH INSUFICIENT TORQUE AS PER FOCA AD HB 2001-500. COVER SCREWS WERE TORQUED TO SPECIFICA	TIONS AND SAFTIED AS PERSB28-009NO SIGNS OF FUEL LEAKAGE OR EXTRUDED GASKET MATERIAL WAS FOUND.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100080	20010921	00080	NE  	2001	9	21	CA010831019      	2	20010824	G	7314	RG9570R1	PUMP            			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1020 								(CAN) INSPECTION OF THE ENGINE DRIVEN FUEL PUMP AS PER PILATUS AWD HB2001-500 AND SB 28-009 REVEALED THAT FUEL PUMP WAS 	LEAKING AND EXTRUDED GASKET MATERIAL WAS FOUND. THE TORQUE OF THE SCREWS WAS CHECKED.  1/8TH TO 1/4 TURNS WERE NEEDED TO	 TORQUE THE SCREWS TO THE SPECIFIED TORQUE OF 23 IN LB TO 25 IN LB. THE PUMP WAS REPLACED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100082	20010921	00082	NM  	2001	9	21	CA010905008      	1	20010717	G	2540	214861	SLEEVE          			BOEING	747   	747475      	       	NM  	GE    	CF6   	CF680C2B6F  	30025	NE  					DUMP VALVE	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A/C 381 M FOUND DURING UNRELATED ROUTINE MAINT IN AREA. EVIDENCE OF FIRE DAMAGE CAUSED BY SHORTED LEAD AT WASTER T	ANK DUMP VALVE HEATER SLEEVE. FIRE TRACK WAS FOLLOWED FROM SOURCE FWD THROUGH LIGHTNING HOLE OF ADJACENT STRUCTURE, & UP	WARD ALONG FRAME TO STRINGER 3 FEET FROM AFT DUMP VALVE LOCATION. INSP OF STRUCTURE CARRIED OUT, NIL DEFECTS TO STRUCTUR	E FOUND. INSULATION BLANKETS REMVD & REPLD DUE TO BURN DAMAGE OF OUTER LAYER. AREA CLEANED OF DUST. AREA RPTECTED. A/C R	ELEASED FOR SERVICE. BOEING FIELD REP INFORMED. AIR CANADA ENGINEERING TO INVESTIGATE & LIASE WITH BOEING CUSTOMER REPS 	FOR SOLUTION & FURTHER INSP REQMTS. FLEET CAMPAIGN TO INSPECT AFFECTED AREA IS UNDER CONSIDERATION.	2	L	7	4 	4F	4	F	RT	A20WE   	E13NE				 
2001092100085	20010921	00085	NE  	2001	9	21	CA010906006      	2	20010902	G	7320	311989203	FUEL CONTROL    			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	INTERMITTENT    	W				C				ABORTED TAKEOFF         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		TO	TAKEOFF        	1			CA			2556 	2556 							(CAN) A/C IN QUESTION IN RED LAKE & ON ITS BACKTRACK.EVERYTHING INDICATING NORMAL.FLT IDLE ASKED FOR & WHEN LEVER SET FO	R FLT IDLE IT NOTICED GEN 1 LIGHT CAME ON. ENGINE IN PROCESS OF FLAME OUT & CONTINUED UNTIL STOPPED. MAINT CONTACTED & I	NSP ENGINE FROM FRONT TO BACK WITH ASSISTANCE OF PRAT REP. BOROSCOPE, CHIP DETECTOR INSP, RUNUPS, NOTHING VIABLE COULD B	E FOUND TO EXPLAIN EVENTS EXCEPT THAT IT WAS  FCU AS IT CNTLS FUEL. PRATT BACKED UP THINKING & FCU REPL. THE STARTER GEN	 REPLACED ALSO. ALL GROUND RUNS CHECKED WITHIN MFGS PARAMETERS.A/C FERRIED TO THUNDER BAY & ENGINE REPLACED FOR OTHER RE	ASONS.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092100103	20010921	00103	EU  	2001	9	21	CA010906017      	1	20010719	G	5530	5357500020000	BOLT            			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					VERTICAL STAB	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING H-CHECK AND ACCOMPLISHING AIRCRAFT MAINTENANCE MANUAL TASK 53-51-00-210-009 FOUND THREE BOLTS LOOSE AS WELL	 AS CORRODED NUT FOR THE TAIL CONE ATTACHMENT.BOLTS RETORQUED AND NUTS REPLACED.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001092100104	20010921	00104	NM  	2001	9	21	CA010906019      	1	20010729	G	8012	97910211	VALVE           			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D17      	52049	NE  					STARTER	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) TWO AIR TURN BACK DUE TO A #1 START VALVE OPEN LIGHT ILLUMINATED DURING FLIGHT. ACCOMPLISHED #1 ENGINE FAILURE SHU	TDOWN TWICE.AFTER THE FIRST INCIDENT, THE STARTER, START VALVE AND ACTUATOR PRESSURE SWITCH WERE CHANGED, & THE SECOND T	IME THE START VALVE & THE PRESSURE SWITCH WAS REPLACED. IT WAS DETERMINED THAT THE FIRST START VALVE WAS A ROGUE UNIT. T	HE FINAL FIX WAS THE REPLACEMENT OF THE STARTER VALVE.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001092100105	20010921	00105	NE  	2001	9	21	CA010906020      	2	20010807	G	7230	1211313010	ACTUATOR        			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				D	R		INFLIGHT SEPARATION       	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			CA											(CAN) COMPRESSOR STALL 25 MINUTES BEFORE LANDING IN TORONTO, AIRCRAFT DECLARED AN EMERGENCY LANDING, THE CREW RE-STARTED	 THE ENGINE AND LANDED SAFELY WITH NO INCIDENT. AIRCRAFT REMOVED FROM SERVICE FOR TROUBLESHOOTING AND RECTIFICATION.FOUN	D TO BE THE VARIABLE STATOR ACTUATOR AT FAULT.REPLACED THE VARIABLE STATOR ACTUATOR.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2001092100107	20010921	00107	NE  	2001	9	21	CA010907001      	1	20010826	G	6230		LINK            			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING A MAIN GEARBOX BUILDUP AND PRIOR TO INSTALLATION OF THE STATIONARY SCISSORS ASSEMBLY, THE ENGINEER NOTICED 	THE UPPER LINK OF STATIONARY SCISSORS WAS ASSEMBLED 180 DEGREES OUT OF POSITION. THE ENGINEER CORRECTED THIS CONDITION P	RIOR TO INSTALLING THE SCISSORS ASSEMBLY ON THE MAIN GEARBOX. UNCORRECTED, THIS WOULD LIMIT THE VERTICALMOVEMENT (DOWN) 	OF THE SWASHPLATE.			1	G	7	2 	3U			 	H1NE    					 
2001092100131	20010921	00131	WP  	2001	9	21	CA010907007      	1	20010823	G	6210	369A10045	PIN             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5295 								(CAN) WHILE CARRYING OUT HIS DAILY INSPECTION, THE PILOT NOTICED THE NUT LOOSE ON THE BLADE PIN UPON INSPECTION THE THRE	ADED PORTION OF THE BLADE PIN WAS SHEARED.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001092100134	20010921	00134	CE  	2001	9	21	CA010907010      	1	20010823	G	5313	05131324	STRINGER        			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1A175	1A175*      	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13201								(CAN) DURING ROUTINE MAINTENANCE INSPECTION, IT WAS DISCOVERED THAT THE RIGHT HAND ENGINE RAIL WAS CRACKED. P/N 0513132-	4 STRINGER ASSEMBLY IN FUSELAGE FRONT SECTION STRUCTURE ASSEMBLY WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P857	 
2001091700033	20010917	00033	CE  	2001	9	17	CA010907020      	1	20010719	G	5230	NAS561F824	ROLL PIN        	CESSNA      	208B        	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ROLL PIN	BENT            	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			CR	CRUISE         	1			CA		 	13231			208B0305					(CAN) IT APPEARS SOMEONE TRIED TO UNLATCH THE UPPER CARGO DOOR WITHOUT PUSHING (ITEM #41) RELEASE KNOB TO RELEASE THE IN	NER HANDLE FROM THE LOCK PLATE (ITEM #46) EXCESSIVE FORCE WAS APPLIED THUS DAMAGING MECHANISM (ROLL PIN ITEM #2), WITH T	HIS CONDITION, IF THE INNER HANDLE WAS POSITIONED IN THE LOCK PLATE THEN THE LOCK PINS WOULD BE RETRACTED ALLOWING THE D	OOR TO COME OPEN. DOOR WARNING SYSTEM CHECKED AFTER REPAIRS AND FUNCTIONED NORMALLY. PILOT REPORTED THAT DOOR WARNING LI	GHT CAME ON JUST PRIOR TO OPENING.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2001092100143	20010921	00143	EA  	2001	9	21	CA010910003      	2	20010822	G	7230	3013511	COMPRESSOR WHEEL			DHAV  	DHC6  	DHC6100     	       	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	FAILED          	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			3543 								(CAN) HOT START LACK OF POWER.HOT SECTION REMOVED FROM POWER OLANT. SERVICEABLE HOT SECTION INSTALLED AIRCRAFT RUN CARRI	ED OUT. FOUND SATISFACTORY. SHROUD P/N 3020259STATOR ASSY P/N 3018490					1	H	7	2 	3T	3	T	 	A9EA    	E4EA				 
2001092400012	20010924	00012	NM  	2001	9	24	CA010910007      	1	20010624	G	3220	141T991113	SPRING          			BOEING	767   	767233      	       	NM  	PWA   	JT9   	JT9D7R4D    	52054	NE  					SPIN BRAKE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON WALK AROUND IN YYZ, FOUND RIGHT HAND NOSE WHEEL SPIN BRAKE SPRING MISSING. INSTALLED SPIN BRAKE SPRING.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE				 
2001092100021	20010921	00021	NM  	2001	9	21	CA010910009      	1	20010810	G	8011	449188	SEAL            	PWA         	JT8D17A     	BOEING	737   	7372T7      	1384482	NM  	PWA   	JT8   	JT8D17A     	52049	NE  					STARTER	LEAKING         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA						702788					(CAN) NR 2 LOW OIL PRESSURE FLICKERING FOR THE LAST 4 MINUTES OF FLIGHT WITH THE PRESSURE GAUGE IN AND OUT OF CAUTION RA	NGE.  TEMPERATURE NORMAL, ENGINE OPERATED AT REDUCED THRUST AND SHUTDOWN AFTER LANDING.  FOUND TO BE THE STARTER DRIVE P	AD CARBON SEAL TO BE LEAKING (AROUND 200 ML/15 MINUTES).   REPLACED SEAL.				2	L	7	2 	4F	4	F	RT	A16WE   	E2EA				 
2001092400014	20010924	00014	SW  	2001	9	24	CA010911002      	1	20010910	G	6330	209040110015	STUD            	BELL        	212040001059	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TRANSMISSION	MISSING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA						ABW50227					(CAN) FOUND BOKEN OFF STUD ON THE LIFT LINK TRANSMISSION MOUNT. ON THE TRANSMISSION THE LEFT REAR STUD HAD BROKEN OFF. T	HEY FOUND THIS DEFECT WHILE CHANGING A SERVO.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001092400015	20010924	00015	SW  	2001	9	24	CA010912003      	1	20010819	G	5302	206031329103S	FITTING         			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ROUTINE INSPECTION UPPER LEFT TAIL ATTACH FITTING FOUND CRACKED.REPLACED AS PER BELL STRUCTURAL REPAIR MANUAL 6-21	4, BUT NUMEROUS REPORTS OF CRACKS IN THIS LH UPPER FITTING AREA OF TAILBOOM/FUSELAGE INTERFACE.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001092400017	20010924	00017	CE  	2001	9	24	CA010912007      	1	20010820	G	5310	50420013451	CROSSBEAM       			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LWR FWD SILL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2617 	2617 							(CAN) IT WAS FOUND THAT AN INDIVIDUAL HAD REMOVED MATERIAL FROM THE DOUBLER & CROSS-TIE IN AN EFFORT TO ELIMINATE CONTAC	T WITH THE EMERGENCY EXCAPE HATCH.CRACKS WERE FOUND PROPAGATING FROM THE SHARP CORNER OF THIS RADIUS. WE ALSO DISCOVERED	 DURING THE REMOVAL OF THIS PART, THAT IT WAS INSTALLED WITH A PRE LOAD DURING THE RIVETING PROCESS. I AM SURE THIS HELP	ED THE CRACKS TO FORM.NO REFERENCES OR DATA WAS FOUND TO SUPPORT THE WORK DONE, BUT IT CLEARLY DID NOT FOLLOW STANDARD P	RACTICES.		1	L	7	2 	3T	4	T	RT	3A20    	E4EA	6	C	P15EA	 
2001092400026	20010924	00026		2001	9	24	CA010912016      	4	20010912	G	3425		HARNESS         			PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	FLIGHT CONTROL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3197 	3197 							(CAN) WHILE MOVING THE ELEVATOR CONTROL, A SLIGHT "CATCH" COULD BE FELT.INVESTIGATION REVEALED THAT WHEN PULLED BACK, TH	E AILERON CROSSOVER TIE ROD P/N 941.93.43.415 ON THE CONTROL COLUMN, CAME INTO CONTACT WITH THE WIRING HARNESS ON THE BA	CK OF THE MULTI FUNCTION DISPLAY (MFD).  THE SCREWS HOLDING THE MFD CONNECTOR TO THE BACK OF THE MFD TRAY WERE ALSO PULL	ED OUT. THE WIRING HARNESS OF THE MFD WAS INSPECTED FOR CHAFFING AND REPOSITIONED AND FASTENED.  NEW SCREWS WERE INSTALL	ED TO HOLD THE MFD CONNECTOR TO THE TRAY.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092400027	20010924	00027	CE  	2001	9	24	CA010912017      	1	20010904	G	5342	04321671	STIFFENER       			CESSNA	150   	150J        	2071820	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C172	1C172TM     	GL  	STAB ATTACH	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4671 								(CAN) COMMON PROBLEM ON OLDER CESSNA 150 SERIES, MANUFACTURER HAS BEEN REPLACED THIS PART WITH A NEW IMPROVE PART P/N 04	32169-1 ALSO INCLUDING NEW IMPROVE BULKHEAD ASSY P/N 0412177-2.					1	H	7	1 	3O	3	O	 	3A19    	E274	5	N	P910	 
2001092400028	20010924	00028	WP  	2001	9	24	CA010912018      	1	20010905	G	6520	369D25400B	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			13075	426  							(CAN) DURING A HELICOPTER ENGINE PERFORMANCE CHECK AT 2000 FT CRUISE, THE TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED AND 	STAYED LIT. AFTER LANDING AT BASE, THERE WAS METAL FLAKES PRESENT ON CHIP DETECTOR. T/R GEARBOX WAS FLUSHED, CHIP DETECT	OR CLEANED, & RE-INSTALLED. AIRCRAFT WAS GROUND RUN FOR 10 MIN AND SHUTDOWN.T/R GEARBOX CHIP DETECTOR REMOVED AGAIN.META	L WAS FOUND ON DETECTOR - T/R GEARBOX REMOVED FROM AIRCRAFT.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001092400029	20010924	00029	SW  	2001	9	24	CA010913001      	1	20010904	G	6210		TRIM TAB        	BELL        	407015001117	BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					M/R BLADE	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			400  	400  		A348					(CAN) DURING SCHEDULED AIRFRAME PERIODIC INSP TRIM TAB ON PARTICULAR MAIN ROTOR BLADE FOUND TO HAVE SEVERE DEBONDING WHI	CH INITIALLY SHOWED UP AS CRACKS IN FILLER MATERIAL AROUND TRIM TAB EDGES. CLOSER INSP REVEALED SEVERE DEBONDING & COMPR	OMISE OF TRIM TAB ATTACHMENT SECURITY. MAIN ROTOR BLADE REPLACED WITH NEW FROM BELL HELICOPTER. MAIN ROTOR BLADE S/N A-3	48 HAD TOTAL TIME SINCE NEW OF 2052.5. IT HAD BEEN INSP & REPLACED AT BELL HELICOPTER AT TOTAL TIME SINCE NEW OF 1652.2 	AT WHICH TIME TRIM TAB REPLACED. (TIME SINCE REPAIR & TRIM TAB REPLACED 400.3). IT IS QUITE COMMON TO SEE MINOR CRACKING	 IN FILLER MATERIAL SURROUNDING TRIM TAB.	1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001092400030	20010924	00030	CE  	2001	9	24	CA010913004      	1	20010912	G	3243	99123057	VALVE           			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA				7984 							(CAN) FOLLOWING AN UNEVENTFUL LANDING AND WHILE TAXING AFTER THE LANDING ROLL OUT, THE CREW ENCOUNTERED A BRAKE FAILURE 	AND HAD TO APPLY THE EMERGENCY BRAKE IN ORDER TO STOP THE AIRCRAFT. MAINTENANCE TROUBLESHOOTING AND INSPECTION OF THE SY	STEM DETERMINED THAT THE POWER BRAKE -ANTI SKID VALVE ASSEMBLY HAD FAILED. THE VALVE ASSY WAS REPLACED AND ALL TESTS CON	DUCTED IN ACCORDANCE WITH THE MM AND THE AIRCRAFT RELEASED.			1	L	7	2 	4F	4	F	RT	A22CE   	E1NE				 
2001092400031	20010924	00031	CE  	2001	9	24	CA010914002      	1	20010824	G	5343	05411212	CASTING         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	REAR GEAR CUTOUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6293 								(CAN) SUPPORT CASTING HAD CRACK FROM RADIUS OF CUTOUT FOR GEAR REARWARD. 0541153 U-BOLT WAS ALSO BROKEN AND REPLACED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA	 
2001092400042	20010924	00042	EU  	2001	9	24	CA010914004      	1	20010910	G	2750	ONL312014	BOLT            		Z4243430000 	ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					FLAP BELLCRANK	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100/500 HOUR INSPECTION THE LT FLAP BELLCRANK BOLT (P/N ONL3120.146X77)WAS FOUND TO BE BENT. THE BOLT WAS	 REPLACED WITH A NEW ONE. IT IS SUSPECTED THAT A STUDENT PILOT EXTENDED THE FLAPS ABOVE THE MAXIMUM SPEED ALLOWED FOR FL	AP EXTENSION. THE MAINTENANCE SCHEDULE ALREADY HAS AN ADDITIONAL INSPECTION ON THE FLAP BOLTS AND THE INSTRUCTORS AND ST	UDENTS WERE AGAIN REMINDED OF THE PROPER PROCEDURE USING THE FLAPS.			1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2001092400059	20010924	00059	EU  	2001	9	24	CA010917001      	1	20010913	G	2434	HEDCR132200	BRUSHES         	BOSCH       	5243212158  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			3296 	3296 							(CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON CAWS PANEL. EIS INDICATED THAT NR 2 GENERATOR HAD COME OFF LINE.TH	E PILOT THEN RE-SELECTED GENERATOR SWITCH TO ON POS,&HAD SAME SEQUENCE OF EVENTS OCCUR AGAIN. NR 2 GENERATOR WE AS LEFT 	OFF LINE FOR REMAINDER OF FLT. GENERATOR BRUSHES WERE REMOVED, & INSPECTED BY MAINTENACE STAFF.  BRUSHES WERE FOUND TO H	AVE WORN BEYOND SERVICEABLE LIMITS.  ONE BRUSH WORN TO POINT WERE CONTACT NOT OCCURRING WITH ARMATURE:THE GENERATOR PREV	IOUS INSTALLATION ON A/C REMOVED DUE TO (4) PREMATURE FAILURES OF BRUSH ASSY.THE CURRENT GENERATOR INSTALLED AS "NEW".  	IS 1ST SET OF BRUSHES TO FAIL ON INSTALLED GENERATOR. MAINTENANCE STAFF HAS NOW IMPLEMENTED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092400083	20010924	00083	EU  	2001	9	24	CA010917006      	1	20010917	G	2434	HEDCR132200	BRUSHES         		9789601090  	PILATS	PC12  	PC1245      	       	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			3373 			NA					(CAN) NR 2 GENERATOR FAILED IN CRUISE FLIGHT. NR 2 GENERATOR WAS TURNED OFF, AND AIRCRAFT RETURNED TO BASE.  INVESTIGATI	ON REVEALED NR 2 GENERATOR BRUSHES WORN. NR 2 GENERATOR BRUSH HOLDER ASSEMBLY P/N 978.96.01.090 REPLACED WITH NEW, AIRCR	AFT GROUND RUN AND CHECKED SERVICEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2001092500090	20010925	00090	SW  	2001	9	25	CA010921005      	1	20010902	G	2910	MS28775212	O-RING          	BELL        	212076007003	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  	 		            		PISTON	SPLIT           	W			    	A	 	 	 	UNSCHED LANDING         				K	 	 	FLUID LOSS                			HO	HOVERING       	1			CA		 	615  			VH9812					(CAN) O-RING ON ACCUMULATOR SPLIT CAUSING HYDRAULIC FLUID LOSS. SUBSEQUENTLY THE PILOT TURNED THE #2 HYDRAULIC SYSTEM OF	F AND LANDED THE AIRCRAFT. FURTHER INVESTIGATION REVEALED THAT THE #2 HYDRAULIC RESERVOIR WAS COMPLETELY DRY. THE ACCUMU	LTOR WAS DISASSEMBLED AND INSPECTED REVEALING THAT THE PISTON O-RING HAD SPLIT THE O-RING WAS REVEALED AND THE REASSEMBL	ED ACCUMULATOR RETURNED TO SERVICE.			1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002011400094	20020114	00094	NE  	2002	1	14	CA010925001      	2	20010916	G	7200		ENGINE          								PWA   	PT6   	PT6A67B     	52043	NE  					NACELLE	MAKING METAL    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) SILVER PLATLETS WERE FOUND IN AN OIL SAMPLE TAKEN AT THE 100 HOUR MARK OF NEWLY INSTALL ENGINE. ENGINE WAS FLUSHED	 AND FILTER REPLACED.  AFTER ANOTHER 40 HOURS OF SERVICE ON THE ENGINE IT WAS INSPECTED AGAIN AND UPON VISUAL INSPECTION	 IT WAS FOUND THAT THERE WAS STILL SILVER PLATLETS IN THE OIL FILTER AND WAS NOW GENERATING FERROUS METAL. IT WAS INITIA	LLY BELIEVED THAT IT WAS JUST JUNK FROM ENGINE ASSEMBLY.  THIS CONFIRMED THAT THE ENGINE WAS INDEED GENERATING METAL. EN	GINE REMOVED AND SERVICIBLE ENGINE INSTALLED.							4	T			E26NE				 
2002011400095	20020114	00095		2002	1	14	CA010926001      	4	20010924	G	3421		INDICATOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	EADI / EHSI	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) CREW REPORTED JUST PRIOR TO LEVELING AT FL250, THE NR 1 EADI (UPPER PILOT WAS FLAGGED WITH "ATITUDE FAIL" .SUBSEQU	ENTLY, THE FLIGHT DIRECTOR AND AUTOPILOT KICKED OFF LINE.CREW SELECTED NR 2 AHRS AND FLIGHT CONTINUED UNEVENTFULLY TO TH	E NEXT DESTINATION. ON THE SUBSEQUENT START THE NR 1 AHRS WAS RESELECTED WITH NO PROBLEMS.  FAILURE COULD NOT BE DUPLICA	TED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011400101	20020114	00101	EU  	2002	1	14	CA010927001      	1	20010926	G	3230	5322012072	DRAG LINK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NLG	BROKEN          	W				O				OTHER                   				D	J		INFLIGHT SEPARATION       	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) FAILURE OF PN 532.20.12.072 NOSE GEAR DRAG LINK ON 25TH JUNE 2001.  SENT IT OUT FOR INDEPENDENT FAILURE ANALYSIS &	 CAME BACK WITH CORROSION PITTING AS CAUSE FOR COMPROMISED STRUCTURAL STRENGTH.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011400105	20020114	00105	CE  	2002	1	14	CA011001002      	1	20010928	G	3097	2601048200	CONNECTOR       			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELECTRICAL PANEL	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION OF THE AREA BEHIND THE ELECTRICAL PANEL BY THE PILOTS LEFT FOOT.  A WIRE CONNECTOR WAS FOUND 	BURNED. THE WIRE CONNECTOR BETWEEN THE PROP ANTI-ICE WIRE HA-20 EXITING FROM THE CIRCUIT BREAKER PANEL AND THE WIRE HA-2	1 GOING TO THE PROP TIMER WAS FOUND BURNED AND DISTORTED FROM HEAT. ON CLOSER EXAMINATION IT WAS FOUND THE TERMINAL ON T	HE WIRE HAD BEEN CRIMPED IMPROPERLY AND WAS ALLOWED TO MAKE CONTACT WITH THE PLACTIC CONNECTOR HOUSING. THE CONNECTOR WA	S REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011400114	20020114	00114	GL  	2002	1	14	CA011002001      	2	20010924	G	7321	23034702	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			CA											(CAN) FUEL CONTROL WAS REPAIRED. FUEL CONTROL WAS INSTALLED ON BELL 206B DUE TO THE OLD ONE NEARING OVERHAUL. AFTER GROU	ND RUNS A TEST FLIGHT WAS CARRIED OUT ON AIRCRAFT. AFTER THE TEST FLIGHT THROTTLE WAS DECREASED TO FLIGHT IDLE WHEN THE 	ENGINE ALMOST FLAMED OUT. ON THE THROTTLE ROLL DOWN THE NG RPM WENT TO 25 PERCENT (NORMAL IDLE SPEED 61PERCENT TO 63 PER	CENT NG) NG RPM WOULD NOT RESPOND TO THROTTLE MOVEMENT. INSTALLED ANOTHER FUEL CONTROL AND DEFECT WENT AWAY.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011400116	20020114	00116	SW  	2002	1	14	CA011002002      	1	20010917	G	7712	6856362	PISTON          	RROYCE      	6894171     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TORQUE METER	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						CAG800082					(CAN) TORQUE INDICATOR ON THE GROUND READ 70 PERCENT TORQUE THEN CLIMBED TO 90 PERCENT TORQUE WITHOUT ADVANCING THE THRO	TTLE OR INCREASING THE POWER. TORQUE INDICATOR REPLACED, DEFECT DID NOT GO AWAY. REPLACED THE ENGINE GEARBOX. IT WAS NOT	ED THAT THE BLEED ORFICE WAS PLUGGED WHICH WOULD LEAD TO AN ADVANCE OF TORQUE INDICATION WITH NO INCREASE IN POWER.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011400118	20020114	00118	SW  	2002	1	14	CA011002003      	1	20010915	G	6320	23034787	BEARING         	RROYCE      	6886442     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R GEARBOX	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA						CAG34833					(CAN) PILOT REPORTED A CHIP LIGHT & A LOUD GRINDING NOISE COMING FROM THE ENGINE REGION. THE PILOT MADE A PRECAUTIONARY 	LANDING TO A LANDING SIGHT. THE CHIP PLUGS WERE REMOVED & FOUND LARGE AMOUNT OF FLAKES. ON THE INVESTIGATION FOUND THE T	WO AND A HALF BEARING FAILED IN THE ENGINE GEARBOX. THE GEARBOX HAS 12264.1 TSN AND 2675.0 TSO. WHEN THE 2 1/2 BEARING F	AILED IT CUT A GROOVE IN THE SPUR ADAPTER GEAR SHAFT RACE.			1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011400121	20020114	00121	SO  	2002	1	14	CA011002004      	1	20010927	G	3260		BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT MLG UPLOCK	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			LD	LANDING        	1			CA			11788								(CAN) RT MAIN GEAR FAILED TO EXTEND. THIS WAS DUE TO RIVETS ATTACHING UPLOCK BRACKETS P/N 40616-01 & 40616-02 SHEARING. 	THIS MAY HAVE BEEN DUE TO CORROSION. THIS ALLOWED W8 OF LDG GEAR TO PULL RIVETS THROUGH 2 ANGLES P/N 40625-00. AS A RESU	LT OF THIS, A MISALIGNMENT OF UPLOCK HOOK WITH UPLOCK ROLLER CAUSED UPLOCK HOOK TO JAM. THIS PREVENTED GEAR FROM EXTENDI	NG. PILOT WAS ABLE TO FREE GEAR BY APPLYING POSITIVE & NEGATIVE G LOADS ON GEAR. GEAR THEN EXTENDED NORMALLY. UPLOCK BRA	CKETS HAD BEEN MODIFIED WHEN BOUNDARY LAYER RESEARCH STC-SA 00202SE SUPER CHIEF II WAS INST & AGAIN WHEN BOUNDARY LAYER 	RESEARCH SB- BLR 105 WAS COMPLIED WITH.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011400122	20020114	00122	CE  	2002	1	14	CA011002005      	1	20011020	G	2897		WIRE            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  					COCKPIT PANEL	BURNED          	W				C				ABORTED TAKEOFF         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) DURING TAKE OFF THE CREW OBSERVED A LOW FUEL PRESSUE LIGHT INDICATION ACCOMPANIED BY THE TRIP OFF OF THE CIRCUIT B	REAKER SWITCH FOR THE LT SECONDARY PUMP.SMOKE WAS EMINATING FROM BEHIND THE LOWER LEFT PANEL AT THE SAME TIME. THE TAKE 	OFF WAS ABORTED AND THE AIRCRAFT WAS SHUTDOWN ON THE RUNWAY. MAINTENANCE FOUND A TERMINAL ON THE CB/SWITCH THAT APPEARED	 TO BE LOOSE WHICH IS BELIEVED TO GENERATED THE WIRING OVERTEMP. THE DAMAGED WIRE AND CB/SWITCH WERE REPLACED.THE CB WAS	 EXAMINED AND FOUND TO HAVE NO INTERNAL ANOMOLIES		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011500001	20020115	00001	SW  	2002	1	15	CA011002006      	1	20010916	G	6220	D2B20000B	LIMITER         			KAMOV 	KA32  	KA32A1      	       	SW  										MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK DISCOVERED DURING POST FLIGHT INSPECTION. FURTHER INVESTIGATION FOUND LEAD AND LAG DRAG HINGE BEARINGS WERE 	VERY STIFF IN TWO OF THE 3 ROTOR HEAD SLEEVES.					1	G	7	2 	4U			NC	        					 
2002011400229	20020114	00229	EA  	2002	1	14	CA011002007      	2	20010916	G	7530	3027249	BLEED VALVE     			DHAV  	DHC6  	DHC6100     	2802610	EA  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	FAILED          	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) DROP IN ENGINE TORQUE, PROP LEVER PUSHED FORWARD, TEMPED OUT AT 35 LBS TORQUE.						1	H	7	2 	3T	3	T	RT	A9EA    	E4EA				 
2002011500002	20020115	00002	SW  	2002	1	15	CA011002009      	1	20010727	G	5302	2060313291	FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12293								(CAN) TAILBOOM FITTING LT FUSELAGE SIDE FOUND CRACKED VERTICALLY 1 INCH IN LENGTH.  NEW PART ORDERED AND INSTALLED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011500003	20020115	00003	CE  	2002	1	15	CA011002010      	1	20010908	G	5312	12128582	BULKHEAD        			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS IN AFT FUSELAGE BULKHEAD.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P3EA	 
2002011500004	20020115	00004	SO  	2002	1	15	CA011003001      	1	20011002	G	6120	B3807	NUT             	HARTZL      	HCE2YR2RBS  	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540*      	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BP9803B					(CAN) THIS IS 2ND OCCURANCE OF PROBLEM.  PROP INSTALLED ON OTHER ENGINE HAD SAME PROBLEM. BOTH PROPS WERE NEW  WITH ASSY	 DATES OF 11-13-97&12-18-97, SHIPPED 4/16/98. PROP CHECKED AS PRECAUTIONARY MEASURE: NUT IS SOLID STEEL SELF LOCKING NUT	, THAT HOLDS PISTON TO PISTON ROD. IF NUT COMES LOOSE, PISTON COMES OFF OF ROD & PROP HAS UNCOMANDED FEATHER WITH NO WAY	 TO UNFEATHER PROP. PISTON SEALS PITCH CHANGE OIL ON ROD. OTHER PROP SER BP9804B, NUT HAD COME COMPLETELY LOOSE. PROP RE	MVD&CHECKED. NUT NOT LOOSE ON PISTON ROD, TORQUE OF NUT CHECKED&NO MOVEMENT FOUND.		1	L	7	2 	3O	3	O	 	1A10    	1E4	5	C	P9EA	 
2002011500005	20020115	00005	GL  	2002	1	15	CA011003002      	2	20010904	G	7321		BEARING         			BELL  	47    	47G4        	1181030	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FCU	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CA						330031					(CAN) INITIAL PROBLEM ENCOUNTERED WAS A CHANGE IN IDLE SPEED. IDLE WAS ADJUSTED, AIRCRAFT WAS TEST FLOWN & NBO PROBLEMS 	EXISTED.NEXT DAY AIRCRAFT IDLE SPEED HAD CHANGED. IDLE WAS ADJUSTED & RIGGING CHECKED. AIRCRAFT WAS RUN & TEST FLOWN. WH	ILE AIRCRAFT WAS RETURNING TO SIGHT IT BEGAN N1 FLUCTUATIONS. THE PILOT LANDED & PULLED COLLECTIVE, FLUCTUATION STOPPED.	 RETURNED A/C TO A MAINTENANCE FACILITY.  AT THIS TIME HE HAD TO REDUCE TO THROTTLE TO PREVENT ENGINE OVERSPEED. FUEL CO	NTROL WAS REMOVED. UPON REMOVAL A LARGE AMOUNT OF METAL FLAKES FELL FROM THE F.C.U. DRIVE BEARING HAD FAILED & THE SHAFT	 WAS FREE FLOATING.	1	G	7	1 	3O	3	U	 	2H3     	E4CE				 
2001101500063	20011015	00063	WP  	2001	10	15	CA011003004      	1	20010921	G	6310	A1902	V-BELT          	LYC         	            	ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  	 		            		FRONT ENGINE	TORN            	W			    	O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			CR	CRUISE         	1			CA		 									(CAN) BELTS SENT TO R.H.C. FOR INVESTIGATION. THEIR RESPONSE WAS THAT THE BELTS WERE DRY AND CAUSED SMALL CRACKS IN THE 	RUBBER WHERE THE BELTS ARE RIDING ON THE SHEAVE.					1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002011500006	20020115	00006	EA  	2002	1	15	CA011003006      	2	20010924	G	7313	LW18853	INJECTOR        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCC4Y	HCC4YR2     	GL  	RT ENG NR 3 CYL	LOOSE           	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) PILOT REPORTED INTERMITTENT SLIGHT POWER LOSS & ROUGH RUNNING AT CRUISE POWER, GROUND POWER RUNS SHOWED NORMAL. IN	SPECTION OF RT ENGINE FOUND NR 3 CYLINDER FUEL INJECTOR "LOOSE" IN CYLINDER HOUSING AND FUEL STAINING AROUND THE AREA. F	UEL INJECTOR THREADS & CYLINDER THREADS WERE DAMAGED. IT WAS NOTED THE FUEL INJECTOR LINES WERE PROPERLY CLMAPED AS OUTL	INED IN AD 93-02-05 (SB 342). INSPECTION OF THE OTHER INJECTORS FOUND NO PROBLEMS. SUSPECT VIBRATION TO HAVE CAUSED THE 	INJECTOR TO LOOSEN. NO UNUSUAL VIABRATION REPORTED PREVIOUS TO THIS.		1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P52GL	 
2002011500007	20020115	00007	SW  	2002	1	15	CA011003009      	1	20010917	G	5320	206063107005	LEG ASSY        			BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					ENGINE BAY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE ENGINEER NOTICED A HILOCK COLLAR IN THE ENGINE BAY. UPON INVESTIGATIO	N IT WAS NOTED THAT THE HI-LOCK PIN HAD CORRODED THROUGH & THE COLLAR FELL OFF. LEG ASSEMBLY REPLACED WITH NEW.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011500008	20020115	00008	SW  	2002	1	15	CA011003010      	1	20010913	G	6730	412076670101	BEARING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					UNIVERSAL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AME WAS COMPLETING A DAILY INSPECTION WHEN HE PULLED THE LT SERVO BRUSH TUBE AND FELT PLAY. UPON INVESTIGATION A B	EARING IN THE UNIVERSAL HAD FAILED.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002011500009	20020115	00009	SO  	2002	1	15	CA011003013      	2	20010523	G	8520		CRANKSHAFT      			CESSNA	337   	T337H       	2075733	CE  	CONT  	O360  	TSIO360H    	17025	SO  	MCAULY	2AF34C	D2AF34C308  	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) INFLIGHT CATASTRPHIC FAILURE, CRANKSHAFT, AT LEAST 2 RODS, HOLE IN TOP OF CRANKCASE, CONTINUED FLIGHT ON, REAR ENG	INE TO VIKING AIRPORT (ALBERTA).					1	H	7	2 	3O	3	O	 	A6CE    	E9CE	5	C	P5EA	 
2002011500010	20020115	00010	CE  	2002	1	15	CA011003014      	1	20010914	G	2750	0512128	BRACKET         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	TE FLAPS	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			10325								(CAN) FLAPS WOULD NOT EXTEND PROPERLY FOR TAKEOFF. PILOT LEFT FLAPS IN UP POSITION AND RETURNED TO BASE. BRACKET IS MOUN	TED TO LOWER BULKHEAD USING 4 SCREWS AND LOCKNUTS ON THE 4 MOUNT TABS. BOTH INBOARD TABS ON BRACKET HAD FAILED AT THE BE	ND RADIUS, ALLOWING THE BRACKET TO BEND FORWARD AND BIND THE CABLE ON THE COTTER PIN THAT KEEPS THE CABLE IN THE PULLEY 	GROOVE. NO OTHER DAMAGE WAS DONE TO THE STRUCTURE OR CABLE.			1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P21EA	 
2002011500011	20020115	00011	CE  	2002	1	15	CA011003015      	1	20010916	G	7120	85921701	SPACER          		J961358     	CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					ENGINE MOUNT	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE INSTALLING NEW ENGINE NOTICED THAT ENGINE ATTACH BOLTS WERE TOO SHORT.  PART NR OF BOLTS WERE CORRECT. ENGIN	E MOUNTS WERE FOUND TO BE PROBLEM. SPACERS IN ENGINE MOUNT KITS WERE WRONG LENGTH & WRONG PART NR.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002011500012	20020115	00012	CE  	2002	1	15	CA011003016      	1	20010903	G	2133	47061	VALVE           			CESSNA	441   	441         	2076020	CE  										CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING AIRCRAFT CLIMB, THE EMERGENCY PRESSURIZATION VALVE OPENED ALLOWING UNCONDITIONAL BLEED AIR INTO THE CABIN. 	CABIN TEMPERATURE INCREASED AT AN UNCONTROLED RATE. AIRCRAFT RETURNED TO THE AIRPORT FROM WHICH IT DEPARTED. THE EMERGEN	CY PRESSURIZATION VALVE WAS REPLACED. AIRCRAFT GROUND RUN "S".				1	L	7	2 	3T			RT	A28CE   					 
2002011500014	20020115	00014	NM  	2002	1	15	CA011004001      	1	20010729	G	2910	8297000269	LINE            			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 20 FH MAINTENANCE INSPECTION, MAINTENANCE FOUND HYDRAULIC FLUID LEAKING AROUND FS UNLOADING VALVE IN ENGINE	 NR 2 NACELLE. THE LINE P/N 8297000-269 IS REPORTED TO HAVE A CRACKED CRYOFLARE FITTING.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002011500016	20020115	00016	NM  	2002	1	15	CA011004003      	1	20010728	G	2910	82970009267	LINE            			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING 20 FH INSPECTION, MAINTENANCE FOUND EVIDENCE OF HYDRAULIC LEAK IN THE LT ENGINE NACELLE. THE LINE P/N 82970	009-267 (FS UNLOADING VALVE TO RETURN MANIFOLD) AND LINE P/N 82970009-157 (RESERVOIR TO HYDRAULIC SOV) CHAFED TOGETHER.T	HE TWO LINES WERE REPLACED.TSN/CSN 896.05/793				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002011500017	20020115	00017	NE  	2002	1	15	CA011004004      	2	20010918	G	8530	ST90P10ER	CYLINDER HEAD   			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON CYLINDER HEAD FROM EXHAUST PORT TO FRONT SPARK PLUG WHILE PERFORMING AD 78-08-07.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002020700002	20020207	00002	EA  	2002	2	7	CA011004005      	1	20010927	G	5523	VALTOCC113618	ATTACH FITTING  	DHAV        	C3TE1213    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					ELEVATOR SERVO	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTIONS FOUND THAT ELEVATOR SERVO TAB HAD TWO SHEARED OFF RIVETS UPPER FORWARD ENGINE AT ARM ATTACHMENT	 BLOCK AND CRACK AT LOWER BETWEEN RIVET HOLES ON ELEVATOR SERVO TAB.					1	H	7	1 	3R	4	T	 	A815    	E4EA				 
2001101500064	20011015	00064	CE  	2001	10	15	CA011004008      	1	20011003	G	3610	S189148	CLAMP           	CESSNA      	CM357024    	CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  	 		            		CLAMP	LOOSE           	W			    	B	 	 	 	EMER. DESCENT           				O	 	 	OTHER                     			CL	CLIMB          	1			CA		 									(CAN) CLIMBING THROUGH FLIGHT LEVEL 290, AIRCRAFT CABIN STARTED TO RAPIDLY CLIMB. FLIGHT CREW INITIATED A RAPID DECENT T	O 10,000 FEET. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND CLAMP ON CABIN BLEED AIR SUPPLY LINE LOOSE AN	D THE AIR SUPPLY LINE HAD BECOME DISCONNECTED. THE AIRCRAFT HAD RECENTLY HAD MAINTENANCE PERFORMED ON THE BLEED AIR SYST	EM. ALL OTHER CLAMPS IN THE BLEED AIR SYSTEM WERE CHECKED FOR SECURITY WITH NO FURTHER PROBLEM FOUND.			1	L	7	2 	4F	4	F	 	A22CE   	E25EA				 
2002011500020	20020115	00020	CE  	2002	1	15	CA011004010      	1	20010829	G	6100	CA462220W	BOLT            	MCAULY      	1C160DTM755 	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						729634					(CAN) ONE OF THE 6 BOLTS ATTACHING THE PROPELLER TO THE ENGINE CRANK SHAFT FLANGE BROKE AT THE TOP OF THE THREADED AERA 	ON INITIAL TORQUE.THE PROPELLER HAD A PLACARD INDICATING TORQUE SPED FOR 1/2" BOLTS. PROLLER IS ATTACHED WITH 7/16" BOLT	S. IT IS SUSPECTED THAT THE BOLTS HAVE BEEN OVER TORQUED ON PREVIOUS INSTALLATIONS. PLACARD WAS REMOVED FROM THE PROPELL	ER AND BOLTS TORQUED TO THE PROPER TORQUE SPEC FOR 7/16 BOLTS.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011500025	20020115	00025	SO  	2002	1	15	CA011004016      	1	20011004	G	7120	12351015	MOUNT           			PIPER 	PA18  	PA18A150    	7101837	SO  	LYC   	O320  	O320A2B     	41508	EA  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT RIGHT DIAGNEL ARM FOUND BROKEN APPROX 2" FROM UPPER RIGHT FIREWALL ATTACH POINT. ENGINE MOUNT REMOVED	 AND REPLACED WITH NEW					1	H	7	1 	3O	3	O	 	1A2     	E274				 
2002011500026	20020115	00026	CE  	2002	1	15	CA011004017      	1	20010918	G	7160	04500704	SEAL            	CESSNA      	04500521    	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					AIRBOX	TORN            	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) - AIRCRAFT ROUGH RUNNING, NOT PRODUCING FULLPOWER.  AIR BOX REMOVED AND BUTTERFLY SEAL FOUND UNSERVICEABLE.   A SM	ALL PIECE A SEAL WAS FOUND IN CARB. VENTURI.  A NEW AIR DOOR SEAL WAS INSTALLED.- AIRCRAFT GROUND RUN & CHECKED OK.					1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002011500028	20020115	00028	CE  	2002	1	15	CA011005001      	1	20010923	G	3510	17201041	REGULATOR       	SCOTT       		BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					OXYGEN BOTTLE	MISMARKED       	W				O				OTHER                   				L			NO TEST                   			LD	LANDING        	1			CA											(CAN) CREW REPORTED O2 SYSTEM NOT FUNCTIONING CORRECTLY. ON INVESTIGATION MAINTENANCE DISCOVERED REGULATOR WAS INSTALLED	 180 DEGREES OUT OF RIG. ON FURTHER EXAMINATION REGULATOR VALVE WAS FOUND TO ROTATE 360 DEGREES FOR MULTI-POSITION INSTA	LLATIONS. O2 BOTTLE HAD RECENTLY BEEN INSTALLED & HAD FLOWN ONE FLIGHT BEFORE BEING SNAGGED. THE POTENTIAL FOR SERIOUS I	NCIDENT AT ALTITUDE COUPLED WITH A DEPRESSURIZATION IS HIGH WITH THIS TYPE OF INSTALLATION. THE VALVE IS NOT "MURPHY PRO	OF" & REQUIRES EXTREME CARE AND ATTENTION ON INSTALLATION AS THE VALVE ON THE REGULATOR IS ALSO POORLY MARKED FOR ON & O	FF POSITION.	1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002011500029	20020115	00029	SW  	2002	1	15	CA011005002      	1	20010926	G	6320	204040701103	BEVEL GEAR      	BELL        	212040001123	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TRANSMISSION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						ABW40395					(CAN) METAL PARTICLES FOUND IN SUMP FILTER AT 50 HOUR INSPECTION. TRANSMISSION REMOVED AND SENT FOR OVERHAUL. WHEN ROTOR	 BRAKE QUILL WAS REMOVED I NOTICED HEAVY WEAR ON THE TEETH OF THE PINION. INSPECTION OF THE SPIRAL BEVEL GEAR REVEALED T	WO BROKEN TEETH AND HEAVY WEAR MARKS ON BACK SIDE OF ALL REMAINING TEETH.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002011600003	20020116	00003	CE  	2002	1	16	CA011005003      	1	20010919	G	2436	VR600A	VOLT REGULATOR  			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	DC ELECTRICAL	INOPERATIVE     	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) INCOMPATIBILITY BETWEEN PARTS.IT HAS BEEN DISCOVERED THAT SEVERAL SUPPLIERS HAVE BEEN INFORMED THAT VOLTAGE REGULA	TORS LAMAR DGR 6 & ELECTROSYS VR600A ARE COMPATIBLE & INTERCHANGEABLE. IN ACTUALFACT LAMAR DGR6 IS INTERCHANGEABLE WITH 	THE  ELECTROSYS VR600. NOTE: VR600 VOLTAGE REGULATORS ARE NO LONGER AVAILABLE. NOTE: ELECTROSYS VR600A HAS BUILT IN OVER	-VOLTAGE PROTECTION CCT.WHEN INSTING ELECTROSYS VR600A FOR 1ST TIME, INST INSTRUCTION REQUI RE YOU TO COMPLETELY REMOVE 	OVER-VOLTAGE SWITCH P/N C593001-010 FROM A/C.		1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002011500030	20020115	00030	CE  	2002	1	15	CA011005004      	1	20010921	G	2710	262400724	BELLCRANK       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE, EXCESSIVE PLAY WAS FOUND BETWEEN THE RT OUTBOARD AILERON BELL CRANK AND THE RESPECTI	VE AILERON PUSH / PULL TUBE. FURTHER INVESTIGATION REVEALED THAT THE ATTACH POINT HOLE DIMENSIONS WERE BEOND ACCEPTABLE 	LIMITS. BELL CRANK WAS REPLACED WITH A NEW ASSEMBLY.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011500039	20020115	00039	SW  	2002	1	15	CA011011007      	1	20010831	G	5302	206020123008	STRUCTURE       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM V FIN	VIBRATION       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART CAUSING HIGH VIBRATION IN T/R SYSTEM. REPLACED VERTICAL FIN.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011500040	20020115	00040	SW  	2002	1	15	CA011011008      	1	20010831	G	5302	206020121006	FITTING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAILBOOM V FIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART CRACK AT REAR RIVET. REPLACED FITTING.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011500041	20020115	00041	SW  	2002	1	15	CA011011009      	1	20010916	G	2822	1C274	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL BOOST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PUMP NOT WORKING MOTOR UNSERVICEABLE. REPLACED PUMP ASSEMBLY.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011500042	20020115	00042	EU  	2002	1	15	CA011011010      	1	20010917	G	2911	704A34240015	ACCUMULATOR     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) PART LEAKING. PART REPLACED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002011500043	20020115	00043	GL  	2002	1	15	CA011011011      	2	20010918	G	7210	4638001001	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) PIC CALLED IN A MAGNETIC LITE ON. A/C LANDED AT SCHOOL. AME INSPECTED MAG PLUG, 1 SMALL FLAKE AND 1 THIN HAIR. A/C	 RUN UP CARRIED OUT NO FURTHER INDICATION. A/C FLOWN APPROX 8 MILES TO MIRIMICHI AIRPORT AND HOVERED AROUND RAMP AREA FO	R APPROX 80 MINUTES. NO FURTHER INDICATION. AME ELECTED TO CHANGE MGB OIL AND INSPECT MGB FINE OIL FILTER. FILTER FOUND 	TO CONTAIN NUMEROUS PIECES OF MATERIAL AND DRAINED OIL WAS SHINY.  A/C REMOVED FROM SERVICE AND TRANSPORTED BACK TO MAIN	TENANCE FACILITY.		1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002011500044	20020115	00044	CE  	2002	1	15	CA011011012      	1	20010919	G	7120	05510171	MOUNT           			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT WAS FOUND CRACKED DURING 50 HOUR INSPECTION. NO CRACKS WERE NOTICED AT THE PREVIOUS INSPECTION AND TH	E CRACK SHOWED NEW MATERIAL. THIS WOULD INDICATE DETERIORATION DURING THE LAST 50 HOUR.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011500047	20020115	00047	EU  	2002	1	15	CA011011015      	1	20011003	G	2710	5271212075	STOP            	PILATS      	5271212003  	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BELLCRANK	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRING OUT ANNUAL INSPECTION IT WAS NOTED THAT THIS AILERON BELLCRANK STOP ON THE LEFT HAND WING WAS MISSIN	G.  LOOKING AT THE STOP ON THE RIGHT HAND WING IT APPEARS TO BE JUST A PLASTIC STOP PUSHED INTO A HOLE IN THE WING STRUC	TURE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011500048	20020115	00048	EU  	2002	1	15	CA011011022      	1	20011002	G	2897	RR53710K	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	BOOST PUMP	PINCHED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON REMOVAL OF THE BOOSTER PUMP, IT WAS FOUND THAT THE WIRE HARNESS, WHICH IS PART OF THE PUMP HAD APPEARED TO HAVE	 BEEN TRAPPED BETWEEN THE BOOSTER PUMP MOUNTING PLATE & THE AIRFRAME. THIS HAS CAUSED ONE WIRE OF THE HARNESS TO BE CRIM	PED FLAT & THE INTERNAL COPPER CONDUCTOR TO BE EXPOSED.THE BOOSTER PUMP WAS CHANGED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011500049	20020115	00049	SW  	2002	1	15	CA011012001      	1	20011002	G	6410	212010750105	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A DAILY INSPECTION THE ENGINEER WAS INSPECTING THE TAIL ROTOR BLADES, ON T/R BLADE S/N A-11101 HE FOUND A DELAM	INATION AT THE TIP.  A REPLACEMENT T/R HUB ASSEMBLY WAS ORDERED (TSN 729.9 OF S/N A-11101) AT TTSN 413.9 T/R BLADE WAS R	EMOVED DUE TO DELAMINATION AND TO CARRY OUT SB 212-00-111 REV.A (SB 205-00-80 REV.A) T/R BLADE TIP BLOCK RETENTION MODIF	ICTION.			1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002011500050	20020115	00050	CE  	2002	1	15	CA011012002      	1	20011011	G	3210		LANDING GEAR    			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					RIGHT	FAILED          	W				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA											(CAN) AFTER TAKE-OFF RT GEAR INDICATION INDICATED RT GEAR NOT RETRACTED.  GEAR WAS CYCLED DOWN AND THEN INDICATED NOT DO	WN AND LOCKED. SUBSEQUENT RE-CYCLE PRODUCED SAME RESULT (NO GREEN FOR RT SIDE AND INTRANSIT LIGHT ON IN GEAR HANDLE).  O	BSERVATION DURING AIRCRAFT FLY-BY SHOWED GEAR IN DOWN AND LOCKED POSITION. ON THE LANDING ROLL, RT GEAR RETRACTED UNDER 	THE WEIGHT OF THE AIRCRAFT. INVESTIGATION UNDERWAY.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011500169	20020115	00169	SW  	2002	1	15	CA011012003      	1	20011002	G	5320	205030163095	CAP             			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5317A      	41549	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A TURN AROUND CHECK AFTER REFUELING THE AIRCRAFT, AN ENGINEER FOUND A CRACK ON THE EXPOSED SIDE OF THE LEFT BEA	M CAP THAT IS LOCATED NEAR THE FORWARD VERTICAL WALL.					1	G	7	1 	4U	4	U	 	H1SW    	E17EA				 
2002011500055	20020115	00055	NE  	2002	1	15	CA011012008      	1	20010529	G	6710	1565202535	SERVO VALVE     			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					MAIN ROTOR	FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA											(CAN) A/C IN LOGGING OPS NEAR SAYWARD, BC. AS PILOT MADE HIS APPROACH TO LOG LDG& INITIATED FLARE TO SLOW DOWN HIS APPRO	ACH, A/C'S NOSE ABRUPTLY PITCHED UP & CONTINUED TO DO SO EVEN WITH FULL FWD CYCLIC APPLIED. A/C FINALLY LEVELED OFF THEN	 BEGAN VIOLENTLY PITCHING UP & DOWN. CNTL OF A/C REGAINED BY SHUTTING OFF 1ST STAGE HYDRAULIC SYS. WITH SYS REMAINING TU	RNED OFF PILOT SET DOWN LOAD OF LOGS & THEN RETURNED TO SERVICE LANDING MAKING UNEVENTFUL LDG. AFTER LDG PILOT CARRIED O	UT FULL HYDRAULIC SERVO CHECK & FOUND CYCLIC COULD NOT BE MOVED FWD WITH 1ST STAGE HYDRAULIC SYS ON. MAIN ROTOR TANDEM S	ERVO INST IN FOR & AFT POS WAS REPL & A/C RT-SRV.	2	G	7	2 	4U	4	U	 	H4EA    	E15EA				 
2002011500056	20020115	00056	WP  	2002	1	15	CA011012009      	1	20010927	G	6520	369D25430	SHAFT           		369D25400   	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						0298					(CAN) GEARBOX RECEIVED FROM CUSTOMER WITH COMPLAINT OF T/R VIBRATION AND METAL GENERATION. ON STRIP DOWN THE OUTPUT GEAR	SHAFT WAS REMOVED AND THE OUTPUT JOURNAL AND THE END OF THE OUTPUT GEARSHAFT WERE FOUND INSIDE OF THE ALIGNMENT BEARING.	THE OUTPUT GEARSHAFT HAD FAILED.THIS THE SECOND OCCURRENCE OF THIS TYPE, THE FIRST OCCURRED 1997-03-05.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002011500057	20020115	00057	EA  	2002	1	15	CA011016001      	1	20011016	G	2120	C6VF11181	SCREEN          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					EXPANSION CHAMB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING MAINTENACE TO CHANGE A GROUND BLOWER THE EXPANSION CHAMBER WAS REMOVED TO GAIN ACCESS TO THE BLOWER.  A RAT	TLE WAS NOTICED INSIDE THE CHAMBER . INVESTATION REVEALED THE INTERNAL SCREEN HAD SEPERATED FROM THE FILTER SCREEN. THIS	 CONDITION COULD POSSIBLY LET FOREIGN OBJECTS INTO THE HEATING SYSTEM.THE AFFECTED PART WAS REPLACED WITH A NEW ITEM .TH	E NEW PART WILL BE INSPECTED PERIODICALLY TO CHECK FOR CONDITION			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002011500058	20020115	00058	WP  	2002	1	15	CA011016002      	1	20011016	G	6310	369D25351	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					CLUTCH ASSY	CHIPPED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON 300 HOUR (SLING TIME OF 221.1 HOURS)  INSPECTION THE SPRAG ASSEMBLY  WAS FOUND TO HAVE ONE BROKE SPRAG						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002011500059	20020115	00059	EU  	2002	1	15	CA011017002      	1	20011011	G	6720	350A33105803	BELLCRANK       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					T/R GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR PITCH CONTROL PUSH-PULL TUBE ROD END BEARING STAKING SLEEVE WORE A CIRCULAR GROOVE INTO THE EAR / CLEVI	S OF THE BELLCRANK THAT IS MOUNTED ON THE T/R GEARBOX.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011500060	20020115	00060	EA  	2002	1	15	CA011017003      	2	20010921	G	7414		GEAR            	BENDIX      	S6LN1208    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MAGNETO	SEIZED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA						8215200					(CAN) RT ENGINE SHUTDOWN IN FLIGHT, AT TOP OF CLIMB AT ABOUT 8,500 FT. PILOT COULD NOT RESTART. INSPECTION ON GROUND THE	 GEAR TRAIN IN ACCESSORY CASE WAS OBSERVED NOT TO TURN. THE LEFT MAG WAS REMOVED AND FOUND TO BE SEIZED. THE GEAR ON REA	R OF CRANKSHAFT HAD TEETH MISSING LOCATING DOWEL SHEARED AND RETAINER BOLT BROKEN. NO DAMAGE TO NEXT GEAR IN TRAIN WAS O	BSERSVED. ENGINE SENT FOR REPAIR / OVERHAUL. MAG SUBMITTED TO OAE TO DETERMINE CAUSE OF FAILURE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011500086	20020115	00086	SO  	2002	1	15	CA011017006      	1	20010504	G	3230	452440	BEARING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NLG UPLOCK	SEIZED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) - NOSE WHEEL WOULD NOT COME DOWN FOR LANDING, CONFIGURATION. A/C LANDED ON MAINS WITH NOSE WHEEL FULLY RETRACTED. 	UPON INSPECTION NOSE WHEEL UPLOCK BEARING FOUND SEIZED WHICH RESULTED IN NOSE WHEEL NOT DISENGAGING FROM UPLOCKED POSITI	ON. - BEARING WAS SERVICED AT PREVIOUS 100 HOUR INSPECTION AND A/C DUE FOR ANOTHER 100 HOUR INSPECTION. - SUSPECTED CAUS	E: A WET SPRING ALSO, OPERATOR'S FLIGHTS ARE MOSTLY DONE OFF OF GRAVEL STRIPS. THERE WAS A LARGE ACCUMULATION OF SAND & 	SILT ON LANDING GEAR. OPERATOR REGULARLY PRESSURE WASHED GEAR AND GREASE JOINTS AND HINGES. BUT UPLOCK WAS OVERLOOKED AN	D NOT CHECKED REGULARLY ON WALK AROUNDS.BEARING ARE NOW INSPECTED ON A/C DAILY PREFLIGHT INSPECTIONS.	1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011500088	20020115	00088	SO  	2002	1	15	CA011017007      	2	20010922	G	8530	CH71HER	VALVE SEAT      			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	CYLINDER HEAD	CRACKED         	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) - NR 6 CYLINDER ASSEMBLY CRACKED FROM EXHAUST VALVE SEAT TO INJECTOR PORT TO INTAKE VALVE SEAT. - INJECTOR AND FUE	L FLOW AND PRESSURE NORMAL SO CAUSE UNKNOWN.- CYLINDER REPLACED.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002011500090	20020115	00090	CE  	2002	1	15	CA011017008      	1	20011001	G	2731	26612158	SCREW           	CESSNA      	26612151    	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TRIM ACTUATOR	DAMAGED         	W				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) FLIGHT CREW REPORTED JAMMED ELEVATOR TRIM. INSPECTION REVEALED DAMAGED SCREW THREADS ON THE ELEVATOR TRIM ACTUATOR	 (PARTS ENCLOSED).SCREW P/N 2661215-8 INTERNAL SCREW P/N 2661215-6					1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011500131	20020115	00131	NM  	2002	1	15	CA011017016      	1	20010627	G	7930	APT761000100DW	TRANSMITTER     			DHAV  	DHC8  	DHC8*       	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	OIL PRESSURE	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) DURING DESCENT CREW REPORTED NR 2 ENGINE OIL PRESSURE DROPPED BELOW 55 PSID. ENGINE POWER WAS REDUCED AND PROP FEA	THERED AS PER FM. NH REMAINED ABOVE 75 PERCENT ON FINAL SO ENGINE WAS SHUTDOWN. NO REPORT ON NR 2 ENGINE OIL PRESSURE WA	RNING LIGHT ON.ON GROUND, MAINTENANCE REPLACED BOTH THE OIL PRESSURE TRANSMITTER AND PRESSURE GAUGE. ENGINE GROUND RUN O	K. AIRCRAFT RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002011500136	20020115	00136	CE  	2002	1	15	CA011018008      	1	20010721	G	2823	1013890253	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUEL SHUTOFF	STUCK           	W				O				OTHER                   				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING PILOT'S PRE-FLIGHT INSPECTION LT FUEL FIREWALL VALVE WOULD NOT CLOSE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002011500147	20020115	00147	CE  	2002	1	15	CA011018009      	1	20011011	G	3260		WIRE            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					LT MLG DOWNLOCK	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) NO DOWN AND LOCK INDICATION FOR THE RT MAIN LANDING GEAR. FOLLOWING A MANUAL EXTENSION THE AIRCRAFT LANDED WITH OU	T INCIDENT. INSPECTION REVEALED A BROKEN WIRE ON THE RT MAIN DOWN AND LOCK SWITCH. REPAIRS CARRIED OUT. LANDING GEAR FUN	CTION CHECKED SERVICEABLE				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011500149	20020115	00149	EA  	2002	1	15	CA011018011      	2	20011001	G	7322	CF30766	FLOAT           	MARVELSCHEBX	105009      	CESSNA	172   	172         	2072402	CE  	LYC   	O320  	O320*       	41508	EA  					CARBURETOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BL2213803					(CAN) CARBURETOR WOULD "FLOOD WHILE AT REST", CARBURETOR BULK DISMANTLED, TOP HALF INVERTED, FOUND FLOAT HEIGHT NON EXIS	TENT, SHOULD BE 7/32. REMOVED FLOAT FOR INSPECTION. FOUND ADJUSTMENT TAB SEVERELY WORN FROM NEEDLE VALVE. REPLACED DEFEC	TIVE FLOAT WITH NEW PILYMER FLOAT.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002011500150	20020115	00150	CE  	2002	1	15	CA011018012      	1	20010928	G	5520	12346391	RIB             	CESSNA      	123463324   	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE INBOARD NUTPLATE WITH PART OF THE RIB HAD COMPLETELY SEPARATED ALLOWING THE COUNTERWEIGHT TO MOVE FREELY FORWA	RD AND AFT IN ELEVATOR HORN.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011500151	20020115	00151	SO  	2002	1	15	CA011018013      	1	20011017	G	3010	25S5D508419	BOOT            			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					DEICE SYSTEM	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			CA											(CAN) ON APPROACH A VIBRATION WAS FELT BY THE FLIGHT CREW. VISUAL INSPECTION BY THE FLIGHT CREW REVEALED THE OB LEFT HAN	D WING DEICE BOOT WAS RIPPED AND FLAPING AGAINST THE WING. THE AIRCRAFT LANDED WITH OUT INCIDENT, HOWEVER A PORTION OF T	HE DEICE BOOT SEPERATED FROM THE AIRCRAFT. THERE WAS NO DAMAGE INFLICTED UPON THE AIRCRAFT.				1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002011500152	20020115	00152	CE  	2002	1	15	CA011018014      	1	20010928	G	2720	0411307	TUBE            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RUDDER ARM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TUBE CRACKED FROM BOLT HOLE TO LOWER EDGE OF TUBE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011500153	20020115	00153	CE  	2002	1	15	CA011018015      	1	20010928	G	2701	126014215	TUBE            	CESSNA      	126014015   	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CONTROL COLUMN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ONE OF 3 BOLT HOLES ATTACHING CONTROL WHEEL TO TUBE CRACKED FROM HOLE TO EDGE OF TUBE.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011500154	20020115	00154	NE  	2002	1	15	CA011018016      	2	20010920	G	7220	555225056	RIVET           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					INLET	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT DOWN FOR PHASE 5 INSPECTION. L/H ENGINE - 2 RIVET IN THE 5 O'CLOCK POSITION AND 3 RIVETS AT 7 O'CLOCK POS	ITION HAD THE HEADS PULLED 1/3 TO 2/3 AROUND THE SHANK DIAMETER.R/H ENGINE 5 TO 6 RIVETS IN THE 3 TO 6 O'CLOCK POSITION 	HAD THE HEADS PULLED 1/4 TO 2/3 AROUND THE SHANK DIAMETER.ALL BAD RIVETS REPLACED.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002011500155	20020115	00155	CE  	2002	1	15	CA011018017      	1	20011005	G	5320	50420013451	CROSSTUBE       			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IT WAS FOUND THAT SOME ONE HAD REMOVED MATERIAL FROM THE CROSS TIE MEMBER, PROBABLY TO DEAL WITH SOME FIT AND CLEA	RANCE PROBLEM. SUBSEQUENT TO THIS WE HAVE FOUND A CRACK PROPAGATING FROM THE RADIUS FORWARD TO THE BULKHEAD. THIS AIRCRA	FT WAS BEING INSPECTED IN PREPARATION FOR A C OF A APPLICATION.				1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002020700044	20020207	00044	CE  	2002	2	7	CA011018018      	1	20011005	G	7500	31A4121	MANIFOLD        			CESSNA	500   	550         	2076604	CE  										BLEED AIR SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEVERAL CRACKS (SEVEN) FOUND AROUND RING WHERE RADIUS MEETS TUBE.						1	L	7	2 	4F			 	A22CE   					 
2002011500156	20020115	00156	CE  	2002	1	15	CA011018020      	1	20011001	G	5330		SKIN            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED MAINTENANCE CESSNA 550 PHASE "5" AND PHASE "49" INSPECTIONS, OF THE R/H F.S. 287.78 SKIN SEAM, A 	1.5" LONG CRACK WAS FOUND CENTERED ABOUT 115.25 (W.L.). - CESSNA INFORMATION: THIS HAVE OCCUR ON SOME AIRCRAFT, FOLLOWIN	G REPAINTING. - OUR AIRCRAFT S/N 550-0702 HAVE ORIGINAL PAINT.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2002011500157	20020115	00157	CE  	2002	1	15	CA011018021      	1	20011007	G	2121		WIRE HARNESS    			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					VENT BLOWER	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LARGE WIRE BUNDLE TOO CLOSE TO VENT BLOWER MOTOR.						1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001110800004	20011108	00004	CE  	2001	11	8	CA011018024      	1	20010920	G	2422	3P639CP589BH	WIRE            	CESSNA      	3P639CP589BL	CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JD15  	JT15D1A     	 	NE  	 		            		SPLICE	SHORTED         	W			    	H	 	 	 	DEACTIVATE SYST/CIRCUITS				H	 	 	ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA		 									(CAN) DURING A ROUTINE FLIGHT, ON ARRIVAL AT YYZ #2 INVERTER FAILED. SYSTEM WAS CHECKED AND FINDINGS WERE THAT THE 115 V	AC OUTPUT FOR THE R/H BUS, RUNNING BETWEEN THE INVERTER AND THE FRONT PRESSURE BULKHEAD THE WIRE WAS FOUND SHORTED. THER	E WAS EVIDENCE OF CORROSION AND ARCING ADJACENT TO A CRIMP SPLICE IN WIRE #3P639-CP589BH. (SEE ACCOMPANYING DIAGRAM). IT	 APPEARS THAT THE INSULATION MAY HAVE BROKEN DOWN ON ONE WIRE ADJACENT TO THE SPLICE, WHICH CAUSED A SHORT CIRCUIT AND A	RCING WHICH CONTINUED TO DETERIORATE THE INSULATION, CAUSING FAILURE IN THE CIRCUIT.		1	L	7	2 	4F	4	F	 	A22CE   	E25EA				 
2001110800005	20011108	00005	CE  	2001	11	8	CA011019001      	1	20011018	G	2436	51539012N	GCU             	            	            	CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	GCU	                	W			    	K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA		 									(CAN) DURING CRUISE, PILOT NOTICED STANDBY POWER ON ANNUNCIATOR FLASHING FOLLOWED SHORTLY BY THE STANDBY POWER INOP ANNU	NCIATOR ON STEADILY.THIS WAS FOLLOWED BY THE GENERATOR OFF ANNUNCIATOR ILLUMINATING.BOTH GENERATOR POWER AND STANDBY POW	ER COULD BE RETURNED ON LINE BY CYCLING THE STANDBY POWER SWITCH AND THE GENERATOR RESET SWITCH.SYSTEM WAS TESTED ON THE	 GROUND WITH A MIN/MAX RECORDING VOLTMETER.  EACH ILLUMINATION OF THE ANNUNCIATOR LIGHT CORRESPONDED WITH A VOLTAGE SPIK	E TO 34+ VOLTS. GENERATOR CONTROL UNIT WAS REPLACED AND SYSTEM CHECKED NORMALLY.		1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011500164	20020115	00164	CE  	2002	1	15	CA011019013      	1	20011019	G	5751	122005312	BRACKET         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10617	10617							(CAN) DURING INSPECTION THE RT  INBOARD AILERON BRACKET WAS FOUND CRACKED AT BOTH I/B & O/B UPPER ATTACH POINTS. {WHERE 	THE BRACKET ATTACHES TO THE REAR SPAR} BRACKET REPLACED					1	H	7	1 	3O	3	O	 	A4CE    	E5CE				 
2002011600006	20020116	00006	NM  	2002	1	16	CA011019022      	1	20010521	G	7930	APT761000100DW	TRANSMITTER     			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	ENG OIL PRESSURE	FAILED          	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) ENGINE OIL PRESSURE DROPPED TO BETWEEN 44-55 PSI DURING FLIGHT. THE ENGINE POWER WAS REDUCED AND PROPELLER WAS SEL	ECTED TO START FEATHER. OIL PRESSURE TRANSMITTER REPLACED, FUNCTION AND LEAK CHECKED SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002011600007	20020116	00007	NM  	2002	1	16	CA011019023      	1	20010524	G	8011	2431K2	CONTACTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF15      	NE  	STARTER	STUCK           	W				E	H			ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS			B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER DID NOT DISENGAGE AFTER ENGINE START, SMOKE WAS NOTICED COMING FROM THE STARBOARD ENGINE. ELECTRICAL POWER	 WAS REMOVED AND THE ENGINE SHUTDOWN. THE START CONTACTOR WAS STUCK CLOSED. - STARTER GENERATOR REPLACED. - GENERATOR CO	ANTROL UNIT REPLACED. - START CONTACTOR REPLACED.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2001110800007	20011108	00007	EU  	2001	11	8	CA011023001      	1	20011016	G	7700	9752902015	DISPLAY         	            	            	PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DISPLAY	                	W			    	K	 	 	 	NONE                    				O	 	 	OTHER                     			LD	LANDING        	1			CA		 				062					(CAN) EIS DISPLAY LIGHTING IS VERY DIM, BARELY READABLE.IT WAS ALSO INTERMITTENTLY FLASHING FROM BRIGHT TO DIM.  ACQ DIS	PLAY REPLACED WITH ASERVICEABLE UNIT. A/C TIME SINCE NEW 435.2 CYCLES SINCE NEW 493 THE ACQUISITION DISPLAY HAS 135.3 HO	URS.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011600010	20020116	00010	EU  	2002	1	16	CA011023002      	1	20011017	G	7700	9752902015	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA						018					(CAN) LOWER HALF OF EIS PANEL WOULD GO BLANK INTERMITTENTLY. TORQUE ITT, NG AND FUEL INDICATION TAPES REMAINED NORMAL.  	ALL OTHER INSTRUMENTS WERE AFFECTED, EITHER FLASHING, DISAPPEARING TOTALLY AND/OR INDICATING ERRONEOUS INFORMATION.YELLO	W AND RED CAUTION LIGHTS WOULD INNUMINATE.  WHEN "MENU" WAS SELECTED, THE TOP ROW WOULD GO BLANK AS PER NORMAL, BUT THE 	TRANSFERRED INFORMATION WOULD NOT SHOW UP ON THE ALTERNATE SCREENS.WHEN "TEST" WAS DEPRESSED EVERYTHING TESTED NORMAL.  	PANEL WOULD RETURN TO NORMAL AFTER SUBSEQUENT POWER UPS.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011600011	20020116	00011	CE  	2002	1	16	CA011023003      	1	20011015	G	3230	08411102	LINK            			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	LTSIO520AE  	17040	SO  					MLG	SHEARED         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			10000								(CAN) DURING CROSS WIND LANDING APPEARENT SIDE LOAD ON LT MAIN U/C STRUT CAUSED THE THREADED PORTION OF THE LINK ASSEMBL	Y TO SHEAR ALLOWING GEAR TO RETRACK.  LT PROPELLER BLADES STRUCK GROUND PILOT APPLIED POWER AND ABORTED LANDING. AFTERBU	RNING OFF FUEL. ATTEMPTED TO RECYCLE GEAR, NOSE AND RT GEAR INDICATED LOCKED LT INDICATED UNLOCKED. WHEN GEAR WAS RECYCL	ED LT GEAR FREE FELL INTO LOCKED POSITION AND A/C LANDED WITHOUT FURTHER DAMAGE.			1	L	7	2 	3O	3	O	RT	A7CE    	E8CE				 
2002011600013	20020116	00013	EA  	2002	1	16	CA011025002      	1	20010614	G	2910	DSC152D8025426	HOSE            			DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	HYD SYSTEM	MISMARKED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A HYDRAULIC HOSE, P/N DSC152D8-0254-260 WAS ORDERED FROM THE COMPANIES STORES DEPARTMENT.  THE INFORMATION ON THE 	PACKAGING INDICATED 3000 PSI WORKING PRESSURE.THE INFORMATION BAND CRIMPED AROUND THE HOSE INDICATED 1000 PSI WORKING PR	ESSURE.  THE HOSE, ALONG WITH 3 OTHERS IDENTIFIED THE SAME WAY WERE RETURED TO THE SUPPLIER.THE SUPPLIER NOTIFIED THE HO	SE MANUFACTURER, AND CHECKED THIER STOCK FOR LIKE HOSES.THE SUPPLIER INDICATED THAT AFTER A SEARCH, ONLY THE FOUR HOSES 	IN QUESTION WERE MISLABLED.		2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE	 
2002011600015	20020116	00015	GL  	2002	1	16	CA011026001      	1	20010717	G	3297	4533516	WIRE            			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340AN1    	52016	NE  					MLG INDICATOR	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR PIN WAS NOT SHOWING ALL THE WAY DOW	N. ALL OTHER GEAR INDICATIONS WERE NORMAL.  (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING	 GEAR INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END.  THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREF	ORE GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED.			1	L	7	1 	3R	3	R	 	EXPA1L71	5E2				 
2002020800001	20020208	00001	GL  	2002	2	8	CA011026002      	1	20010717	G	3260	4533516	CABLE           			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340AN1    	52016	NE  					MLG INDICATOR	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR WAS NOT SHOWING ALL THE WAY DOWN. A	LL OTHER GEAR INDICATIONS WERE NORMAL.  (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING GEA	R INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END.  THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREFORE 	GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED.			1	L	7	1 	3R	3	R	 	EXPA1L71	5E2				 
2002020800002	20020208	00002	GL  	2002	2	8	CA011026003      	1	20010717	G	3260	4533516	CABLE           			NAMER 	T6    	HARVARDMK4  	1922828	GL  	PWA   	R1340 	R1340AN1    	52016	NE  					MLG INDICATOR	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA											(CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR WAS NOT SHOWING ALL THE WAY DOWN. A	LL OTHER GEAR INDICATIONS WERE NORMAL.  (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING GEA	R INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END.  THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREFORE 	GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED.			1	L	7	1 	3R	3	R	 	EXPA1L71	5E2				 
2002011600016	20020116	00016		2002	1	16	CA011026004      	4	20010828	G	3460	KFC295	COMPUTER        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					FLIGHT DIRECTOR	MALFUNCTIONED   	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) PILOT REPORTED THE INABILITY TO CANCEL THE 'FD' FLIGHT DIRECTOR ANNUNCIATOR LIGHT ON THE AUTOPILOT ANNUNCIATOR PAN	EL. COMMAND BARS ON ADI WOULD NOT DROP OUT OF VIEW. FLIGHT DIRECTOR COMPUTER REMOVED AND REPAIR.					1	L	7	2 	3O	3	O	RT	3A16    	3E1				 
2002011600017	20020116	00017	SO  	2002	1	16	CA011029001      	1	20011014	G	3210	14445	BALL JOINT      			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					TORQUE LINK	DAMAGED         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) ON ROLL OUT FOLLOWING LANDING THE BALL JOIINT ASSEMBLEY PULLED OUT OF THE UPPER TORQUE LINK. THIS CAUSED THE RIGHT	 MAIN WHEEL TO TURN 180 DEGREES. REPAIRS REQUIRED THE REPLACEMENT OF BOTH THE UPPER TORQUE LINK AND THE BALL JOINT ASSEM	BLY				1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002011600018	20020116	00018	CE  	2002	1	16	CA011029003      	1	20010915	G	5510	26320273	SUPPORT         	CESSNA      		CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION, WHEN THE HORIZONTAL STABALIZER WAS REMOVED TO CARRY OUT A REPLACEMENT OF A SPAR CAP. 	CORROSION (PITTING) WAS NOTED IN ONE OF THE FORWARD SUPPORTS AND BOTH OF THE AFT SUPPORTS. NO DAMAGE IS ALLOWED TO CASTI	NGS OR FITTINGS. 3 OF THE 4 ATTACH SUPPORTS REQUIRED REPLACEMENT AS PER FACTORY RECOMMENDATION.				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600019	20020116	00019	CE  	2002	1	16	CA011029005      	1	20010915	G	5343	26111379	FITTING         			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION PITTING WAS NOTED ON BOTH OF THE FORWARD AND BOTH OF THE AFT LANDING GEAR  ATTACH FITT	INGS. WHILE ATTEMPTING TO REMOVE THIS CORROSION THE DAMAGE WAS FOUND TO BE TOO SEVERE TO ATTEMPT. THE LANDING GEAR WAS R	EMOVED AND MORE CORROSION WAS NOTICED IN THE AREA THAT THE GEAR ATTACHES TO THE FITTING. ALL FOUR MAIN LANDING GEAR FITT	INGS WERE REPLACED AS PER VERBAL INSTRUCTIONS FROM FACTORY TECH. REP.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600020	20020116	00020	CE  	2002	1	16	CA011029006      	1	20010915	G	2731	26612151	ACTUATOR        			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	ELEVATOR TRIM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AN ANNUAL INSPECTION ON THIS CESSNA CARAVAN THE ELEVATOR TRIM JACKS WAS NOTED TO HAVE SIGNIFICANT	 CORROSION ON SEVERAL OF THE PARTS. THE FOLLOWING PARTS REQUIRED REPLACEMENT HOUSING P/N 2661215-2/BEARINGS P/N 6361620-	6 AND MS27641-66/PINS P/N MS35675-12/ROD ENDS P/N S2629-1. THESE TRIM ACTUATORS HAD BEEN SIGNED AS INSPECTED LESS THAN 1	00 HOURS PRIOR TO THIS FINDING.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600021	20020116	00021	CE  	2002	1	16	CA011029007      	1	20010915	G	5347	261106014	SEAT TRACK      			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AN ANNUAL INSPECTION THE AREA AT THE AFT END OF NR 2 / 3 / 4 SEAT RAIL UNDER THE FLOOR AT FS 283.	85 WAS NOTED TO HAVE SEVERE CORROSION ON THE STIFFENER P/N 2611131-3 AND THE DOUBLERS P/N 2611192-4 AS WELL AS THE SEAT 	RAIL. THE CORROSION WAS CLEANED AS REQUIRED FROM THE STRUCTURE AND SEAT RAILS NR 2 AND NR 4. THE STIFFENER, DOUBLERS AND	 NR 3 SEAT RAIL, AS WELL AS THE ATTACHING HARDWARE WAS REPLACED.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600022	20020116	00022	CE  	2002	1	16	CA011029008      	1	20010915	G	5550	263440221	HINGE           			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	EMPENNAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, EXCESSIVE MOVEMENT WAS NOTED FROM THE OUTBOARD AND CENTRE 	HINGE BEARINGS FOR THE R/H ELEVATOR. WHEN THE HINGE SUPPORTS WERE DISMANTLED TO REPLACE THE BEARINGS, CORROSION WAS FOUN	D ON BOTH HALVES OF THE INBOARD AND CENTRE HINGE SUPPORTS. THE HINGE SUPPORTS AS WELL AS THE BEARINGS WERE REPLACED AS P	ER FACTORY RECOMMENDATION.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600023	20020116	00023	CE  	2002	1	16	CA011029009      	1	20010915	G	5312	2612591	BULKHEAD        			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION ON THIS AIRCRAFT AN AREA OF CORROSION WAS FOUND ON THE AFT CANTED BULKHEAD AT STATION 	427.88 AFT LEFT WL 1 OR 2 INCHES OFF CENTRE. THE CORRORION WAS REMOVED AND THE DAMAGE WAS FOUND TO BE THROUGH 50 PERCENT	 OF THE MATERIAL. THE AFT BULKHEAD WASREPLACED PER THE 208 S.R.M.				1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600024	20020116	00024	CE  	2002	1	16	CA011029010      	1	20010915	G	5511	26320233	SPAR CAP        			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN ANNUAL INSPECTION OF THIS AIRCRAFT, SEVERE CORROSION WAS NOTED ON THE AFT UPPER TRAILING EDGE SPAR CAP O	N THE HORIZONTAL STABILIZER AT APPROXIMATELY SS 80.60 LEFT HAND AND ARIGHT HAND SIDES. THE CORROSION HAS GONE THROUGH TH	E SPAR CAP BUT HAD NOT YET DAMAGED THE WEB. THIS CORROSION WAS NOT INITIALLY NOTICED DUE TO THE FACT THE CORROSION HAD B	EEN PAINTED OVER THE ENTIRE SPAR CAP WAS REPLACED.			1	H	7	1 	3T	3	T	NT	A37CE   	E4EA	5	C	P60GL	 
2002011600025	20020116	00025	EU  	2002	1	16	CA011029011      	1	20011015	G	6520	770441	CARBON SEAL     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR GB	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING A GROUND RUN ON OIL LEAK WAS DETECTED FROM THE TAIL ROTOR GEAR BOX. AIRCRAFT WAS SHUT DOWN LEAK INVESTIGATE	D. OIL LEAK FROM INPUT MAG SEAL. SEAL AND HOUSING REMOVED. THE STATIONARY PORTION OF SEAL FOUND TO HAVE MULTIPLE CRACKS.	 MAG SEAL WAS PREVIOUSLY REMOVED DUE TO SMALL LEAK. SEAL WAS "RE-SEATED" AND REINSTALLED. POSSIBLE CAUSE WAS INCORRECT I	NSTALLATION OF SEAL.A NEW CARBON MAG SEAL WAS INSTALLED. AIRCRAFT WAS GROUND RUN AND NO FURTHER LEAK PRESENT.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011600026	20020116	00026	CE  	2002	1	16	CA011029012      	1	20010802	G	5550	07321008	HINGE           	CESSNA      	07326004    	CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION FOUND LT OUTBOARD ELEVATOR BEARING LOOSE. REMOVED LT ELEVATOR TO CHANGE BEARING. WITH E	LEVATOR REMOVED, FOUND LT OUTBOARD HINGE ASSEMBLY TO BE CORRODED AND CRACKED WHERE BEARING IS INSTALLED.					1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002011600027	20020116	00027	EA  	2002	1	16	CA011029013      	1	20011012	G	2560		RING            		4494701     	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					SEAT BELT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION LOCATED UNDER THE ('D' RING) WHERE SEAT BELT WEBBING CONTACTS ALUMINIUM D-RING.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002011600028	20020116	00028	NE  	2002	1	16	CA011029014      	2	20011009	G	8520	128511	CONNECTING ROD  			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HARTZL	HCB3R	HCB3R304    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE IN CRUISE AT 2,000 FEET A LOUD REPORT WAS HEARD FROM THE ENGINE. FOLLOWED WAS EXTREME ENGINE VIBRATION. POWE	R WAS REDUCED TO IDLE. THE AIRCRAFT WAS LANDED. UPON INVESTIGATION IT WAS DETERMINED THAT NR 5 AND NR 1 CONNECTING RODS 	WERE BROKEN. ENGINE CHANGED.				1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P28EA	 
2002011600029	20020116	00029	NE  	2002	1	16	CA011029015      	2	20011003	G	8530		CYLINDER HEAD   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN1     	52008	NE  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		CR	CRUISE         	1			CA											(CAN) CYLINDER HEAD CRACKED.						1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002011600030	20020116	00030	EU  	2002	1	16	CA011029016      	1	20011005	G	5302	350A23002021	SKIN            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A 6 INCH LONG CRACK FOUND ON TAILBOOM FWD UPPER SKIN UNDER N5 BEARING MOUNT SUPPORT AT BOOM STA A868. TAILBOOM INS	T IN EUROCOPTER APPRD AS350/355 TAILBOM REPAIR FIXTURE FOR REPL OF UPPER SKIN&FOUND N5SUPPORT HAD BADLY MISALIGN TO FIXT	URE: N5 BEARING MOUNT SUPPORT HAD BEEN PREV REPL IN FIELD BY OPERATOR PER EUROCOPTER AS350 REPAIR MANUAL CHAPT 53.10.40.	773.A 2ND TAILBOOMN FOUND WITH SIMILAR DEFECT, ALSO N 5 BEARING MOUNT SUPPORT HAD BADLY MISALIGN TO FIXTURE: N5 BEARING 	MOUNT SUPPORT HAD BEEN PREV REPL IN FIELD.WE FEEL THAT MAIN REASON SKIN CRACKED MISALIGNMENT OF #5 BEARING MOUNT WHICH R	EPL IN FIELD W/O USE OF FIXTURE:	1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002011600031	20020116	00031	EU  	2002	1	16	CA011029017      	1	20011025	G	6520	350A33105803	LEVER           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE TAIL ROTOR CONTROL LEVER MAYBE THE SAME AIRFRAME TIME BUT WE ARE NOT 100 PERCENT SURE. THE TAILROTOR CONTROL L	EVER HAD A DEFECT OF WEAR ON INSIDE EAR. UPON REMOVAL MAINTENANCE ENGINEER FOUND CRACKS IN THE WEBBING, TOP SIDE AT T/R 	SPIDER ATTACHMENT POINT.				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011600034	20020116	00034	EU  	2002	1	16	CA011029020      	1	20010514	G	6410	355A12004008	SKIN            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					T/R BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 131 MM CRACK ORIGINATING FROM THE RIVET HOLE FOR THE TRAILING EDGE TAB ON BOTH THE UPPER AND LOWER SURFACE.SDR NO.	 20010112018 AND 2019 ADDRESSES THIS SAME DEFECT.SINCE DISCOVERY OF THIS DEFECT EUROCOPTER FRANCE HAS ISSUED INFO TELEX 	00000035 REQUIRING A BEFORE FLIGHT/BETWEEN FLIGHT /AFTER FLIGHT AN 500 HOUR/24 MONTH INSPECTION OF THIS AREA FOR CRACKIN	G.			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002011600035	20020116	00035	SO  	2002	1	16	CA011030001      	1	20011004	G	5713	6208603	STRINGER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					WING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FLANGES AT END OF STRINGER ARE CRACKING. EVENTUALLY THE ENTIRE END OF STRINGER WILL SEPARATE. EACH WING HAS TWO ST	RINGERS ON INBOARD BOTTOM SKIN. BOTH ARE BROKEN ON THE RIGHT WING. LEFT WING IS OKAY. IT IS VERY DIFFICULT TO INSPECT TH	IS AREA ON NEWER PA28'S. IT IS TOTALLY IMPOSSIBLE ON OLDER PA28'S DUE TO LACK OF INSPECTION PANEL.I HAVE SEEN THIS BEFOR	E, ABOUT TWO YEARS AGO. BUT, IT WAS ON A PA34-200 TWIN. IT LOOKED LIKE AN ONE TIME EVENT, PECULIAR TO THAT AIRCRAFT. NOW	 I SEE IT AGAIN ON A SIMILAR WING BUT, IT HAS CROSSED MODEL LINES.#11 PART AVAILABLE. "NO", BUT PICTURES WERE TAKEN WITH	 A DIGITAL CAMERA. THEY ARE IN MY COMPUTER AND CAN BE E-MAILED IF YOU WISH.	1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002011600036	20020116	00036	EA  	2002	1	16	CA011030002      	1	20011016	G	5311	C6FSM142236	FRAME           			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN SIDE FRAME AT RT. STATION 218.125 RUNNING ON AN ANGLE FROM TOP OF FRAME. NOTE PART IS POST MOD 6/14	62 AS DIRECTED BY CF-78-17R1. DHC SB 6/371 REV.B.PLEASE SEE PHOTOS.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002011600037	20020116	00037	SO  	2002	1	16	CA011030003      	1	20011015	G	2912	AN62341	FILTER HOUSING  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENG FIRE WALL	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA											(CAN) THE PILOT REPORTED THAT THE LANDING GEAR WOULD NOT EXTEND WHEN SELECTED DOWN. THE EMERGENCY HAND PUMP SUCCESSFULLY	 EXTENDED THE GEAR TO INDICATE 3 GREEN. LOW HYDRAULIC FLUID LEVEL WAS FOUND TO BE THE CAUSE OF THE PROBLEM DUE TO A CRAC	K IN THE THREADS OF THE RT HYDRAULIC FILTER BOWL. THE CRACK IS MOST LIKELY CAUSED BY OVER TIGHTENING THE BOWL, ALTHOUGH 	IT HAD BEEN IN PLACE 32.5 HOURS BEFORE THE GEAR PROBELM OCCURRED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011600038	20020116	00038	SO  	2002	1	16	CA011030004      	1	20011015	G	2140	A07D32	SWITCH          	JANITROL    	B4050       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HEATER	OVERHEATED      	W				F	A			ACTIVATE FIRE EXT.      	UNSCHED LANDING         			B	I		SMOKE/FUMES/ODORS/SPARKS  	FLT. ATTITUDE INST.       		CR	CRUISE         	1			CA						4B11145					(CAN) THE AIRCRAFT WAS IN LEVEL FLIGHT. THE AFT HEATER WAS BROUGHT ON LINE. A SHORT TIME LATER, THE PASSENGERS NOTED SMO	KE AND SPARK'S COMING FROM THE OUTLET. THE HEATER WAS SHUT DOWN AND THE CABIN FIRE EXTINGUISHER WAS DISCHARGED INTO THE 	INLET. THE AIRCRAFT LANDED AND MAINTENANCE DISCOVERED THE CYCLE SWITCH HAD MALFUNCTION.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011600039	20020116	00039	CE  	2002	1	16	CA011030005      	1	20011009	G	5743	082210045	BRACKET         	CESSNA      		CESSNA	401   	401B        	207590E	CE  	CONT  	O520  	TSIO520EB   	17040	SO  					MLG	CRACKED         	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CA											(CAN) DURING RETRACTION OF GEAR AFTER TAKEOFF PILOT HEARD A BANG. UPON LANDING AT BASE THE AIRCRAFT WAS INSPECTED AND TH	E RT FORWARD GEAR DOOR HINGE BRACKET WAS FOUND TO BE CRACKED.					1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002011600041	20020116	00041	GL  	2002	1	16	CA011030007      	2	20011009	G	7250	A23037403	SHAFT           								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS TURBINE WAS RECD FOR ROUTINE SCHED MAINT. THERE WAS NO SERVICE COMPLAINT. ON DISASSY, TURBINE PT ROTOR NUT FO	UND UNTHREADED FROM PT INNER SHAFT. SCORING EVIDENCE ON THE PT INNER SHAFT INDICATES NUT UNTHREADED DURING OP. NUT HAD B	EEN STAKED AT 2 PLACES DURING ASSY. LOCKING DIMPLES ON PMA PT INNER SHAFT APPEAR UNDERSIZED WHICH PREVENTS PROPER  LOCKI	NG OF NUT ASSY. WHEN NUT UNTHREADED, CLAMPING LOAD BETWEEN NR 3 & NR 4 TURBINE WHEELS WAS COMPROMISED. AS A ARESULT, CUR	VIC COUPLES ON TURBINE WHEELS SHOW EVIDENCE OF MOVEMENT & FRETTING. TIME ON TURBINE IS AS FOLLOWS:TSN: 10494.0 HRS, TSO:	 3476.2 HRS NOTE: PT INNER SHAFT IS A PMA PART.						3	U			E4CE				 
2002011600042	20020116	00042	EU  	2002	1	16	CA011031001      	1	20011030	G	3397		WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	LT WING STROBE	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA											(CAN) DURING CRUISE, THE STROBE LIGHT CIRCUIT BREAKER POPPED.  THE CIRCUIT BREAKER WAS NOT RESET IN FLIGHT. INVESTIGATIO	N REVEALED A CHAFED WIRE (P/N L08E20) IN THE LEFT HAND WING.  THE WIRE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE	.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011600045	20020116	00045	EU  	2002	1	16	CA011031005      	2	20011019	G	8520	861115	DIAPHRAGM       			DIAMON	DA20  	DA20A1      	2990000	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					CYLINDER	SWOLLEN         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 200 HR INSP OIL FOUND BETWEEN NR 1 & 3 CYLINDERS. COMPRESSION CHECK CARRIED OUT TO DETERMINE CYLINDER THAT 	PRODUCING OIL. BOTH CYLINDERS PRODUCED NORMAL COMPRESSION READINGS. WHEN BOTTOM SPARK PLUGS WERE REMVD ONE FROM CYLINDER	 NR 3 FOUND TO HAVE EVIDENCE ON BURNED OIL. NR 3 CYLINDER ASSY & PISTON REMVD. PISTON HEAD COVERED IN BURNED OIL RESIDUE	. PISTON HEAD HAD ALSO HAD SMALL PORTIONS OF ITS SURFACE CHIPPED AWAY. DURING THE PREVIOUS INSP (50 HR) NR 1 CYLINDER AS	SY & PISTON WERE REPL. IT BELIEVED THAT FAILURE OF NR 1 PISTON RESULTED FROM FAILURE OF PISTON RING.		1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I				 
2002011600065	20020116	00065	SW  	2002	1	16	CA011031012      	1	20011018	G	2750	12395	PULLEY          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					FLAP SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - LT & RT PULLEYS INBOARD & OUTBOARD ALL FOUND WORN.- LT & RT CABLES FRAYED UNSERVICEABLE AND REPLACED. - CABLES F	RAYED AT PULLEYS ON OUTBOARD POSITION.- SOLID ALUMINUM PULLEYS WITH SMALL RADIUS AND SEIZE EASILY CAUSING EXCESSIVE CABL	E WEAR.				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002011600066	20020116	00066	SO  	2002	1	16	CA011031013      	1	20011004	G	3213	4033600	LINK            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      	 	EA  					NLG DRAG BRACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON INSPECTION, A CRACK WAS FOUND AT NOSE GEAR LINK ATTACH POINT.						1	L	7	2 	3T	4	T	 	A8EA    	E4EA				 
2002011600067	20020116	00067	SO  	2002	1	16	CA011031014      	1	20011006	G	7120	4000707	MOUNT           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	LT & RT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF THE ENGINE MOUNT FOUND CUT MARKS ON LOWER TRUSS MEMBERS OF THE MOUNT. AFTER SOME INVESTIGATIO	N FOUND THAT THE CUTS WERE MADE BY COWL FLAPS OF RESPECTIVE ENGINES. NO EVIDENCE OF COWL FLAP MISRIGGING OR DAMAGE ON CO	WL FLAPS. THE WEAR MARKS FOUND WERE ABOUT 1/2 THE WALL THICKNESS OF TUBES. TUBES WERE REPAIRED IAW AC43-13 AND AIRCRAFT 	RETURNED TO SERVICE.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011600082	20020116	00082	SO  	2002	1	16	CA011031015      	1	20011006	G	5414	4166300	SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENG NACELLES	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION NOTICED SMOKING & LOOSE RIVETS AROUND INBOARD SIDE OF LT AND RT ENGINE NACELLE JUST AFT OF FIREW	ALL. REMOVED LOWER ACCESS PANEL AND FOUND THAT BOTH LT & RT INBOARD NACELLE PLATES P/N 41663-00 (LT) AND 41663-01 (RT) W	ERE CRACKED FROM L/E OF PLATE TO AFT END. THIS PLATE CREATE A WRAP AROUND L/E SKIN AND ATTACHES NACELLE STRUCTURE TO SKI	N. PART REQUIRED TO BE REPLACED SINCE THERE IS NOT MUCH ROOM TO BE REPAIRED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002011600085	20020116	00085	CE  	2002	1	16	CA011031016      	1	20011011	G	2823	1013890255	SHUTOFF VALVE   			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					BOOST PUMP	STUCK           	W				D				RETURN TO BLOCK         				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA											(CAN) PILOT CLOSED THE VALVE, BOOST PUMP ON, LOW FUEL PRESSURE LIGHT WENT OFF, MEANING THE FUEL IS LEAKING BY THE VALVE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002011600086	20020116	00086	GL  	2002	1	16	CA011031017      	1	20011005	G	6520	28135255R	GEARBOX         			ENSTRM	F28   	280         	3300502	GL  	LYC   	O360  	HIO360C1A   	41514	EA  					TAIL ROTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE 100 HOUR INSPECTION OIL DRAINED FROM T/R GEARBOX, FOUND EXCESSIVE SLUG & METAL PARTICLES ON CHIP DR	AIN PLUG. FLUSHED GEARBOX. ADDED FRESH OIL. DISCONNECT INPUT SHAFT & ROTATED INPUT GEAR WITH T/R ATTACHED TO OUTPUT SIDE	. NOISE NOTED FROM INPUT SIDE OF GEAR. ASSEMBLY REMOVED FROM SERVICE AND RETURNED TO ENSTROM FOR WARRANTY AND EVALUATION	. REPORT OF FINDINGS REQUESTED.			1	G	7	1 	3O	3	O	 	H1CE    	1E10				 
2002011600087	20020116	00087	CE  	2002	1	16	CA011031018      	1	20010928	G	2842		TRANSMITTER     			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	FUEL INDICATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH LT AND RT SENDING UNITS FOUND SEVERELY CORRODED WITH CORROSION DEBRIS IN TANKS. ALUMINUM 3/8 INCH FUEL LINES 	FROM TANKS TO TRANSFER PUMPS WRE ALSO FOUND CORRODED.					1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011600088	20020116	00088	CE  	2002	1	16	CA011031019      	1	20010928	G	5751	122008516	SKIN            			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 7 OUT OF 11 SCREW HOLES FOR MOUNTING BALANCE WEIGHT FOUND CRACKED.  LT AILERON INSPECTED AND ONE CRACK FOUND.						1	H	7	1 	3O	3	O	 	A4CE    	E5CE	5	C	P47GL	 
2002011600089	20020116	00089	NE  	2002	1	16	CA011031021      	1	20011031	G	5551		ATTACH FITTING  			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  					HORIZONTAL STAB	MISMANUFACTURED 	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AD 98-10-12, HORIZONTAL STAB ATTACHMENT FITTING NO OF NEW CUSTOMERS A/C HAVE BEEN INSPECTED AT COMPANY & ARE NOT I	N COMPLIANCE WITH AD, ALTHOUGH ITS BEEN PREVIOUSLY SIGNED OFF. MOST INSPECTIONS REVEAL THAT CLEARANCE I S LESS THAN THE 	REQUIRED 5/32 INCH.  OTHER A/C HAVE HAD FITTING RADIUS REWORKED INSTEAD OF DOUBLER FLANGE.COMPLIANCE IS ALSO BEING ACCOM	PLISHED W/O REMOVAL OF STAB FOR FITTING INSP, AS EVIDENT IN REWORK WHICH I S CAUSING GOUGING & MORE DAMAGE TO SPAR DOUBL	ER&FITTING RADIUS. VISUAL & L. P. INSPECTIONS ARE ALSO NOT COMPLETED ON FITTING RADIUS TO DOUBLER MATING SURFACES. MANY 	A/C ARE STILL CONSIDERED AIRWORTHY & ARE NOT IN COMPLIANCE.	1	H	7	1 	3O	3	O	 	1A13    	1E10				 
2002011600090	20020116	00090	SO  	2002	1	16	CA011031024      	1	20011005	G	3020	86245834	HEATER          			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					CARBURETOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE ENGINE INSPECTION OF THE LT ENGINE, THE CARB AIR BOX WAS FOUND BROKEN AT THE HEATED AIR INTAKE PI	PE. THE COMPLETE CIRCUMFERENCE OF THE WELD ON THE RT END OF THE BOX HAD BROKEN. THE ONLY REASON THE PART STAYED WITH THE	 AIRCRAFT WAS THE CLAMP ON THE HOSE CONNECTING IT TO THE HEAT INTAKE SHROUD. THE PART WAS REMOVED FOR REPAIR. A SECOND A	IRCRAFT WAS FOUND TO HAVE THE SAME PROBLEM. THE PILOT'S WHO FLY THE AIRCRAFT WERE INFORMED THAT IF THEY DO NOT GET A DRO	P IN RPM WHEN SELECTING CARB HEAT DURING THEIR RUN-UP NOTIFY MAINTENANCE AND A CHECK OF THE CARB HEAT SYSTEM WILL BE CAR	RIED OUT.	1	L	7	2 	3O	3	O	 	A19S0   	E286				 
2002011600091	20020116	00091	EU  	2002	1	16	CA011031025      	1	20011005	G	7120	L24263100000	MOUNT           			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION A CRACK WAS FOUND ON THE UPPER RT MOUNT WEB. THE MOUNT WAS REMOVED FOR FURTHER INSPEC	TION AND IT WAS NOTICED THAT THE CRACK WAS ABOUT 1 INCH IN LENGTH. MAINTENANCE HAS BEEN INSTRUCTED TO PAY SPECIAL ATTENT	ION TO THIS AREA DURING 50 AND 100 HOUR INSPECTIONS FOR ANY SIGN OF STRESS OR TINY CRACKS.NOTE: ILLUSTRATION ATTACHED.				1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002011600092	20020116	00092	SW  	2002	1	16	CA011031026      	1	20010928	G	5302	205032821023	BULKHEAD        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					TAILBOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A SCHEDULED MAINTENANCE INSPECTION THE CRACK WAS DISCOVERED. HEADQUARTERS HAS RECEIVED THE PARTICULARS AND 	IS PREPARING A REPAIR SCHEME.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002011600093	20020116	00093	CE  	2002	1	16	CA011031027      	1	20011031	G	3246	16218000	WHEEL           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEEL HALF WAS REMOVED DUE TO CUTS IN THE RUBBER.  UNIT DISASSENBLED AND DYE PEN INSPECTED.  CRACK INDICATIONS WER	E FOUND ON THE INSIDE OF THE OUTER WHEEL HALF. UNIT SCRAPPED OUT PART TIME AND CYCLES ARE UNKNOWN.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011600127	20020116	00127	EA  	2002	1	16	CA011101011      	1	20011015	G	5410	601350061	WEB             			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					SUPPORT BEAM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TWO CRACKS FOUND ON ENGINE SUPPORT BEAM AT THE LOWER WEB FS 630, LBL 36, RBL 36 WHILE PERFORMING SB A601R-53-059. 	AREA TO BE REPAIRED IAW REO 601R-53-61-361.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002011600128	20020116	00128	CE  	2002	1	16	CA011101012      	1	20011031	G	3260	903610373	DOWNLOCK SWITCH 			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HIGH RESISTANCE (2.9 OHM) ENCOUNTERED ON CONTACTS AT CONNECTOR A210 PI PINS D TO E WHILE DOING PHASE 1 INSPECTION 	DUES ITEM CAMP CARD 321171 (CONTINUITY CHECK R/H DOWNLOCK MICRO SW) MICRO SW REPLACED AND RETRACTION TEST CARRIED OUT.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002011700001	20020117	00001	SO  	2002	1	17	CA011102002      	1	20011018	G	5553	9556300	SPAR            			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					VERICAL STAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FAILURE OF RIVETS SECURING LOWER 4 INCHES OF SPAR FLANGES TO FITTING P/N 63501-00. FOUR RIVETS HAD FAILED ON LT SI	DE AND ONE RIVET FAILED ON RT SIDE.					1	L	7	2 	3O	3	O	 	A7SO    	1E10				 
2002011700002	20020117	00002	EU  	2002	1	17	CA011102003      	1	20011017	G	6220	350A37124520	SCREW           	AEROSP      	355A31000109	SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARFLEX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M1429					(CAN) DURING REPLACEMENT OF STARFLEX, DISCOVERY OF ONE OF TWELVE BOLT FOUND BROKEN. PRESENCE OF RUST ON THE BROKEN SECTI	ON, SHOWS THAT THE DEFECT OCCURRED A LONG PERIOD BEFORE DISCOVERY.BECAUSE OFTHE DESIGN OF THE HEAD, THERE WAS NO POSSIBL	E WAY TO LOSE ANY PART. NOTE THAT RETIREMENT OF STARFLEX AND BROKEN SCREW IS 2200 HOURS.ATTACHMENT SCREW P/N 350A37-1245	-20, S/N 28998			1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2002011700003	20020117	00003	WP  	2002	1	17	CA011102005      	1	20010815	G	7921	C1861	HUB             			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					COOLER FAN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PART C186-1 FOUND CRACKED WHILE REPLACING MICROSWITCH V3-1001. THE FAN WAS REMOVED AND THE HUB WAS FOUND CRACKED. 	THE FAN SHAFT ASSEMBLY C007-5 WAS CORRODED. THE FAN TORQUE WAS FOUND ACCEPTABLE (450-550 FT LBS).\PIECE C186-1 WAS REPLA	CED AND THE FAN SHAFT C007-5 WAS RETURNED TO ROBINSON FOR OVERHAUL. THE SECOND PROBLEM WAS REPORTED ON 3 OTHER HELICOPTE	RS IN THE LAST 2/3 YEARS. THE THIRD ONE WAS FOUND CRACK FREE BUT CORRODED.			1	G	7	1 	3O	3	O	 	H11NM   	E295				 
2002011700004	20020117	00004	EA  	2002	1	17	CA011102006      	2	20010506	G	8530		SPRING          			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C218   	GL  	INTAKE VALVE	BROKEN          	W				A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN) ENGINE VIBRATION WHILE IN FLIGHT. AFTER INSPECTION, THE NR 2 ENGINE CYLINDER WAS FOUND WITHOUT COMPRESSION. THE AD	MISSION VALVE WAS FOUND INOPERATIVE. A NEW CYLINDER WAS INSTALLED AND SUCCESSFUL ENGINE TESTS WERE CARRIED OUT. THE CYLI	NDER WAS SENT TO A REPAIR SHOP FOR INSPECTION AND REPAIR (INTAKE VALVE SPRING BROKEN).				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2002011700005	20020117	00005	CE  	2002	1	17	CA011102007      	1	20010731	G	2720	031019613	SPRING          			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					RUDDER CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A PRE-FLIGHT INSPECTION, THE PILOT SAW THE RUDDER TURNED WHILE THE FRONT WHEEL WAS STRAIGHT AND THE PEDALS 	WERE OFF-CENTERED. AN INSPECTION DETERMINED THE RIGHT SPRING WAS MISSING AND FOUND BELOW IN THE FUSELAGE.					1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002011700006	20020117	00006	EA  	2002	1	17	CA011102008      	2	20010802	G	8510	LW14675	CRANKCASE       			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	2D34C	B2D34C214   	GL  	ENGINE	CRACKED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) THE PILOT NOTICED AFTER AN HOUR OF FLIGHT THAT THE OIL PRESSURE WAS DROPPING. HE PERFORMED A PRECAUTIONARY LANDING	 ON THE ROAD WITHOUT ANY PROBLEM. AFTER INSPECTION OF THE ENGINE, A CRACK WAS FOUND ON THE ENGINE BLOCK BETWEEN NR 1 AND	 3 CYLINDERS. THE ENGINE WAS REMOVED AND SENT TO A REPAIR SHOP.				1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	P7EA	 
2002020800006	20020208	00006	CE  	2002	2	8	CA011102009      	1	20011031	G	2720	031019613	SPRING          			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS IS SECOND OCCURANCE OF SAME DEFECT IN 1205 HRS/18 MONTHS.  HAS ALSO OCCURED ON OTHER 152 IN OUR FLEET.  OBSER	VED DURING WALK-AROUND BY NEXT PILOT (RUDDER SWINGS FREELY WITHOUT NORMAL RESISTENCE). OUR AMO SAYS THAT BROKEN SPRING C	OULD INTERFERE WITH FLIGHT CONTROLS DURING FLIGHT.				1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002011700007	20020117	00007	CE  	2002	1	17	CA011105001      	1	20011031	G	7810	265400610	FLANGE          			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	EXHAUST SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE EXHAUST FLANGE WAS FOUND CRACKED AT THE FORWARD RADIUS IN 3 SPOTS. THERE IS A HOLE IN THE FLANGE THAT LINES UP	 WITH THE THREADS OF A BOLT FROM THE OIL COOLER. THIS HOLE DID NOT LINE UP WITH THE BOLT AND PRODUCED STRESS ON THE FLAN	GE RESULTING IN THE CRACKS. THE FLANGE WAS REPLACED AND THE BOLT FROM THE OIL COOLER WAS SHORTENED SO IT DOES NOT INTERF	ERE WITH THE FLANGE.			1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011700008	20020117	00008	SW  	2002	1	17	CA011105002      	1	20010925	G	6320	206040526001	TUBE            	BELL        	206040004101	BELL  	206   	206L        	1181522	SW  	ALLSN 	25OC  	250C20R     	 	GL  					TRANSMISSION	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BMC45132					(CAN) DURING TRANSMISSION 1500 HOUR INSPECTION CORROSION AND PITTING FOUND ON THE FLARE OF THE TUBE ASSEMBLY.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011700009	20020117	00009	SW  	2002	1	17	CA011105003      	1	20010921	G	2910	70012J220W234	LINE            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					HYD SYSTEM	LEAKING         	W				D				RETURN TO BLOCK         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) DURING RUN UP THE SUBJECT LINE STARTED LEAKING, THIS WAS REPORTED BY PASSENGERS IN AIRCRAFT WHO NOTICED HYDRULIC F	LUID LEAKING INTO CABIN FROM OVERHEAD.AIRCRAFT WAS SHUT DOWN AND THE AME LOCATED THE LEAKING LINE ON NR 2 HYDRAULIC SYST	EM. THIS LINE WAS LAST PRESSURE TESTED 10/98. NEW LINE WILL BE INSTALLED PRIOR TO AIRCRAFT RETURN TO SERVICE.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002011700010	20020117	00010	CE  	2002	1	17	CA011105004      	1	20011104	G	2752	99105863RX	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					TE FLAPS	STUCK           	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA											(CAN) PILOT REPORTED IN FLIGHT FAILURE OF FLAP SYSTEM LOCKED IN ONE POSITION.  RETURNED TO MAINTENANCE BASE AND REPLACED	 FLAP ACTUATOR.  AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2002011700011	20020117	00011	NE  	2002	1	17	CA011105005      	2	20010526	G	7261		LABYRINTH SEAL  			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) TEARDOWN REPORTS - SEVERE FAILURE OF LABYRINTH SEAL. SMALL DIAMETER ROTATING LABYRINTH SEAL ALMOST COMPLETELY DISI	NTEGRATED. SMALL PIECES RECOVERED. OUTER TWO ROTAING SEALS SEPERATED FROM LABYRINTH SHAFT. ACRO AEROSPACE W/O 21-8077PAR	TS SHIPPED TO TURBOMECA FRANCE FOR ANALYSIS.				1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002011700012	20020117	00012	SO  	2002	1	17	CA011105006      	2	20011001	G	7321	632558	LINK ROD        	CONT        	IO470VO     	CESSNA	310   	310Q        	2074242	CE  	CONT  	O470  	IO470VO     	17026	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FCU	DISCONNECTED    	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		AP	APPROACH       	1			CA						170718R					(CAN) ON APPROACH PILOT NOTICED ROUGHNESS FROM LEFT ENGINE AND UPON LANDING REPORTED THAT THE LEFT ENGINE WOULD NOT IDLE	 UNLESS MIXTURE PULLED BACK HALFWAY. INSPECTION REVEALED THAT THE COTTER PIN WHICH HOLD THE MIXTURE INTERCONNECT ROD TO 	THE THROTTLE VALVE HAD BROKEN AND THE ARM FELL OFF ALLOWING NO MIXTURE ADJUSTMENT WITH THROTTLE MOVEMENT AS REQUIRED. NE	W COTTER PIN INSTALLED, AIRCRAFT GROUND RUN AND CHECKED SERVICEABLE. ADDITIONAL CHECK CARRIED OUT TO ALL CYLINDERS, COMP	RESSION AND BORESCOPE REVEALED NO APPARENT DAMAGE CAUSED AIRCRAFT RETURNED TO SERVICE.		1	L	7	2 	3O	3	O	 	3A10    	3E1	5	C	P22EA	 
2002011700013	20020117	00013	CE  	2002	1	17	CA011105014      	1	20010731	G	3250	07430118	ARM             			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS PROBLEM WAS DISCOVERED DURING THE AIRCRAFTS ANNUAL INSPECTION. THE CRACK IS ALL OF THE WAY THROUGH THE FORWAR	D SIDE OF THE ARM, VERTICALLY ORIENTED AND PASSES THROUGH THE GREASE FITTING HOLE.IT APPEARS TO HAVE ORIGINATED AT THE F	ILLET FORMED BY THE RIGHT SIDE OF THE STEERING STOP LUG, AND THE UPPER MACHINED SURFACE OF THE ARM. ALL RELEVANT STEERIN	G PARTS ARE SERVICEABLE AND THERE IS NO APPARENT CAUSE FOR THE CRACK.			1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002011700014	20020117	00014	EA  	2002	1	17	CA011105015      	2	20011015	G	8500		CASE            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND IN CASE AROUND FORWARD UPPER THROUGH BOLT.						1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002011700015	20020117	00015	EU  	2002	1	17	CA011105016      	1	20011005	G	6320	4638001009	GEARBOX         			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	MAKING METAL    	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) ON ENGINE START UP - PILOT REPORTED MGB CHIP LIGHT ON, PULSED OFF AND 4 SECONDS LATER LIGHT BACK ON. ENGINE SHUT D	OWN, MAG PLUG PULLED 2 SMALL FLAKED AND SOME FUZE ON PLUG. FINE OIL FILTER REMOVED AND FOUND TO BE CONTAMINATED WITH NUM	EROUS, VARIOUS SIZED PARTICLES. AIRCRAFT REMOVED FROM SERVICE PENDING MGB CHANGE.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001110800008	20011108	00008	EU  	2001	11	8	CA011105017      	1	20011015	G	2913	62052RSIMT47CR	BEARING         	AEROSP      	350A35013004	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  	 		            		INTERNAL	BROKEN          	W			    	A	L	 	 	UNSCHED LANDING         	ABORTED APPROACH        			F	J	 	FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA		 									(CAN) DURING TAKEOFF/CLIMB OUT OF A WOODED AREA, THE PILOT GOT A HYDRAULIC LIGHT INDICATION. HE LATER REPORTED THAT THE 	AIRCRAFT HAD A COMPLETE HYDRAULIC FAILURE. THE CAUSE OF THE FAILURE WAS DUE TO A BEARING FAILURE IN THE HYDRAULIC DIVE P	ULLEY, THE CAGE OR THE BEARING HAD BROKEN APART CAUSING THE PULLEY ASSEMBLY TO SEIZE AND THE HYDRAULIC BELT TO BREAK. TH	E AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011700016	20020117	00016	SO  	2002	1	17	CA011105018      	1	20010816	G	3230	455180	STRUCTURE       			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					MLG	GALLED          	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA											(CAN) IT WOULD APPEAR, UPON INVESTIGATION THAT A PIECE OF MATERIAL FROM THE INNER ATTACHMENT (TELEFLEX) BROKE AND BECAME	 LODGED BETWEEN IT AND THE OUTER PORTION (SLIDE) AND CAUSED GALLING/SCORING WHICH JAMMED THE U/C AND WOULD NOT ALLOW GEA	R TO EXTEND. AFTER MUCH EFFORT THE GEAR WAS EXTENDED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.				1	L	7	2 	3O	3	O	 	A1EA    	1E12				 
2002020800055	20020208	00055	NE  	2002	2	8	CA011107001      	1	20011004	G	3246	5003450	WHEEL           			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEEL SUBASSEMBLY FOUND CRAKED WHILE INVESTIGATING SLOW LEAK.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002011700017	20020117	00017	EU  	2002	1	17	CA011108001      	1	20011029	G	6210	350A11001007	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION A CRACK WAS FOUND ON THE LOWER SURFACE OF THE BLADE AT STN. 1003. CRACK LENGTH WAS APPROXIMATELY	 155.52 MM STARTING 111.46 FROM THE LEADING EDGE TRAVELLING CORDWISE TO 33.02 MM FROM THE TRAILING EDGE.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011700018	20020117	00018	NE  	2002	1	17	CA011108002      	2	20011023	G	8530	71166	EXHAUST VALVE   			BEECH 	18    	TC45G       	1151016	CE  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) NR 1 EXHAUST VALVE HEAD BROKE OFF CONTACTING PISTON AND BENDING CONNECTING ROD.						1	L	7	2 	3R	3	R	 	A765    	5E1				 
2002011700019	20020117	00019	CE  	2002	1	17	CA011108003      	1	20011106	G	2730	505244325	BRACKET         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15320	15320							(CAN) WHILE CONDUCTING THE INSPECTION OF THE ELEVATOR PULLEY BRACKETS IAW BEECH SB 2150 ELEVATOR PULLEY BRACKET PART NR 	 50-524432-5 AND 50-524432-7 WERE FOUND CRACKED. SERVICE KIT NR 90-4098-1 S INSTALLED IN ACCORDANCE WITH BEECH SB 2150 R	EVLL				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011700021	20020117	00021	NM  	2002	1	17	CA011108007      	1	20011029	G	7602	600035549	CONTROL CABLE   			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					MIXTURE CONTROL	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE ENGINES WERE BEING REMOVED FOR REPLACEMENT. DURING INSPECTION OF THE ENGINE CONTROLS,	 BOTH THE LT MIXTURE CONTROL CABLE P/N 600035-549 AND RIGHT HAND MIXTURE CONTROL CABLE P/N 600035-547 WERE FOUND TO BE S	EPARATED AT THE SWAGED END. THE LT CABLE HAD A TIME OF 2125.8 HOURS SINCE NEW. TIME ON R/H CABLE UNKNOWN. THE CABLES WER	E REPLACED WITH SERVICEABLE UNITS.			1	M	7	2 	3O	3	O	RT	A17WE   	1E4				 
2002011700027	20020117	00027	EA  	2002	1	17	CA011108011      	2	20011029	G	7414	1038291018	MAGNETO         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	DAMAGED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING CRUISE FLIGHT THE RT ENGINE SURGED ONCE AND THEN FAILED. CREW BELIEVE RPM REMAINED NORMAL BUT MANIFOLD PRES	SURE DROPPED TO 20 INCH HG THEN BACK UP AND AGAIN DOWN TO 20 INCH. ELECTRIC FUEL PUMP WERE TRIED BUT DID NOT HELP SO ENG	INE WAS SHUT DOWN AND NORMAL LANDING CARRIED OUT ON ONE ENGINE.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002020800057	20020208	00057	EA  	2002	2	8	CA011108012      	2	20011031	G	8520	STD1065	DOWEL PIN       			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	O540E4C5    	41532	EA  					CRANKSHAFT	SHEARED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA											(CAN) DURING CRUISE JUST PRIOR TO LANDING IN YVR,  LT ENGINE BEGAN TO RUN VERY ROUGH WITH MOST OR ALL POWER LOSS. PILOT 	SHUT ENGINE DOWN AND LANDED NORMALLY IN YVR. PRELIMINARY INVESTIGATION FOUND BOTH VALVE AND MAG TIMING TO HAVE ALTERED S	IGNIFCANTLY.				1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2002011700028	20020117	00028	EU  	2002	1	17	CA011108013      	1	20011107	G	3097	3E23602	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DEICE HARNESS	BROKEN          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) PILOT REPORTED PROP DE-ICE SYSTEM OPERATING INTERMITTENTLY. INVESTIGATION REVEALED THAT THE GROUND WIRE IN THE HAR	NESS BETWEEN THE BACKING PLATE TERMINAL BLOCK AND THE BLADE DE-ICER BOOT WAS BROKEN INTERNALLY. WITH FEATHERING AND UNFE	ATHERING OF THE PROPELLOR THE HARNESS IS CONSTANTLY BENDING THE WIRES CAUSING THE BREAKAGE. THE WIRE APPEARS TO HAVE MAD	E CONTACT WITH THE TWO BROKEN ENDS CAUSING THE WIRE ENDS TO ARC TOGETHER THUS GIVING THE INTERMITTENT OPERATION OF THE S	YSTEM. THE HARNESS WAS REPLACED WITH NEW AND SYSTEM FUNCTIONED NORMALLY.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011700029	20020117	00029	EU  	2002	1	17	CA011109002      	1	20010808	G	3240	NB73A4354	LINE            			BNORM 	BN2   	BN2A27      	1520227	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RT MLG BRAKE	CHAFED          	W				D				RETURN TO BLOCK         				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			17401								(CAN) ONE OF THE TWO BRAKE LINES THAT RUN DOWN THE LEG CHAFED THROUGH AT THE TOP CLAMP. BRAKES WERE SOFT ON THAT SIDE.						1	H	7	2 	3O	3	O	 	A17EU   	E295				 
2002011700030	20020117	00030	SO  	2002	1	17	CA011109003      	1	20011109	G	3230	4204200	LINK            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) LINK FAILED AFTER TAKEOFF AND GEAR WOULD NOT COME UP. FORTUNATELY IT WENT BACK DOWN AND AIRCRAFT LANDED NORMALLY. 	IT COULD HAVE BEEN WORSE VERY EASILY. I WAS ALSO INFORMED BY OPERATOR THAT THIS IS THE SECOND TIME THAT THIS HAS HAPPENE	D.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011700036	20020117	00036	SO  	2002	1	17	CA011109004      	1	20010917	G	3242	753407	BOLT            	CLEVELAND   	3095A       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					BRAKE ASSY	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN) UPPER TORQUE PIN (ANCHOR PIN) FAILED ALLOWING BRAKE TO ROTATE INTO BACK OF MAIN LANDING GEAR STRUT. ALSO INSIDE SU	RFACE OF MAIN WHEEL SCORED. PIPER ANCHOR BOLT P/N 753-407 CLEVELAND ANCHOR BOLT P/N 69-4					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002011700037	20020117	00037	CE  	2002	1	17	CA011109006      	1	20011023	G	5330	97400021101	SKIN            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUSELAGE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				10337							(CAN) DUE TO THE ANGLE OF CONTACT BETWEEN THE WING CENTRE SECTION TO FUSELAGE FILLET P/N 50-420023-37 AND -38 AND THE FU	SELAGE SKIN P/N 97-400021-101 AND -102 WHEN THE RIVETS WORK LOOSE IN THE FILLET IT IS ALLOWED TO CHAFE INTO THE FUSELAGE	 SKIN. THIS SKIN IS A PRESSURE SKIN AND REQUIRES ENGINEERING APPROVED FOR REPAIRS.TO REDUCE RECURRENCE OF THIS PROBLEM T	HERE SHOULD BE AN ANTI-CHAFE MEDIUM BETWEEN FILLET AND SKIN, I.E. PRC 1422-B 1/2 AND RIVETS SHOULD BE KEPT IN TOP CONDIT	ION, FIXING ANY DEFECTS AS THEY OCCUR.		1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011700039	20020117	00039	SW  	2002	1	17	CA011109007      	1	20011024	G	6520	204001739003	SEGMENT         			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					T/R G/B CHAIN	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGM	ENT.					1	G	7	1 	4U	4	U	 	H1SW    	E1EA				 
2002011700040	20020117	00040	EU  	2002	1	17	CA011109008      	1	20011009	G	6710	350A2705510602	FRICTION RING   			SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A2 	41560	NE  					MAIN ROTOR	FAILED          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) LOCK PIN NR 10 EITHER NOT PROPERLY INSTALLED OR CAME LOOSE ALLOWING NUT NR 9 TO VIBRATE LOOSE FROM LOWER THREAD PO	RTION OF COLLAR NR 8, THIS ALLOWED THE ENTIRE FRICTION ASSY TO BE LIFTED BY HAND. THIS COULD EASILY THEN CAUSE BINDING O	R LIMIT CYCLIC MOVEMENT. COLLAR NR 8 IS DRILLED TO ACCEPT THE LOCK RING. ALL PARTS EXAMINED AND REINSTALLED TO ENSURE PR	OPER LOCKING EFFECTIVENESS.			1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2002011700041	20020117	00041	WP  	2002	1	17	CA011109010      	2	20011009	G	7261	8971973	DRIVE SHAFT     								GARRTT	TPE331	TPE33110UA  	01514	WP  					SCAVE PUMP	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION OF PARTS REMOVED FROM P-63110 AT TIME OF OVERHAUL IT WAS NOTED THAT THE FRONT SCAVENGE PUMP DRIVE SH	AFT SAFTY COLLER IS 0.210 SMALLER THAN THE REPLACEMENT PART THIS CAN ALLOW THE SHAFT TO ENTER THE PUMP TO FAR AND ALLOW 	THE FUEL DRIVE SYSTEM TO UNCOUPPLE. ON SDR 20001206012 THE SAME PROBLEM WAS NOTED ON ENGINE S/N P-63111.									4	T			E4WE				 
2002011700042	20020117	00042	SO  	2002	1	17	CA011109014      	1	20011013	G	5710		FASTENER        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					LT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 12C INSPECTION (7200 HOUR) MAINTENANCE PERSONNEL FOUND SEVERAL SHEARED HILOCKS ON THE LEFT HAND WING AT R	IB NR 6.THE LEFT HAND LANDING GEAR WAS REMOVED AND AREA INSPECTED, NO STRUCTURAL DAMAGE WAS FOUND. 22 HILOCKS WERE REPLA	CED AND GEAR REINSTALLED. THE SAME INSPECTION WAS COMPLETED ON THE RIGHT HAND SIDE AND NO DEFECTS WERE NOTED. A GEAR SWI	NG WAS COMPLETED AND AIRCRAFT WAS RETURNED TO SERVICE.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002011700052	20020117	00052	EU  	2002	1	17	CA011113007      	1	20011113	G	3060	3E23602	WIRE            			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	DEICE HARNESS	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN)  DURING PROP DEICE OPERATION THE SYSTEM INDICATED A FAILURE.UPON INVESTIGATION / TROUBLESHOOT IT WAS FOUND THE HAR	NESS P/N 3E23060-2 HAD AN INTERNAL BREAK WITH LITTLE OR NO CONTINUITY WHILE MOVING THE HARNESS AS INSTALLED.PART WAS REM	OVED NEW ONE INSTALLED SYSTEM TESTED SERVICEABLE.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002020800059	20020208	00059	EA  	2002	2	8	CA011113017      	1	20010111	G	5410	60135006	SUPPORT         			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12120								(CAN) FOUND THREE CRACKS DURING CHECKS. CRACKED AT FS 630 & 640, LT & RT BL 36 & 00.						2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2001121200011	20011212	00011	EU  	2001	12	12	CA011114001      	1	20011001	G	5230	D2586	LATCH           	DART        	D350600042  	SNIAS 	350   	AS350D      	8680803	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  	 		            		LATCH	FAILED          	W			    	B	 	 	 	EMER. DESCENT           				D	D	 	INFLIGHT SEPARATION       	INFLIGHT SEPARATION       		CR	CRUISE         	1			CA		 									(CAN) PRIOR TO COMMENCING HIS FLT PILOT HAD REMVD SEAT CUSHIONS&STOWED THESE IN SIDE CARGO COMPT POD. DURING FLT POD "DO	OR OPEN" LIGHT ILLUMINATED WHICH FOLLOWED BY LOUD BANG&SEVERE VIBRATIONS. PILOT IMMEDIATELY LANDED&FOUND THAT R/H POD DO	OR HAD OPENED&SEAT CUSHION HAD FALLEN OUT STRIKING TAILBOOM&TAIL ROTOR WHILE IN FLT. REAR LATCH INSIDE LOCK BROKEN&SUBST	ANTIAL DAMAGE TO A/C. FWD LATCH  APPEARED UNDAMAGED BUT NOT POSITIVELY LATCHED. IT APPEARS THAT FWD LATCH MAY HAVE ALLOW	ED FRONT EDGE OF POD DOOR TO OPEN IN FLT AFTER WHICH PRESSURE FROM SLIPSTREAM PROBABLY BROKE REAR LATCH DUE TO EXCESSIVE	 PRESSURE B EING EXERTED ON DOOR. ALLOWED DOOR T	1	G	7	1 	3U	3	U	 	H9EU    	E5NE				 
2002011700072	20020117	00072	CE  	2002	1	17	CA011114014      	1	20011011	G	7120	045111432	MOUNT           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 50 HOUR INSPECTION THE ENGINE MOUNT WAS FOUND CRACKED. THE SUPPORT WAS REPLACED.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002011700073	20020117	00073	SO  	2002	1	17	CA011114015      	1	20011024	G	5751	6210500	HINGE           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					LT AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AN INSPECTION AN ONE AND A HALF INCH CRACK WAS DETECTED ON THE DOUBLER HINGE OUTSIDE OF THE LEFT AILERON.						1	L	7	1 	3O	3	O	 	A3SO    	1E4				 
2002021100005	20020211	00005	EU  	2002	2	11	CA011114016      	1	20011102	G	6320	4619302046	BEARING         			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	PEELING         	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			CA											(CAN) CHIP LIGHT INDICATION.GEARBOX DISASSEMBLED FOR INVESTIGATION.BEARING PLATING FOUND PEELING.REPLACED WITH NEW						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2002020500122	20020205	00122	EU  	2002	2	5	CA011114017      	1	20011114	G	6320	4619310072	BEARING         	BOLKMS      	4619002003  	BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  	 		            		INPUT	DEFECTIVE       	W			    	O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			IN	INSP/MAINT     	1			CA		 				1112					(CAN) BOTH INNER AND OUTER RACE OF BEARING DISPLAYED MODERATE PITTING AND PEELING						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2002011700076	20020117	00076	NE  	2002	1	17	CA011114018      	1	20011030	G	7712	9609000254	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					TORQUEMETER	FAILED          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) SUBJECT: ESN 15051- PARTICLES ANALYSIS. WE HAVE RECEIVED THE ANALYSIS RESULTS OF THE PARTICLES FOUND ON THE MODULE	  05 S/N 03199 MAGNETIC PLUG . THE  PARTICLES ARE 100 C6 MATERIAL AND HAVE AS THE ORIGIN ONE OF THE HYDRAULIC TORQUEM	ETER BEARINGS ("TRIPLEX") .				1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002011700078	20020117	00078	SW  	2002	1	17	CA011116001      	1	20011107	G	5210	90000949722	PUSHROD         			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					PAX DOOR	BENT            	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) DURING CLIMBOUT THE AIRCRAFT PRESSURIZATION REDUCED FROM 4.8 PSI TO 3.5 PSI. UPON INVESTIGATION IT WAS NOTED THAT 	THE LOWER AFT ENTRANCE DOOR BAYONET WAS NOT EXTENDING INTO THE AIRFRAME. THE TWO PUSHRODS P/N'S 900009-49-7.22 AND 90000	9-49-9.70 WERE FOUND BENT WHICH CAUSED THE BAYONET NOT TO EXTEND INTO THE AIRFRAME. THE PUSHRODS WERE REPLACED AND THE C	ABIN DOOR MECHANISM WAS RE-RIGGED. DOOR OPERATIION WAS CHECKED, THE DOOR SEAL WAS INSPECTED AND A PRESSURIZATION CHECK W	AS COMPLETED AND CHECKED SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.		1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2002021100006	20020211	00006		2002	2	11	CA011116002      	4	20011107	G	6122	A20609	CONTROL ARM     	MCAULY      	C290D3RT9   	CESSNA	185   	A185E       	2072818	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROP GOVERNOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						010596					(CAN) GOVERNOR WOULD NOT CYCLE PROP BELOW 1500 RPM. CONTROL ARM INSTALLED IN THE INCORRECT POSITION ON CONTROL SHAFT.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002011700080	20020117	00080	SW  	2002	1	17	CA011116003      	1	20011023	G	6230	269A21725	SUPPORT         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					M/R MAST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT MAIN ROTOR MAST SUPPORT (TAILBOOM TO M/R GEARBOX MAST).						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2002011700082	20020117	00082	SW  	2002	1	17	CA011116004      	1	20011107	G	6230	269A21725	SUPPORT         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					M/R MAST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT MAIN ROTOR MAST SUPPORT (TAILBOOM TO MAIN ROTOR GEARBOX MAST)						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2002011700090	20020117	00090	EA  	2002	1	17	CA011116005      	1	20011023	G	7714	659450105	INDICATOR       			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENG TRIPLE GAUGE	EXPLODED        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) ENGINE TRIPLE GAUGE EXPLODED: - CASE SPLIT (TOTAL CIRCUMFERENCE). - 1 LARGE PORTION OF CASE BROKEN OFF. - FRONT GL	ASS FACE PLATE SHATTERED OUTWARD SLIGHTLY INJURING PASSENGER IN CO-PILOT SEAT.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002011700091	20020117	00091	NE  	2002	1	17	CA011116006      	1	20011029	G	6220	7610308010049	HUB             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					M/R DAMPER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) A CRACK APPROXIMATELY 2.5 CM, EXTENDING INBOARD FROM BUSHING BORE ON UPPER LUG OF RED MAIN ROTOR DAMPER SUPPORT.						1	G	7	2 	3U	3	U	NC	H1NE    	E00054EN				 
2002011700092	20020117	00092	SW  	2002	1	17	CA011116007      	1	20010908	G	3212	108839	REGULATOR       			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					MLG FLOAT	LEAKING         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) AIRCRAFT BELL 222U POP-OUT FLOAT SYSTEM CHARGED TO 3000 PSI AFTER CHANGING FLOAT BOTTLE. SYSTEM LEAKED APPROXIMATE	LY 200 PSI OVER A 12 HOUR PERIOD. BY REMOVING THE LINES TO AIR BAG IT WAS CONFIRMED THAT AIR WAS LEAKING THROUGH SHEAR H	EAD BY SMALL CRACKS. THE SHEAR HEAD IS TO MAINTAIN 3000 PSI IN THE FLOAT BOTTLE TILL FLOATS ARE  DEPLOYED.				1	G	7	2 	3U	3	U	 	H9SW    	E5NE				 
2002011700093	20020117	00093	EU  	2002	1	17	CA011116009      	1	20010711	G	6220	704A33633160	BUSHING         	AEROSP      	350A31190701	SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					M/R SPIDER	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						M1012					(CAN) BOLT P/N 22208BC10001GL BACKED OUT ALLOWING DEBONDED BUSHING P/N 704A33-633-160 TO MOVE OUTWARD APPROXIMATELY 1/4 	INCH ON THE OUTBOARD END OF THE RED ARM. DAMAGE WAS DISCOVERED ON A DAILY INSPECTION. PILOT HAD COMPLAINED OF VIBRATION 	ON GROUND WHILE RUNNING.ON REPLACEMENT OF THE STAR, BEARING P/N 11-7775P IN THE FREQUENCY ADAPTER WAS FOUND WITH EXCESSI	VE PLAY ON THE SAME ARM.			1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011700094	20020117	00094	EU  	2002	1	17	CA011116010      	1	20011109	G	6720	350A33105803	BELLCRANK       	AEROSP      	350A33105803	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					T/R CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AS PER A COMPANY MEMO TO CHECK THIS LEVER/BELLCRANK FOUND ANOTHER ONE CRACKED IN THE SAME REGION (SEE ATTACHED DOC	UMENT). NOTE: THE FIRST SDR SUBMITTED THE ARROWS WERE POINTING IN THE WRONG REGION. THE ARROWS SHOULD BE MORE OUTBOARD F	ROM WHERE THEY WERE POINTING. THIS WAS C-FSPR DATED 01/10/25 CONTROL NUMBER UNKNOWN.SDR CONTROL #20011029017 (C-FSPR)				1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002021100007	20020211	00007		2002	2	11	CA011116011      	4	20011029	G	3422	200DC	GYRO            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COCKPIT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA						2909					(CAN) ON FINAL FOR LANDING,  PILOT AND PASSENGERS NOTICED AN ELECTRICAL SMELL, SECONDS LATER WHITE SMOKE FILLED THE CABI	N COMING FROM BEHIND INSTRUMENT PANEL. ALL CIRCUIT BREAKERS WERE PULLED AND AIRCRAFT SHUT DOWN. INSPECTION REVEALED DIRE	CTIONAL GYRO HAD SHORTED INTERNALLY AND MELTED DOWN.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002011700095	20020117	00095	NM  	2002	1	17	CA011116012      	1	20011115	G	2910	82970010249	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			30700								(CAN) THE FLIGHT CREW NOTICED FLUID LEAKING FROM THE LEFT NACELLE DURING THEIR WALK-AROUND INSPECTION.MAINTENANCE FOUND 	THE "MLG DOWN PRESSURE" HYDRAULIC TUBE LEAKING FROM A PIN HOLE UNDER THE EXHAUST SHROUD. THE RIGID TUBE WAS TEMPORARILY 	REPLACED WITH TWO FLEXIBLE HOSES AS PER AMM 20-50-52. THE SYSTEM WAS TOPPED UP AND LEAK CHECKED PRIOR TO RETURNING THE A	IRCRAFT TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002011700096	20020117	00096	CE  	2002	1	17	CA011116013      	1	20011105	G	2752	C145350	ACTUATOR        			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	TE FLAPS	SEIZED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) ON APPROACH FLAPS SELECTED FROM 10 TO 20 AS FLAPS TRAVELLED THROUGH APPROXIMATELY 15 DEGREES THE FORWARD FLAP MOTO	R FAILED AND BROKE FREE OF THE TRANSMISSION/JACKSCREW ASSY. THIS CAUSED  THE FLAP ACTUATOR ASSEMBLY TO BRAKE FREE OF THE	 ATTACHING STRUCTURE, THUS CAUSING THE FLAP TO RAPIDLY RETRACT TO THE STOWED POSITION.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002011700097	20020117	00097	SO  	2002	1	17	CA011116014      	2	20011106	G	7314	6462121	PUMP            			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	FUEL	FAILED          	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) DURING CLIMB AFTER TAKEOFF FROM RUNWAY 16 AT YYC WHEN THE PILOT ADJUSTED THROTTLE AND MIXTURE THE ENGINE STOPPED P	RODUCING POWER. AN EMERGENCY LANDING WAS CARRIED OUT ON THE END OF RUNWAY 16.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P3EA	 
2002020500123	20020205	00123	SW  	2002	2	5	CA011116015      	1	20011101	G	6320	204040135001	BEARING         	BELL        	212040001123	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  	 		            		BEARING	FAILED          	W			    	A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			DE	DESCENT        	1			CA		 				ABW40334					(CAN) WHILE IN DESCENT TO THE LANDING AREA THE MAIN ROTOR TRANSMISSION CHIP LIGHT ILLUMINATED. THE PILOT MAINTAINED ITS 	APPROACH AND LANDED. UPON INSPECTION ON THE CHIP DETECTOR METAL WAS FOUND AND THEN THE WAFFER FILLER WAS CHECKED WHERE M	ORE METAL WAS FOUND. MAIN ROTOR TRANSMISSION CHANGED.				1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002021100008	20020211	00008	CE  	2002	2	11	CA011116016      	1	20010611	G	3221		TAIL WHEEL      			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470*       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	MLG	SEPARATED       	W				O				OTHER                   				W	D		INADEQUATE Q C            	INFLIGHT SEPARATION       		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF FROM ROUGH STRIP ON HERSEL ISLAND, PILOT HEARD LOUD BANGING SOUND. HE WAS ABLE TO SEE TAIL WHEEL MIS	SING. ON LANDING AT AKLAVIK, STEERING CONTROL LOST.  MINOR DAMAGE TO TAIL STRINGER. NEW TAIL WHEEL ASSEMBLY INSTALLED WI	TH PROPER AIRCRAFT BOLTS. THE AIRCRAFT RETURNED TO SERVICE. THE CAUSE WAS FOUND TO BE A NON AIRCRAFT BOLT HOLDING ASSEMB	LY ON.			1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002011700098	20020117	00098	EA  	2002	1	17	CA011116017      	2	20011102	G	8520	LW1594485	CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND UNDERNEATH URETHABOND COATING APPLIED BY FACTORY AT OVERHAUL AS PER SB 505B AND SB 530A AND AD 98-	02-08.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002011700099	20020117	00099	CE  	2002	1	17	CA011116018      	1	20011108	G	5610	10138402521	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) THE AIRCRAFT WAS IN CRUISE AT FLIGHT LEVEL 290, APPROXIMATELY 50 MILES NW OF SUDBURY, ONTARIO, ENROUTE FROM THUNDE	R BAY TO THETFORD MINES, QUEBEC, WHEN THE LT WINDSHIELD INNER PANE SHATTERED. THE CREW REDUCED PRESSURIZATION TO 4 PSI D	IFFERENTIAL PRESSURE AS PER FLIGHT MANUAL PROCEDURES AND DIVERTED TO QUEBEC CITY.THE CREW REPORTED THAT THE WINDSHIELD H	EAT WAS IN THE "HIGH" SELECTION AND THAT THE OAT WAS -36 DEGREES C AT THE TIME OF THE OCCURRENCE.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA				 
2002011700101	20020117	00101	CE  	2002	1	17	CA011116020      	1	20011106	G	5610	101384002522	WINDSHIELD      			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCD4N3	HCD4N3A     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH INTO CIGAR LAKE, SASKATCHEWAN (JWY) THE RIGHT HAND WINDSHIELD INNER PANE SHATTERED IN A LATTICE LIKE M	ODE. THE NETWORK OF CRACKS EXTENDED OVER THE ENTIRE INNER SURFACE OF THE SHIELD AND AN ORIGINATING POINT OR CAUSE COULD 	NOT BE DETERMINED.				1	L	7	2 	4T	4	T	 	A24CE   	E4EA	5	C	STC	 
2002011700103	20020117	00103	SW  	2002	1	17	CA011119001      	1	20010914	G	6510	2060403255	SHAFT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R DRIVE	GROOVED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ONLY APPLIES TO A/C EQUIPPED WITH CASEY HEATER & ATTACHED DUCTING. DURING GROUND RUN CHECKS AFTER OPS CHECK (600 H	R) INBOARD HEATING DUCT CONTACTED SHAFT ASSY P/N 206-040-325-5 & ADAPTER P/N 206-040-328-003 HEATING DUCT (HOSE) WASTORN	 & WIRE IN HEATER (HOSE) BROKE & CONTACTED THEAFT END OF SHAFT & ADAPTER CAUSING DEEP GROOVES IN BOTH.DURING INSP BOTH S	HAFT/COUPLING ADAPTER & BLOWER ASSY WERE REMOVED, & DRIVE SHAFT BEARING WERE REPLACED. DURING THE REMOVAL OR REINSTALLAT	ION OF SHAFT OR BLOWER ASSY HEATER DUCT (HOSE) WHICH HAD BEEN REMVD FOR MAINT ACTION MUST HAVE BEEN SQUEEZED, OR SLIGHTL	Y DEFORMED,&WHEN REINST, CLEARANCE BETWEEN SHAFT/COUPLING ADAPTER NOT OBTAINED.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011700105	20020117	00105	CE  	2002	1	17	CA011119002      	1	20011029	G	2720	03101965	SPRING          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER	BROKEN          	W				A				UNSCHED LANDING         				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		CR	CRUISE         	1			CA											(CAN) SHORTLY AFTER TAKEOFF & DRING CRUISE EXCESSIVE LT RUDDER WAS AREQD TO KEEP A/C STRAIGHT. PILOT CALLED THUNDER BAY 	TOWER, & REPORTED RUDDER PROBLEMS & DIFFICULTY CNTLLING AIRCRAFT. PILOT REQED TO LAND WITH EMERG VEHICLES READY. A/C LAN	DED SAFELY & TAXIED BACK TO COLLEGE HANGAR. ON MECHANICAL INVESTIGATION, IT FOUND THAT LT RUDDER SPRING HAD BROKEN AT TO	RQUE TUBE END, & WAS HANGING OFF FRONT BRACKET END. (UNDER FLOOR AT PILOTS FEET) THE SPRING WAS CHANGED, RIGGING & RUDDE	R TRAVEL WERE CHECKED, & A/C WAS RELEASED BACK TO SERVIC E.AGE OF SPRING COULD BE A CONTRIBUTING FACTOR IN THIS CASE AS 	THERE IS NOT A HIGH STRESS LOAD ON THIS PART.	1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011700107	20020117	00107	SW  	2002	1	17	CA011119004      	1	20011031	G	6210	407015001107	BLADE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING AIRFRAME PERIODIC INSP 3.5 INCH DIAGNAL CRACK ON LOWER SKIN OF SUBJECT BLADE FOUND AT BLADE STATION 71.0-73	.0.ATTEMPTS TO DRESS OUT CRACK WITH LIGHT SANDING REVEALED SUSPECT LACK OF FIBERGLASS MATTING USED IN CONSTRUCTION OF BL	ADE TYPE. EVIDENCED BY FURTHER EXPLORATORY SANDING GOING THROUGH GEL ADHESIVE COATING & FILLER MATERIAL & ENDING AT HONE	YCOMB CORE W/O 1ST ENCOUNTERING FIBERGLASS CLOTH MATTING.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002011700112	20020117	00112	EU  	2002	1	17	CA011120001      	1	20011111	G	2434	9789601090	BRUSH HOLDER    			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE  BRUSH ASSEMBLY WAS WORN	 EXCESSIVELY, AND HAS BEEN REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021100010	20020211	00010	EU  	2002	2	11	CA011120002      	1	20011116	G	2750	9787320015	FCU             			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAPS	MALFUNCTIONED   	W				D				RETURN TO BLOCK         				H			ELECT. POWER LOSS-50 PC   			TX	TAXI/GRND HDL  	1			CA											(CAN) THE PILOT REPORTED AN AMBER FLAPS LIGHT ON THE CAWS PANEL WHEN THE AIRCRAFT POWER WAS TURNED ON.  THE AIRCRAFT WAS	 ON THE GROUND OUTSIDE FOR APPROXIMATELY THREE HOURS,  OUTSIDE TEMPERATURE WAS -20C. ONCE TEH AIRCRAFT HAD BEEN WARMED U	P IT WAS POSSIBLE TO CARRY OUT A FLAP RESET ON THE FLAP SYSTEM, AND THE SYSTEM FUNCTIONED NORMALLY AFTER THE RESET.THE F	LAP CONTROL AND WARNING UNIT WAS REMOVED FROM THE AIRCRAFT AND PLACED IN A FREEZER FOR TWO HOURS, AFTER REMOVING THE UNI	T FROM THE FREEZER AND RE-INSTALLING IT IN THE AIRCRAFT IT WAS POSSIBLE TO DUPLICATE THE SAME FAILURE AND RESET SENARIO.	  THE FCWU HAS BEEN REPLACED.	1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002011700113	20020117	00113	SW  	2002	1	17	CA011120003      	1	20011002	G	2720	12364	CABLE           			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) BOTH LT AND RT CABLES FRAYED JUST INCHES FWD OF BAGGAGE COMPARTMENT PULLEYS.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002011700117	20020117	00117	CE  	2002	1	17	CA011120009      	1	20010827	G	7120	04112816	MOUNT           			CESSNA	170   	170A        	2072304	CE  	CONT  	C145  	C1452       	17012	SO  					LT ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LT UPPER ENGINE MOUNT BRACKET AFT OF FIREWALL EXTREME CORROSION (HALF OF BRACKET MISSING) VERY DIFFICULT TO SEE DU	E TO INSULATION COVERING ON FIREWALL.					1	H	7	1 	3O	3	O	 	A799    	E253				 
2002011700118	20020117	00118	CE  	2002	1	17	CA011120010      	1	20011109	G	5610	5042006937	WINDSHIELD      			BEECH 	100   	B100        	1152919	CE  										COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WHILE AT CRUISE ALTITUDE THE NR 1 (PILOT'S) WINDSHIELD STARTED CRAZING AND CONTINUED PROGRESSIVELY UNTIL OUTWARD V	ISION WAS SEVERELY IMPAIRED. CABIN PRESSURIZATION WAS LOWERED, WINDSHIELD HEAT WAS DISCONTINUED AND THE AIRCRAFT CONTINU	ED ON TO DESTINATION. THE UNSERVICEABLE WINDSHIELD WAS REMOVED. A NEW WINDSHIELD WAS INSTALLED. THE AIRCRAFT WAS RETURNE	D TO SERVICE.			1	L	7	2 	4T			 	A14CE   					 
2002021100012	20020211	00012	CE  	2002	2	11	CA011120011      	1	20011115	G	5753	5016000310	RIB             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15323	15323							(CAN) WHILE CONDUCTING A PREFLIGHT INSPECTION A CRACK IN THE FLAP SKIN WAS DETECTED. THE CRACK WAS LOCATED AROUND THE FL	AP ACTUATOR ATTACH BRACKET. FURTHER INVESTIGATION REVEALED THAT BOTH THE FLAP SKIN  AND THE NOSE RIB  OF THE LT I/B FLAP	 WERE CRACKED. FURTHER INVESTIGATION REVEALED THAT THE LT O/B FLAP WAS CRACKED IN THE SAME AREA BUT TO A LESSER DEGREE. 	THE NOSE RIBS IN BOTH THE LT INBOARD AND OUT BOARD ALONG WITH ASSOCIATED FLAP SKINS.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2002011700120	20020117	00120	EA  	2002	1	17	CA011120013      	2	20011108	G	8520	LW1594470	CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CORROSION FOUND UNDERNEATH PROTECTIVE COATING APPLIED BY FACTORY AT OVERHAUL AS PER LYCOMING SB 505B AND 530A AND 	AD 98-02-08.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002011700122	20020117	00122	NE  	2002	1	17	CA011121001      	2	20011004	G	8530		STUD            			AYRES 	S2    	S2RNORMAL   	7630202	SO  	PWA   	R1340 	R1340AN1    	52016	NE  					ENGINE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NR 1 AND 5 CYLINDERS BASE RETAINING STUDS SHEARED.						1	L	7	1 	3R	3	R	NC	A3SW    	5E2				 
2002021100015	20020211	00015	SO  	2002	2	11	CA011121002      	2	20011112	G	7322	S123019	CONTROL CABLE   			CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  					CARB HEAT	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			CA											(CAN) PILOT APPLIED CARB HEAT ON DOWNWIND AND KNOB SHAFT ASSEMBLY CAME OUT IN HER HAND. PUSH / PULL WIRE HAD BROKEN ABOU	T 3 INCHES PAST THE END OF THE SHAFT.  EXAMINATION OF THE BREAK INDICATED A LONG STANDING CRACK ABOUT 2/3 OF THE WAY THR	OUGH THE WIRE. THERE ARE NO SHARP BENDS AT THIS POINT, THOUGH THE CABLE IS CURVED SOMEWHAT. NO EVIDENCE OF PREVIOUS TRAU	MA TO THE WIRE.THE AIRCRAFT WAS LANDED IN NORMAL FASHION AND SHUT DOWN.			1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002021100016	20020211	00016	GL  	2002	2	11	CA011121004      	2	20011109	G	7323	252476914	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			CA											(CAN) THE HELICOPTER WAS INVOLVED IN FOREST INVENTORY WORK AT LOW ALTITUDE AT NEAR GROSS WEIGHT AT SLOW SPEED WHEN PILOT	 NOTICED HIS ROTOR RPM DROPING, LOW ROTOR WARNING AND AN INDICATION OF 95 PERCENT. HE MANAGED TO DROP COLLECTIVE AND LAN	D IN A SMALL CLEARING.THE GOVERNOR WAS REPLACED, AIRCRAFT RUN-UP AND OPERATIONAL CHECKED, OK.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011700124	20020117	00124	EA  	2002	1	17	CA011121005      	1	20011115	G	5320	C2FS3282A	STRUT           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					WINDOW FRAME	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14676								(CAN) THE AIRCRAFT WAS UNDERGOING SCHEDULED MAINTENANCE.THE RIGHT HAND WINDSHIELD WAS BEING REPLACED. THE RIGHT FRONT FU	SELAGE STRUT ASSY WAS FOUND CORRODED UNDER THE WINDSHIELD SUPPORT ASSY. THIS STRUT ASSY WAS EXAMINED IN ACCORDANCE WITH 	CF-98-37R1 IN FEBRUARY OF THIS YEAR. THE AREA CORRODED IS NOT ACCESSIBLE UNLESS THE WINDSHIELD IS REMOVED.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002011700129	20020117	00129	SO  	2002	1	17	CA011121008      	1	20011116	G	3230	401195	BOLT            			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					MLG	BROKEN          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		LD	LANDING        	1			CA											(CAN) FLT CREW WERE UNABLE TO EXTEND LT MLG THROUGH NORMAL (HYDRAULIC) OR EMERG (HYDRAULIC/PNEUMATIC) MEANS PRIOR TO LDG	. LOSS OF HYDRAULIC FLUID EVIDENT AROUND TRAILING EDGE OF LT WING & FLAP AREAS. NOSE & RT MLG WERE RETRACTED & A/C MADE 	SUCCESSFUL GEAR UP LDG. INVESTIGATION. DETERMINED LT MLG ACTUATING CYLINDER TOP BOLT HAD BROKEN. ALLOWED CYLINDER TO SLI	DE DOWN RAM WHEN GEAR INITIALLY SELECTED DOWN, INSTEAD OF RAM RETRACTING INTO STATIONARY CYLINDER. CYLINDER MOVEMENT BRO	KE LOWER FITTING THAT IS COMMON TO BOTH HYDRAULIC&PNEUMATIC SYS PRESSURES, RESULTING IN OVERBOARD LOSS OF HYDRAULIC FLUI	D A ND ANY PENUMATIC PRESSURE:	1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2002011700130	20020117	00130	SO  	2002	1	17	CA011121009      	1	20011116	G	3230	668346	WIRE HARNESS    			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					MLG	DISCONNECTED    	W				H				DEACTIVATE SYST/CIRCUITS				R	L		PARTIAL RPM/PWR LOSS      	NO TEST                   		LD	LANDING        	1			CA											(CAN) PILOT ACTIVATED LDG GEAR EMERG BLOWDOWN PNEUMATIC SYS SWITCH DURING LDG GEAR EXTENSION MFLFUNCTION. LATER GROUND I	NSP DETERMINED THAT PENUMATIC SYS (LT MLG) HAD NOT PROPERLY ACTIVATED. SYS SHOULD HAVE FIRED T HE NITROGEN BOTTLE EXPLOS	IVE SQUIB (ON LDG GEAR NOT DOWN & LOCKED) WHEN 28 VOLTS WERE APPLIED BY PUSHING EMERG GEAR EXTENTION SWITCH. VOLTAGE CHE	CK CONDUCTED AT L/H SQUIB CONNECTOR SHOWED ONLY 0 TO 4 VOLTS WHEN SWITCH ACTIVATED&GEAR UNLOCKED. TROUBLESHOOTING DISCOV	ERED WIRE LEADING FROM SWITCH TO BE ATTACHED BY ONLY ONE OR 2 STRANDS&PROTECTIVE HEAT SHRINK (VISUALLY NORMAL BUT DISCON	NECTED IMMEDIATELY UPON TOUCHING WIRE).	1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2002011700131	20020117	00131	SO  	2002	1	17	CA011121013      	1	20011112	G	3222	6531904	CYLINDER        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					TORQUE LINK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - UPON INSPECTION OF AIRCRAFT FOR A REPORTED HARD LANDING TORQUE LINK LUGS FOUND TO HAVE FAILED (UPPER).- UPON REM	OVAL IT APPEARS OUTBOARD LUG TO HAVE BEEN CRACKED FOR SOMETIME. INBOARD LUG HAD A SMALL CRACK ALSO ABOUT 20 PERCENT OR A	REA. - AREA COVERED BY FAIRING, TO INSPECT FAIRING HAS TO BE REMOVED.- S.L. 760 COVERS INSPECTION OF THIS AREA.OLEO CYLI	NDER P/N 65319-04 HAS BEEN SUPERCEDED BY 65490-00.			1	L	7	1 	3O	3	O	 	2A13    	E274				 
2002021100028	20020211	00028	SO  	2002	2	11	CA011121014      	1	20011119	G	3260	1459500001	DOWNLOCK SWITCH 			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					LT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) DURING DESCENT INTO YMO THE CREW SELECTED GEAR DOWN AND DID NOT GET A LT MAIN GEAR DOWN AND LOCKED INDICATION. THE	 LANDING GEAR WAS CYCLED A FEW TIMES AND GEAR DOWN AND LOCKED WAS CONFIRMED WITH INDICATION OF DOWN AND LOCKED. AS A PRE	CAUTION THE CREW ELECTED TO RETURN AND DECLARE AN EMERGENCY. THE CREW SUBSEQUENTIALLY PERFORMED AN UNEVENTFUL LANDING. U	PON INVESTIGATION BY MAINTENANCE PERSONNEL IT WAS DETERMINED THAT THE LT DOWNLOCK SWITCH PLUNGER HAD FAILED. THE DOWNLOC	K WAS REPLACED AND GEAR SWINGS COMPLETED SERVICEABLE. THE AIRCRAFT WAS RELEASED FOR RETURN TO SERVICE.		1	L	7	2 	4T	4	T	 	A21SO   	E4EA				 
2002011700137	20020117	00137	CE  	2002	1	17	CA011122006      	1	20011120	G	3260	41EN16	SWITCH          			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG	INTERMITTENT    	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA											(CAN) AIRCRAFT DEPARTED AIRPORT AND COULD NOT RETRACT GEAR.  AIRCRAFT DEVERTED TO HOME BASE AND LANDED WITHOUT INCIDENT.	THE SAFETY SWITCH WAS FOUND INTERMITTTANT ON THE RIGHT HAND GEAR TORQUE KNEES.SWITCH WAS REPLACED AND AIRCRAFT RETURNED 	TO SERVICE. NOTE:  PART TIME IS UNKNOWN				1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002011800002	20020118	00002		2002	1	18	CA011123001      	4	20011116	G	6113	055032110	PLATE           	CESSNA      	05503671    	CESSNA	172   	172S        	2072439	CE  	LYC   	IO360 	IO360L2A    	 	EA  	MCAULY	1A170	1A170E      	GL  	PROP SPINNER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE CORNER SECTION OF SPINNER AT LEADING EDGE OF PROPELLER BLADE CUT-OUT BADLY BENT (PEELED BACK) BY CENTRIFUGAL F	ORCE. THIS WAS CAUSED BY THE ADJACENT CORNER SECTION OF THE BACKPLATE (AROUND ANCHOR NUT) BREAKING OFF DURING OPERATION.	 CESSNA HAS RECOGNIZED THIS PROBLEM AND ISSUED MOD KIT MK172-61-01 UNDER SB01-61-01. NEW BACKPLATE DESIGN AND P/N INCORP	ORATED AS PER LISTED KIT AND SB NUMBERS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10	5	N	P857	 
2002021100077	20020211	00077	EU  	2002	2	11	CA011126001      	1	20011122	G	6320	4638302023	BEARING         			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OUTER AND INNER RACE OF BEARING DISPLAY MODERATE PITTING AND PEELING.ONE BALL DISPLAYS HEAVY PITTING						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2002011800005	20020118	00005	GL  	2002	1	18	CA011126002      	2	20011123	G	7250	6006T87G13	NOZZLE          								GE    	CT58  	CT58*       	30011	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE BAFFLE OF THE 3RD STAGE NOZZLE WAS REMOVED TO INVESTIGATE THE CAUSE OF AIR LEAKAGE.  VISUAL AND NDT INSPECTION	 REVEALED CRACKS IN THE SHEET METAL OF THE SUMP ABOVE THE AIR TUBE LOCATION.TELCON WITH GE ON NOV. 21 REGARDING THE CRAC	KS AND THE LACK OF REPAIRABLE OR SERVICEABLE LIMITS IN THIS AREA.  THE PARTS HAVE BEEN FORWARDED TO GE FOR THEIR INVESTI	GATION. 4 OF 5 NOZZLES CHECKED HAD SIMILAR CRACKS.								4	U			1E3				 
2002021100078	20020211	00078	CE  	2002	2	11	CA011126003      	1	20011010	G	5552	1156200219	HINGE           	BEECH       		BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  					LT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			39106	39106							(CAN) DURING ROUTINE INSPECTION, CRACK WAS FOUND ON ELEVATOR HINGE.  PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.	PART AVAILABLE FOR INSPECTION IN QUARANTINE.PART TSO/TSN/CYCLES ARE AIRCRAFT FIGURES.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002021100082	20020211	00082	SW  	2002	2	11	CA011127001      	1	20011113	G	6310	CL422501	CLUTCH          	BELL        	20604023013 	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FREEWHEEL UNIT	BROKEN          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						B12468					(CAN) FREEWHEEL UNIT SENT IN FOR REPAIR OWNER REPORTS: LEAKING AND ROUGH TO TURN ONCE REMOVED. FREEWHEEL DISASSEMBLED AN	D CLUTCH CAGE FOUND CRACKED AND A PIECE BROKEN OFF. THE INNER RACE AND OUTER RACE BOTH FOUND WORN BEYOND LIMITS. BELL HE	LICOPTER PRODUCT SUPPORT TECH REP CONTACTED AND HE WILL BE HERE THURSDAY NOVEMBER 15, 2001 TO VIEW THE DAMAGED UNIT.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002011800006	20020118	00006	EA  	2002	1	18	CA011127002      	2	20010927	G	7414	4771	MAGNETO         			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON LANDING ROLL PILOTS REPORTED A GRINDING NOISE FROM THE ENGINE. - THEY TAXIED OFF THE RUNWAY AND SHUT DOWN. AIRC	RAFT PUSHED TO HANGAR.- INITIAL INVESTIGATION SHOWED DEAD LT MAGNETO (TIMING INDICATOR). - MAGNETO REMOVED, SHAFT BENT A	ND GEAR GROUND BY ENGINE DRIVE GEAR.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002011800007	20020118	00007	GL  	2002	1	18	CA011127004      	2	20011115	G	7250	6898731	SUPPORT         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CA											(CAN) TURBINE ASSY WAS RECD IN FOR SMOKING ON SHUTDOWN. SMOKING WAS ENCOUNTERED APPROX 7 2NDS AFTER THROTTLE WAS ROLLED 	TO OFF POS.UPON DISASSY & INSPECTION OF PT SUPPORT IT FOUND THAT INNER DIAMETER (DIA.S) SHOULDER WIDTH WAS INSUFFICIENT 	FOR PROPER SEALING OF U-RING GASKET. AS A RESULT, THERE WAS A LOSS OF LABYRINTH SEAL PRESSURE & AN INCREASE IN AIR PRESS	URE WITHIN POWER TURBINE SUPPORT OIL SUMP, ALLOWING OIL FROM 6 & 7 BEARING AREA TO ENTER GAS PATH. NOTE: SHOULDER WIDTH 	OF INNER DIAMETER SHOULD BE INSP TO ENSURE SUFFICIENT SURFACEAREA EXISTS FOR PROPER SEALING OF U-RING GASKET (PRINT DIM.	 FOR SHOULDER WIDTH UNAVAILABLE).P/N 6898731;S/N MK18387	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002021200002	20020212	00002	SW  	2002	2	12	CA011127005      	1	20011116	G	2750	B10006	COUPLING        			AIRTRC	AT802 	AT802       	0390305	SW  										FLAP DRIVE	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL INSPECTION THE FLAP DRIVE RUBBER COUPLING WAS FOUND TO BE SPLIT, EARLIER IN THE OPERATING SEASON A L	OOSE WIRE ON THE FLAPS DOWN SWITCH CAUSED THE FLAPS TO OVERTRAVEL AND BOTTOM OUT THE ACTUATOR. EXPERIENCE HAS SHOWN THAT	 WHEN THIS SITUATION HAPPENS, THE RUBBER COUPLING IS DAMAGED FROM THE SUDDEN STOPPAGE. THE RUBBER COUPLING SHOULD BE INS	PECTED ANY TIME AN OVERTRAVEL IS EXPERIENCED.			1	L	7	1 	3T			NC	A19SW   					 
2002021200003	20020212	00003	CE  	2002	2	12	CA011127006      	1	20011126	G	5730		SKIN            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON A RECENT ROUTINE INSPECTION ON LJ886 A CRACK WAS FOUND ON THE LT UPPER WING SKIN AT STA 175 AND WL 81 SEEN FROM	 THE UNDERSIDE IN THE WHEELWELL.  THE AFT NACELLE FAIRING WAS REMOVED AND ANOTHER CRACK WAS FOUND AT STA 182 AND WL70.TH	E AFT NACELLE FAIRING OF THE RT WING WAS REMOVED AND SUBSEQUENTLY TWO MORE CRACKS IN THE SAME LOCATIONS DESCRIBED ON THE	 LT WING WERE FOUND.			1	L	7	2 	3T	4	T	 	3A20    	E4EA				 
2002011800008	20020118	00008	EU  	2002	1	18	CA011127009      	1	20011022	G	2434	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE CARRYING OUT REPLACEMENT OF GEN 2 DRIVE ASSY OUTER BEARING FOR 3000 HR REQUIREMENTS, IT WAS NOTED THAT THE D	RIVE SHAFT WAS WORN AT THE BEARING JOURNAL AND THE BEARING WAS LOOSE ON THE SHAFT. THE DRIVE SHAFT HAD TO BE REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021200004	20020212	00004	EU  	2002	2	12	CA011127010      	1	20011120	G	2497	350A311851	STRAP           			SNIAS 	350   	AS350B2     	8680813	EU  										ELECTRICAL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  THREE BONDING STRAPS ARE FRAYED HALFWAY THROUGH.						1	G	7	1 	3U			 	H9EU    					 
2002021200005	20020212	00005	CE  	2002	2	12	CA011127011      	1	20011120	G	5343	36653RH	FITTING         			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INTERGRANULAR CORROSION ON FUSELAGE FITTING.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002021200006	20020212	00006	EU  	2002	2	12	CA011127012      	1	20011120	G	2750	9740338111	CONTACTOR       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	TE FLAP PDU	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE LOWERING THE FLAPS DURING ROUTINE MAINTENANCE, THE FLAP POWER DRIVE UNIT (PDU )WAS LABOURING. THE FLAP DRIVE	 SHAFTS WERE DISCONNECTED AT THE PDU,  BUT THE PDU WAS STILL LABOURING. THE PDU WAS REPLACED,  BUT THE CONDITION STILL P	ERSISTED. THE K670 CONTACTOR WAS REPLACED AND THE PDU OPERATED NORMALLY. THE SUSPECT K670 CONTACTOR WAS TAKEN APART AND 	DISCOVERED THAT THE CONTACTS WERE BADLY BURNED.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021200024	20020212	00024	EA  	2002	2	12	CA011128008      	1	20010722	G	2432		CELL            	MARATHON    	MA300H      	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					BATTERY	DEFORMED        	W				H				DEACTIVATE SYST/CIRCUITS				B	H	M	SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   	OVER TEMP                 	TX	TAXI/GRND HDL  	1			CA						9802292					(CAN)    SMOKE WAS VISIBLE IN THE BAGGAGE COMPARTMENT WHEN OPENED ON THE RAMP.  ONE CELL WITHIN THE BATTERY WAS FOUND TO	 BE DEFORMED FROM HEAT.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002021200028	20020212	00028	CE  	2002	2	12	CA011128016      	1	20011030	G	5411	90120003	ANGLE           			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT & RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INSIDE LT AND RT MAIN LANDING GEAR WELLS, OUTBOARD SIDE WALL, ANGLE AT CORNER OF SIDE WALL AND FORWARD FACE OF MAI	N SPAR WEB, LOWER END OF ANGLE. POSSIBLE NEED TO REMOVE PAINT TO NOTE CRACK. BOTH CRACKS  APPROX. .75 INCHES IN LENGTH.					1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002021200054	20020212	00054	CE  	2002	2	12	CA011128017      	1	20011114	G	3500	503800573	HOSE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					OXYGEN SYS	BROKEN          	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN)  HOSE BROKE CAUSING LOSS OF PRESSURIZATION, REPLACED HOSE AND FLIGHT TESTED SERVICEABLE.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002021200055	20020212	00055	SO  	2002	2	12	CA011128018      	1	20011120	G	2910	4083300	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					HYD POWERPACK	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH PILOT SELECTED GEAR DOWN WITH NO INDICATION OF ANY MOVEMENT OF THE GEAR.  MANUALLY HAND PUMPED GEAR WI	TH NO SUCCESS.  AFTER SEVERAL ATTEMPTS AND BURNING OFF EXCESS FUEL MADE A GEAR UP LANDING WITH NO DIFFICULTY. ON INSPECT	ION FOUND THE GEAR DOWN LINE AT THE POWER PACK BROKEN AT THE FLARE. REPAIRED LINE INSTALLED AND GEAR FUNCTIONED NORMALLY	 AFTER FILLING WITH FLUID.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021200056	20020212	00056	SW  	2002	2	12	CA011130001      	1	20011108	G	2750	12395	PULLEY          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAPS	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - LT & RT PULLEYS AT WING ROOT FOUND SEIZED AND WORN. - BOTH FLAP CABLES FRAYED AT THAT POSITION. - SMALL ALUMINUM	 PULLEYS, HARD TO LUBRICATED AND PROVIDE A TIGHT DEFLECTING RADIUS FOR CABLES.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200057	20020212	00057	SW  	2002	2	12	CA011130002      	1	20011108	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 & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS.   BOTH LT & RT PULLEYS FOUND SEIZED AND WORN.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200058	20020212	00058	SW  	2002	2	12	CA011130003      	1	20011109	G	2750	12395	PULLEY          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					TE FLAPS	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   LT & RT PULLEYS AT WING ROOT FOUND SEIZED AND WORN.   BOTH FLAP CABLES FRAYED AT SAME LOCATION.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200059	20020212	00059	SW  	2002	2	12	CA011130004      	1	20011109	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 & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS.    BOTH LT & RT PULLEYS FOUND SEIZED AND WORN.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200060	20020212	00060	SW  	2002	2	12	CA011130005      	1	20011109	G	2810	714941R	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RT OUTBOARD	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) RT OUTBOARD TANK CRACKED,  LOWER SIDE,  AT THE END OF REINFORCING INDENT,  ON PREVIOUSLY REPAIRED WELD.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200061	20020212	00061	SW  	2002	2	12	CA011130006      	1	20011124	G	6500	407340339103	BEARING         	BELL        	407040303101	BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					FAN SHAFT	FAILED          	W				A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) WHILE ON 5TH SCENIC TOUR OF DAY, AT 2,500 FT ASL IN QUIET MODE CRUISE, A/C SOUND & VIBRATION LEVEL SUDDENLY CHANGE	D FROM NORMAL TO LOUD WITH HEAVY VIBRATION FROM TAIL ROTOR DRIVE AREA.  PILOT IMMEDIATELY RETURNED A/C TO NORMAL MODE CR	UISE RPM & EXITED SCENIC ROUTE. HE RETURNED DIRECTLY TO MAIN BASE AT PQ3 WITH PRECAUTIONARY LDG & SHUTDOWN WITHOUT FURTH	ER INCIDENT. TAIL ROTOR CONTROL AUTHORITY NEVER LOST.  AFTER ENGINE SHUTDOWN, INSPECTION REVEALED A COMPLETELY FAILED FW	D FAN SHAFT BEARING WITH DISINTEGRATED BEARING CAGE.		1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2002021200064	20020212	00064	SO  	2002	2	12	CA011130012      	1	20011121	G	3260	487312	SPRING          	PIPER       		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					DOWNLOCK	BROKEN          	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) - RIGHT HAND MAIN LANDING GEAR INDICATION FAILED IN FLIGHT. - PILOT RECYCLED GEAR AND LIGHT APPEARED TO WORK. - IN	SPECTION REVEALED A BROKEN DOWNLOCK SPRING.					1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2002021200065	20020212	00065	CE  	2002	2	12	CA011130014      	1	20011121	G	7820	04504004	MUFFLER         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENG EXHAUST	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) A NOISE WAS HEARD IN CRUISE. MUFFLER FOUND CRACKED BEFORE RISER.						1	H	7	1 	3O	3	O	 	3A19    	E252				 
2002021200069	20020212	00069	EA  	2002	2	12	CA011203001      	2	20011127	G	7414	1068291013	CASE            	BENDIX      	1068291013  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						85410122T					(CAN) CASE FLANGE BROKEN UNDER UPPER RETAINER.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021200072	20020212	00072	EU  	2002	2	12	CA011203005      	1	20011203	G	6320	461920400146382	BEARING         			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEAR BOX	PEELING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   BOTH THE PLANETARY AXLE AND ROLLER BEARING PLATING PEELING.						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2002021200074	20020212	00074	SW  	2002	2	12	CA011205001      	1	20011204	G	5712	21588	RIB             			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3 RIBS RT,  2 RIBS LT WING FOUND CRACKED AT UPPER CORNER OF FLANGE WHERE RIB ATTACHES TO REAR SPAR.  ALL RIBS LOCA	TED CLOSEST INBOARD AT WING ROOT, AND ALL RIBS CRACKED EXACTLY THE SAME.					1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021200104	20020212	00104	CE  	2002	2	12	CA011205003      	1	20011204	G	5744	0523921	BUSHING         	CESSNA      	0523919     	CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  					TE FLAP SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE PREFORMING A FLAP SUPPORT INSPECTION,  A CRACK WAS FOUND ON THE FLAP ROLLER BUSHING (LT REAR). THE CYLINDRIC	AL BUSHING WAS SPLIT IN HALF AND ONLY BECAME APPARENT WHEN THE BUSHING WAS REMOVED FROM THE FLAP ROLLER ASSEMBLY.					1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002021200105	20020212	00105	CE  	2002	2	12	CA011205004      	1	20011204	G	2720	05121602	BRACKET         			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  					CABLE PULLEY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A ROUTINE 100 HOUR INSPECTION THE RUDDER CABLE PULLEY BRACKETS THAT ARE LOCATED AT THE BATTERY BOX BULKHEAD	,  WERE BOTH FOUND TO BE CRACKED AT THE TOP ATTACH POINT (RIVET). BOTH BRACKETS WERE REPLACED.					1	H	7	1 	3O	3	O	 	5A6     	E273				 
2002021200106	20020212	00106	EA  	2002	2	12	CA011205005      	1	20011204	G	3250	C2UT473	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					TAIL WHEEL	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) INVESTIGATION REVEALED A SHEARED TAIL WHEEL STEERING TORQUE TUBE ASSEMBLY (WATER RUDDER).  INTERNAL CORROSION WAS 	PRESENT INSIDE THE TUBE ASSEMBLY. NO ABNORMAL CONDITION PRESENT ON THE EXTERNAL PORTION OF THE TUBE.THE TORQUE TUBE FAIL	URE TOOK PLACE AT THE WELDED JUNCTION OF THE SPLINE SHAFT AND TUBE ASSEMBLY.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002021200107	20020212	00107	EA  	2002	2	12	CA011205006      	1	20011115	G	6123		CONTROL UNIT    			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF15      	NE  	NR 2 ENGINE	MALFUNCTIONED   	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) PRIOR TO TAKE-OFF,  AUTOFEATHER ARMING BAULKED,  ACTIVATED ON RE-SELECTION.  ON TAKE-OFF,  AFTER GEAR UP SELECTION	, NR 2 ENGINE INITIATED UNCOMMANDED AUTOFEATHER (TORQUE 125 PERCENT PLUS). CREW DE-SELECTED AUTOFEATHER WITHIN FOUR SECO	NDS, TORQUE RETURNED TO NORMAL. AIRCRAFT RETURNED TO BASE, AND ENGINE / PROP CHANGE CARRIED OUT. ENGINE TORQUE PROBE, HA	RNESS AND TSCU SHIPPED TO OEM FOR ANALYSIS,			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002021200108	20020212	00108	EU  	2002	2	12	CA011207002      	1	20011207	G	7170	6859172	TUBE            			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL DRAIN	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DRAIN LINE CHAFING ON FUEL CONTROL TO FUEL PUMP BY PASS TUBE  IS 99 PERCENT CHAFED.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002021200114	20020212	00114	EU  	2002	2	12	CA011207004      	1	20011022	G	2920	MVT1001	SELECTOR VALVE  			AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) THE AIRCRAFT ARRIVED TO YYZ,  WITH THE "YELLOW" HYDRAULIC SYSTEM EMPTY.   FOUND RT ELEVATOR,  OUTBOARD SERVO (F.I.	N.3CS2) SELECTOR VALVE HOUSING CRACKED.					1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002021200118	20020212	00118	EU  	2002	2	12	CA011209002      	1	20011129	G	3251	C247820001	SOLENOID VALVE  		C248560014  	AIRBUS	330   	A330342     	       	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					NLG STEERING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DEACTIVATION OF THE NOSE LANDING GEAR STEERING SYSTEM, THE NOSE WHEELS TURNED 90 DEGREES RIGHT WITHOUT ANY 	STEERING INPUT WHEN STEERING / ANTI-SKID SWITCH WAS TURNED OFF. AT THAT MOMENT THE THE AIRCRAFT CONDITION WAS:-STEERING 	BY-PASS PIN INSTALLED IN TOW POSITION.-BOTH ENGINE MASTER SWITCH OFF. -GREEN ELECTRICAL HYDRAULIC PUMP ON.-UPON REMOVING	 AND OPENING THE SOLENOID VALVE ASSY , WE DISCOVERED THAT THE LINER (MADE OF ALUMINIUM ALLOY) WAS BROKEN (SHEARED).			1	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002021200131	20020212	00131	CE  	2002	2	12	CA011210009      	1	20011029	G	7170	A1090	DRAIN VALVE     			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RT ENGINE	BROKEN          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) DURING THE LATTER PART OF A FLIGHT THE RT NACELLE WAS SHOWING A DECLINE IN DUEL CAPACITY ABOVE NORMAL. WHEN REACHI	NG THE DESTINATION IT WAS DISCOVERED THAT FUEL WAS ESCAPING FROM THE RT FUEL MANIFOLD DRAIN. UPON FURTHER INVESTIGATION 	IT WAS FOUND THAT THE CENTRE PORTION OF THE DRAIN VALVE HAD BROKEN OFF AND FALLEN OUT.				1	L	7	2 	3T	3	T	 	A14CE   	E4EA				 
2002021200133	20020212	00133	GL  	2002	2	12	CA011210010      	2	20011130	G	7323		DRIVE SHAFT     	ALIDSG      	252476914   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						17611					(CAN) PILOT REPORTED IN NORMAL LEVEL CRUISE FLIGHT AT LOW TO MEDIUM TORQUE SETTING. HE FELT, HEARD AND NOTICED A POWER S	URGE AND GAUGE FLUCTUATION APPROX. 2 PERCENT N1. THIS WOULD OCCUR FOR JUST A SECOND AND WOULD ONLY OCCASIONALLY HAPPEN 1	 TIME OR SEVEERAL TIMES IN A 1 HOUR PERIOD. THE A/C RETURNED BACK TO BASE AFTER COMPLETING HIS WORK AND WAS DUE FOR 100 	HR INSPECTION,  THE GOVERNOR WAS REMOVED FOR INSPECTION AND THE DRIVE END AND CIRCLIP WERE FOUND LOOSE AND READY TO FALL	 OFF. THIS GOVERNOR HAS BEEN REMOVED 3 PREVIOUS TIMES FOR SURGING, DROOPING AND THE LAST TIME FOR THE DRIVESHAFT END FAI	LURE.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002021200134	20020212	00134	NE  	2002	2	12	CA011210012      	2	20011126	G	8520		CONNECTING ROD  			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			CA											(CAN) THE A/C WAS ESTABLISHED IN CRUISE WHEN THE PILOT NOTICED ENGINE VIBRATION FOR APPROXIMATELY 5 SECONDS. THIS WAS FO	LLOWED BY AN ABRUPT ENGINE STOPPAGE. THE PILOT SAFELY GLIDED TIME A/C TO A NEARBY RIVER. UPON ENGINE TEARDOWN THE NR 1 &	 2 CONNECTING RODS WERE BROKEN & THE NR 1 WRIST PIN BENT.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002021200136	20020212	00136	CE  	2002	2	12	CA011210013      	1	20011122	G	3397	20GAUGE	WIRE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	EXTERIOR LIGHTS	SHORTED         	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA											(CAN) NAV. LIGHT CIRCUIT BREAKER WAS FOUND POPPED THE WIRES TO THE LIGHT IN THE TAIL CONE WERE SHORTED TOGETHER. THESE 2	 WIRES SHORTED PORTION WERE REMOVED AND THE WIRES SPLICED TOGETHER. THERE ARE TIE-WRAPS HOLDING THE WIRES TO THE SIDE OF	 THE TAIL CONE.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002021200146	20020212	00146	SW  	2002	2	12	CA011210017      	1	20011203	G	5532	410008173	SKIN            			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  DURING INSPECTION OF THE AIRCRAFT,  CRACKS WERE NOTED ON THE VERTICAL STABILIZER SKIN.  THE CRACKS WERE LOCATED A	T THE FIRST FASTENER ABOVE THE DOUBLER AT THE CENTRE SPAR. THE LONGEST CRACK MEASURED .75 INCHES IN LENGTH. A X-RAY INSP	ECTION WAS ACCOMPLISHED IN THE AREA OF THE DOUBLER AND 2 CRACKS WERE NOTED ON THE SKIN AT THE FASTENER THAT WAS UNDERNEA	TH THE DOUBLER. THE DOUBLER WAS REMOVED FROM THE AIRCRAFT TO INSPECT THE AREA NO FURTHER DAMAGE WAS NOTED.			1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2002021200149	20020212	00149	SW  	2002	2	12	CA011210018      	1	20011203	G	2810	5129811	LINE            			AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A67A     	52043	NE  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE AIR CONDITIONER DRIVE ASSY WAS BEING REMOVED FOR LUBRICATION. IT WAS NOTED THAT THE FIRE SLE	EVING OF THE FLEX FUEL PRESSURE LINE,  HAD BEEN WORN THROUGH. FURTHER INVESTIGATION REVEALED THAT THE STEEL FITTING ATTA	CHING THE FUEL LINE TO THE FUEL PUMP ASSY. HAD COME LOOSE AND ALLOWED THE FUEL LINE TO CONTACT THE AIR CONDITIONING SYST	EM COMPRESSOR PULLEY. THE OUTER RUBBER OF THE FUEL LINE WAS ALSO DAMAGED.  THE LINE WILL BE REPLACED WITH A SERVICEABLE 	UNIT,  AND THE REST OF THE AIRTRACTOR FLEET WILL BE INSPECTED PRIOR TO FURTHER FLIGHT.		1	L	7	1 	3T	4	T	NC	A19SW   	E26NE				 
2002021200155	20020212	00155	EU  	2002	2	12	CA011210020      	1	20011207	G	2434	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3000 HR. REPLACEMENT OF OUTER DRIVE SHAFT BEARING WAS CARRIED OUT.  ON DISASSEMBLY OF DRIVE HOUSING ASSEMBLY,  THE	 INNER BEARING MOUNTING SURFACE OF DRIVE SHAFT WAS FOUND WORN DUE TO DRIVE SHAFT SPINNING IN THE INNER RACE OF THE BEARI	NG.A NEW DRIVE SHAFT WAS INSTALLED AND AFTER 4 HRS. OF OPERATION, GENERATOR NR 2 FAILED.IT WAS FOUND THAT THE NEW DRIVE 	SHAFT INSTALLED HAD SHEARED AFTER THE SPLINE DRIVE.			1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021200161	20020212	00161	GL  	2002	2	12	CA011211001      	2	20011207	G	7321	6859172	DRAIN LINE      			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DRAIN LINE CHAFING ON FUEL CONTROL TO FUEL PUMP BYPASS TUBE P/N 6859172 TUBE IS 99 PERCENT CHAFED.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002021200174	20020212	00174	SW  	2002	2	12	CA011211002      	1	20011122	G	6510	204040612001	BOLT            	BELL        	212040004003	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					QUILL ASSY	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THIS BOLT HOLDS THE TAIL ROTOR DRIVESHAFT COUPLING TO THE INPUT QUILL OF THE 90 DEGREE GEARBOX. WHEN THE BOLT WAS 	REMOVED FOR SCHEDULED MAINTENANCE (GREASE REPACKING). IT WAD NOTICED THAT IT WAS NOT THE NORMAL COLOR (BLACK) THAN IT WA	S NOTICED THAT IT WAS DISTORTED AROUND THE FLANGE RADIUS. EVEN CLOSER INSPECTION SHOWS THAT THE BOLT DUE TO THE BEND IN 	THE FLANGE IS NOW LONGER. THE BOLT SHOWS SIGNS OF STRETCHING AND TOOL MARKS MAY INDICATE THAT IT WAS MANUFACTURED BY SOM	EONE OTHER THAN THE ORIGINAL MANUFACTURE. THERE IS NO PART NO. WRITTEN ON THIS PART AS THERE IS A NEW ONE. I BELIEVE THI	S IS AN UNAPPROVED PART (BOGUS). PART HELD FOR INVESTIGATION.	1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002021200176	20020212	00176	EA  	2002	2	12	CA011211003      	1	20010516	G	7603	C2CE67A	CONTROL CABLE   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUEL SELECTOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15315	15315							(CAN) CABLE FRAYED WHERE IT BENDS AROUND FUEL SELECTORPULLEY. ITEM NOTED DURING ANNUAL INSPECTION. IT IS ADVISEABLE TO H	AVE SOMEONE MOVE THE FUEL SELECTOR CONTROL WHILE INSPECTING TO ACCESS AS MUCH OF CABLE AS POSSIBLE AS ITS INSTALLED.					1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002021200179	20020212	00179	CE  	2002	2	12	CA011211004      	1	20010614	G	2720	0510105173	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FWD (CARRY-THROUGH) CABLE REMOVED TO CARRY OUT AN INSPECTION ON IT'S CONDITION DUE TO THE FACT THAT IT IS IMPOSSIB	LE TO FEEL OR SEE MOST OF THE CABLE AS IT'S INSTALLED IN THE A/C. INSPECTION REVEALED FRAYED SECTION WHERE CABLE GOES AR	OUND THE PULLEY SUGGEST REMOVING ALL SIMILAR CABLE AT TAT 5000HRS TO COMPLETE INSPECTION.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002021200180	20020212	00180	CE  	2002	2	12	CA011211005      	1	20010520	G	5511	07326032	CHANNEL         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CHANNEL FOUND CRACKED DIRECTLY BEHIND LT STAB HINGE REINFORCEMENT,   WHICH WAS ALSO CRACKED. FURTHER INVESTIGATION	 REVEALED CRACKED SPAR  ALSO IN SAME AREA.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002021300001	20020213	00001	GL  	2002	2	13	CA011211009      	1	20010516	G	2720	C2CF741AND	CONTROL CABLE   			DHAV  	DHC1  	DHC1B2      	2801736	GL  										RUDDER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13345	13345							(CAN)  CONTROL CABLE NOTED TO BE FRAYED AFT OF IT'S ATTACHMENT TO THE LT RUDDER PEDAL.						1	L	7	1 	3O			 	EXPA1L71					 
2002021300004	20020213	00004	SW  	2002	2	13	CA011211013      	1	20011204	G	3222		STRUT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20R2    	 	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2002021300005	20020213	00005	SW  	2002	2	13	CA011211014      	1	20011204	G	3222		STRUT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2002021300006	20020213	00006	SW  	2002	2	13	CA011211015      	1	20011204	G	3222		STRUT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2002021300007	20020213	00007	SW  	2002	2	13	CA011211016      	1	20011123	G	3222		STRUT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2002021300008	20020213	00008	SW  	2002	2	13	CA011211017      	1	20011204	G	3222		STRUT           			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	25OC  	250C20R     	 	GL  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE				 
2002020500128	20020205	00128	EA  	2002	2	5	CA011211018      	2	20011205	G	7320	A5222690	THROTTLE CABLE  	BELL        	A5222640    	BELL  	47    	47G2        	1181008	SW  	LYC   	O435  	VO435A1E    	41516	EA  	 		            		BELOW RH ENGINE	FROZEN          	W			    	B	 	 	 	EMER. DESCENT           				F	 	 	FLT CONT AFFECTED         			CR	CRUISE         	1			CA		 									(CAN) THROTTLE FROZEN AT CRUISE POWER WHEN HELICOPTER CLIMBED THROUGH FREEING LEVEL AT APPROXIMATE 3,000'. THE CABLE BEC	AME UNSTUCK WHEN THE HELICOPTER RETURNED TO A LOWER LEVEL. BY THIS TIME THE PILOT (FLIGHT INSTRUCTOR) CARRIED OUT AN AUT	O ROTATION TO ABBOTSFORD AIRPORT AND HOVER TAXIED BACK TO THE HANGAR.				1	G	7	1 	3O	3	O	 	H1      	E279				 
2002021300009	20020213	00009	CE  	2002	2	13	CA011211019      	1	20010508	G	5521	07346041	RIB             			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	LT ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEAD BALANCE WEIGHT ATTACHES TO AFFECTED RIB AND CORROSION FORMED DUE TO DISSIMILAR METAL.  AREA IMPOSSIBLE TO INS	PECT UNLESS ELEVATOR TIP SKIN IS REMOVED TO ACCESS RIB. UPON REPLACEMENT OF RIB,					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002021300017	20020213	00017	EA  	2002	2	13	CA011212002      	2	20011203	G	8530	AEL6510241	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING A REGULAR MAINTENANCE INSPECTION THE CYLINDERS WERE VISUALLY CHECKED USING A BORESCOPE,  CRACKS WERE NOTED 	AT THE SPARK PLUGS PORTS OF NR 1 & 2 CYLINDERS. ALL CYLINDERS WERE REMOVED AND REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002021300018	20020213	00018	CE  	2002	2	13	CA011212003      	1	20011202	G	5610	5042006938	WINDSHIELD      			BEECH 	100   	B100        	1152919	CE  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) WINDSHELD CRACKED / CRAZED DURING CRUISE FLIGHT. THE CREW LOWERED CABIN PRESSURE,  DISCOUNTINUED HEAT AND LANDED W	ITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE INNER LAMINATE LAYER OF THE WINDSHIELD PRC SEALED TO THE WINDOW FRAME STR	UCTURE WHICH PREVENTED FREE FLOATING OF THE WINDSHIELD WITHIN THE WINDOW FRAME CREATING STRESS TO THE INNER LAMINATE LAY	ER WHICH-EVENTUALLY CRACKED. A NEW WINDSHIELD ASSY WAS INSTALLED.			1	L	7	2 	4T			 	A14CE   					 
2002021300019	20020213	00019	CE  	2002	2	13	CA011212004      	1	20011211	G	2140		DIAPHRAGM       			CESSNA	401   	401         	207590C	CE  	CONT  	O520  	TSIO520E    	17040	SO  					HEATER FUEL PUMP	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)  FUEL WAS NOTICED LEAKING FROM THE HEATER FUEL PUMP VENT LINE. THE FUEL PUMP WAS DISMANTLED AND THE DIAPHRAM WAS F	OUND TO HAVE FAILED CAUSING FUEL TO LEAK DOWN TO THE BEARING, REMOVING ALL LUBRICATION AN ALSO FALLING. THE FUEL PUMP WA	S REPLACED.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE				 
2002021300020	20020213	00020	CE  	2002	2	13	CA011214001      	1	20011214	G	7931	PTI052287579522	OIL FILTER      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE OIL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN REPLACING INBD O-RING, FOUND VERY SHARP EDGE IN OIL FILTER BODY DAMAGING O-RING EVERY TIME.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002021300021	20020213	00021	CE  	2002	2	13	CA011217001      	1	20011011	G	3233	115380103	BEARING         			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					MLG ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN)  ON CLIMBOUT  RT GEAR DID NOT INDICATE UP & LOCKED & INTRANSIT LIGHT ILLUMINATED.  GEAR EXTENDED, THIS TIME GEAR D	ID NOT INDICATE DOWN & LOCKED & INTRANSIT LIGHT REMAINED ILLUMINATED.  UPON LDG RT MAIN GEAR COLLAPSED.  LDG GEAR ACTUAT	OR REMOVED & SENT TO TSB LAB FOR ANALYSIS.  IT DETERMINED THAT THRUST BEARING IN ACTUATOR WAS INSTALLED BACKWARDS.  RESU	LTING FAILURE OF THRUST BEARING CAUSED TEETH ON PINION & RING GEAR TO FAIL.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002021300023	20020213	00023	EU  	2002	2	13	CA011217004      	1	20011212	G	2434	5243212137	DRIVE SHAFT     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	NR 2 GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE 3000 HOUR INSPECTION THE DRIVE SHAFT WAS FOUND TO BE WORN AT THE FWD END OF THE SHAFT.  THIS CAUSED	 THE SHAFT TO WOBBLE EVEN WITH THE NEW BEARING IN PLACE.FWD BEARING WAS NOT SIEZED OR STIFF.NEW SHAFT AND BEARINGS INSTA	LLED.				1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021300024	20020213	00024	SO  	2002	2	13	CA011217005      	1	20011028	G	3710	61183	GASKET          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					VACUUM PUMP	TORN            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K			FLUID LOSS                			CR	CRUISE         	1			CA											(CAN) PILOT EXPERIENCED OIL PRESSURE LOSS RT ENGINE WHILE INCRUISE. SHUTDOWN AND A/C LANDED WITH NO OTHER INCIDENT. ENGI	NE WAS REMOVED. INSPECTION FOUND ONE LOOSE VACUUM PUMP RETENSION NUT. WHEN PUMP AND ADAPTOR REMOVED GASKET FOUND TORN AR	EA NEAR LOOSE NUT. THIS AREA COVERS AN OIL JET WHICH IS NOT USED FOR THIS VACUUM PUMP INSTALLATION.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021300029	20020213	00029	WP  	2002	2	13	CA011217011      	2	20011120	G	7250	31081251	BLADE           								GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  BORESCOPE INSPECTION REVILED ERODED BLADES AT FUEL NOZZLE CHANGE.											4	T			E4WE				 
2002021300030	20020213	00030	EU  	2002	2	13	CA011217013      	1	20011212	G	2435	23085024	STARTER GEN     			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	ENGINE	WRONG PART      	W				D				RETURN TO BLOCK         				W			INADEQUATE Q C            			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER- GEN REMOVED PREMATURELY AT 950 HRS TSO DUE TO UNIT BEING VERY NOISY AT LOWER RPMS. UNIT TAKEN TO AMO FOR 	OVERHAUL. ON DISASSEMBLY, IT WAS NOTICED THAT UNIT DOES NOT PHYSICALLY CORRESPOND WITH MANUFACTURE`S STARTER-GEN.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021300032	20020213	00032	SO  	2002	2	13	CA011217016      	1	20011210	G	2140	88D9310	COMBUST CHAMBER 	JANITROL    	90D382      	PIPER 	PA44  	PA44180     	7104402	SO  										HEATER	CRACKED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						A95080021					(CAN)   THE COMBUSTION TUBE LEAK RATE WAS GREATER THAN ALLOWED AMOUNT. THE HEATER ASSEMBLE WAS REMOVED AND THE COMBUSTIO	N TUBE WAS REMOVED FROM THE HEATER ASSEMBLY. ANOTHER DECAY TEST WAS CARRIED OUT ON THE COMBUSTION TUBE AND WAS FOUND TO 	HAVE A 1 INCH CRACK ON THE AFT FACE. THE COMBUSTION TUBE WAS SENT OUT FOR REPAIR. IT IS FELT THAT THE HEATER CRACKED DUE	 TO THE CONSTANT HEATING AND COOLING DURING REGULAR CYCLES OF THE HEATER OPERATIONS.			1	L	7	2 	3O			 	A19S0   					 
2002021300033	20020213	00033	CE  	2002	2	13	CA011217017      	1	20011207	G	3213	30A04000100	STRUT           			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 1/4 INCH RETAINER PIN BROKE AT COTTER PIN HOLE ON RT SHOCK STRUT ASSY. WHEN THE RETAINER PIN FALLS OUT THE LANDING	 GEAR FALLS DOWN.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2002021300034	20020213	00034	EA  	2002	2	13	CA011217018      	2	20011130	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING SCHEDULED 50 HOUR INSPECTION THAT CONTAINED TASKS REQUIRED TO COMPLY WITH THE ENGINE ON THE CONDITIONS PROG	RAM ESTABLISHED FOR THE ENGINE BEING INSPECTED, A MODERATE AMOUNT OF VERY SMALL METAL PARTICLES WERE FOUND IN THE OIL FI	LTER ELEMENT DURING INSPECTION. NUMBER ONE CYLINDER WAS REMOVED IN ORDER TO INVESTIGATE THE SOURCE OF THE SOURCE OF THE 	METAL CONTAMINATION. WITH THE CYLINDER REMOVED IT WAS OBSERVED THAT THE FRONT LOBE OF THE ENGINE CAM SHAFT WAS WORN ABNO	RMALLY AND THE CAM FOLLOWER WAS VERY BADLY SPALLED. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT OUT FOR REPAIR.		1	L	7	1 	3O	3	O	0	A76EU   	1E10				 
2002021300035	20020213	00035	NM  	2002	2	13	CA011217019      	1	20011101	G	6320	A0061	GEARBOX         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					MAIN ROTOR	MAKING METAL    	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) OCT23 AT 1290 HRS M/R OIL CHANGED (500 HR CHANGE. OCT 30 IN CRUISE FLIGHT MAIN ROTOR CHIP LIGHT -M/R CHIP PLUG REM	OVED AND CLEANED OCT 31. OCT 31 MADE ANOTHER FLIGHT 1.1 HRS NO CHIP LIGHT. NOV.1 ON START UP CHIP LIGHT ON M/R AGAIN. SH	UT-DOWN AND INSPECTED-FOUND NUMEROUS CHIPS AGAIN. M/R TRANSISSION REMOVED AND SENT TO ROBINSON FOR REPAIR OVERHAUL WAS R	EQUIRED. NO REPORT ON WHAT PART FAILED.			1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002021300053	20020213	00053	EA  	2002	2	13	CA011217025      	1	20011217	G	3411		CONNECTOR       	KOLLSMAN    	518B02      	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					PITOT HEAD	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA			21548			3342					(CAN) DURING A ROUTINE INSPECTION ,  WHEN THE PITOT HEATER SWITCH WAS SELLECTED THE CIRCUIT BREAKER WOULD POP.  INVESTIG	ATION REVEALED THAT THE FEMALE ELECTRICAL CONNECTER TO THE PITOT HEAD HAD FAILED CAUSING A DIRECT SHORT.  THE FEMALE PIN	 CONNECTER WAS REPLACED WITH A NEW UNIT.				1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002021300054	20020213	00054	EA  	2002	2	13	CA011218002      	1	20011128	G	7603	C6EC12551	THROTTLE CABLE  			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURIING A ROUTINE EMMA CHECK 46, THE LT ENGINE THROTTLE CABLE TURNBUCKLE END WAS FOUND FRACTURED AND WAS ONLY HELD	 TOGETHER BY LOCKWIRING. CABLE REPLACED.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA				 
2002021300065	20020213	00065	EA  	2002	2	13	CA011218009      	1	20011129	G	2720	VALLT2CF1029R1	CONTROL CABLE   			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	FRAYED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA											(CAN)  FOUND THE FORWARD RUDDER CABLE TO BE SHOWING WEAR AT THE LOCATION AT THE FAIRLEAD AT STATION 8.00.  THE CABLE WAS	 REPLACED WITH A NEW UNIT AND THE CABLE RUN WAS CHECKED THROUGH THE FAIRLEAD.					1	H	7	1 	3R	4	T	 	A806    	E4EA	6	C	P15EA	 
2002021300068	20020213	00068		2002	2	13	CA011218012      	4	20011217	G	2562		ELT             																	SAFETY EQUIP	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING ANNUAL RECERTIFICATION ELT WAS FOUND TO HAVE NO TRANSMIT.  UNIT WAS RETURNED TO THE MANUFACTURER FOR REPAIR	.																		 
2002021300069	20020213	00069		2002	2	13	CA011218013      	4	20011217	G	2562		SWITCH          	POINTER     	400010      															ELT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						408494					(CAN) DURING ANNUAL RECERTIFICATION ELT G-SWITCH FAILED TO ACTIVATE UNIT. UNIT WAS RETURNED TO THE MANUFACTURER FOR REPA	IR.																		 
2002021300070	20020213	00070	SO  	2002	2	13	CA011219003      	1	20011130	G	7603	2489418	THROTTLE CABLE  			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) UPON REACHING CRUISE ALTITUDE,  WHILE ATTEMPTING TO SET CRUISE POWER LEFT THROTTLE CABLE JAMMED AT 38 INCHES MANIF	OLD PRESSURE. MTCE INSP REVEALED.  LE THROTTLE CABLE SEIZED UPON ATTEMPTS TO FREE CABLE, CABLE BROKE APPROX. 1 INCH INSI	DE CABLE FROM QUADRANT SWAGE CONNECTION.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021300072	20020213	00072	CE  	2002	2	13	CA011219004      	1	20011205	G	3220	124340215	TRUNNION        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NOSE LANDING GEAR LOWER TRUNNION FOUND CRACKED.						1	H	7	1 	3O	3	O	 	3A21    	E8CE	5	C	P47GL	 
2002021300074	20020213	00074	EA  	2002	2	13	CA011219005      	2	20011123	G	7322	1060301	CARBURETOR      			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	MALFUNCTIONED   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CA											(CAN)   ENGINE ROUGH AND SLOW AT RECOVERY FROM AUTOROTATOR. REPLACE CARBURATOR.						1	G	7	1 	3O	3	O	O	4H12    	E286				 
2002021300077	20020213	00077	CE  	2002	2	13	CA011219006      	1	20010520	G	5312	07421155	BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	CARGO BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK NOTED ON LT BULKHEAD DURING INSPECTION WITH MIRROR. BULHEAD IS LOCATED DIRECTLY ADJACENT TO BAGGAGE DOOR.						1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002021300078	20020213	00078	CE  	2002	2	13	CA011219007      	1	20011212	G	1100		PLACARD         			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  	MCAULY	3AF34C	3GFR34C703  	GL  	COCKPIT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AIRSPEED LIMIT PLACARD NOT INSTALLED ON COMPANY PER T.C. A37CE.						1	H	7	1 	3T	3	T	 	A37CE   	E4EA	5	C	P60GL	 
2002021300081	20020213	00081	CE  	2002	2	13	CA011219008      	1	20011203	G	2720	05430224	TUBE            			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					RUDDER	JAMMED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA											(CAN) A/C HAS 15120.6 T.AT. TIME ON PART UNKNOWN, MAY BE ORIG. UPON TAXI TO HOLD LINE, PILOT TURNED FULL LEFT THEN FULL 	RIGHT TO CHECK BRAKES & STEERING. PILOT APPLIED FULL POWER AFTER T/O CLEARENCE & HAD TO KEEP GREATER THAN NORMAL RIGHT R	UDDER TO KEEP A/C STRAIGHT. WHEELS LEFT GROUND AT 70K A/C IMMEDIATLY YAWED HARD LEFT. PILOT PUT IN FULL RIGHT RUDDER & A	ILERON TO COMBAT, RUDDER STAYED JAMMED HARD LEFT. A/C LANDED ON GRASS & HIT DITCH CAUSING EXTENSIVE ENGINE, PROP & FUSEL	AGE DAMAGE. AME & TSB DISCOVERED THAT RT STEERING PUSH-PULL ROD COULD HAVE JAMMED IN SHORTENED POS&AS OLEO EXTENDED, IT 	PULLED LT RUDDER PEDAL IN, IN TURN DEFLECTING RUDDER FULL LEFT. WASHER THAT USUALLY SLIDES FREELY IN S TEERING TUBE	1	H	7	1 	3O	3	O	NT	3A19    	E223				 
2002021300082	20020213	00082	NE  	2002	2	13	CA011219009      	1	20011209	G	2910	7665103004073	LINE            			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					HYD SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DURING POST FLIGHT WALK AROUND FLIGHT CREW NOTICED HYD FLUID LEAKING OUT OF COWLING. COWL WAS REMOVED. HYD RESEVOI	R WAS 1/2 FULL AND A/C GROUND RUN A LEAK WAS DETECTED UNDER A CLAMP OF NR 2 SYSTEM PRESSURE LINE. THE LINE WAS REPLACED 	WITH A NEW PART, NR 2 SYSTEM HYD OIL TOPPED UP TO FULL MARK. A/C GROUND RUN & LEAK CHECKED SERVICEABLE & RETURNED TO SER	VICE.			1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2002021300093	20020213	00093		2002	2	13	CA011220001      	4	20011219	G	6122		NUT             	MCAULY      	C290D4MT4   	CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RELIEF VALVE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						980085					(CAN) DURING ROUTINE GROUND MAINTENCE OIL WAS DISCOVERED EMINATING FROM THE ENGINE COWLING.  INVESTIGATION WHICH INCLUDE	D WASHING DOWN THE AREA AND A RUN UP REVEALED OIL LEAKING FROM THE RELIEF VALVE ADJUSTMENT NUT.  REPLACED PROPELLOR GOVE	RNOR,  RAN ENGINE NO LEAKS FOUND.NO PART NUMBER AVAILABLE FOR THE ADJUSTMENT NUT/RELIEF VALVE				1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL	 
2002021300094	20020213	00094	SO  	2002	2	13	CA011220002      	1	20011217	G	3213		HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT MAIN GEAR	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			16538								(CAN) AFTER T/O SELECTED GEAR UP, THE HANDLE RETURNED WITH A RED LIGHT.  THE GEAR WAS RECYCLED, WITH NO CHANGE.GEAR SELE	CTED DOWN AND AIRCAFT LANDED WITHOUT INCIDENT. PART TIMES AND CYCLES FROM AIRCRAFT TIME.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021300100	20020213	00100	WP  	2002	2	13	CA011220003      	1	20011218	G	6700		BUNGEE CYLINDER 			ROBSIN	R44   	R44         	7640120	WP  										CYCLIC	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) PLIOT COMPLAINED OF HEAVY AFT CYCLIC FORCES.INVESTIGATION REVEALED CYCLIC BUNGEE TO BE DISCONNECTED FROM AFT ATTAC	H POINT ON PUSH ROD P/N C121-9 AT C317-1 BELLCRANK. SUSPECT DISCONNECTION IS DUE TO COLD OPERATING ENVIRONMENT AT THIS T	IME.   LOCAL TEMERATURES REACHED BELOW -25 DEGREES C.BUNGEE MATERIAL MAY STIFFEN WHEN COLD CAUSING A LOS OF ELASTICITY A	ND ALLOWING THE DISCONNECTION. THIS AIRCRAFT HAS THE UPDATED STYLE BUNGEE ATTACHMENT CLIP.			1	G	7	1 	3O			 	H11NM   					 
2002021300101	20020213	00101	WP  	2002	2	13	CA011220004      	1	20011219	G	6700		BUNGEE CYLINDER 			ROBSIN	R44   	R44         	7640120	WP  										CYCLIC	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING 100 HOUR INSPECTION, BOTH AFT BUNGEES WERE FOUND TO BE DISCONNECTED AT THE AFT PUSH PULL TUBE C121-9 AT THE	 C317-1 BELLCRANK.SUSPECT DISCONNECTION IS DUE TO COLD OPERATING ENVIRONMENT AT THIS TIME.  LOCAL TEMPERATURES REACHED B	ELOW -25 DEGREES C. BUNGEE MATERIAL MAY STIFFEN WHEN COLD CAUSING A LOSS OF ELASTICITY AND ALLOWING FOR DISCONNECTION.NO	TE THIS AIRCRAFT HAS THE UPDATED STYLE BUNGEE ATTACHMENT CLIP.			1	G	7	1 	3O			 	H11NM   					 
2002021300103	20020213	00103	CE  	2002	2	13	CA011221001      	1	20010520	G	5511	07321014	BRACKET         	CESSNA      	12320008    	CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACK NOTED FROM RETAINER'S EDGE TO INBOARD ATTACHMENT SCREW HOLE AS VIEWED FROM THE LT SIDE OF A/C.  ANOTHER CRAC	K NOTED IN BOTTOM BEND RADIUS OF BRACKET AND EXTENDING ALONG THE BEND FOR APPROX. 1 INCH. PROBABLE CAUSE IS FROM CARRYIN	G EXTERNAL LOADS ON THE SIDE OF THE A/C SUCH AS CANOES, SMALL BOATS ETC.				1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL	 
2002021300107	20020213	00107	SW  	2002	2	13	CA011221004      	1	20011203	G	5343	71470101R	TUBE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   TUBE FOUND BROKEN THROUGH APPROXIMATELY AT WELD TO RT FORWARD END OF LDG FITTING.						1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021400005	20020214	00005	CE  	2002	2	14	CA011221007      	1	20011205	G	3222	030A39313	BOLT            			MTSBSI	MU2   	MU2B36      	5780412	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE NOSE LANDING GEAR DRAG STRUT ATTACH BOLT WAS FOUND CRACKED. THIS BOLT HAD BEEN MAGNETIC PARTICAL INSPECTED EVE	RY 2000 HOURS.					1	H	7	2 	3T			RT	A10SW   					 
2002021400006	20020214	00006	CE  	2002	2	14	CA011221008      	1	20011220	G	7920	017A4710127	LINE            	MTSBSI      		MTSBSI	MU2   	MU2B36      	5780412	CE  										OIL COOLER	CHAFED          	W				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			CA											(CAN) THE OIL LINE RUNNING FROM THE OIL COOLER WAS FOUND CHAFED BY A SCREW THAT WAS TOO LONG IN A PANEL ON THE SIDE OF T	HE NACELLE. THE LINE WAS REPLACED AND THE SCREW WAS REPLACED WITH A SHORTER ONE					1	H	7	2 	3T			RT	A10SW   					 
2002021400012	20020214	00012	CE  	2002	2	14	CA011231003      	1	20011224	G	2460	5036430821	DIODE           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					BUSS FEEDER	BURNED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) PILOT HAD MULTIPLE FAILURES WHEN COMING IN TO LAND,  SOME EXTERIOR AND INTERIOR LIGHTS WOULD NOT WORK AND THE LAND	ING GEAR WOULD NOT COME DOWN.  THE PILOT EXTENDED THE GEAR MANUALLY AND LANDED WITHOUT INCIDENT.  MAINTENANCE FOUND THE 	RT NR 1 BUSS FEEDER DIODE BURNT. THE RT NR 1 BUSS FEEDER DIODE WAS REPLACED, NR 2 BUSS FEEDER DIODE WAS REPLACED AND THE	 RT NR 1 BUSS FEEDER WIRE CONNECTOR PIN WAS ALSO REPLACED AT THE RT CIRCUIT BREAKER PANEL. BEECHCRAFT HAS AN INSPECTION 	EVERY 800 HOURS THAT WOULD HAVE IDENTIFIED THE PROBLEM DIODE BEFORE THIS HAPPENED, THIS AIRCRAFT WAS 150 HOURS AWAY FROM	 THAT INSPECTION. I SUBMITTED ANOTHER SDR ON THIS SUBJECT SEE CONTROL NUMBER 19991230038	1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002021400014	20020214	00014	EU  	2002	2	14	CA020102001      	1	20011211	G	6410		BLADE           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL2B    	 	NE  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						6875					(CAN) 35 MM CRACK IN BLADE SKIN ON TAIL ROTOR.						1	G	7	1 	3U	3	U	 	H9EU    	E00054EN				 
2002021400016	20020214	00016	CE  	2002	2	14	CA020102003      	1	20011120	G	5510	05320019	SPAR            	CESSNA      	0532001201  	CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300D       	17022	SO  					HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AT ANNUAL INSPECTION THE CENTRE SECTION OF THE STABILIZER SPAR WAS FOUND TO BE BUCKLED AND CRACKED AT THE CENTRE L	IGHTENING HOLE, WHERE THE TRIM CABLES RUN THROUGH. THERE WERE TWO CRACKS ABOUT 2 IN. LONG, RUNNING FROM THE BOTTOM RIGHT	 AND TOP LEFT SIDES OF THE HOLE, WITH CORRESPONDING BUCKLING. THE CRACKS WOULD OPEN AND CLOSE AS PRESSURE WAS APPLIED TO	 THE TIP OF THE STABILIZER - UP OR DOWN. THE STABILIZER HAD ONLY A SLIGHT LOSS OF STIFFNESS - SO THE PROBLEM WAS ONLY NO	TICED BY VISUAL INSPECTION OF THE AFFECTED AREA. THE STABILIZER WAS REMOVED AND REPAIRED.		1	H	7	1 	3O	3	O	NT	3A12    	E253				 
2002021400017	20020214	00017	EU  	2002	2	14	CA020103001      	1	20011201	G	6320	4638302023	BEARING         		4638001010  	BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1159					(CAN) GEARBOX RECEIVED FROM THE USA FOR INVESTIGATION OF METAL CONTAMINATION. UPON DISASSEMBLY THE SUBJECT BEARING SHOWS	 SIGNS OF EXCESSIVE PEELING ON ONE BALL, 75 PERCENT OF AREA AFFECTED. ANOTHER BALL ALSO STARTING TO PEEL.  ONE HALF OF S	PLIT INNER RACE HAD SPALLING OVER 10 PERCENT OF BEARING SURFACE.				1	G	7	2 	3U	3	U	NC	H3EU    	E4CE				 
2002021400018	20020214	00018	EU  	2002	2	14	CA020103003      	1	20011209	G	2916	PPEV3008EA3B	POWERPACK       			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	HYD SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)  DURING A DAILY INSPECTION BY MAINTENANCE STAFF AT THE COMPLETION OF SCHEDULED FLIGHT. HYDRAULIC FLUID WAS FOUND A	T LH WING ROOT, BOTTOM OF WING,WHERE ACCESS PANEL IS LOCATED FOR HYDRAULIC POWER PACK. THE AMOUNT OF FLUID LOST DID NOT 	EFFECT OPERATION OF SYSTEM. THE LEAK WAS DETERMINED TO BE A CRACK IN THE RESEVOIR OF THE HYDRAULIC POWER PACK STARTING A	T THE TOP OF RESEVOIR AND TRAVELLING DOWN TO THE BOTTOM OF RESEVOIR WHERE THE ELECTRIC MOTOR IS MOUNTED. HYDRAULIC POWER	 PACK WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.		1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002020500133	20020205	00133	EA  	2002	2	5	CA020103004      	2	20011211	G	7414	1038255514	MAGNETO         	LYC         	            	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ROTOR & GEAR	FAILED          	W			    	A	 	 	 	UNSCHED LANDING         				R	 	 	PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA		 									(CAN) THE AIRCRAFT ENGINE HAD JUST UNDERGONE AN ON CONDITION INSPECTION AND HAD MET ALL REQUIRED PARAMETERS, INCLUDING F	ULL POWER CHECK. ONE SIDE OF THE DUAL MAG FAILED ON FIRST FLIGHT POST INSPECTION. UPON DISSASSEMBLY OF DISTRIBUTION BLOC	K. SEVERAL ROTOR TEETH WERE FOUND BROKEN OFF. THE ROTOR BEARING WAS FOUND WITH EXCESSIVE WEAR AND THE DISTRIBUTOR CONTAC	TS APPEAR TO HAVE TOUCHED.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002021400019	20020214	00019	GL  	2002	2	14	CA020103005      	3	20011201	G	6114	MS20073XXXX	BOLT            			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHILE REMOVING MCCAULEY PROP FOR 5 YEARS CORRISON INSPECTION IT WAS NOTED THAT PROP BOLTS WERE TO SHORT APPROX 4 T	HREADS ON ALL BOLTS WERE SECURING THE PROP. NEW BOLT KIT A2513-77 INSTALLED & LOCKED.					1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002021400020	20020214	00020	NE  	2002	2	14	CA020103006      	2	20011213	G	7230	350A070867	SEAL            			SNIAS 	350   	AS350BA     	8680817	EU  	LYC   	LTS101	LTS101600A3 	41560	NE  					COMPRESSOR	DESTROYED       	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA											(CAN) A/C IN CRUISE. FLYING IN SNOW, VISIBILITY 1 MILE, TEMP -2 DEGS. ON 1ST FLT OF DAY. AFTER 25 MIN FROM TAKEOFF, A/C 	HAD LIGHT COMPRESSOR STALL.  THEN HAS A SERIES OF LARGE ONES.  HAD SOME RPM DROP.    ON INSPECTION AFTER LDG. FOUND 2 OF	 INTAKE SEALS INCLUDING RETAINING STRIPS & CLIPS IN INTAKE BOX. ONE RETAINING STRIP & CLIPS & ALSO ONE RUBBER SEAL MISSI	NG. AXIALCOMPRESSOR WHEEL BLADES ARE SEVERELY DAMAGED. ENGINE IS PRESENTLY REMOVED..			1	G	7	1 	3U	3	U	NC	H9EU    	E5NE				 
2002022800001	20020228	00001	EA  	2002	2	28	CA020103010      	1	20011220	G	7921		OIL COOLER      	GENELC      	CF343B1     	CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343B1     	 	NE  					LEFT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			AP	APPROACH       	1			CA						872259					(CAN) A/C ON APPROACH WHEN CREW NOTED LEFT OIL PRESSURE FLUCTUATING. CREW RPTED PRESSURE FLUCTUATING UP TO 25 PSI&AVERAG	ING 30 PSI LOWER THAN RIGHT ENGINE. NO MENTION OF WARNINGS OR OTHER ACTION TAKEN. MAINT FOUND LEFT ENGINE TO BE 5 QTS LO	W OF OIL. ENGINE SERVICED&RUN WITH AG AXIS LEAK PORTS OPEN. GE REP&FSR WITNESSED MUCH FLUID NOTED FROM J AXIS PORT, CONS	IDERABLE STREAM COMING FROM IT&ENGINE SHUTDOWN. THISENGINE OF CONFIG THAT DID NOT HAVE CARBON SEAL&RUNNER ON THAT SHAFT.	 O RINGS WERE REPL&PUMP REINST ENGINE SERVICED PER GE RECOMMENDATIONS&RUN AGAIN. TIME WHEN OIL TANK CAP REMVD, QUART OR 	MORE OF OIL CAME OUT OF IT. THROUGH FURTHE	2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2002021400025	20020214	00025	SO  	2002	2	14	CA020103013      	1	20011030	G	5280	4752932	HINGE           	PIPER       	4752932     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  MAIN LANDING GEAR DOOR HINGES CRACKED.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002021400038	20020214	00038	EU  	2002	2	14	CA020103017      	1	20011205	G	3150	972813201	DISPLAY         			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) MISC. WARNINGS LITES ILLUMINATED ALONG WITH MASTER CAUTION EVEN THOUGH ALL SYSTEMS WERE FUNCTIONING NORMALLY. ALSO	 CAWS DISPLAY WOULD NOT PASS LITE TEST. CAWS DISPLAY REPLACED.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021400039	20020214	00039	EU  	2002	2	14	CA020103018      	1	20011224	G	3150	9752902014	PANEL           			PILATS	PC12  	PC1245      	7090551	EU  	PWA   	PT6   	PT6A67B     	52043	NE  	HARTZL	HCE4A	HCE4A3D     	GL  	COCKPIT	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) EIS GIVING FALSE READING FOR ITT. EIS PANEL REPLACED.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE	5	C	P210NE	 
2002021400040	20020214	00040	EA  	2002	2	14	CA020104001      	1	20011126	G	2731	AN3C6A	BOLT            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR TRIM	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)    DURING 100 HR INSP REMOVED PUSH/PULL ROD FOR MAINTENANCE.  RE-INSTALLED PUSH / PULL ROD AT LATER TIME WITH PREV	IOUSLY REMOVED HARDWARE.  WORK WAS CHECKED DURING INDEPENDENT INSPECTION.  BOLT WAS FOUND SHEARED THE FOLLOWING DAY AFTE	R SITTING OVERNIGHT IN THE HANGAR, THE BOLT HEAD HAD SHEARED CLEAN OFF AND WAS FOUND ON THE HANGAR FLOOR.  PART RETURNED	 TO SEALAND AVIATION FOR EVALUATION.			1	H	7	1 	3R	3	R	 	A806    	5E1				 
2002021400041	20020214	00041	EA  	2002	2	14	CA020104002      	2	20011214	G	7261	PT1052287579522	OIL FILTER      			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ENGINE OIL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WHEN REPLACING INBD O-RING  VERY SHARP EDGE IN OIL FILTER BODY DAMAGING O-RING EVERY TIME.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002021400042	20020214	00042	SW  	2002	2	14	CA020104003      	1	20011128	G	7930	31039721	CHIP DETECTOR   			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 	 	NM  					NR 2 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON REINSTALLATION OF THE CHIP DETECTOR DRAIN VALVE BODY IN ENGINE NR 1 BEFORE TORQUE VALVE WAS OBTAINED (75 IN L	B) , THE NUT PORTION WHICH INCLUDES A RECEPTICLE FOR THE CHIP DETECTOR SEVERED OFF.  INSPECTION OF THE PART SHOWED PRESE	NCE OF PREVIOUS CRACKING AROUND THE RADIUS. THE VALVE BODY WAS REMOVED FROM NR  2 ENGINE AND FOUND IT WAS ALSO CRACKED A	ROUND THE RADIUS OF THE NUT. THE REMAINING AIRCRAFT IN THE FLEET WILL BE INSPECTED FOR ANY DAMAGE IN THIS AREA.			1	H	7	2 	3T	4	T	 	2A4     	E2WE				 
2002021400043	20020214	00043	EU  	2002	2	14	CA020104004      	1	20011211	G	2432		WIRE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					BATTERY	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			CA											(CAN) JUST PRIOR TO LDG PILOT SMELLED SOMETHING LIKE PLASTIC OR RATHER BURNING BUT NOT SMOKE.  AFTER SHUTTING DOWN,  PIL	OT COULD SEE SMOKE INSIDE TAILBOOM & STRONG SMOKE OF SOMETHING ELECTICAL SMOKING IN MAIN CARGO BAY,  PILOT INVESTIGATED 	FURTHER TO FIND SOURCE & FOUND NOTHING OUT OF ORDINARY.  PILOT TRIED START WHEN GUIDE & PASSENGER COULD SEE 3 SPARKS UND	ER BELLY OF A/C. FURTHER INVESTIGATION LEAD TO BATTERY BAY.  ONE OF WIRE CONNECTORS ON POSITIVE POST OF BATTERY GOT WELD	ED TO BATTERY CASE. BOTTOM OF BATTERY CASE BURNT&SOURCE TO GROUND TO AIRFRAME. ARE 2 WIRES OR CABLES TO POSITIVE POST OF	 BATTERY.	1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002021500011	20020215	00011		2002	2	15	CA020104012      	4	20011130	G	3421		GYRO            			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					COCKPIT	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			49328	49328							(CAN) ON TAKE OFF FROM EDMONTON, ELECTRICAL SPIKE MOMENTARILY FLAG CAPT.'S ADI AUTOPILOT, WHEN SELECTED ON TRIPPED, TRIE	D ONE MORE TIME AND WITH LIGHT PRESSURE ON ELEVATOR ON AUTOPILOT TRIPPED AGAIN. NUMBER 1 VERTICAL GYRO AND AIR DATA COMP	UTER REPLACED. SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002021500027	20020215	00027	NE  	2002	2	15	CA020104021      	2	20011231	G	7323	LN9367GE12N2	BEARING         			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TURBINE GOVERNOR	CONTAMINATED    	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) LACK OF DROOP COMPENSATION OBSERVED BY PILOTS. ENGINEERING NOTIFIED. ENGINEERING DISCOVERED A BINDING BEARING IN T	HE N2 CONTROL SYSTEM, LOCATED IN CABIN CEILING. BEARING WAS CLEANED OF DIRT, LUBRICATED AND FUNCTION TESTED SERVICABLE.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2002021500029	20020215	00029	NE  	2002	2	15	CA020104022      	2	20011231	G	7323	LN9367GE5DN2	BEARING         			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					TURBINE GOVERNOR	WORN            	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA											(CAN) WHEN INSPECTING THE N2 DROOP SNAG(PLEASE SEE PREVIOUS SDR ON SAME DAY), THE BALL WAS DISCOVERED TO BE WORN THROUGH	 THE SOCKET. THE ARM ASSY WAS REPLACED BY A SERVICABLE UNIT AND THE HELICOPTER WAS RETURNED TO SERVICE.					1	G	7	2 	3U	3	U	 	H13EU   	E5NE10				 
2002021500030	20020215	00030	SW  	2002	2	15	CA020104023      	1	20011227	G	6230		OIL JET         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					M/R MAST	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) DURING INSTALLATION OF MAIN ROTOR MAST ASSEMBLY IT WAS VISUALLY IDENTIFIED THAT THE OIL JET WAS LOCATED IN THE WRO	NG POSITION FOR CONNECTION OF OIL SUPPLY LINE. PART WAS REPLACED WITH SERVICEABLE UNIT.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002021500034	20020215	00034	EA  	2002	2	15	CA020108002      	2	20011127	G	8530	AEL6510241	CYLINDER        			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA											(CAN) DURING CLIMB THE PILOT NOTICE A LOSS OF POWER AND ENGINE VIBRATION. RETURNED TO BASE.  MAINTENANCE FOUND NR 3 CYLI	NDER CRACKED AT THE EXHAUST VALVE.  THIS IS THE 3RD CYLINDER ON 2 DIFFERENT ENGINES TO CRACK IN THIS PLACE.  ALL CYLINDE	RS REMOVED AND RETURNED TO SUPPLIER.  OVERHAULED CYLINDERS INSTALLED AND AIRCRAFT RETURNED TO SERVICE.				1	H	7	1 	3O	3	O	NT	3A12    	E274				 
2002021500035	20020215	00035	EA  	2002	2	15	CA020108003      	2	20011214	G	7314	025323300	PUMP            			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL SYS	STRIPPED        	W				A				UNSCHED LANDING         				X	Y	J	ENGINE FLAMEOUT           	ENGINE STOPPAGE           	WARNING INDICATION        	CR	CRUISE         	1			CA											(CAN)  ENGINE SHUT DOWN IN CRUISE FLIGHT. AIRCRAFT MADE AN UNSCHEDULED LANDING TROUBLESHOOTING REVEALED NO FUEL FLOW TO 	DIVIDER. HIGH PRESSURE FUEL PUMP REMOVED. FUEL PUMP SPLINES FUND TO BE STRIPPED. PUMP REPLACED.					1	L	7	2 	4T	4	T	 	A23SO   	E4EA				 
2002021500036	20020215	00036	EU  	2002	2	15	CA020109001      	1	20011203	G	5302	11203025221	FLANGE          			BOLKMS	117   	BK117A1     	5626010	EU  										TAILBOOM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAILBOOM SENT FROM A CUSTOMER IN THE USA FOR REPAIR OF A DAMAGED SKIN.  DURING DISASSEMBLY THE TAILBOOM TO FUSELAG	E ATTACHMENT RING FOUND CORRODED.  AT THE 1:00 AND 11:00 O'CLOCK POSITION DEPTH 1 MM AT THE 2:00 AND 10:00 O'CLOCK  POSI	TION 0.2 MM AT THE 6:00 O'CLOCK POSITION DEPTH OF 0.6MM.				1	G	7	2 	3U			 	H13EU   					 
2002021500037	20020215	00037	EA  	2002	2	15	CA020109002      	2	20011102	G	8520	LW1594485	CRANKSHAFT      								LYC   	O320  	O320H2AD    	41508	EA  					MAIN JOURNAL	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  CORROSION FOUND UNDER URETHABOND COATING APPLIED BY FACTORY AT OVERHAUL AS PER SB 505B AND SB 530A AND AD 98-02-0	8.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION.										3	O			E274				 
2002021500039	20020215	00039	EA  	2002	2	15	CA020109005      	2	20011214	G	7261	PT6A27	ENGINE          			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 2	CONTAMINATED    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			14795								(CAN) OIL CONTAMINATION NR 2 LIGHT ILLUMINATED AFTER TAKEOFF,  DURING CLIMB OUT.  RETUNED FOR LANDING. LANDING WAS UNEVE	NTFUL. MAINTENANCE INSPECTION REVEALED OIL CONTAMINATED WITH METAL PARTICLES.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA	 
2002021500041	20020215	00041	SO  	2002	2	15	CA020109006      	1	20011221	G	2140		COMBUSTION LINER			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					HEATER	BURNED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN)  PILOT SMELLED FUMES IN THE CABIN.  HE SHUT OFF THE JANITROL HEATER.  HEATER WAS REMOVED AND INSPECTED FOUND A HOL	E BURNED THROUGH COMBUSTION TUBE.  INSTALLED NEW OVERHAULED HEATER.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002022800002	20020228	00002	EU  	2002	2	28	CA020110003      	1	20011223	G	2420		IDG             	HAMSTD      		AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    	 	NE  					IDG	OVERHEATED      	W				H				DEACTIVATE SYST/CIRCUITS				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) @1 IDG OIL PRESSURE AND OVERHEAT ON ON DESCENT TO YVR. TEMPERATURE GRADUALLY RISING (PULSATING GREEN) ECAM ACTION 	CARRIED OUT. IDG DISCONNECTED PRIOR LANDING.IDG FOUND OVERSERVICED. MEL 24-20-01 APPLIED. OIL STILL FLUCTUATING.IDG REPL	ACED AS PER AMM 24-21-51.				2	L	7	2 	4F	4	F	RT	A28NM   	E29NE				 
2002021500093	20020215	00093	SW  	2002	2	15	CA020112001      	1	20011203	G	2810	71493	FUEL TANK       			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2A     	41514	EA  					LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN)   FUEL LEAK DISCOVERED BY VISIAL INSPECTION AT FABRIC DRAIN HOLES IN TE OF WING.  INBOARD FUEL TANK OF LEFT WING R	EMOVED AND PIN HOLE FOUND IN THE WELD WHERE DRAIN BOSS WHERE FUEL HOSE ATTACHES.  BOSS REWELDED AND PRESSURE TESTED TANK	.  NO FURTHER LEAKS FOUND.				1	H	7	1 	3O	3	O	 	A21CE   	E286				 
2002021500094	20020215	00094	SO  	2002	2	15	CA020114001      	1	20010812	G	8120	LW12463	SEAL            	GARRTT      	LW12463     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	LEAKING         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA						AG020227					(CAN) TURBO OIL SEAL LEAKING (EXHAUST SIDE).  ABORT TAKEOFF.  LOST POWER ON RT AND SMOKE.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002021500100	20020215	00100	NE  	2002	2	15	CA020114008      	2	20011116	G	7200		ENGINE          								PWA   	JD15  	JT15D1A     	 	NE  					LT OR RT	FAILED          	W				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN)  ENGINE WAS UNABLE TO ACHIEVE THE RATED POWER WITHIN THE SPECIFIED TEMPERATURE LIMITS. THE OPERATOR DECIDED TO PER	FORM AN HSI AND REMOVED THE HOT SECTION COMPONENTS FOR SHIPMENT TO ATLANTIC TURBINES FACILITY IN ATLANTA. AT THIS POINT 	IT WAS NOTED THAT THE ENGINE HAD SUSTAINED AN HP TURBINE BLADE FAILURE WITH CONSIDERABLE FOD. THE HP & LP TURBINE COMPON	ENTS WERE FORWARDED TO ATLANTIC TURBINES FOR INVESTIGATION AND RESTORATION TO SERVICEABLE CONDITION.								4	F			E25EA				 
2002021500101	20020215	00101	EA  	2002	2	15	CA020114009      	2	20011130	G	7200		ENGINE          								PWA   	PT6   	PT6A41      	52043	EA  					LT OR RT	FAILED          	W				O	O			OTHER                   	OTHER                   			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			CA											(CAN) ENGINE WAS SENT TO ATI FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THAT ENGINE HAD BEEN SHUT DOWN IN 	FLIGHT. THE OPERATOR REPORTED THAT DURING THE APPROACH THE PILOT HAD NOTICED THE TURBINE INTERSTAGE TEMPERATURE HAD INCR	EASED TO 950 DEGREES C, AND HAD SHUT DOWN THE ENGINE AND LANDED ON THE ONE REMAINING ENGINE. THE OPERATOR HAS SPLIT THE 	ENGINE, NOTED EXTENSIVE INTERNAL DAMAGE, AND RE-ASSEMBLED THE UNIT PRIOR TO SHIPMENT TO ATI.								4	T			E4EA				 
2002021500102	20020215	00102	CE  	2002	2	15	CA020116001      	1	20011130	G	3310	A91641	BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520MB     	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LIGHT	BROKEN          	W				F				ACTIVATE FIRE EXT.      				A			FLAME/FIRE                			AP	APPROACH       	1			CA											(CAN)   FIRE IN COCKPIT ON DESCENT FROM FLIGHT TO AIRPORT. SMOKE EMITING FROM RT DASH BY PROP DE-ICE GAUGE. SMOKE TURNED	 TO FLAME AND EXTINGUISHER EXERCISED.  EXAMINATION REVEALED POST LIGHT PLASTIC BROKEN AND FELL DOWN TO METER. LINE POST 	LIGHT SHORTED ON METER TERMINAL. POST LIGHT SOCKET PLASTIC HEATED UP AND PLASTIC CAUGHT FIRE.				1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P22EA	 
2002021500106	20020215	00106	GL  	2002	2	15	CA020116007      	3	20011106	G	6114		PROPELLER       			MOONEY	M20   	M20C        	5870208	SW  	LYC   	O360  	O360A1D     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	FORWARD	DAMAGED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) OWNER DISCOVERED PROP WOULD NOT CYCLE AT PRE-FLIGHT INSPECTION.  AIRCRAFT WAS BROUGHT TO THE SHOP AND THE SPINNER 	WAS REMOVED.   GREASE FITTINGS WERE REMOVED AND OIL BEGAN TO RUN OUT.  PROP WAS REMOVED AND SENT FOR INSPECTION.					1	L	7	1 	3O	3	O	 	2A3     	E286	5	C	P920	 
2002021900056	20020219	00056	SO  	2002	2	19	CA020117010      	1	20011120	G	2460	454709	CIRCUIT BREAKER 			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					COCKPIT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   AT A ROUTINE 100 HOUR ANNUAL INSPECTION IT WAS DISCOVERED THAT TWO CIRCUIT BREAKERS HAD BROKEN REAR ATTACHMENT L	UG AT THE BUS BAR ATTACH POINT.					1	L	7	1 	3O	3	O	 	2A13    	E286				 
2002021900125	20020219	00125	EU  	2002	2	19	CA020117017      	1	20011210	G	5240	A2151060200200	DOOR            			AIRBUS	310   	A310        	       	EU  	GE    	CF6   	CF680C2A5   	 	NE  					FUELING PANEL	MISSING         	W				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			CA											(CAN)   FOUND REFUELING PANEL DOOR MISSING ON ARRIVAL TO "VRA".  REFUELING DOOR AND AN AIR INLET PANEL WERE REPLACED.						2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2002021900126	20020219	00126	WP  	2002	2	19	CA020117018      	1	20011204	G	2780		CONTROL VALVE   			LKHEED	1011  	10113853    	5265020	WP  	RROYCE	RB211 	RB211524B402	54555	NE  					LE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN)   ON FERRY FLIGHT TSC 2257 FROM CUN-YMX , DURING TAKE OFF , SLAT SYSTEM LOCKED IN EXTEND POSITION , BUT FLAPS RAIS	ED FULL UP. FLAP RED LIGHT WAS ILLUMINATED ON THE FLAP POSITION INDICATOR (PILOTS CENTER INSTRUMENTS PANEL) AND SLAT MON	ITOR INDICATED SLATS AT 30 DEGREES.-AIRCRAFT RETURNED TO "CUN".-ON GROUND , POP OUT INDICATOR FOUND OK ON BOTH WING FOR 	BRAKE INDICATOR. -C/B RESETTED , SYSTEM TEST C/OUT IN ACCORDANCE WITH M.M. 27-81-00. NO FAULTS FOUND.-NO DEFECTS WERE RE	PORTED AFTER TAKE OFF.		2	L	7	3 	4F	4	F	 	A23WE   	E12EU				 
2002021900127	20020219	00127	EU  	2002	2	19	CA020118001      	1	20011220	G	2780	4907905	CONTROL UNIT    			AIRBUS	310   	A310300     	3930305	EU  	GE    	CF6   	CF680C2A5   	 	NE  					LE FLAPS	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN)   MANY INDICATIONS (DEFECTS REPORTED) OF SLATS / FLAPS SYSTEM NR 1 & 2 FAULTS HAVE BEEN REPORTED ON AIRCRAFT, HAVI	NG SEVERAL MAINTENANCE ACTION C/OUT FROM 2001-11-25 TO 2001-12-20 AND THE FINAL RECTIFICATION BEING THE REPLACEMENT OF T	HE LAT FLAP CONTROL COMPUTER (SFCC); _DATE 2001-12-20 ; FLAPS SYS NR 2 FAULT WITH SPEED LIMIT ON RT SIDE PFD  SLATS AND 	FLAPS MOVE AT HALF SPEED  ALL MTCE ACTIONS C/O AND "O" OPERATION FOR FLIGHT CREW  PLACED ON DMI AS PER MEL 27-18  A C T 	I ON  TA  KE  N SFCC 2 REPLACED IAW 27-51-18 AND BITE TEST PERFORMED.CHECKED  SERVICEABLE.		2	L	7	2 	4F	4	F	RT	A35EU   	E13NE				 
2002021900128	20020219	00128	SW  	2002	2	19	CA020118003      	1	20010725	G	6230	2060400365	BEARING         	BELL        	20601033217 	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR MAST	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						FAJF56057					(CAN) UPON INSPECTION 3 BALL BEARINGS,  FOUND EXCESSIVELY SPALLED AND INNER RACE SHOWED 3 SIGNS OF PITTING IN 3 AREAS. B	EARING WAS SCRAPPED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002021900129	20020219	00129	SW  	2002	2	19	CA020118004      	1	20010725	G	6230	20601033217	MAST            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) UPON 1500 HOUR INSPECTION OF MAST BEARING RETAINING NUT REMOVAL. PRC SEALANT WAS REMOVED FROM THE LOWER MAST THREA	DS TO UNCOVER CORROSION PITTING WELL IN EXCESS OF CORROSION TOLERANCES. MAST WAS SCRAPPED.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002021900130	20020219	00130	EU  	2002	2	19	CA020118005      	1	20011221	G	2910	AE71112111	LINE            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						41063					(CAN) -DURING CURRENT C03 /A06 HEAVY MAINT VISIT , NR 2 HYDRAULIC PUMP PRESSURE TUBE POSED WITH NO CLEARANCE WITH RESPEC	T TO THE FUEL / OIL HEAT EXCHANGER HOUSING (ADJACENT TO THE FUEL INLET). AFTER NUMEROUS TIMES OF REPOSING LINE PER AMM G	UIDELINES , MIN CLEARANCE OF  0.100 INCH COULD NOT BE ACHIEVED.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002021900132	20020219	00132	EU  	2002	2	19	CA020118007      	1	20011207	G	2913	974976	PUMP            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)  NR  2 ENGINE, YELLOW HYDRAULIC PUMP,  SUCTION LINE CONNECTOR LOOSE AT MOUNTING PUMP.   THE PUMP WAS REPLACED I.A.	W. AMM 29-11-51					2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002021900139	20020219	00139	NM  	2002	2	19	CA020121008      	1	20011115	G	5521	657378436	SPAR            			BOEING	737   	737217      	1384464	NM  	PWA   	JT8   	JT8D17      	52049	NE  					RT ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ELEVATOR REAR SPAR  AT TRIM TAB ATTACHMENT POINT FOUND CRACKED.  ELEVATOR REMOVED FOR REPAIR, LOCATION OF DAMAG	ED LOCATED AT STATION 66.54 REPLACED ELEVATOR.  DAMAGE REPAIRED AS PER SRM					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002022000002	20020220	00002	EU  	2002	2	20	CA020121012      	1	20011218	G	2910	AE7111216	LINE            			AIRBUS	330   	A330243     	3930330	EU  	RROYCE	RB211 	RB211TRENT77	 	NE  					HYD SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) - DURING CURRENT C03 /A06 HEAVY MAINTENANCE VISIT,  ENGINE NR 2,  A HYDRAULIC LINE,  WAS FOUND TO BE RUBBING HARD 	AGAINST THE AIR OIL HEAT EXCHANGER,  THE RUBBER PROTECTIVE COATING WAS GOUGED  (BUT NOT THROUGH ),  STILL WITHIN REPAIRA	BLE LIMITS.				2	L	7	2 	4F	4	F	RT	A46NM   	E39NE				 
2002022000005	20020220	00005		2002	2	20	CA020122003      	4	20011219	G	3197		WIRE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	INSTRUMENT PANEL	BINDING         	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN)  ON DESCENT INTO ST. JOHN'S, YYT, PILOT NOTICED THAT HE HAD NO AURAL WARNINGS FOR DECISION,  H8, ALTITUDE,  ALERT,	  OVERSPEED,  GEAR WARNING OR STALL WARNING. MAINT INSPECTED PLUGS FOR AURAL AMPLIFIERS & NOTHING APPEAR TO BE WRONG. WI	RING INSP & FOUND 2 WIRES HAD BEEN CHAFED BY LARGE PLASTIC TYWRAPS. ONE WIRE (CODE 24A22) FOR 28VDC INPUT OF AURAL ANNUN	CIATOR AMPLIFIER, P/N 207 & AN OTHER WIRE AT PLUG W314P8 FOR CO-PILOTS SPEAKERS. WIRING REPLACED BY MEANS OF BUTTSPLICES	. OPAL CHECKS WERE CARRIED OUT FOR APPLICABLE WARNINGS & CHECKED SERVICEABLE. WIRES IN QUESTION WERE TIE WRAPPED AT A PO	INT WHERE BUNDLE WAS BENDING. IF TIE WRAPS HAD TO BE 1CM ON EITHER SIDE OF BEND THIS WOULD NOT HAVE HAPPENED.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002020500147	20020205	00147		2002	2	5	CA020122004      	4	20011115	G	3400	ELT1104	ELT             	ARTEX       	            	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	ELT	FAILED          	W			    	O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA		 				57781					(CAN) ELT REMOTE SWITCH INDICATOR LIGHT ON IN THE HANGAR WITH NO SIGNAL BEING RECEIVED ON COMM FREQUENCY 121-5. ELT AND 	WIRING INSPECTED AT ZONE 312, WIRES W3150-12, W3150-13 AND W3150-15 FOUND CHAFED AND GROUNDING OUT. PLASTIC TYWRAP AND P	LASTIC CLAMP CUTTING INTO WIRING. WIRING SPLICED AND SPIRAL WRAP INSTALLED AROUND WIRE BUNDLE AND PROTRUDING THROUGH CLA	MP TO ENSURE FAULT WOULD NOT RE-OCCUR. ELT UNIT REPLACED AND OPERATIONAL CHECK CARRIED OUT.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE	 
2002022000013	20020220	00013	CE  	2002	2	20	CA020124003      	1	20011212	G	3242	30146	HOUSING         			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					BRAKE ASSY	DAMAGED         	W				O				OTHER                   				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			CA			18687								(CAN) THE PILOT REPORTED WHEN STOPPING AT THE RAMP THE LT BRAKE PEDAL WENT TO THE FLOOR.  UPON INSPECTION THE LT FWD CAL	IPER WAS FOUND DRAGING ON THE GROUND.  IT WAS DISCOVERED AFTER THE MISSING PARTS WERE OBTAINED AFT THE TAXI-WAY, THAT TH	E BOLT HOLDING THE DOWL PIN INTO THE CALIPER HAD WORKED LOOSE, & THE DOWL PIN UNSCREWED OUT OF THE CALIPER DISENGAGING T	HE CALIPER FROM THE BACK PLATE. (HOWEVER THE BOLT WAS STILL CORRECTLY LOCKWIRED IN POSITION.) THE CALIPER THEN FELL DOWN	 HITTING THE GROUND AND DISINTEGRATING. INSPECTION OF THE BOLTS ASSEMBLED THERE IS NO INDICATION THAT THE DOWL PIN IS LO	OSE OR NOT, MISLEADING THE INSPECTOR TO THINK ALL IS OK.	1	L	7	2 	3T	4	T	 	A14CE   	E4EA				 
2002022000061	20020220	00061	EU  	2002	2	20	CA020129004      	1	20011114	G	2520	NAS110436	BOLT            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										SEAT BELT	FAILED          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA											(CAN) UPON DEPLANING OF A/C AT DESTINATION, PASSENGER NOTIFIED CAPTAIN THAT OUTBOARD PORTION (LATCH SIDE) OF HIS SEAT BE	LT HAD BECOME DETACHED FROM HIS SEAT WHEN HE ATTEMPTED TO SECURE IT FOR DESCENT INTO AIRPORT. HE HAD THEN MOVED TO ONE O	F UNOCCUPIED SEATS IN PREPARATION FOR LDG. MAINT DISCOVERED THAT NUT & SPACER-BUSHING WERE MISSING FROM SEAT BACK PIVOT 	/ SHACKLE RESTRAINT BOLT, WHICH HAD ALLOWED SEAT BELT SHACKLE TO  COME DETACHED FROM SEAT (S/N 15065)			2	L	7	2 	4F			RT	A16NM   					 
2002022000065	20020220	00065	EA  	2002	2	20	CA020130002      	1	20011212	G	2710		CONTROL CABLE   			CNDAIR	CL215 	CL2156B11215	       	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   					 
2002022000069	20020220	00069	CE  	2002	2	20	CA020130006      	1	20011121	G	2433	D2FF10B379AA	RECTIFIER       	FORD        	POFF10300F  	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ALTERNATOR	WORN            	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			AP	APPROACH       	1			CA						A146794					(CAN)  ALTERNATOR RECTIFIER FAILED CAUSING  ELECTRICAL FAILURE DURING FLIGHT.						1	H	7	1 	3O	3	O	 	3A19    	E252	5	N	P918	 
2002032100092	20020321	00092	NM  	2002	3	21	CA020131007      	1	20011128	G	2140	4100S02801	ADAPTER         			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	BURNED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA						75					(CAN) DURING THE FINAL APPROACH OF FLIGHT 5632 ON THE 28 NOVEMBER 2001, THE PILOT OF AIRCRAFT DHC8400 S/N 4027, REPORTED	 THAT THE ENGINE ADAPTER NR 1 CL CAME ON AND THE C/B POPPED.  INVESTIGATION FOUND THE NR 1 HEATER INTAKE ADAPTER IN BURN	ED CONDITION.				2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002022000077	20020220	00077	NE  	2002	2	20	CA020131008      	2	20011209	G	7314	324485317	FUEL CONTROL    			DHAV  	DHC8  	DHC8301     	       	NM  	PWA   	PW120 	PW123       	 	NE  	HAMSTD	14SF	14SF23      	NE  	NR 2 ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	E	J	ENGINE STOPPAGE           	VIBRATION/BUFFET          	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) ON TAKEOFF ROLL NR 2 ENGINE CAUTION LIGHT FLICKERED. WERE NO ABNORMAL IND.S. AFTER TAKEOFF AT 600 FT MSL NR 2 ENGI	NE MANUAL CAUTION LIGHT ILLUMINATED FOLLOWED BY COMPLETE FAILURE OF NR 2 ENGINE.  ENGINE AUTO-FEATHERED, ALL ENGINE PARA	METERS INDICATED ZERO EXCEPT ITT WHICH AT 126. ENGINE FAILURE / FIRE SHUTDOWN DRILL CARRIED OUT. LDG COMPLETED SUCCESSFU	LLY. ALSO NOTED, THAT DURING TAXI PILOT NOTICED EEC LIGHT ILLUMINATED ACCOMPANIED BY MILT TQ SUR GE&THEN RETURNED TO NRO	MAL. MAINT FINDINGS: ENGINE EXTERNALLY INSP, PRE-COOLER DISCOVERED CRACKED BUT NOT ENOUGH TO BE CONTRIBUTING FACTOR AS B	LEEDS HAD NOT BEEN SELECTED ON. ENGINE OIL FILTERS CHECKED - NO FAULTS FOUND.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2002032100095	20020321	00095	NM  	2002	3	21	CA020131010      	1	20011205	G	2613	10109601	SWITCH          			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					OVERHEAT SENSOR	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) DURING APPROACH TO BASE AT 2,500 THE NR 1 ENGINE INDICATED A FIRE CONDITION. ONCE ENGINE SECURED, (PER IAC) T-HAND	LE INDICATION EXTINGUISHED. CONTINUED WITH CHECK LIST (DID NOT FIRE BOTTLES), FIRE INDICATION REAPPEARED (T-HANDLE LIGHT	 & BELL). FIRED BOTH BOTTLES ACCOMPLISHED SAFE EMERGENCY LANDING WITHOUT INCIDENT. NO ENGINE INSTRUMENT OR OTHER VISUAL 	INDICATIONS WERE OBSERVED,  BUT DUE TO WEATHER COULD NOT VISUALLY OBSERVE NR 1 ENGINE NACELLE.  INVESTIGATION FOUND FAIL	ED CLOSED FIRE/OVERHEAT SENSOR SWITCH, INTERNAL WARNING SWITCH CLOSED AS MEASURED ACROSS PINS A & D.1343.0 HOURS/1841 CY	CLES.	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002030800066	20020308	00066	SO  	2002	3	8	CA020211013      	1	20010709	G	8011	636058	WORM GEAR       	CONT        		PIPER 	PA36  	PA36285     	7103610	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					STARTER CLUTCH	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) THE PILOT COULD NOT START THE ENGINE.  NOTED THAT ALTHOUGH THE STARTER APPEARED TO SPIN,  IT WAS NOT TURNING THE E	NGINE.  THE AME INVESTIGATED AND DETERMINED THAT THE PROBLEM WAS INTERNAL. THE ENGINE WAS DISMANTLED TO REVEAL THE START	ER WORM GEAR BROKEN IN 3 PLACES. PREVIOUSLY, THE ENGINE HAD BEEN KICKING BACK EXCESSIVELY ON STARTUP.  IT WAS FOUND THAT	 THE MAGNETO SHOWER OF SPARKS WAS WIRED TO THE ADVANCE POINTS RATHER THAN THE RETARD AND THIS COULD HAVE WEAKENED THE WO	RM GEAR TO THE POINT OF SUBSEQUENT FAILURE.		1	L	7	1 	3O	3	O	 	A10SO   	1E4				 
2002031100004	20020311	00004	EA  	2002	3	11	CA020219001      	2	20011213	G	8520	LW19340	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540*     	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN THE PROCESS OF PREFORMING A CYLINDER CHANGE, THE MECHANIC WAS UNABLE TO GET THE REQ'D VALVE CLEARANCE WITH THE 	APPLICABLE PUSHROD LENGHTS. UPON REMOVAL OF THE CYLINDER AND FURTHER INVESTIGATION, IT WAS DETERMINED THAT THE CAM LOBE 	WAS TOO WORN TO ALLOW THE LONGEST AVAILIABLE PUSHROD TO BRING THE VALVE CLEARANCE INTO LIMITS. THE ENGINE WAS SUBSEQUENT	LY REMOVED FROM THE AIRCRAFT AND SENT TO A SERCICE FACILITY FOR REPAIR.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA	 
2002031100027	20020311	00027	SO  	2002	3	11	CA020226006      	1	20010608	G	7931	77808	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					OIL PRESSURE ADJ	WEAK            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OVERHAULED ENGINE INSTALLED, TEST RUN COMPLETED SATISFACTORY, ON TEST FLIGHT OIL PRESSURE DROPPED TO 65 P.S.I. AIR	CRAFT LANDED AND OIL PRESSURE READJUSTED TO 75 P.S.I., BUT WAS AT MAX ADJUSTING LIMITS. REPLACEMENT ADJUSTMENT SPRING IN	STALLED AND OIL SCREEN CHECKED AND METAL WAS EVIDENT AT THIS TIME, AFTER A PERIOD OF TIME THE ENGINE WAS REMOVED AND SEN	T BACK TO OVERHAUL FACILITY FOR REPAIR. NO CAUSE OF CONTAMINATION WAS FOUND.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002031100028	20020311	00028	SO  	2002	3	11	CA020226007      	1	20011204	G	3700	442CW6	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					VACUUM SYS	FAILED          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA											(CAN) VACUUM PUMP INSTALLED ON ENGINE, TEST SHOWED EXCESSIVE OIL LEAK AT MOUNT BASE. OIL PRESSURE ON ENGINE WENT TO "0" 	INDICATED AND ENGINE WAS SHUT DOWN. REPLACEMENT PUMP INSTALLED AND OIL SCREEN DETECTED METAL IN ENGINE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002032500015	20020325	00015	CE  	2002	3	25	CA020227008      	1	20010130	G	3241		CONNECTOR       			LEAR  	35    	35LEAR      	5170600	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ANTI-SKID SYSTEM	DAMAGED         	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA											(CAN) ON A BASE INSPECTION IT WAS NOTED THAT THE NR 1 AND NR 2 TIRES HAD FLAT SPOTS FROM SKIDDING. THERE WAS NO REPORTED	 ANTI-SKID FAILURE LIGHT ILLUMINATION.  INVESTIGATION REVEALED THAT THE LT ANTI-SKID CONTROL VALVE WAS NOT RELEASING THE	 PRESSURE TO THE SKIDDING WHEEL. CONNECTOR PIN "G" ON THE CONTROL VALVE WAS FOUND TO HAVE CORRODED TO THE POINT THAT IT 	BROKEN OFF INSIDE THE CONNECTOR PLUG. THIS CIRCUIT CONTROLS THE RETURN SHUT-OFF SOLENOID IN THE VALVE. THE FAILURE LOGIC	 IN THE ANTI-SKID CONTROL BOX CHECKS THE OPERATION OF THE WHEEL TRANSDUCERS BUT DOES NOT INDICATE A FAILURE OF THE VALVE	.  THE CONTROL VALVE IS LOCATED IN THE WHEEL WELL WHERE IT IS SUBJECT TO WATER CONTAMINATION.	2	L	7	2 	4F	4	F	 	A10CE   	E6WE				 
2002032500025	20020325	00025	EU  	2002	3	25	CA020228011      	1	20011212	G	5730		PANEL           			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					RT WING	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA											(CAN) THIS IS BRIEF DESCRIPTION OF EVENTS LEADING UP TO INCID. OF PANEL 691AT, LOCATED ON RT UPPER WING, EXITING A/C MSN	 183 AT TAKEOFF ON 8 DEC 2001.ON 11 NOV 01, PANEL REMOVED TO PERFORM INSP OF LOW SPEED AILERON HINGEBOLTS FOR CORROSION.	 INSPECTION COMPLETED & PANEL REINSTALLED SAME DAY.				2	L	7	2 	4F	4	F	RT	A35EU   	E23EA				 
2002051300010	20020513	00010	WP  	2002	5	13	CA020322008      	1	20011207	G	5540		STRUCTURE       			NAMER 	B25   	B25J        	6400710	WP  	WRIGHT	R2600 	R260035     	67050	EA  					RT RUDDER	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT RUDDER WAS FOUND TO HAVE APROXIMATELY TWO GALLONS OF WATER INSIDE DUE TO A PLUGGED DRAIN GROMMET.  FURTHER INSP	ECTION FOUND DETERIORATED COTTON TAPES FROM AN OLD CECONITE FABRIC RE-COVERING JOB.  RUDDER REMOVED AND RECOVERED					2	M	7	2 	4R	4	R	 	AL2     	PAGE42				 
2002041100022	20020411	00022	NM  	2002	4	11	CA020402006      	1	20010430	G	2131	7612608	CONTROLLER      			BOEING	737   	7372H4      	138448C	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					CABIN PRESSURE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AIRCRAFT CABIN PRESSURIZATION FAILED ON  CLIMB.  AUTO FAIL WARNING LIGHT ILLUMINATED. CREW TRANSFERED TO STANDBY M	ODE BUT AIRCRAFT WOULD NOT PRESSURE. AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT.MAINTENANCE CHANGED THE CABIN PRESSUR	E CONTROLLER IAW MM 21-31-21 AND THE SYSTEM FUNCTION CHECKED SERVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER IN	CIDENTS TO REPORT.			2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2002050300024	20020503	00024	EA  	2002	5	3	CA020402008      	1	20011213	G	3246	GY22623	BOLT            			CNDAIR	CL604 	CL604       	1900301	EA  										WHEEL ASSY	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) IN THE PROCESS OF PERFORMING A D.I. THE ENGINEER FOUND A MISSING BOLT ON THE NR 4 MAIN WHEEL ASSY. UPON REMOVAL OF	 THE WHEEL THE HEAD OF THE BOLT AND HALF OF THE SHANK WHERE STILL IN THE INBOARD WHEEL HALF. THE THREADED END OF THE BOL	T AND NUT WERE LATER FOUND BY THE HANGAR WALL.  AS A RESULT THE WHEEL ASSY  WAS REPLACED WITH A SERVICABLE UNIT AND REPA	IRED AS PER M.M.			2	L	7	2 	4F			RT	A21EA   					 
2002050300027	20020503	00027	CE  	2002	5	3	CA020405002      	1	20011115	G	3213	740017	STRUT           			CESSNA	185   	185C        	2072808	CE  	CONT  	O470  	IO470F      	17026	SO  					MLG	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) AS A PRECAUTION DUE TO NOT KNOWING THE HISTORY.  THE MAIN LANDING GEAR LEGS WERE SENT FOR MAGNAFLUXING.  TWO LONGI	TUDINAL CRACKS OF ABOUT ONE AND ONE QUARTER INCH LONG WERE DETECTED ON THE LOWER THIRD OF THE LEFT HAND GEAR LEG. NOTE: 	PART CYCLES, PART TSN AND PART TSO TO BE DESREGARDED.				1	H	7	1 	3O	3	O	 	3A24    	3E1				 
2002050300029	20020503	00029	GL  	2002	5	3	CA020405008      	2	20010413	G	7210		NUT             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TORQUEMETER GEARSHAFT NUT WORN.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300030	20020503	00030	GL  	2002	5	3	CA020405009      	2	20010524	G	7314	1C2710FR	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL BOOST	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) AFT BOOST PUMP NOT FUNCTIONAL.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300033	20020503	00033	GL  	2002	5	3	CA020405013      	2	20011004	G	7240	2303910	CASE            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28      	03013	GL  					COMBUST CHAMBER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKED ARMPIT ON COMBUSTION CASE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050300034	20020503	00034	GL  	2002	5	3	CA020405014      	2	20011122	G	7250	23008593	NOZZLE          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TURBINE SECTION	BURNED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) HOT END INSPECTION REVEALED THE FIRST STAGE NOZZLE BURNT BEYOND ACCEPTABLE LIMITS.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2002050300035	20020503	00035	NM  	2002	5	3	CA020405015      	1	20010411	G	8011	MZ4222	STARTER         			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER NOT FUNCTIONAL.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002050300036	20020503	00036	NM  	2002	5	3	CA020405016      	1	20010601	G	2841		TRANSMITTER     			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					FUEL QTY IND	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FUEL GAUGE INOPERATIVE REPLACE TRANSMITTER.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002050300037	20020503	00037	NM  	2002	5	3	CA020405017      	1	20010912	G	7921	A30915	PLATE           			ROBSIN	R22   	R22BETA     	7640110	NM  	LYC   	O320  	O320B2C     	41508	EA  					OIL COOLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OIL COOLER MOUNTING PLATE CRACKED.						1	G	7	1 	3O	3	O	 	H10WE   	E274				 
2002050300038	20020503	00038	SW  	2002	5	3	CA020405018      	1	20010706	G	2822	10274	PUMP            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL BOOST	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) FORWARD BOOST PUMP INOPERATIVE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300039	20020503	00039	SW  	2002	5	3	CA020405019      	1	20010804	G	2435	23032018	STARTER GEN     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) STARTER GENERATOR INOPERATIVE.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300040	20020503	00040	SW  	2002	5	3	CA020405020      	1	20010425	G	6230	204011430001	BEARING         	BELL        	204011400127	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					SWASHPLATE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						JI199175					(CAN)  SWASHPLATE BEARING WORN BEYOND LIMITS.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300041	20020503	00041	NE  	2002	5	3	CA020405021      	2	20010728	G	7310		FLEX LINE       			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) LEAK AT CROSSOVER FLEX LINE TO AUXILIARY TANK CONNECTION.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2002050300042	20020503	00042	SW  	2002	5	3	CA020405022      	1	20010503	G	6210	206010152003	BOLT            	BELL        	206010200133	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					M/R BLADE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						A498					(CAN) EXCESSIVE WEAR ON THE MAIN ROTOR BLADE BOLT SHANK.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300043	20020503	00043	GL  	2002	5	3	CA020405023      	2	20011119	G	7250	6878496	NOZZLE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FIRST STAGE NOZZLE FOUND CRACKED BEYOND ACCEPTABLE LIMITS.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300044	20020503	00044	SW  	2002	5	3	CA020405024      	1	20010708	G	2910	206076031013	SERVO           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYD SYSTEM	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FEEDBACK IN THE FLIGHT CONTROLS. HYDRAULIC SERVO FAILED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002042600060	20020426	00060	SW  	2002	4	26	CA020405025      	1	20011114	G	5302	206030446001F	BULKHEAD        	BELL        	206B        	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BCJN07389					(CAN) CRACK FOUND DURING INSPECTION IN AFT LT TAIL ROTOR GEARBOX MOUNTING AREA.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050300045	20020503	00045	GL  	2002	5	3	CA020405026      	2	20011128	G	7323	252466714	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) GOVERNOR WILL NOT HOLD 100 PERCENT IN FLIGHT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002050600012	20020506	00012		2002	5	6	CA020411006      	4	20010816	G	6113	055032110	BULKHEAD        	CESSNA      	055032110   	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) AFT SPINNER BULKHEAD CRACKED AT RADIUS OF PROP CUT OUT.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2002061200105	20020612	00105	NM  	2002	6	12	CA020508014      	1	20011027	G	2435	11521062	STARTER GEN     			DHAV  	DHC8  	DHC8*       	       	NM  	PWC   	150   	PW150A      	 	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FL250 NR 2 STALL SYS & PUSHER SYS CAUTION LTS CAME ON. ACTION ACC QRH. WITHING NEXT 2 MINS SEVERAL OTHER CAUTIO	N ITS CAME ON FOLLOWED BY NR 2 FMS/PFD/MFD MALFS&COMPLETE RT SIDE WITH OUT LIGHTING (COCKPIT & LDG/APPR LTS). ALSO STBY 	PRESSURE & HYD QTY NR 2 WERE INDICATING ZERO. DECISION TO DIVERT MADE. LDG UNEVENTFUL FOLLOWED BY NORMAL DISEMBARKATION.	 UPON COMPLETING "AFTER LDG CHECKLIST" RT SIDE LIGHTS CAME ON AGAIN & MOST CAUTION LTS & MESSAGES WENT OUT. AIRCRAFT GRO	UNDED FOR INSP. NR 2 DC STARTER GEN REPLACED. EPCU READOUT CARRIED OUT - NO FINDINGS, OPS TEST OF MAIN 28V DC GENERATION	 SYS&DC BUS CONTACTOR K21 CARRIED OUT - WITHOUT FINDINGS. GCU REPLACED. EPCU REPLACED. GCU RETURN ED NFF, EPCU RETURNED 	2	H	7	2 	4T	4	T	RT	A13NM   	E00062EN				 
2002080700234	20020807	00234	EA  	2002	8	7	CA020715006      	1	20010621	G	5610	601R330335	WINDSHIELD      			CNDAIR	CL600 	CL6002B19   	1900309	EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPTAIN`S WINDSHIELD SHATTERED WHILE IN CRUISE AT 35,000 FEET. PRESSURIZATION WAS NORMAL. FLIGHT DIVERTED TO TXK.						2	L	7	2 	4F			RT	A21EA   					 
2002091800047	20020918	00047	SO  	2002	9	18	CA020905004      	1	20010830	G	8120		BEARING         	GARRTT      	LW12463     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					TURBOCHARGER	STIFF           	W				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA						LBR0200					(CAN) MANIFOLD PRESSURE FLUCTUATING.TURBOCHARGER TURBINE WHEEL FOUND STIFF TO SPIN.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2002120600023	20021206	00023	CE  	2002	12	6	CA021101007      	1	20011030	G	7160	109910029115	SKIN            			BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					AIR INLET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN)   ENGINE AIR INLET COWLING FOUND CRACKED ALONG STIFFENER RIVET LINE.						1	L	7	2 	3T	4	T	RT	3A20    	E4EA				 
2002120600051	20021206	00051	EA  	2002	12	6	CA021108007      	2	20010731	G	7414	67542	BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					LT MAGNETO	DESTROYED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT ENGINE, LT MAGNETO ENGINE HOURS: 745.2 DAMAGE WAS DISCOVERED DURING ROUTINE SCHEDULED MAGNETO REPLACEMENT. WHEN	 THE MAGNETO WAS REMOVED THE MAGNETO GEAR RETAINER  ASSY AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE CO	UPLING.UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE GEAR RETAINER  ASSY BEARING WAS DESTROYED AND REQUIRED REPLACE	MENT.  THE BEARING RECESS WAS INSPECTED AND CHECKED O.K. THE BEARING WAS REPLACED WITH NEW AND ASSEMBLY WAS REINSTALLED.	 NO FURTHER ACTION.		1	L	7	2 	3O	3	O	 	1A10    	1E4				 
2003071800092	20030718	00092	SO  	2003	7	18	CA030709005      	2	20010806	G	8520		BUSHING         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	COUNTERWEIGHT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE REMOVED FROM VIBRATION. ENGINE COUNTERWEIGHT BUSHINGS WORN OUT.						1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA	 
2003102100073	20031021	00073	EA  	2003	10	21	CA030922001      	1	20011016	G	5610	NP1393225	WINDOW          			CNDAIR	CL600 	CL6002B19   	1900309	EA  	GE    	CF34  	CF343A1     	30015	NE  					COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) CAPT'S SIDE WINDOW SHATTERED AT 29000 FT.  LANDED AT SCHEDULED DESTINATION.  WINDOW REPLACED.  AIRCRAFT RETURNED T	O SERVICE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE				 
2004012600098	20040126	00098	SW  	2004	1	26	CA031117009      	1	20010601	G	3243	206031301025	SUPPORT         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11430								(CAN) WHILE PERFORMING AN AW CHECK, CRACKS WERE SUSPECTED IN AFT CROSS TUBE SUPPORT AREA.  AFTER PAINT STRIPPING CRACKS 	CONFIRMED AS FOLLOWS. A SMALL HAIRLINE CRACK WAS FOUND ON THE  FWD LEG OF THE LT CROSS TUBE SUPPORT. CRACK IS JUST  OUTB	OARD OF 90 DEGREE ANGLE. CRACK STARTS AT BOTTOM OF SUPPORT & EXTENDS VERTICAL TO FIRST RIVET & THEN VEERS INBOARD & VERT	ICAL. CRACK IS APPROX. 1 INCH IN LENGTH. A SMALL HAIRLINE CRACK ALSO FOUND JUST BELOW FWD LEG OF THE RT CROSS TUBE SUPPO	RT. CRACK IS JUST BELOW THIS LEG & RUNS HORIZONTAL & IS ABOUT 1/2 INCH LONG.  BELL HELICOPTER IS AWARE OF CRACKS IN THIS	 AREA & HAS MADE AN UPGRADE TO THESE PARTS. NEW PARTS ARE OF A MUCH THICKER MATERIAL TO PREVENT CRACKING.	1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2005041800078	20050418	00078	NE  	2005	4	18	CA041018011      	2	20010813	G	7261	01R311159601	TUBE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	GAS GENERATOR	CRACKED         	W				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		TX	TAXI/GRND HDL  	1			CA			35615					120097			(CAN) DURING TAXI OUT TO RUNWAY CREW NOTICED AN ODOR WHICH ALSO SET OFF THE LAVATORY SMOKE DETECTOR. AIRCRAFT RETURNED T	O GATE. TROUBLESHOOTING BY MAINTENANCE REVEALED SMOKE WAS ENTERING INTO CABIN WHEN BLEED AIR SELECTED ON, NR 1 ENGINE. E	NGINE WAS REPLACED. ENGINEERING REPORT BY FROM ENGINE TEARDOWN INDICATED THAT THE OIL PRESSURE SUPPLY TUBE FOR THE NR 5 	BEARING AREA WAS CRACKED AT A WELD SEAM IN THE GASGENERATOR CASE. ENGINE WAS REPAIRED. REPORT AVAILABLE IF REQUIRED.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE	 
2005050300118	20050503	00118	SW  	2005	5	3	CA050228010      	1	20010324	G	6320	BP252	GEARBOX         			KAMOV 	KA32  	KA32A1      	       	SW  	AMTR  	VK1A  	KLIMOVK1A   		GL  					MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) GEARBOX CHIP LIGHT, GEARBOX REPLACED.						1	G	7	2 	4U	4	J	NC	        	EXPE4J				 
2005050300116	20050503	00116	SW  	2005	5	3	CA050228011      	1	20010714	G	6320	BP252	GEARBOX         			KAMOV 	KA32  	KA32A1      	       	SW  										MAIN ROTOR	MAKING METAL    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) GEARBOX CHIP LIGHT, GEARBOX REPLACED.						1	G	7	2 	4U			NC	        					 
2001083100189	20010831	00189		2001	8	31	CAXR106173       	4	20010629	G	3425	5040122902	INDICATOR       			UROCOP	EC120 	EC120B      	8680987	EU  	TMECA 	ARRIUS	ARRIU2F     	 	NE  					INSTRUMENT PNL	FAILED          	C			CAXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	15	408DC	259  				1151				ATTITUDE INDICATOR - INSTRUMENT FAILED, INOPERATIVE.  RMA NR 031964						1	G	7	2 	3U	3	U	NC	R0001RD 	E34NE				 
2001030600090	20010306	00090	NM  	2001	3	6	COOSDR000033     	1	20010215	G	5320		TORQUE BOX      			BOEING	727   	727225      	1384077	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NLG WW	FATIGUED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	8887Z					21856				COOPESA REPORTED THE NOSE WHEEL WELL TORQUE BOX LOWER CHORD LBL 19, WL 148 CHORD WITH CORROSION.  REPLACED THE SUBJECT C	HORD.  PROBABLE CAUSE OF CORROSION WAS FATIGUE.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA				 
2001050900288	20010509	00288	SO  	2001	5	9	CWA1             	2	20010118	G	7260	632617	GEAR            	CONT        		CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360GB     	17025	SO  					ACCESSORY DRIVE	WORN            	D				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			GL	13	72361	188  	188  			33701568	244627R			DURING RUN-UP, FOLLOWING ANNUAL INSPECTION, NO VACUUM INDICATION OBSERVED FROM REAR ENGINE.  REMOVED PUMP FOR REPLACEMEN	T AND OBSERVED DRIVE ON ENGINE DID NOT TURN WITH PROPELLER.  REMOVED ACCESSORY DRIVE COVER AND FOUND NO TEETH LEFT ON DR	IVING BEVEL GEAR.  DRIVEN GEAR WAS NOT WORN.				1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001030700595	20010307	00595	SW  	2001	3	7	E27R1730         	1	20010112	G	5310	3107041310704	CHANNEL         			GULSTM	690TP 	690A        	0141722	SW  										WING ROOT	CRACKED         	B			E27R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	921ST	10645				11200				DURING PRESSURAZATION LEAK CHECKS, THE CABIN WAS FOUND TO HVE TWO LARGE LEAKS IN LT AND RT WING ROOT AREA.  ON EXAM OF T	HE SUSPECT AREAS IT WAS FOUND THAT THE LT AND RT SUPPORT CHANNELS PN310704-1 AND 310704-2 HAD FAILED FROM FS 144 WL10 TO	 FS 175 WL 14.  THE FAILURE IS IN THE FORM OF A CRACK ON THE VERTICAL OB PORTION OF THE CHANNELS FROM RIVET TO RIVET.  T	HIS FAILURE ALLOWED THE AIRCRAFT SKIN TO PULL AWAY FROM ITS SUPPORTING STRUCTURE ABOVE THE PICTURE WINDOWS IN EXCESS OF 	.25 IN.		1	H	7	2 	3T			 	2A4     					 
2001032600430	20010326	00430	SW  	2001	3	26	E27R730          	1	20010122	G	5300	3107041	CHANNEL         			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE331*     	01514	WP  					LT & RT	FAILED          	B			E27R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	921ST	10545				11200				DURING PRESSURIZATION LEAK CHECKS, THE CABIN WAS FOUND TO HAVE TWO LARGE LEAKS IN THE LEFT AND RIGHT WING ROOT AREA.  ON	 EXAMINATION OF THE SUSPECT AREAS IT WAS FOUND THAT THE LEFT AND RIGHT SUPPORT CHANNELS PN 3107041 & 3107042 HAD FAILED 	FROM FS 144 WL TO FS 175 WL 14, THE FAILURE ALLOWED THE AIRCRAFT SKIN TO PULL AWAY FROM ITS SUPPORTING STRUCTURE ABOVE T	HE PICTURE WINDOWS IN EXCESS OF .25.			1	H	7	2 	3T	3	T	 	2A4     	E2WE				 
2001032600431	20010326	00431	WP  	2001	3	26	E27R7302         	2	20010122	G	7210	3103435	GEAR            			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE33110    	01514	WP  					BULL GEAR	FAILED          	B			E27R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	48AZ	6991 	1612 			11307	P79291C			BULL GEAR FOUND TO HAVE SHED APPROX 6 IN OF TEETH IN 2 SEGMENTS CAUSING EXTENSIVE DAMAGE TO GEAR BOX COMPONENTS AND CASE	. WHICH RESULTED IN AN IN FLIGHT SHUTDOWN.					1	H	7	2 	3T	4	T	 	2A4     	E4WE				 
2001050700351	20010507	00351	SO  	2001	5	7	ER00101          	1	20010502	G	2710	5540802	CONTROL CABLE   			PIPER 	PA31T 	PA31T1      	7103126	SO  	PWA   	PT6   	PT6A11      	52043	NE  					FUSELAGE	CROSSED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2480X	2655 	200  			8104026				DURING SCHEDULED INSPECTION, THE RIGHT HAND AILERON INTERCONNECT CABLE WAS FOUND TO BE CROSSED OVER THE PRIMARY RUDDER C	ONTROL CABLE (PT NO 46845-0)AT THE UNDERFLOOR SECTION AFT OF THE CABIN DOOR.  THERE IS NO WEAR APPARENT AT THIS TIME, TH	E AIRCRAFT LOG BOOKS ARE BEING INSPECTED IN AN ATTEMPT TO ASCERTAIN WHEN THE SYSTEM WAS LAST DISTURBED.				1	L	7	2 	3T	3	T	 	A8EA    	E4EA				 
2001072600065	20010726	00065	EU  	2001	7	26	ERAA072935       	1	20010420	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL	LEAKING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	426EH					552				SHAFT HAS 36.9 HRS TSO AND IS CAUSING INPUT SEAL TO LEAK EVEN WITH THE NEW IMPROVED SEAL INSTALLED.						1	G	7	2 	3U			 	H3EU    					 
2001072600066	20010726	00066	NE  	2001	7	26	ERAA072936       	1	20010424	G	8000	60692032	BLOWER          			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	INOPERATIVE     	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	577EH					760222				PART IS  INOPERABLE.   MOTOR WON'T START WITH BLOWER ON.  HAVE TO TAP ON PLUG CONNECTOR BOX TO START.  INSTALLING NEW BL	OWER SOLVED PROBLEM.  TSO IS ONLY 47.1 HRS.  RETURNING TO CORPORATE ROTABLE ON REPAIR ORDER #  RW-883735 REQUESTING WARR	ANTY REPAIR.				1	G	7	2 	3U			 	H1NE    					 
2001072600067	20010726	00067	NE  	2001	7	26	ERAA072937       	1	20010501	G	7120	0292108940	SUPPORT         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	BROKEN          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	578EH	2147 				760099	3016			FRONT SUPPORT IS BROKEN IN HALF.  PART HAS 2147.0 HRS ON IT.  THIS INFORMATION FOR FAA SDR REPLACED WITH NEW SUPPORT.						1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001072600068	20010726	00068	EU  	2001	7	26	ERAA072938       	1	20010501	G	6320	4638001007	TRANSMISSION    			BOLKMS	105   	BO105A      	       	EU  										M/R GEARBOX	MAKING METAL    	A			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	290EH	12460				S850				TRANSMISSION MAKING METAL.  REMOVED SLIP RING CARRIER, FOUND LT BEVEL GEAR BREAKING DOWN.  FOUND OIL PUMP DAMAGED FROM M	ETAL CONTAMINATION.  PUMP SENT OUT FOR REPAIR. THIS INFORMATION FOR FAA SDR.  ACTION TAKEN:  REPAIRED TRANSMISSION I/A/W	 REM 103, INST'D NEW L/H INPUT PINION & BEVEL GEAR, SERVICEABLE OIL PUMP.  COMPLIED WITH FREEWHEEL INSPECTION I/A/W REM 	103.  NEXT INSPECTION DUE IN 600 HRS.  ASSEMBLED TRANSMISSION AND ADJUSTED PATTERN AND BACKLASH.			1	G	7	2 	3U			 	H3EU    					 
2001072600069	20010726	00069	EU  	2001	7	26	ERAA073270       	1	20010516	G	2435	230321825	STATOR          			BOLKMS	105   	BO105S      	5626006	EU  										GENERATOR	CHAFED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	153EH					S572				ARMATURE RUBBING INSIDE STATOR.  ISSUED TO AC 153EH BUT COULD NOT BE INSTALLED DUE TO PROBLEM WHEN TRYING TO INSTALL IN 	GENERATOR.					1	G	7	2 	3U			 	H3EU    					 
2001072600076	20010726	00076	SW  	2001	7	26	ERAA073271       	1	20010521	G	2822		SCREW           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					VALVE	STRIPPED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	419EH	1881 				33043				SCREW IS STRIPPED.  SCREWS STRIPPED  OR BACKING OUT OF VALVE BODY. NOTE:  SCREWS WERE LOCK WIRED.  T						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001072600077	20010726	00077	EU  	2001	7	26	ERAA073274       	1	20010531	G	3246	10550103	SKID            			BOLKMS	105   	BO105S      	5626006	EU  										MLG	MISOVERHAULED   	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	125EH					S562				SKID TUBE ISSUED TO AC 125EH BUT COULD NOT BE INSTALLED.  SKID TUBE WAS OVERHAULED  AND RETURNED  WITH NUT PLATES NOT LI	NING UP WITH SKID SHOES.					1	G	7	2 	3U			 	H3EU    					 
2001072600079	20010726	00079	EU  	2001	7	26	ERAA073275       	1	20010601	G	3246	10550103	SKID            			BOLKMS	105   	BO105A      	       	EU  										MLG	MISOVERHAULED   	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	148EH					703				SKID TUBE ISSUED TO AC 148EH BUT COULD NOT BE INSTALLED.  SKID TUBE WAS OVERHAULED  AND RETURNED  WITH NUT PLATES NOT LI	NING UP WITH SKID SHOES.					1	G	7	2 	3U			 	H3EU    					 
2001080200300	20010802	00300	SW  	2001	8	2	ERAA074613       	1	20010612	G	2433	2010001	CONVERTER       			BELL  	412   	412         	1182202	SW  										ELECTRICAL	MALFUNCTIONED   	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH	16   				33001				NEW CONVERTER REC'D FROM ANCHORAGE ORDERED FROM BENZ AIRBORNE.  UNIT WILL NOT ADJUST LOW ENOUGH.  ONLY HAS 15.5 HRS SINC	E NEW.  RETURNING TO BENZ ON ERA REPAIR ORDER  RW-884522 REQUESTING WARRANTY REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2001080200301	20010802	00301		2001	8	2	ERAA074614       	4	20010612	G	3444	066303102	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										RADAR	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	576EH					760212				RADAR ALTIMETER WAS OVERHAULED BY FREESCAN  2 / 2001  AND RET'D TO ERA .  INSTALLED ON AIRCRAFT AND HAD TO REMOVE DUE TO	 BEING TOTALLY INOPERABLE.  RETURNING TO FREESCAN ON ERA REPAIR ORDER RW-884523 REQUESTING WARRANTY REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001080200306	20010802	00306	SW  	2001	8	2	ERAA074615       	1	20010612	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS HIGH      	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	418EH									TRIPLE TACH REM'D FROM AIRCRAFT AFTER 111.3 HRS AFTER O/H WITH ROTOR NEEDLE READING 5 PERCENT HIGH.						1	G	7	2 	4U			 	H4SW    					 
2001080200309	20010802	00309	EU  	2001	8	2	ERAA074616       	1	20010613	G	6320	4638001007	TRANSMISSION    			BOLKMS	105   	BO105A      	       	EU  										MAIN ROTOR	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	290EH	12460				S850				TRANSMISSION IS CONTAMINATED BY TRASH FROM OIL COOLER.  REMOVED ALL OIL JETS TO FLUSH OUT ALL OIL PASSAGES.   REMOVED TO	P CASE & CENTER HOUSING, CLEANED AND FLUSHED ALL OIL JETS AND OIL PASSAGES, REPAIRED ACCEDSSORY DRIVE, REASSEMBLED TRANS	MISSION WITH NEW O-RINGS IAW REM 103.				1	G	7	2 	3U			 	H3EU    					 
2001080200312	20010802	00312	EU  	2001	8	2	ERAA074617       	1	20010613	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	BINDING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	131EH	11983				559				T/R ASSY IS BINDING.  REPAIRED, PARTIAL DISASSEMBLY, VISUALLY INSPECTED.  FOUND NO CAUSE FOR BINDING, INST'D NEW GRIP BU	SHINGS AND SEALS.  CHECKED FRICTION FORCES 10N AND 17N (MAX 25N)  REASSEMBLED T/R ASSY AND MARVEL BALANCED ALL WORK IAW 	BO105 MM 32, MARVEL MANUAL REM 301.				1	G	7	2 	3U			 	H3EU    					 
2001080200315	20010802	00315	EU  	2001	8	2	ERAA074618       	1	20010613	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	BINDING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	131EH	13133				559				THIS INFORMATION FOR FAA SDR.  CC: AMERICAN EUROCOPTER CORP.  T/R ASSY IS BINDING. ACTION TAKEN:  FOUND INNER SLEEVE AND	 BLADE MOUNTING, FORK BEARING BUSHINGS COATED WITH TEFLON FILM  REPAIRED FOR BINDING.  DISASSEMBLED, CLEANED, VISUALLY I	NSPECTED, REASSEMBLED WITH NEW SEALS AND BALANCED.  ALL WORK DONE IAW MBB-BO105 REM 301, MM CHAP 34 & 107 & MARVEL BOOK.	.			1	G	7	2 	3U			 	H3EU    					 
2001080200319	20010802	00319	GL  	2001	8	2	ERAA074619       	2	20010613	G	7313	6890040	NOZZLE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL INJECTION	MISREPAIRED     	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	296EH					S849				1ST STAGE NOZZLE SHIELD RET'D FROM OVERHAUL AT DALLAS AIRMOTVE, ISSUED TO AIRCRAFT BUT COULD NOT BE INSTALLED DUE TO NOT	 BEING WELDED ALL THE WAY AROUND.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001080200326	20010802	00326		2001	8	2	ERAA074620       	4	20010614	G	2312	4120073010	CONTROL HEAD    			BELL  	412   	412         	1182202	SW  										COCKPIT	MISREPAIRED     	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	167EH					33089				CONTROL HEAD  MODIFIED INCORRECTLY.  WAS MODIFIED TO S INSTEAD OF A.						1	G	7	2 	4U			 	H4SW    					 
2001080300013	20010803	00013	EU  	2001	8	3	ERAA074621       	1	20010615	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	BINDING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	131EH	3137 				559				T/R ASSY IS BINDING.  FOUND NO ABNORMAL WEAR OR DEFECTS.  DISASSEMBLED, CLEANED AND INSPECTED BUSHINGS ON INNER SLEEVE. 	 REMOVED AND REPLACED BUSHINGS AND SEAKS IN BLADE MOUNTING FORKS.  REASSEMBLED AND BALANCED.  ALL WORK DONE IAW MBB BO10	5 REM 301, MBB-BO105  MM CHAPTERS 34& 107 AND MARVEL BOOK.				1	G	7	2 	3U			 	H3EU    					 
2001080300072	20010803	00072	EU  	2001	8	3	ERAA074622       	1	20010615	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	STIFF           	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	128EH	12475				572				THIS INFORMATION FOR FAA SDR.   CC: AMERICAN EUROCOPTER CORP.  T/R ASSY HAS STIFF PEDALS. FOUND NO ABNORMAL WEAR OR DEFE	CTS ACTION TAKEN:  DISASSEMBLED, CLEANED AND INSPECTED BUSHINGS ON INNER SLEEVE, REPLACED SEALS AND BUSHIGS IN BLADE MOU	NTING FORKS  REASSEMBLED AND BALANCED.  ALL WORK DONE IAW MBB BO105 REM301, MBB BO105MM CHAPTERS 34 & 107 AND MARVEL BOO	K.			1	G	7	2 	3U			 	H3EU    					 
2001080300073	20010803	00073	EU  	2001	8	3	ERAA074623       	1	20010615	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	STIFF           	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01		13133								THIS INFORMATION FOR FAA SDR.  CC:  AMERICAN EUROCOPTER CORP.  STIFF T/R PEDALS AT 100% FOUND NO CAUSE FOR BINDING. ACTI	ON TAKEN:  DISASSEMBLED, CLEANED & VISUALLY INSPECTED.   REASSEMBLED USING NEW BUSHINGS & SEALS.  C/W FRICTION CHECK (TE	STED 3N & 44) & MARVEL BALANCED.  ALL WORK IAW BO105 REM 301 & MM CH 33 & 34 & MARVEL BOOK.				1	G	7	2 	3U			 	H3EU    					 
2001080300075	20010803	00075	EU  	2001	8	3	ERAA074624       	1	20010618	G	6420	10531714	HEAD            			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	STIFF           	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	127EH	12841				571				T/R   ASSY HAS HEAVY LEFT PEDAL. ACTION TAKEN:  REPAIRED, DISASSEMBLED, CLEANED, VISUALLY INSPECTED.  INSTALLED NEW GRIP	 BUSHINGS AND SEALS.  INST'D SERVICEABLE CONTROL LEVERS.  REASSEMBLED AND BALANCED ALL WORK IAW BO105 REM 301 MM 33,34.					1	G	7	2 	3U			 	H3EU    					 
2001080300077	20010803	00077	SW  	2001	8	3	ERAA074626       	1	20010619	G	6520	212040004009	GEARBOX         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	417EH	13445				33031				GEARBOX IS MAKING METAL. BEARINGS BREAKING DOWN. ACTION TAKEN:  OVERHAULED, DISASSEMBLED, CLEANED, VISUALLY INSPECTED AN	D NDT.  C/W TB 412-99-157.  INSTALLED NEW BEARINGS OP SHAFT, EXCLUDER ASSY AND ALL SEALING ELEMENTS.  REASSEMBLED 90 DEG	REE GEARBOX AND CHECKED BACKLASH.  .009, .009, .009 REPACKED COUPLING WITH GREASE DATED GREASE DATED NOV.  12, 1999.				1	G	7	2 	4U			 	H4SW    					 
2001080300078	20010803	00078	GL  	2001	8	3	ERAA074627       	2	20010619	G	7230	250C20B	COMPRESSOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	SEIZED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	296EH	12458				S849				COMPRESSOR LOCKED UP. PLASTIC ON CASE 1/2 MISSING. ACTION TAKEN:  INSTALLED SERVICEABLE CASE.						1	G	7	2 	3U	3	T	 	H3EU    	E10CE				 
2001080300079	20010803	00079	EA  	2001	8	3	ERAA074628       	2	20010621	G	7230		COMPRESSOR      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	421EH	13292				33067				AFTER 451.2 HRS T.S.O. C-BOX REMOVED FROM AIRCRAFT DUE TO HIGH OIL PRESSURE.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001092100155	20010921	00155	NE  	2001	9	21	ERAA074826       	1	20010718	G	6730	BH185R154	SERVO           			SKRSKY	S61   	S61N        	8142104	NE  											FLUCTUATES      	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	563EH					61808				INSTALLED ON A/C AND HAD TO REMOVE DUE TO GAUGE FLUCTUATING.  RETURNING ON ERA REPAIR ORDER # RW -885179 REQUESTING WARR	ANTY REPAIR.					2	G	7	2 	4U			 	1H15    					 
2001092100157	20010921	00157	EU  	2001	9	21	ERAA074827       	1	20010718	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105A      	       	EU  										FREEWHEEL UNIT	LEAKING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	291EH					S842				FREEWHEEL SHAFT IS CAUSING INPUT SEAL TO LEAK.  NEEDS SPECIAL COATING REPLACED. WAS PURCHASED NEW 2/14/00.  RETURNING ON	 ERA REPAIR ORDER  885185 REQUESTING  WARRANTY EXCHANGE.					1	G	7	2 	3U			 	H3EU    					 
2001092100161	20010921	00161	EU  	2001	9	21	ERAA074828       	1	20010720	G	6520	4619002003	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	134EH	2837 				635				BEARINGS SCORED AND INPUT BUSHING FRETTING. DISASSEMBLED, VISUALLY INSPECTED.  REPLACED ALL FIVE BEARINGS, INPUT BUSHING	, ALL O RINGS, ALL SEALING RINGS, BOTH SEALS, ONE SCREW AND THE LOCKING PLATE.  REASSEMBLED, SET GEAR DISTANCE, BACKLASH	 & PATTERN PRO-SEALED.  REPAIRED IAW BO-105  REM-304. COMPLIED WITH ASB BO-105-30-111. COPY SENT TO AMERICAN EUROCOPTER 	CORP.			1	G	7	2 	3U			 	H3EU    					 
2001092100162	20010921	00162	EU  	2001	9	21	ERAA074829       	1	20010723	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	FLAKING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	152EH	2306 				S701				SEVERE PAINT AND RUBBER FLAKEING.  SENT TO AEC FOR REPAIR  AND INSTALLED ON AIRCRAFT 1-22-01.  RETURNING ON ERA REPAIR O	RDER# RW-885245 REQUESTING WARRANTY REPAIR.					1	G	7	2 	3U			 	H3EU    					 
2001092100163	20010921	00163	EU  	2001	9	21	ERAA074830       	1	20010730	G	3212	307561	SQUIB VALVE     			BOLKMS	105   	BO105S      	5626006	EU  										MLG	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	133EH	881  				598				SQUIB VALVE CORRODED.  VALVE BODY IS  BULGING (OR PERTRUDING)  AS INDICATED ON VALVE. CORRECTIVE ACTION:  SQUIB VALVE RE	MOVED  FROM AIRCRAFT AND TAGGED AS UNSERVICEABLE.					1	G	7	2 	3U			 	H3EU    					 
2001092100165	20010921	00165	GL  	2001	9	21	ERAA074831       	2	20010801	G	7320	252464430N	FUEL CONTROL    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MISOVERHAULED   	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	293EH	6921 				S844				FUEL CONTROL OVERHAULED BY HONEYWELL 2/23/01.  UNIT IS SLOW STARTING AND HANGS AT 55 PERCENT. RETURNING ON ERA REPAIR OR	DER  RW-885436 REQUESTING WARRANTY REPAIR.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001092100167	20010921	00167	SW  	2001	9	21	ERAA074832       	1	20010802	G	5260	LA11A2129	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	SPARE									STEP ACTUATOR WAS REPAIRED BY ITT AND RET'D TO ERA 5/30/2001.  COULD NOT BE USED ON AIRCRAFT BECAUSE UNIT WOULD NOT RETR	ACT.  RETURNING ON ERA REPAIR ORDER  RW-885450 REQUESTING WARRANTY REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2001092100168	20010921	00168	SW  	2001	9	21	ERAA075871       	1	20010802	G	5260	LA11A2129	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	A			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	SPARE									STEP ACTUATOR WAS REPAIRED BY ITT AND RET'D TO ERA 5/30/2001.  COULD NOT BE USED ON AIRCRAFT BECAUSE UNIT WOULD NOT RETR	ACT.  RETURNING ON ERA REPAIR ORDER# RW-885450 REQUESTING WARRANTY REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2001092400093	20010924	00093	EU  	2001	9	24	ERAA075875       	1	20010809	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL UNIT	LEAKING         	H			ERAA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	294EH	615  				S675				FREEWHEEL SHAFT LEAKS.  WAS SENT TO ZF FOR OVERHAUL  1/26/01 AND WAS INSTALLED ON AIRCRAFT 8/04/01.  AFTER 18.2 HRS,  UN	IT CAUSING INPUT SEAL TO LEAK.  SPECIAL COATING WORN.  RETURNING TO ZF ON ERA REPAIR ORDER RW-885574 REQUESTING WARRANTY	 REPAIR.				1	G	7	2 	3U			 	H3EU    					 
2001092400095	20010924	00095	EU  	2001	9	24	ERAA075876       	1	20010822	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL UNIT	LEAKING         	H			ERAA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	294EH	457  				S846				FREEWHEEL SHAFT PREVIOUSLY SENT TO ZF 4/2001 FOR REPAIR FOR SAME PROBLEM, CAUSING LEAKING OF INPUT SEALS.   REF MMIR ERA	A 0001202.  RETURNING ON ERA REPAIR ORDER  RW-885812 REQUESTING WARRANTY REPAIR.  ALSO RETURNING (2) INPUT SEALS THAT AR	E LEAKING WITH THE SAME AMOUNT OF HOURS AS FREEWHEEL SHAFT.  ATTN: HERBERT BODENMILLER				1	G	7	2 	3U			 	H3EU    					 
2001122600001	20011226	00001	SW  	2001	12	26	ERAA076643       	1	20010921	G	7500	3032247	AIR FILTER      			BELL  	412   	412         	1182202	SW  										ENGINE	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH	106  				33001				PART IS DEBONDED.  THIS PARTICULAR AIR FILTER HAD 106.0 HRS BUT HAVE TRIED SEVERAL OTHERS AND IMMEDIATELY AIR FILTERS BE	GAN TO BREAK DOWN AND DEBOND.					1	G	7	2 	4U			 	H4SW    					 
2001122600002	20011226	00002	EU  	2001	12	26	ERAA076644       	1	20010921	G	6310	4638302093	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										FREEWHEEL UNIT	LEAKING         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	426EH	245  				552				FREEWHEEL SHAFT CAUSES INPUT SEAL TO LEAK. SPECIAL COATING NEEDS TO BE REPLACED.  ONLY HAS 245.1 HRS SINCE LAST RETURNED	 TO ZF.  LAST RETURNED ON WARRANTY CLAIM.					1	G	7	2 	3U			 	H3EU    					 
2001122600003	20011226	00003	SW  	2001	12	26	ERAA076647       	1	20010927	G	7500	3032247	AIR FILTER      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	422EH					33068	CPPS62136			PART IS DEBONDED.  FILTER PURCHASED FROM PUR FLOW MFG.  IMMEDIATELY COME APART AFTER INSTALLATION.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001122600004	20011226	00004	SW  	2001	12	26	ERAA076648       	1	20010927	G	7500	3032247	AIR FILTER      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	164EH					33004				PART IS  DEBONDED.  THIS INFORMATION FOR FAA SDR ONLY.   PURCHASED FROM PUR FLOW MFG.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001122600005	20011226	00005	SW  	2001	12	26	ERAA076649       	1	20010928	G	7500	3032247	AIR FILTER      			BELL  	412   	412         	1182202	SW  										NR 1 & 2 ENGINES	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH					33001				PART IS  DEBONDED.  INSTALLED ON NR 1 AND NR 2 ENGINE BUT BOTH FILTERS DEBONDED AND FELL APART IMMEDIATIATELY.						1	G	7	2 	4U			 	H4SW    					 
2001122600006	20011226	00006	SW  	2001	12	26	ERAA076650       	1	20010928	G	7500	3032247	AIR FILTER      			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH					33001				PART IS  DEBONDED.  INSTALLED ON   NR 2 ENGINE BUT FILTER FELL APART.  THIS INFO FOR FAA  SDR. FILTERS PURCHASED FROM PU	R-FLOW MFG.					1	G	7	2 	4U			 	H4SW    					 
2001122600007	20011226	00007	NE  	2001	12	26	ERAA076652       	1	20011003	G	3040	40008330202	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										RADAR UNIT	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	561EH	135  				61471				RADAR INDICATOR HAS WATER DAMAGE.   UNIT HAD BLANK SCREEN AND WOULD NOT COME ON.MAJOR WATER DAMAGE WS FOUND IN UNIT. ACT	ION TAKEN:  REMOVED CORROSION, REPAIRED TRACES, ALIGNED AND TESTED.  THIS INFORMATION FOR FAA SDR.					2	G	7	2 	4U			 	1H15    					 
2001122600008	20011226	00008		2001	12	26	ERAA076653       	4	20011003	G	3440	40008330208	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										RADAR UNIT	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	561EH	1073 				61471				RADAR INDICATOR HAS  WATER DAMAGE.   UNIT WOULD NOT COME ON. FOUND WATER DAMAGE. ACTION TAKEN :  REMOVED CORROSION, REPL	ACED BLOWN RESISTOR AND TESTED UNIT.					2	G	7	2 	4U			 	1H15    					 
2001122600009	20011226	00009		2001	12	26	ERAA076654       	4	20011003	G	3440	40008330208	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										RADAR	CONTAMINATED    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	561EH	831  				61471				RADAR INDICATOR HAS WATER DAMAGE.  INOPERABLE.  UNIT HAS WATER DAMAGE ACTION TAKEN:  REPLACED BLOWN RESISTOR, REMOVED CO	RROSION AND TESTED.					2	G	7	2 	4U			 	1H15    					 
2001122600024	20011226	00024	GL  	2001	12	26	ERAA076655       	2	20011003	G	7320	252466715H	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	292EH	13707				562				GOVERNOR OCCASIONALLY  DROOPS IN FLIGHT.  TEST RESULTS CONFIRM SNAG OF DROOP. UNIT WAS DOOPING BY 250 RPM @ T.P. 3.01 EC	CENTRIC SHAFT FOUND CORRODED AND WORN BEYOND LIMITS ON LOBES.  BEARINGS PN 2520503 AND 2523237 FOUND TO BE ROUGH AND DRY	. ACTION TAKEN:  ABOVE PARTS REPLACED WITH NEW AND UNIT WAS REPAIRED AND TESTED SERVICEABLE IAW HONEYWELL OH FORM 15-109	5A.  THIS INFORMATION FOR FAA SDR.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122600025	20011226	00025	GL  	2001	12	26	ERAA076656       	2	20011003	G	7320	252466715H	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	153EH	11164				S572				NR 1 GOVERNOR IS SLOW,NR HIGH WITH REDUCED POWER.  TEST RESULTS INDICATE GOVERNOR WAS DROOPING OFF SLIGHTLY (100 RPM) SE	VERAL INTERNAL BEARINGS PN 2520503 & 2523237 FOUND DRY AND ROUGH.  THROTTLE BUSHING WORN ALLOWING SHAFT TO HAVE EXCESSIV	E PLAY.  ECCENTRIC SHAFT CORRODED AND WORN BEYOND LIMITS. ACTION TAKEN:  REPAIRED AND TESTED SERVICEABLE IAW HONEYWELL O	HM 15--1095A.  ABOVE PARTS REPLACED.  CEB A-1353 R1 FOUND N/AB, UNIT S/N, CEB A-1361R1 FOUND C/W.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122600026	20011226	00026	GL  	2001	12	26	ERAA076657       	2	20011003	G	7320	2524667	GOVERNOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  						WORN            	H			ERAA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	149EH	8461 				S705				SPLINES ON DRIVESHAFT OF GOVERNOR IS WORN.  MAX GOVERING DROOPS OFF 300 RPM TO EARLY.  THROTTLE BUSHING VERY SLOPPY WORN	 SPLINES ON DRIVESHAFT AS WELL AS THE MATING FACE OF THE SPOOL BEARING EXHIBITED HEAVY WEAR FROM THE GOVERNOR WEIGHT FEE	T.  ECCENTRIC SHAFT AND CAM LEVER WERE FOUND SEIZED TOGETHER N THE DRIVE BODY BY CORROSION.  AFTER CLEANING THEY WERE BO	TH PITTED AND WORN BEYOND LIMITS ACTION TAKEN:  OVERHAULED.  NOTE:  THE CONDITION OF THIS GOVERNOR SEEMS TO INDICATE A V	IBRATION PROBLEM ON THE A/C, POTENTIALLY STARTER GENERATOR ON GEARBOX. CEB'S 1347 R1, A-1361R1 AND GT320. C/W CEB A-1353	R1 FOUND N/A BY UNIT S/N. THIS INFORMATION FOR FAA SDR	1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122600027	20011226	00027	EU  	2001	12	26	ERAA076658       	1	20011004	G	6210	1051410110	BOLT            			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	149EH					S705				PRIMARY BLADE BOLTS HAS  WORN PLATING. ACTION TAKEN :  CLEANED & C/W VISUAL & NDT INSPECTION.  SCRAPPED 3 BOLTS DUE TO M	ECHANICAL DAMAGE.  THIS INFORMATION FOR FAA SDR.					1	G	7	2 	3U			 	H3EU    					 
2001122600028	20011226	00028	EU  	2001	12	26	ERAA076663       	1	20011005	G	6210	10515170	BLADE           			BOLKMS	105   	BO105A      	       	EU  										MAIN ROTOR	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	135EH	11317				S675				M/R BLADE IS  DEBONDED.   LEADING EDGE DEBONDING, POTTING NEEDS CHANGING. ACTION TAKEN:  ALL ABRASION STRIPS VOID, HEAVY	 ERROSION ON ABRASION STRIP, P.U. FILM DETERIORATION, PAINT PEELING, HARDWARE CORRODED SWEEP OUT -13.21MM, NOSE AND NECK	 SHELLS CRACKED SKIN CRACKED @ NECK SHELL, SKIN DEBONDED @ NECK AREA.  REPAIRED. THIS INFORMATION FOR FAA SDR.				1	G	7	2 	3U			 	H3EU    					 
2001122600029	20011226	00029	EU  	2001	12	26	ERAA076664       	1	20011009	G	6210	10515170	BLADE           			BOLKMS	105   	BO105A      	       	EU  										MAIN ROTOR	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	135EH	11319				S675				BLADE IS DEBONDING ON LEADING EDGE.  POTTING NEEDS CHANGING NOSE AND NECK SHELLS CRACKED @ NECK DOWN AREA, SKIN CRACK AN	D VOIDED @ NECK AREA, TEFLON MISSING FROM MAIN BUSHING, DRAG BUSHING HAS FRAYED AND MISSING TEFLON, DAMPNER WRAP VOID LO	WER SURFACE, ALL ABRASION STRIPS VOID @ SCARF JOINTS, HEAVY ERROSION ON OUTBOARD ABRASION STRIP, MINOR CORROSION ON THE 	TABS. DU DISKS MISSING, MINOR CORROSION ON PENDULUM ARM, SWEEP OUT 10.34MM  ACTION TAKEN:  REPLACED NR 1 OUTBOARD ABRASI	ON STRIP, REPLACED PT REINSTALLED NR 2,3,4 ABRASION STRIPS, REPLACED DU DISKS REPLACE MAIN BUSHING, REPLACED DRAG BUSHIN	G, REM'D AND TREAT CORROSION OR TRIM TABS, PERFORM SMALL SKIN REPAIR @ NECK, REPLACED NOSE AND NECK SHELLS, REPLACED DAM	1	G	7	2 	3U			 	H3EU    					 
2001122600031	20011226	00031	EU  	2001	12	26	ERAA076665       	1	20011009	G	6210	10515170	BLADE           			BOLKMS	105   	BO105A      	       	EU  										MAIN ROTOR	DEBONDED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	135EH	11428				S675				BLADE IS DEBONDING ON LEADING EDGE.  POTTING NEEDS CHANGING.  ALL ABRASI9ON STRIPS VOID  SCARF JOINT, NR 1 ABRASION STRI	P ERROSION NOSE AND NECK SHELL CRACKED AT FITTING, SKIN AT ROOT AREA CRACKED ROVING FILLER SEPERATED, UPPER SURFACE AT T	RAILING EDGE, DAMPNER VOID, MINOR ERROSION ON TRIM TABS, TEFLON LINING ON BUSHING FRAYED AND MISSING SWEEP OUT OF TOLERA	NCE 9.6MM. ACTION TAKEN:  REPAIRED AS PER FORM 8130-3 BLOCK, 13 .  THIS INFORMATION FOR FAA SDR.			1	G	7	2 	3U			 	H3EU    					 
2001122700004	20011227	00004		2001	12	27	ERAA076667       	4	20011009	G	3450	D120P2T	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	412EH	483  				33001				PART IS CORRODED.  CONNECTOR CORRODED, PIN MISSING, DIRTY INSIDE AND ALSO OUT OF CALIBRATION. ACTION TAKEN:  OVERHAULED,	 REPAIRED LEAKS, TREATED METAL, CALIBRATED AND FUNCTIONALLY TESTED OK TO 20,000 FEET.  COMPLIED WITH AIRWORTHINESS DIREC	TIVES AS PER MFG PUB 7421 REV A JAN. 1993.				1	G	7	2 	4U			 	H4SW    					 
2001122700005	20011227	00005		2001	12	27	ERAA076668       	4	20011009	G	3450	D120P2T	INDICATOR       			SKRSKY	S61   	S61N        	8142104	NE  										COCKPIT	MISMANUFACTURED 	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	561EH	360  				61471				PART MISSING.   FILTER MISSING ON PORT;  TAKEN FROM STOCK.  CONNECTOR PLATE BROKEN, CORROSION ON INSIDE OF BASE AND CASE	, UNIT LEAKS, AND NEEDS ADJUSTMENT. ACTION TAKEN:  REPAIRED, CLEANED CORROSION, REPLACED CONNECTOR PLATE, FIXED LEAKS, A	DJUSTED AND FUNCTRIONALLY TESTED OK TO 20,000 FEET.  C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TSM 7421 REV A JAN 1993	.			2	G	7	2 	4U			 	1H15    					 
2001122700006	20011227	00006		2001	12	27	ERAA076669       	4	20011009	G	3450	D120P2T	INDICATOR       			BOLKMS	105   	BO105A      	       	EU  										COCKPIT	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	291EH					S842				PART IS CORRODED.  CONNECTOR INSERTS PULLED OUT .  CONNECTOR PLATE BROKEN, CORROSION ON CASE INSIDE AND ON BASE, UNIT LE	AKS AND OUT OF ADJUSTMENT. ACTION TAKEN:  REPAIRED, CLEANED CORROSION, REPLACED CONNECTOR PLATE, FIXED LEAKS, AND FUNCTI	ONALLY TESTED OK TO 20,000 FEET.  C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TSM 7421 REV A JAN 1993.				1	G	7	2 	3U			 	H3EU    					 
2001122700007	20011227	00007	SW  	2001	12	27	ERAA076670       	1	20011009	G	5302		STRUCTURE       			BELL  	412   	412         	1182202	SW  										TAILBOOM	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	415EH	6871 			ADW06067	33009				NO. 2 BULKHEAD CRACKED ABOVE ROOF PANEL.  STINGER BULKHEAD UPPER SUPPORT ANGLE CRACKED.  STIFFNER  P/N 212-030-099-028 C	RACKED. ROOF PANEL PN 205-032-815-127 HAS CORROSION & SEPERATED.  VERTICAL FIN SUPPORT BULKHEADS PN 212-030-127-029 AND 	021 CRACKED.  L/H LOWER VERTICAL FIN SKIN CRACKED FWD BULKHEAD PN 212-030-143-009 SEPERATED. ACTION TAKEN:  REPLACED STI	FFNER PN 212-030-99-028.  REPLACED ROOF PANEL & REPLACED FWD BULKHEAD PANEL.  REPLACED BOTH VERTICAL FIN SUPPORT BULKHEA	DS.  FABRICATED L/H LOWER VERTICAL FIN SKIN.  REPAIRED NO 2 BULKHEAD ABOVE ROOF PANEL.  FABRICATED STINGER BULKHEAD SUPP	ORT ANGLE.  C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER ASB 412-90-49 PART II.    THIS INFORMATION FOR FAA SDR.	1	G	7	2 	4U			 	H4SW    					 
2001122700008	20011227	00008	EU  	2001	12	27	ERAA076671       	1	20011009	G	5302		STRUCTURE       			BOLKMS	105   	BO105S      	5626006	EU  										TAIL BOOM	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	127EH					571				TAILBOOM IS  CRACKED.  RT SKIN CRACKED PN 105-30251-56, LT CONTOUR SKIN PN 105-30101-14 CRACKED, SPAR PN 105-30401-16-00	1 CRACKED, 90 DEGREE GEARBOX FITTING PN 105-30402-12 HAS CORROSION, STRINGER PN 105-30251-25 IS CRACKED, STRINGER PN 105	-30251-26  IS CRACKED, FRAME SHEET PN 105-30401-29 IS CRACKED, SPAR PN 105-30412-03 HAS CORROSION. ACTION TAKEN:  FAB R/	H SKIN AND FAB NEW CONTOUR SKIN, REPLACEC TWO STRINGERS AND CHANGED THE FITTING PN 105-30402-12, REPLACED SPAR PN 105-30	401-16-001 AND SPAR PN 105-30412-003 WITH NEW SPECS.  REPLACED FRAME SHEET PN 105-30401-29 WITH NEW.		1	G	7	2 	3U			 	H3EU    					 
2001122700009	20011227	00009	GL  	2001	12	27	ERAA076672       	2	20011009	G	7200	250C20B	ENGINE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	426EH	13405				552				ENGINE IS MAKING METAL.   G.B. SN CAG-36092 PTO GEAR PITTED.  ACTION TAKEN:  INSTALLED SERVICEABLE GEAR BOX.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122700010	20011227	00010	GL  	2001	12	27	ERAA076673       	2	20011009	G	7200	6898735	ENGINE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NACELLE	MALFUNCTIONED   	H			ERAA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			FS	01	426EH	11039				552				TURBINE RUNS HOT, LOW  POWER.   STRETCHED NR 1 BLADES.  ACTION TAKEN:  INSTALLED NEW NR 1 & 2 WHEEL & NR 2 NOZZLE.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122700011	20011227	00011	GL  	2001	12	27	ERAA076674       	2	20011009	G	7200		ENGINE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NACELLE	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	298EH	5449 				S845				ENGINE IS MAKING METAL.   HAS METAL ON MAG PLUGS.  2 1/2 BEARING INNER RFACE HAS METAL.  GROOVES ON SEVERAL ROLLERS. ACT	ION TAKEN:  DISASSEMBL3D ENGINE CAE-836436, TURBINE, COMPRESSOR, GEARBOX. CHANGED 11/2 BEARING SN MR55741, INSTALLED MP7	5985, GEARSHAFT SN 69437 INSTALLED CI21-543. C/W AIRWORTGHINESS DIRECTIVES OR SB'S AS PER CEB-1298.  SEAL ON GEARBOX ASS	Y - PRESSURE OIL FITTINGS.			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001122700012	20011227	00012	SW  	2001	12	27	ERAA076675       	1	20011009	G	3213	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01										FORWARD CROSSTUBE HAS CORROSION.  ACTION TAKEN:  CROSSTUBE IS SCRAPPED.						1	G	7	2 	4U			 	H4SW    					 
2001122700013	20011227	00013	SW  	2001	12	27	ERAA076676       	1	20011011	G	6220	412010145103	DAMPER          			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	SEPARATED       	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168EH	4949 				33067				SEPERATED, UNABLE TO BALANCE MAIN ROTOR.   ACTION TAKEN: RETIRED & SCRAPPED BOTH DAMPER SETS IAW 412 CR&O.						1	G	7	2 	4U			 	H4SW    					 
2001122700014	20011227	00014	SW  	2001	12	27	ERAA076677       	1	20011011	G	6220	412010145103	DAMPER          			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	SEPARATED       	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168EH	225  				33067				SEPERATED, UNABLE TO BALANCE MAIN ROTOR.    ACTION TAKEN:  RETIRED & SCRAPPED BOTN DAMPER SETS IAW 412 CR&O.  THIS INFOR	MATION FOR FAA SDR.					1	G	7	2 	4U			 	H4SW    					 
2001122700015	20011227	00015	SW  	2001	12	27	ERAA076678       	1	20011011	G	6220	412010145103	DAMPER          			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	419EH	5488 				33043				DAMPER SET IS CRACKED.  FOUND SETS WORN & CRACKED ACTION TAKEN:  RETIRED & SCRAPPED IAW 412 CR&O,  THIS INFORMATION FOR 	FAA SDR.					1	G	7	2 	4U			 	H4SW    					 
2001122700016	20011227	00016	SW  	2001	12	27	ERAA076679       	1	20011011	G	6220	412010145103	DAMPER          			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	419EH	6519 				33043				DAMPER SET IS WEAK/ WORN / CRACKED. ACTION TAKEN:  DAMPER SET WAS RETIRED & SCRAPPED IAW 412 CR&O.  THIS INFORMATION FOR	 FAA SDR.					1	G	7	2 	4U			 	H4SW    					 
2001122700017	20011227	00017	SW  	2001	12	27	ERAA076680       	1	20011011	G	6410	212011701003FM	BLADE           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	422EH	4048 				33068				TAIL ROTOR BLADE A-11090 HAS VOID AT TIP, TRUNNION IS ROUGH.  TAIL ROTOR BLADE SENT TO CTI FOR REPAIR.  TRUNNION, TRUNNI	ON HOUSING ASSYS SCRAPPED. ACTION TAKEN:  INST'D NEW TRUNNION, TRUNNION HOUSINGS, BEARINGS, & SEALS, INSTALLED SERVICEAB	LE TAIL ROTOR BLADE.  ASSEMBLED, BALANCED & LUBED T/R ASSY IAW 412 CR& O & T.B. 412-95-134.  C/W AIRWORTHINESS DIRECTIVE	S OR SB'S AS PER TB 412-95-134.  THIS INFORMATION FOR FAA SDR.			1	G	7	2 	4U			 	H4SW    					 
2001122700018	20011227	00018	SW  	2001	12	27	ERAA076681       	1	20011011	G	6320	412040002103	TRANSMISSION    			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	164EH	8992 				33004				TRANSMISSION DUE 3100 HOUR INSPECTION.  LOWER SPIDER BREAKING, UPPER SUN GEAR BREAKING, MAIN INPUT LINER, MAIN CASE HAS 	EXCESSIVE CORROSION DAMAGE, MAIN INPUT QUILL ALIGNMENT MARKS BEARING PINION OFF, RING GEAR OUTER SURFACE RUSTING, MAIN I	NPUT BEARING SLEEVE RUSTED. ACTION TAKEN:  SENT TO ERA REPAIR STATION ALASKA FOR INSPECTION.  THIS INFORMATION FOR FAA S	DR.			1	G	7	2 	4U			 	H4SW    					 
2001122700020	20011227	00020	EU  	2001	12	27	ERAA076682       	1	20011012	G	5302		STRUCTURE       			BOLKMS	105   	BO105A      	       	EU  										TAILBOOM	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	290EH	5756 				S850				TAILBOOM REMOVED FROM AIRCRAFT DUE TO CRACKED SKIN RT SIDE BASE OF VERTICAL FIN.  FOUND RUSTED, CORRODED & PITTED TAIL S	KID BRACKETS.  CORRODED FWD MOUNTING FLANGES.  CORROSION & PITTED SPOTS ON 90 DEGREE GEARBOX FITTING BOLT HOLES. ACTION 	TAKEN:  INSTALLED NEW TAILSKID BRACKETS, FWD & AFT, INSTALLED NEW 90 DEGREE GEARBOX FITTING AND REPLACED FWD MOUNT FLANG	E.  FABRICATED & INSTALLED NEW R/H FWD SKIN, PLUS VALVE MOUNT BRACKETS & DOUBLER AND CLEARED ALL OTHER MAINTENANCE DESCR	EPANCIES IN BLUE WORK FORMS OF WORK ORDER C298015.  THIS INFORMATION IS FOR FAA SDR.		1	G	7	2 	3U			 	H3EU    					 
2002012300049	20020123	00049	SW  	2002	1	23	ERAA076683       	1	20011012	G	3212	412050045107	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	A			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	412EH					33001				AFT CROSSTUBE IS  CORRODED.  ACTION TAKEN:  PART WAS SCRAPPED.						1	G	7	2 	4U			 	H4SW    					 
2002012300050	20020123	00050	SW  	2002	1	23	ERAA076684       	1	20011012	G	5520	205030856113	SKIN            			BELL  	412   	412         	1182202	SW  										RT ELEVATOR	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	167EH					33089				RT ELEVATOR SKIN CRACKED.  FOUND SPAR TO BE UNBONDED AT FLANGE & ROOT RIB TO BE CORRODED BEYOND LIMITS. ACTION TAKEN:  R	E-MANUFACTURER OUTER SKIN,  REPLACED SPAR & ROOT RIBS & REASSEMBLED. C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TB-412-	83-31.  THIS INFORMATION IS FOR FAA SDR.				1	G	7	2 	4U			 	H4SW    					 
2002012300052	20020123	00052	GL  	2002	1	23	ERAA077281       	1	20011022	G	6410	332A12005001	BLADE           			AMTR  	PURE  	PUREAIR     	       	GL  										TAIL ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	170EH	286  				2016				TAIL ROTOR BLADE HAS AN INTERNAL NOISE AND SUSPECT THAT THERE MAY BE SOMETHING LOOSE INSIDE.						1	H	7	1 	3O			 	EXPA1H71					 
2002012300055	20020123	00055	EU  	2002	1	23	ERAA077284       	1	20011029	G	6410		PAINT           			BOLKMS	105   	BO105S      	5626006	EU  										T/R BLADE	CRACKED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	293EH	1540 			587588	559				TAIL ROTOR BLADE PAINT IS CRACKED AND VOIDED ON END CAP.						1	G	7	2 	3U			 	H3EU    					 
2002012300058	20020123	00058	NE  	2002	1	23	ERAA077285       	1	20011031	G	5320		BUSHING         			SKRSKY	S61   	S61N        	8142104	NE  										BATTERY ABSORBER	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	563EH					61808				BUSHINGS WORN.						2	G	7	2 	4U			 	1H15    					 
2002012300062	20020123	00062	EU  	2002	1	23	ERAA077292       	1	20011115	G	6520	4619311033	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  										T/R XMSN	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	133EH					598				BEARING ROLLER FALLS OUT OF CAGE.						1	G	7	2 	3U			 	H3EU    					 
2002012300074	20020123	00074	NE  	2002	1	23	ERAA077293       	2	20011115	G	7311		STRUCTURE       			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COOLER BLOWER	CORRODED        	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	417EH	8358 			5100712	33031				VANE GUIDE ASSY HAS PITTING & CORROSION.  COATING ASSY HAS MECHANICAL DAMAGE ON OUTER LIP.  SLIGHT CORROSION ON LOCK PLA	TE. SPACER FAILED DUE TO MECHANICAL DAMAGE.  IMPELLAR HAS CRACKED BLADES. ACTION TAKEN:  DISASSEMBLED & STRIPPED PAINT. 	 COMPLIED WITH VISUAL & NDT INSPECTIONS.  REMOVED & TREATED SLIGHT CORROSION.  HAD VARIOUS PARTS PAINTED.  REASSEMBLED &	 OVERHAULED USING NEW COATING ASSY., IMPELLAR, GUIDE VANE ASSY, NEW BEARINGS, PACKING, GASKET, AND HARDWARE AND NEW DECA	L IAW 412 CR&O CHAPTER 79 & BHT-ALL-SPM.		1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2002012300075	20020123	00075	GL  	2002	1	23	ERAA077294       	2	20011116	G	7200	250C20B	ENGINE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENG BAY	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	294EH	6308 				S675				ENGINE IS MAKING METAL, BOTH PLUGS.  FC-OP GEARSHAFT DAMAGED PN 6896437 ACTION TAKEN:  INSTALLED NEW GEARSHAFT & COMPLIE	D WITH CEB-A-1386 TQ METER GEAR INSPECTION .					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2002012300076	20020123	00076	EU  	2002	1	23	ERAA077295       	1	20011116	G	2435		GEARSHAFT       			BOLKMS	105   	BO105S      	5626006	EU  										STARTER GEN	WORN            	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	124EH	4928 				S559				ENGINE IS  MAKING METAL.  .  STARTER GENERATOR GEARSHAFT IS WORN. ACTION TAKEN:  INSTALLED NEW GEARSHAFT AND BEARINGS.  	COMPLIED WITH CEB A-1374 PRESSURE PROBE INSPECTION.					1	G	7	2 	3U			 	H3EU    					 
2002012300079	20020123	00079	SW  	2002	1	23	ERAA077296       	1	20011116	G	6320	412040002103	BEARING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	MAKING METAL    	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	418EH	7849 								TRANSMISSION IS  MAKING METAL. TAILROTOR QUILL BEARINGS CAUSE OF METAL CONTAMINATION.  SEAL LEAKS.  MAIN INPUT R/B QUILL	, SYS II HYD QUILL AND AUX JETS ON RING GEAR CASE. ACTION TAKEN:  REPAIRED, PARTIALLY DISASSEMBLED, VISUALLY INSPECTED E	XPOSED COMP. INSTALLED NEW BEARINGS T/R QUILL AND PACKED WITH GEAR, INSTALLED NEW SEALS, AND GASKET, O RINGS TO REPAIR L	EAKS.  ALL WORK IAW BHT 412 CR&O.			1	G	7	2 	4U			 	H4SW    					 
2002012300084	20020123	00084	SW  	2002	1	23	ERAA077297       	1	20011116	G	6210		SKIN            			BELL  	412   	412         	1182202	SW  										M/R BLADE	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168EH	8848 				33067				REMOVED FOR FLIGHT CHARACTERISTICS BLADE HAS CREASES UPPER AND LOWER, PAINT WORK NEEDED.  L/S HAS SKIN DAMAGE WITH VOID 	AT STA 192-194, T/B AND CTR TRIM TABS HAVE SKIN DAMAGE WITH VOIDS, WATER FOUND IN CORE DURING BOND PREP FOR PATCHES, UPP	ER SURFACE SKIN DAMAGE AT STA 226- 258 ESTENE DETERIORATED, REFLEX DOUBLER DEBONDED.				1	G	7	2 	4U			 	H4SW    					 
2002012300086	20020123	00086	EU  	2002	1	23	ERAA077298       	1	20011116	G	6410		BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	293EH	11985				559				END CAP OF ONE BLADE HAS A SPLIT IN THE PAINT.  PITCH MOVEMENT FEELS ROUGH.  BLADES DAMAGED, BUSHINGS (TEFLON) DIRTY, SE	ALS WARPED. ACTION TAKEN:  REM'D BLADES AND SENT OUT FOR REPAIR.  DISASSEMBLED TO FACILLITATE TEFLON BEARING CLEANING . 	CLEANED BEARING SURFACES AND REASSEMBLED HUB WITH NEW SEALS & NUTS.  INSTALLED SERVICEABLE BLADES AND STATIC BALANCED TA	ILROTOR ASSY. REPAIRED IAW BO105 REM M/M CHAPTER 34 & 33 AND MARVEL BOOK.			1	G	7	2 	3U			 	H3EU    					 
2002012300090	20020123	00090	GL  	2002	1	23	ERAA077515       	2	20011204	G	7230		PLUG            			BOLKMS	105   	BO105A      	       	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DISLODGED       	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	423EH	6244 				543				ENGINE IS MAKING METAL.  RESI-WELD  FE 186 SEALANT PLUG DISLODGED FROM COMPRESSOR MOUNT.  SEALANT PLUG LODGED IN OIL PUM	P SCAVENGE PORT. THIS DID NOT LET THE OIL SCAVENGE, THUS LETTING THE BEARINGS STARVE FOR OIL CAUSING IT TO MAKE METAL. A	CTION TAKEN:  DISASSEMBLED ENGINE.  GEARBOX AND TURBINE WILL NEED OVERHAUL AND COMPLETE INSPECTION OF COMPRESSOR.  GEARB	OX SN CAG-37622 TT 12330.8  TSO 4694.6  (LAST O/H 3-5-91)			1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001050200063	20010502	00063	NM  	2001	5	2	ERKR200100067    	1	20010326	G	5330		SKIN            			DOUG  	MD88  	MD88        	3023688	NM  										FUSELAGE	DAMAGED         	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12FQ					49766				REPAIRED SKIN PANEL, STATION 560, STRINGER 24R-25R RIGHT.						2	L	7	2 	4F			RT	A6WE    					 
2001050200064	20010502	00064	NM  	2001	5	2	ERKR20010068     	1	20010326	G	5512	5922577506	SKIN            			DOUG  	MD88  	MD88        	3023688	NM  										HORIZONTAL STAB	CORRODED        	B			ERKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	12FQ					49766				RIGHT HORIZONTAL STABILIZER, BARREL NUT HOLES XHS 27.234. THIS DOCUMENT PROVIDES REPAIR INSTRUCTIONS FOR CORROSION FOUND	 IN THE THREE BARREL NUT HOLE BORES OF THE RIGHT HORIZONTAL STABILIZER LOWER FORWARD AND LOWER CENTER SKIN PANELS. PART 	NUMBERS 5922576504 AND 5922577506.PER ECRA N12FQ55MD88002EAC.				2	L	7	2 	4F			RT	A6WE    					 
2001121100030	20011211	00030	SO  	2001	12	11	ERY2001F00000    	2	20011115	G	8520		CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      	 	SO  					ENGINE	CRACKED         	F				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	384P	399  				TH1888	684243			ENGINE OIL LEAK, FOUND 3 INCH LONG CRACK IN CRANKCASE ABOVE NR 3 CYLINDER, CRACK SEEMS TO ORIGINATE FROM UPPER CASE LEFT	 AND EXTEND DOWNWARD.					1	L	7	2 	3O	3	O	 	3A16    	E3SO				 
2001080300081	20010803	00081	CE  	2001	8	3	ERYR682D2001     	1	20010511	G	3242	50300010121	LINER           			BEECH 	90    	E90         	1152914	CE  										LT MLG BRAKE	BROKEN          	B				E	D			ENGINE SHUTDOWN         	RETURN TO BLOCK         			L			NO TEST                   			TX	TAXI/GRND HDL  	1			SO	11	22TL					LW334				OVERHAULED BRAKE ASSEMBLY WAS INSTALLED AND FUNCTIONALLY TESTED BY MAINTENANCE PERSONNEL WITH NO NOTED DEFECTS. DURING T	AKEOFF ROLL PILOT NOTICED AIRCRAFT SEEM TO PULL TO ONE SIDE, PILOT ABORTED TAKEOFF AND RETURNED TO CHOCKS. MAINTENANCE P	ERSONNEL VISUALLY EXAMINED BRAKES AND FOUND NO OBVIOUS DEFECTS. MAINTENANCE AND OPERATOR DECIDED TO PERFORM HIGH SPEED T	AXI TO FURTHER TROUBLESHOOT BRAKING SYSTEM. DURING TAXI CHECK LT BRAKE FAILED AND BECAME COMPLETELY INEFFECTIVE. OPERATO	R SHUT DOWN ENGINES AND AIRCRAFT WAS TOWED BACK TO MAINTENANCE FOR EVALUATION. MAINTENANCE EVALUATION DISCOVERED APPROXI	MATE THREE INCH SECTION OF BRAKE LINING ASSEMBLY HAD BROKEN LOOSE AND ALLOWED LINING TO ROTATE OUT OF KEYWAY SLOTS.	1	L	7	2 	3T			 	3A20    					 
2001082900261	20010829	00261	SO  	2001	8	29	GAC081601        	1	20010816	G	2432	1159SCAV5201	CHARGER         			GULSTM	G1159 	GIV         	3980115	SO  										TAIL	FAILED          	B				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SO	11	426QS	359  				1426				DURING NORMAL MAINTENANCE WHILE ON THE GROUND THE BATTERY CHARGER BEGAN TO SMOKE AND THE CIRCUIT BREAKER POPPED.  REMOVE	D AND REPLACED BATTERY CHARGER WITH REPAIRED UNIT.					2	L	7	2 	4F			RT	A12EA   					 
2001080300083	20010803	00083	SW  	2001	8	3	GDMA073295       	1	20010612	G	7910	H33C32	BEARING         		204062540001	BELL  	205   	205A1       	1181414	SW  										ENGINE	ROUGH           	H			GDMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	97HJ	398  			1771292	30173				MEDIUM FREQ VIBRATION IN THE AIRFRAME. REPLACED BEARINGS IN THE FAN						1	G	7	1 	4U			 	H1SW    					 
2001042400307	20010424	00307	CE  	2001	4	24	GLBA2001085      	1	20010419	G	2720		CONTROL UNIT    			BEECH 	1900  	1900D       	1154162	CE  										RUDDER	MALFUNCTIONED   	A			GLBA	A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CE	01	257GL					UE257				UNCOMMANDED RUDDERR BOOST IN FLIGHT, PENDING CORRECTIVE ACTION						2	L	7	2 	4T			RT	A24CE   					 
2001051500132	20010515	00132	CE  	2001	5	15	GLBA2001094      	1	20010506	G	5270		HANDLE          			BEECH 	1900  	1900D       	1154162	CE  										PAX DOOR	MALFUNCTIONED   	A			GLBA	D				RETURN TO BLOCK         				N			FALSE WARNING             			CL	CLIMB          	1			CE	01	257GL					UE257				CABIN DOOR ANNUNCIATOR ILLUMINATED ON CLIMB-OUT, INSPECTED RESET CABIN DOOR HANDLE OPS CHECKED GOOD						2	L	7	2 	4T			RT	A24CE   					 
2001071700050	20010717	00050	CE  	2001	7	17	GLBA2001104      	1	20010521	G	2130	13037432	CONTROLLER      			BEECH 	1900  	1900D       	1154162	CE  										ONLY	INOPERATIVE     	A			GLBA	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	01	257GL	138  				UE257				CABIN PRESSURIZATION NOT HOLDING, REPLACED CONTROLLER						2	L	7	2 	4T			RT	A24CE   					 
2001080300084	20010803	00084	CE  	2001	8	3	GLBA2001105      	1	20010522	G	2840	12281301	METER           			BEECH 	1900  	1900D       	1154162	CE  										FUEL FLOW	FAILED          	A			GLBA	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CE	01	257GL	423  				UE257				LEFT AND RIGHT FUEL FLOW GAUGES FLUCTUATED WHEN POWER ADVANCED, REPLACED FLOW METER						2	L	7	2 	4T			RT	A24CE   					 
2001080300085	20010803	00085		2001	8	3	GLBA2001111      	4	20010527	G	3443	6227337001	RADAR           			EMB   	120   	EMB120      	3260201	SO  										WX RADAR	INOPERATIVE     	A			GLBA	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CE	01	92GL	6786 	15   			120092				WEATHER RADAR FAILED, INSPECTED FOUND RT UNIT BAD REPLACED OPS CHECKED SYSTEM SATISFACTORY						2	L	7	2 	4T			RT	A31SO   					 
2001041700100	20010417	00100	NE  	2001	4	17	H1IR069Y01       	2	20010305	G	7230	3029051	VANE            			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114A    	52043	NE  					COMPRESSOR	CRACKED         	B			H1IR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	28AN	2221 				208B0751	PCEPC0677			COMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT 	OF SEVEN.  11 LUGS SEPARATED AND 1 EA CRACKED FROM A TOTAL OF 14.  EXPERIENCE INDICATES NORMAL AS REMOVED VANE RINGS WIT	H THIS TOTAL TIME SHOULD HAVE NO DEFECTS IN THIS AREA.				1	H	7	1 	3T	3	T	 	A37CE   	E4EA				 
2001041700101	20010417	00101	EA  	2001	4	17	H1IR069Y02       	2	20010305	G	7230	3032151	VANE            								PWA   	PT6   	PT6A34      	52043	EA  					COMPRESSOR	CRACKED         	B			H1IR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01							9D149			COMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT 	OF SEVEN.  9 OF 14 LUGS FOUND SEPARATED.										4	T			E4EA				 
2001091000313	20010910	00313	EU  	2001	9	10	HCMA075341       	1	20010117	G	6420	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	997BH	837  				2666				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000318	20010910	00318	EU  	2001	9	10	HCMA075358       	1	20010124	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	PEELING         	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	35   				2889				WHITE PAINT IS PEELING OFF BLADE AND IS EXTREMELY HARD TO BALANCE. PLEASE REPAIR UNDER FULL WARRANTY.						1	G	7	1 	3U			 	H9EU    					 
2001091000321	20010910	00321	EU  	2001	9	10	HCMA075365       	1	20010522	G	6420	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	805  				2889				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000323	20010910	00323	EU  	2001	9	10	HCMA075367       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350BA     	8680817	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	642BH	606  				2495				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			NC	H9EU    					 
2001091000324	20010910	00324	EU  	2001	9	10	HCMA075368       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350BA     	8680817	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	862BH	159  				2713				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			NC	H9EU    					 
2001091000325	20010910	00325	EU  	2001	9	10	HCMA075369       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	982BH	934  				2876				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000327	20010910	00327	EU  	2001	9	10	HCMA075370       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	474  				2889				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000328	20010910	00328	EU  	2001	9	10	HCMA075371       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	184  				2889				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000329	20010910	00329	EU  	2001	9	10	HCMA075372       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	599  				2889				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091000331	20010910	00331	EU  	2001	9	10	HCMA075373       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	193BH	643  				2894				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100001	20010911	00001	EU  	2001	9	11	HCMA075374       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	194BH	499  				2903				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100002	20010911	00002	EU  	2001	9	11	HCMA075375       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	194BH	258  				2903				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100003	20010911	00003	EU  	2001	9	11	HCMA075376       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	194BH	170  				2903				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100004	20010911	00004	EU  	2001	9	11	HCMA075377       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	995BH	245  				2987				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100005	20010911	00005	EU  	2001	9	11	HCMA075378       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH	932  				3036				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100006	20010911	00006	EU  	2001	9	11	HCMA075379       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	197BH	751  				2666				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100007	20010911	00007	EU  	2001	9	11	HCMA075380       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	198BH	900  				3126				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100008	20010911	00008	EU  	2001	9	11	HCMA075381       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	198BH	89   				3126				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100009	20010911	00009	EU  	2001	9	11	HCMA075382       	1	20010706	G	6420	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	198BH	546  				3126				PART IS WORN BEYOND LIMITS.						1	G	7	1 	3U			 	H9EU    					 
2001091100010	20010911	00010	EU  	2001	9	11	HCMA075388       	1	20010814	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	874  				2889				TAIL ROTOR BLADE CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2001091100011	20010911	00011	EU  	2001	9	11	HCMA075391       	1	20010821	G	5302	350A2300000201	TAIL BOOM       			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL	MISMANUFACTURED 	E			HCMA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	13	642BH	15023				2495				TAILBOOM SKIN NOT PROPER THICKNESS.						1	G	7	1 	3U			NC	H9EU    					 
2001041900237	20010419	00237	NE  	2001	4	19	HEEA071922       	1	20010403	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X	12811				760050				TRAILING EDGE OF PADDLE A IS SPLIT OPEN.  THE CENTER PLUG IS ALSO DEBONDED. SENT TO INTERNATIONAL AVIATION COMPOSITES FO	R INSPECTION AND REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001041900238	20010419	00238	NE  	2001	4	19	HEEA071923       	1	20010405	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR BLADE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				TOP SKIN HAS A CRACK SPANWISE APPROXIMATELY 2 INCHES FROM TRAILING EDGE.  THE ABRASION STRIP HAS A CRACK WITH SEPARATION	. SENT TO COMPOSITE TECHNICS FOR INSPECTION AND REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001041900239	20010419	00239	NE  	2001	4	19	HEEA071924       	1	20010405	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR BLADE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911UK					760275				TOP INNER AND OUTER DOUBLER SEPARATED BEYOND LIMITS.  ABRASION STRIP HAS CRACKS ON BOTH SIDES. SENT TO COMPOSITE TECHNIC	S FOR INSPECTION AND REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001041900240	20010419	00240		2001	4	19	HEEA071925       	4	20010405	G	2340	A3016W	CONTROL PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										INTERPHONE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	761PH					760224				NEEDS EVALUATION. PERFORMED PRELIMINARY INSPECTION AND TESTED.  FOUND SWITCHES S1, S4, S5, S8, LIGHT PANEL, VOLUME KNOB 	AND TRANSMIT KNOB BAD.  ALSO LIGHT PANEL LIGHTS BAD FROM STOCK.  REPLACED ALL AND RESOLDERED BAD SOLDER CONNECTION ON LI	GHT PANEL.  REPAIRED.  BENCH CHECK GOOD.				1	G	7	2 	3U			 	H1NE    					 
2001041900241	20010419	00241	SW  	2001	4	19	HEEA071926       	1	20010402	G	5302	214021211110S	PANEL           			BELL  	214   	214ST       	1182106	SW  										TAILBOOM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										PANEL RECEIVED PREVIOUSLY TRIMMED ALONG FORWARD END.  CANNOT POSITION ON TAILBOOM TO ACHIEVE PROPER EDGE DISTANCE ON ALL	 FASTENERS.  PANEL NEEDS TO BE MOVED FORWARD AND CORE TRANSITION IS ALREADY CONTACTING STRAP AT BOOM STATION 293.50.  PA	NEL IS SHORTER THAN THE PANEL REMOVED FROM THE TAILBOOM SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.				2	G	7	2 	4U			 	H10SW   					 
2001041900242	20010419	00242	SW  	2001	4	19	HEEA071927       	1	20010402	G	6330	206033505101	NODAL ARM       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ARM IS NOT MACHINED OUT AT INBOARD RADIUS.						1	G	7	1 	3U			 	H2SW    					 
2001041900243	20010419	00243	SW  	2001	4	19	HEEA071928       	1	20010402	G	5302	206033412001A	BRACKET         			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BRACKET HAS PILOT HOLES FROM FACTORY DRILLED OPPOSITE OF REQUIRED LAYOUT.						1	G	7	1 	3U			 	H2SW    					 
2001041900244	20010419	00244	SW  	2001	4	19	HEEA071929       	1	20010403	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL LOW LEVEL LIGHT COMES ON INTERMITTENTLY.						1	G	7	2 	4U			 	H4SW    					 
2001041900245	20010419	00245	SW  	2001	4	19	HEEA071930       	1	20010403	G	2612	30236ET1	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										FIRE DETECTOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SW	03	5759N					33002				WHILE IN CRUISE FLIGHT THE BAGGAGE COMPARTMENT FIRE LIGHT ILLUMINATED. NO FIRE OBSERVED.  MAINTENANCE REPAIRED CHAFED WI	RE AT AMPLIFIER CONTROL CONNECTOR.					1	G	7	2 	4U			 	H4SW    					 
2001041900246	20010419	00246	SW  	2001	4	19	HEEA071931       	1	20010403	G	7600		CONTROL UNIT    			BELL  	214   	214ST       	1182106	SW  										NR 2 ENGINE	MALFUNCTIONED   	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	3897N					28106				IN CRUISE FLIGHT, NR 2 ENGINE DROPPED OFF LINE THEN RECOVERED BACK TO 100 PERCENT. PLACED NR 2 ENGINE IN ECU LOCKOUT AND	 RETURNED TO BASE.					2	G	7	2 	4U			 	H10SW   					 
2001041900247	20010419	00247	SW  	2001	4	19	HEEA071932       	1	20010403	G	2435		BRUSHES         			BELL  	407   	407         	       	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	2544 				53399				BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2001041900248	20010419	00248	SW  	2001	4	19	HEEA071933       	1	20010403	G	2435		BRUSHES         			BELL  	407   	407         	       	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	1337 				53378				BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2001041900249	20010419	00249	SW  	2001	4	19	HEEA071934       	1	20010403	G	2822	1C641	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL BOOST	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				TRANSFER LIGHT COMING ON ABOVE 1700 LBS.  REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900250	20010419	00250	SW  	2001	4	19	HEEA071935       	1	20010403	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900251	20010419	00251	SW  	2001	4	19	HEEA071936       	1	20010403	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900252	20010419	00252	SW  	2001	4	19	HEEA071937       	1	20010403	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900253	20010419	00253	SW  	2001	4	19	HEEA071938       	1	20010403	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900254	20010419	00254	SW  	2001	4	19	HEEA071939       	1	20010403	G	3340	7028521	STROBE          			BELL  	412   	412         	1182202	SW  										EXTERIOR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				NO OUTPUT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900255	20010419	00255	SW  	2001	4	19	HEEA071940       	1	20010403	G	3340	G62504	LIGHT           			BELL  	412   	412         	1182202	SW  										EXETERIOR SEARCH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				SEARCH LIGHT WILL NOT POINT FORWARD. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900256	20010419	00256		2001	4	19	HEEA071941       	4	20010403	G	3416	5934D3	ALTIMETER       			BELL  	407   	407         	       	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				ALTIMETER IS 120 FEET OFF.						1	G	7	1 	3U			O	H2SW    					 
2001041900257	20010419	00257	SW  	2001	4	19	HEEA071942       	1	20010403	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251Y	1340 				51556				TRAILING SKIN AND SPAR HAS EXCESSIVE CORROSION NEAR THE TIP ON THE LOWER SIDE.						1	G	7	1 	3U			 	H2SW    					 
2001041900258	20010419	00258	SW  	2001	4	19	HEEA071943       	1	20010403	G	2435	23081018	STARTER GEN     			BELL  	206   	206L3       	1182108	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	4835					51131				SMOKE AND SPARKS FROM AREA OF TERMINAL BLOCK WHEN MOTORING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900259	20010419	00259	SW  	2001	4	19	HEEA071944       	1	20010403	G	8011	SM20ACD200A21	RELAY           			BELL  	206   	206L3       	1182108	SW  										STARTER	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8592X					51508				STUCK IN ENERGIZED POSITION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900260	20010419	00260	GL  	2001	4	19	HEEA071945       	2	20010403	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C	2612 				51425				HIGH TOT. OVERHAULED AND REPLACED DIAPHRAGMS P/N 6899114.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001041900261	20010419	00261	GL  	2001	4	19	HEEA071946       	2	20010403	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	49EA	2131 				51507				ENGINE RUNS HOT. OVERHAULED AND REPLACED DIAPHRAGMS P/N 6899114.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001041900262	20010419	00262		2001	4	19	HEEA071947       	4	20010403	G	3416	1003511326	ALTIMETER       			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5009N					30936				ALTIMETER WILL NOT ZERO OUT.						1	G	7	1 	4U			 	H4SW    					 
2001041900263	20010419	00263		2001	4	19	HEEA071948       	4	20010403	G	3416	212070238003	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ALTIMETER ADJUSTMENT KNOB DOES NOT TURN.						1	G	7	2 	4U			 	H4SW    					 
2001041900264	20010419	00264		2001	4	19	HEEA071949       	4	20010403	G	3416	212070238007	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				WHEN BARO KNOB ON ALTIMETER IS TURNED, NEEDLE MOVES INTERMITTENTLY.						1	G	7	2 	4U			 	H4SW    					 
2001041900265	20010419	00265	SW  	2001	4	19	HEEA071950       	1	20010403	G	2432	30126001	BATTERY         			BELL  	412   	412         	1182202	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				BATTERY WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	2 	4U			 	H4SW    					 
2001042000086	20010420	00086	SW  	2001	4	20	HEEA071951       	1	20010403	G	2432	30703001	BATTERY         			BELL  	412   	412         	1182202	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			SW	03	107X					33113				LOST ALL POWER AND WOULD NOT CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	2 	4U			 	H4SW    					 
2001041900266	20010419	00266	SW  	2001	4	19	HEEA071952       	1	20010403	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3178K					45765				BOOST PUMP CARTRIDGE INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001041900267	20010419	00267	SW  	2001	4	19	HEEA071953       	1	20010403	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										BOOST PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3905B					45598				LEFT HAND FUEL BOOST PUMP CARTRIDGE FAILED.						1	G	7	1 	3U			 	H2SW    					 
2001041900268	20010419	00268	SW  	2001	4	19	HEEA071954       	1	20010403	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L3       	1182108	SW  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				BOOST PUMP CARTRIDGE INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001041900269	20010419	00269	SW  	2001	4	19	HEEA071955       	1	20010403	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5019F					45244				BATTERY IS TOO WEAK TO REACH PROPER N1 FOR START. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001041900270	20010419	00270	SW  	2001	4	19	HEEA071956       	1	20010403	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				BATTERY WEAK DURING STARTS. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001041900271	20010419	00271	SW  	2001	4	19	HEEA071957       	1	20010403	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3178K					45765				BATTERY DEAD AND WILL NOT HOLD CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001041900272	20010419	00272	SW  	2001	4	19	HEEA071958       	1	20010403	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5745S					45491				WEAK STARTING CAPACITY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001041900273	20010419	00273	SW  	2001	4	19	HEEA071959       	1	20010403	G	3300	A413AHDACF1428	POWER SUPPLY    			BELL  	206   	206L1       	1182107	SW  										LIGHTING	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	45RP					45521				POWER SUPPLY HAS NO POWER OUTPUT.						1	G	7	1 	3U			 	H2SW    					 
2001041900274	20010419	00274	SW  	2001	4	19	HEEA071960       	1	20010403	G	3340	A490A	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6160Y					51609				INOPERATIVE - NO FLASH ON STROBE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900275	20010419	00275	SW  	2001	4	19	HEEA071961       	1	20010403	G	3340	A490A	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6251X					51552				NO POWER TO LIGHT BULB. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900276	20010419	00276	SW  	2001	4	19	HEEA071962       	1	20010403	G	2432	RG222	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5014Y					45219				BATTERY TOO WEAK TO START AIRCRAFT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900277	20010419	00277	SW  	2001	4	19	HEEA071963       	1	20010403	G	2432	A1077	RELAY           			BELL  	206   	206L3       	1182108	SW  										BATTERY	OVERHEATED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4180F									BATTERY RELAY STARTED SMOKING AFTER GENERATOR WAS PLACED ON LINE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001041900278	20010419	00278	SW  	2001	4	19	HEEA071964       	1	20010403	G	2430	A1077V	CONTACTOR       			BELL  	206   	206L4       	1182110	SW  										DC GENERATOR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7074W					52033				CONTACTOR STUCK CLOSED.						1	G	7	1 	3U			NC	H2SW    					 
2001041900279	20010419	00279	SW  	2001	4	19	HEEA071965       	1	20010403	G	2435	SM20ACD200A21	RELAY           			BELL  	206   	206L4       	1182110	SW  										STARTER GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				WHEN PILOT ENGAGED STARTER DURING ENGINE RINSE THE STARTER WOULD NOT COME OFF LINE UNTIL BATTERY SWITCH WAS TURNED OFF. 	 FOUND STARTER RELAY WAS STUCK CLOSED. SENT TO PRECISION AVIONICS & INSTR. INC. FOR INSPECTION AND REPAIR.					1	G	7	1 	3U			NC	H2SW    					 
2001041900280	20010419	00280	SW  	2001	4	19	HEEA071966       	1	20010403	G	3260	XA7503DC	SQUAT SWITCH    			BELL  	206   	206L3       	1182108	SW  										MLG	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	42EA					51542				STUCK OPEN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001041900281	20010419	00281	NE  	2001	4	19	HEEA071967       	2	20010403	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 ENGINE	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				COMBINING GEARBOXMAKING METAL NR 1 SIDE.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001041900282	20010419	00282	SW  	2001	4	19	HEEA071968       	1	20010405	G	2432	30703001	BATTERY         			BELL  	412   	412         	1182202	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				VOLTAGE WAS AT 24 VOLTS AND THEN DROPPED TO 20 WITH ONLY THE BATTERY SWITCHES ON. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	2 	4U			 	H4SW    					 
2001041900283	20010419	00283	SW  	2001	4	19	HEEA071969       	1	20010405	G	6730	C42641100	SERVO VALVE     		206076031109	BELL  	206   	206L3       	1182108	SW  										ACTUATOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03					RH0366					SERVO VALVE IS CAUSING EXCESSIVE INTERNAL LEAKAGE IN NEUTRAL POSITION. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRA	NTY REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001041900284	20010419	00284	SW  	2001	4	19	HEEA071970       	1	20010405	G	2432	RG222	BATTERY         			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5007Q					45187				UNABLE TO START AIRCRAFT ON FIRST START ATTEMPT AND WAS WEAK ON THE SECOND START ATTEMPT. REPLACED WITH SERVICEABLE BATT	ERY.					1	G	7	1 	3U			 	H2SW    					 
2001041900285	20010419	00285	SW  	2001	4	19	HEEA071971       	1	20010405	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3897N					28106				WEAK. FOUND DEEP GASH ON LOWER BATTERY CASE.						2	G	7	2 	4U			 	H10SW   					 
2001041900286	20010419	00286	SW  	2001	4	19	HEEA071972       	1	20010405	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N					28106				WILL NOT START AIRCRAFT. REPLACED WITH SERVICEABLE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001041900287	20010419	00287	SW  	2001	4	19	HEEA071973       	1	20010405	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N					28106				WILL NOT GO IN A SERIES, WEAK. REPLACED WITH SERVICEABLE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001041900288	20010419	00288		2001	4	19	HEEA071974       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				WILL NOT RECEIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.  FOUND FREQUENCY SELECTOR I	NTERMITTENTLY SWITCHING TO MEMORY PRESETS WHEN ADJUSTING FREQUENCY.  CLEANED SW102 SWITCH AND SELECTOR CONTACTS.  REPAIR	ED.  ADJUSTED SQUELCH AND MIC GAIN.  BENCH CHECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001041900289	20010419	00289		2001	4	19	HEEA071975       	4	20010405	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				SQUELCH IS STICKING. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.  REMOVED CORROSION FROM 	UNIT.  REPLACED BROKEN L505 COIL.  ADJUSTED C/N SQUELCH, FREQUENCY, MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900290	20010419	00290		2001	4	19	HEEA071976       	4	20010405	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				TRANSMITS UNREADABLE. PERFORMED PRELIMINARY INSPECTION AND TESTED.  FOUND MODULATION VERY WEAK.  ADJUSTED MIC GAIN, TRAN	SMIT POWER, AND SIDETONE.  FOUND MODULATION WOULD BECOME DISTORTED AFTER KEYED UP A FEW TIMES.  REPLACED Q109 AND Q110 M	ODULATORS.  REPAIRED.  REMOVED CORROSION FROM CHASSIS.  BENCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001041900291	20010419	00291		2001	4	19	HEEA071977       	4	20010405	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	UNRELIABLE      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				TRANSMITS UNREADABLE. PERFORMED PRELIMINARY INSPECTION AND TESTED.  ALIGNED TRANSMITTER.  REPAIRED PROBLEM.  BENCH CHECK	 GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900293	20010419	00293		2001	4	19	HEEA071979       	4	20010405	G	3451	066106902	DISPLAY         			BELL  	412   	412         	1182202	SW  										DME/TACAN UNIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				DME DISPLAY TOO DIM. PERFORMED PRELIMINARY INSPECTION.  FOUND PHOTOCELL V901 HAD BROKEN LEG.  REPAIRED LEG.  REPAIRED UN	IT.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900294	20010419	00294		2001	4	19	HEEA071980       	4	20010405	G	3452	066104100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										ATC	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				NO TRANSMIT OR RECEIVE. PERFORMED PRELIMINARY INSPECTION, TESTED UNIT, FOUND WOULD NOT POWER UP.  FUSE BAD.  ALSO TROUBL	ESHOT UNIT DUE TO FUSE SHORTED AND FOUND TRANSISTOR Q101 BAD.  INSTALLED FUSE AND TRANSISTOR Q101.  TESTED UNIT AND FOUN	D SHIELD IN POWER SUPPLY SHORTED. ALIGNED UNIT.  BENCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001041900295	20010419	00295		2001	4	19	HEEA071981       	4	20010405	G	3457	13824120234	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6251Y					51556				CONSTANTLY CYCLES. PERFORMED PRELIMINARY INSPECTION.  FOUND WPT BUTTON CYCLES THROUGH SEVERAL PAGES WHEN PRESSED.  ALSO 	FOUND MSG, APT/VOR AND NAV BUTTONS INTERMITTENT.  SELECTOR SWITCH ALSO INTERMITTENT.  REPLACED 4 EACH SWITCHES FOR BUTTO	NS AND SELECTOR SWITCH. REPAIRED PROBLEM.  REPLACED WORN KEY CAPS.  BENCH CHECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001041900296	20010419	00296		2001	4	19	HEEA071982       	4	20010405	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				TURN NEEDLE ON ATTITUDE INDICATOR INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001041900297	20010419	00297	SW  	2001	4	19	HEEA071983       	1	20010405	G	2844	124044	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										FUEL PRESSURE INDICATOR NEEDLE STAYS ON ZERO.						1	G	7	2 	4U			 	H4SW    					 
2001041900298	20010419	00298	SW  	2001	4	19	HEEA071984       	1	20010405	G	2844	124044	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				FUEL PRESSURE INDICATOR FLUCTUATES 8 TO 10 PSI.						1	G	7	2 	4U			 	H4SW    					 
2001041900299	20010419	00299	SW  	2001	4	19	HEEA071985       	1	20010405	G	2800	20038000001	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				FUEL LOW LIGHT COMES ON AFTER REFUELING. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001041900300	20010419	00300	SW  	2001	4	19	HEEA071986       	1	20010405	G	3040	204070907102	MOTOR           			BELL  	412   	412         	1182202	SW  										WINDSHIELD WIPER	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				MOTOR IS LOOSE ON COVERTER.						1	G	7	2 	4U			 	H4SW    					 
2001041900301	20010419	00301	SW  	2001	4	19	HEEA071987       	1	20010405	G	7810	212061202010	EXHAUST STACK   			BELL  	412   	412         	1182202	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				EXHAUST STACK IS CRACKED AT SEAMS OF DUCT HALVES.  THE CRACKED AREA EXCEEDS THE LIMITS.						1	G	7	2 	4U			 	H4SW    					 
2001041900302	20010419	00302	SW  	2001	4	19	HEEA071988       	1	20010405	G	2910	212076006007	VALVE           			BELL  	412   	412         	1182202	SW  										NR 2 HYD SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				NR 2 HYDRAULIC SYSTEM VALVE WILL NOT SHUT OFF.						1	G	7	2 	4U			 	H4SW    					 
2001041900303	20010419	00303	SW  	2001	4	19	HEEA071989       	1	20010405	G	2820	212076015001	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				FUEL VALVE LEAKING THROUGH WEEP HOLE. SENT TO BELL HELICOPTER TEXTRON FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001041900304	20010419	00304		2001	4	19	HEEA071990       	4	20010405	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										TURN RATE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				RATE OF TURN NEEDLE TRAVELS FULL LEFT AND RIGHT IN HOVER.						1	G	7	2 	4U			 	H4SW    					 
2001041900305	20010419	00305	SW  	2001	4	19	HEEA071991       	1	20010405	G	2611	302319	SMOKE DETECTOR  			BELL  	412   	412         	1182202	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				SMOKE DETECTION UNIT WOULD TEST INCONSISTENTLY.						1	G	7	2 	4U			 	H4SW    					 
2001041900306	20010419	00306	SW  	2001	4	19	HEEA071992       	1	20010405	G	7714	39433339002	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				NR 1 NEEDLE ON TRIPLE TACH INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001041900307	20010419	00307	SW  	2001	4	19	HEEA071993       	1	20010405	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										CROSSTUBE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				RUBBER WORN  AND DETERIORATED ON CROSSTUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900308	20010419	00308	SW  	2001	4	19	HEEA071994       	1	20010405	G	3246	412050015110	SKID            			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				SADDLE FASTENERS  MAKING MUD - SHOWING WEAR.						1	G	7	2 	4U			 	H4SW    					 
2001041900309	20010419	00309	SW  	2001	4	19	HEEA071995       	1	20010405	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				LOW FUEL LIGHT COMING ON AFTER REFUELING AIRCRAFT.						1	G	7	2 	4U			 	H4SW    					 
2001041900310	20010419	00310	SW  	2001	4	19	HEEA071996       	1	20010405	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				TRANSFER LIGHT CAME ON AT 1850 LBS.						1	G	7	2 	4U			 	H4SW    					 
2001041900311	20010419	00311	SW  	2001	4	19	HEEA071997       	1	20010405	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL INDICATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				TRANSFER LIGHT CAME ON AT 1850 LBS.						1	G	7	2 	4U			 	H4SW    					 
2001041900312	20010419	00312		2001	4	19	HEEA071998       	4	20010405	G	2340	AA34300	INTERPHONE      			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				TRANSMITS AND RECEIVES POORLY. SENT TO EDMO DIST. FOR WARRANTY REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001041900313	20010419	00313		2001	4	19	HEEA071999       	4	20010405	G	2561	PHI10090	LIFE VEST       			BELL  	412   	412         	1182202	SW  										CABIN	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2148K					36001				LIFE VEST FAILED 3 MONTH INSPECTION.						1	G	7	2 	4U			 	H4SW    					 
2001041900314	20010419	00314		2001	4	19	HEEA072000       	4	20010405	G	3451	066106901	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				DIGITS FLICKERING. REPLACED DISPLAY AND LENS.  COOKED UNIT, INSPECTED AND BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001041900315	20010419	00315		2001	4	19	HEEA072001       	4	20010405	G	3451	066106902	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				SEGMENT VERY DIM IN DAYLIGHT. FOUND PHOTOCELL BAD.  INSTALLED NEW PHOTOCELL.  ALSO MISSING 2 EACH COVER SCREWS.  INSTALL	ED 2 SCREWS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900316	20010419	00316		2001	4	19	HEEA072002       	4	20010405	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										ATC	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				NO OUTPUT. PERFORMED PRELIMINARY INSPECTION.  FOUND MODULATOR WAS LOADING DOWN THE POWER SUPPLY VOLTAGES.  REPLACED TWO 	EACH INSULATORS AND ONE EACH BUSHING FOR TRANSISTORS Q501 AND Q502.  CLEANED CORROSION FROM BACKSIDE OF THE TRANSISTORS.	  REPAIRED.				1	G	7	2 	4U			 	H4SW    					 
2001041900317	20010419	00317		2001	4	19	HEEA072003       	4	20010405	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										ATC	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	33008					36004				REPORTED INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  CLEANED EXCESSIVE CORROSION FROM UNIT.  FOUND WEAK RECEIVER SEN	SE AND WEAK TRANSMIT POWER.  REPLACED TRANSMITTER BOARD AND ALIGNED TO SPECS.  ALIGNED THE RECEIVER.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900318	20010419	00318		2001	4	19	HEEA072004       	4	20010405	G	3455	066107700	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				WILL NOT HOME TO STATIONS. PERFORMED PRELIMINARY INSPECTION.  FOUND EXCESSIVE CORROSION IN UNIT AND UNDER F.C. I323 AND 	CAPACITOR C380.  REPLACED I323 AND C380 AND CLEANED CORROSION.  ALODYNED CHASIS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900319	20010419	00319		2001	4	19	HEEA072005       	4	20010405	G	3454	071121627	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										NAVIGATION SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				WILL NOT CHANNEL PROPERLY CAUSING VOR NOT TO WORK PROPERLY. PERFORMED PRELIMINARY INSPECTION.  FOUND UNIT WILL NOT DISPL	AY NAV FREQUENCY ON KTS-143.  REPLACED IC I201 AND PHOTOCELL LENS.  REPAIRED.   BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001041900320	20010419	00320	SW  	2001	4	19	HEEA072006       	1	20010405	G	5210	204031762002	SPRING          			BELL  	412   	412         	1182202	SW  										BLOCKS	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				DOOR SPRING BROKEN. REPLACED WITH SERVICEABLE SPRING.						1	G	7	2 	4U			 	H4SW    					 
2001041900321	20010419	00321	SW  	2001	4	19	HEEA072007       	1	20010405	G	6320	212040233001	LINE            			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900322	20010419	00322	SW  	2001	4	19	HEEA072008       	1	20010405	G	6320	212040233001	LINE            			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900323	20010419	00323	SW  	2001	4	19	HEEA072009       	1	20010405	G	6320	212040234001	LINE            			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900324	20010419	00324	SW  	2001	4	19	HEEA072010       	1	20010405	G	6320	212040234001	LINE            			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900325	20010419	00325	SW  	2001	4	19	HEEA072011       	1	20010405	G	6320	212040234001	LINE            			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900326	20010419	00326	SW  	2001	4	19	HEEA072012       	1	20010405	G	2911	212076007003	ACCUMULATOR     			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				ACCUMULATOR LEAKS FROM WEEP HOLE. REPLACED WITH SERVICEABLE ACCUMULATOR.						1	G	7	2 	4U			 	H4SW    					 
2001041900327	20010419	00327	SW  	2001	4	19	HEEA072013       	1	20010405	G	2910	212076302001	LINE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				CHAFED BEYOND LIMITS. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900328	20010419	00328	SW  	2001	4	19	HEEA072014       	1	20010405	G	2910	212076311001	LINE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				CHAFED BEYOND LIMITS. REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001041900329	20010419	00329	SW  	2001	4	19	HEEA072015       	1	20010405	G	2560	214070966107	SEAT BELT       			BELL  	412   	412         	1182202	SW  										COCKPIT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				SEAT BELT TORN. REPLACED WITH SERVICEABLE BELT.						1	G	7	2 	4U			 	H4SW    					 
2001041900330	20010419	00330	SW  	2001	4	19	HEEA072016       	1	20010405	G	6710		BEARING         			BELL  	412   	412         	1182202	SW  										BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				BEARINGS FOUND WORN DURING DAILY CHECK. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900331	20010419	00331	SW  	2001	4	19	HEEA072017       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				BEARING FOUND WORN. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900332	20010419	00332	SW  	2001	4	19	HEEA072018       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BEARING FOUND WORN. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900333	20010419	00333	SW  	2001	4	19	HEEA072019       	1	20010405	G	6230	412010405109	DRIVE LINK      			BELL  	412   	412         	1182202	SW  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900334	20010419	00334	SW  	2001	4	19	HEEA072020       	1	20010405	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900335	20010419	00335	SW  	2001	4	19	HEEA072021       	1	20010405	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										ROD END	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900336	20010419	00336		2001	4	19	HEEA072022       	4	20010405	G	2350	A3016W	AUDIO PANEL     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				TRANSMITS WITH MIC SELECTOR IN FM1 POSITION AND RECEIVES FM1 ON THE FM2 POSITION. PERFORMED PRELIMINARY INSPECTION AND F	OUND UNIT TRANSMIT OUTPUT DISTORTED.  REPLACED CAPACITOR C30 AND ALSO LIGHT PANEL WORN.  REPLACED LIGHT PANEL.  BENCH CH	ECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001041900337	20010419	00337	SW  	2001	4	19	HEEA072023       	1	20010405	G	2840	APTE1391500SG	TRANSDUCER      			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				CAUSING INDICATOR TO READ 5 PSI WHEN AIRCRAFT IS SHUTDOWN. REPLACED WITH SERVICEABLE TRANSMITTER.						1	G	7	2 	4U			 	H4SW    					 
2001041900338	20010419	00338	SW  	2001	4	19	HEEA072024       	1	20010405	G	3340	G62504	SEARCH LIGHT    			BELL  	412   	412         	1182202	SW  										EXTERIOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				RETRACTION MOTOR WILL NOT SHUT OFF WHEN FULLY RETRACTED. REPLACED WITH SERVICEABLE LIGHT.						1	G	7	2 	4U			 	H4SW    					 
2001041900339	20010419	00339	SW  	2001	4	19	HEEA072025       	1	20010405	G	6220	412010100193FM	HUB             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	VIBRATION       	E			HEEA	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	6559Z					36019				BLUE SPINDLE CAUSING VIBRATION. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900340	20010419	00340	SW  	2001	4	19	HEEA072026       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900341	20010419	00341	SW  	2001	4	19	HEEA072027       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900342	20010419	00342	SW  	2001	4	19	HEEA072028       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900343	20010419	00343	SW  	2001	4	19	HEEA072029       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900344	20010419	00344	SW  	2001	4	19	HEEA072030       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900345	20010419	00345	SW  	2001	4	19	HEEA072031       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900346	20010419	00346	SW  	2001	4	19	HEEA072032       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900347	20010419	00347	SW  	2001	4	19	HEEA072033       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900348	20010419	00348	SW  	2001	4	19	HEEA072034       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900349	20010419	00349	SW  	2001	4	19	HEEA072035       	1	20010405	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900350	20010419	00350	SW  	2001	4	19	HEEA072036       	1	20010405	G	6230	412010405109	DRIVE LINK      			BELL  	412   	412         	1182202	SW  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900351	20010419	00351	SW  	2001	4	19	HEEA072037       	1	20010405	G	6230	412010405109	DRIVE LINK      			BELL  	412   	412         	1182202	SW  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900352	20010419	00352	SW  	2001	4	19	HEEA072038       	1	20010405	G	6720	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				MAIN ROTOR VIBRATION. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001041900353	20010419	00353	SW  	2001	4	19	HEEA072039       	1	20010405	G	3212	412050013117	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				LEAKING FROM AROUND FORWARD AIR VALVE. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001041900354	20010419	00354	SW  	2001	4	19	HEEA072040       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900355	20010419	00355	SW  	2001	4	19	HEEA072041       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900356	20010419	00356	SW  	2001	4	19	HEEA072042       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900357	20010419	00357	SW  	2001	4	19	HEEA072043       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900358	20010419	00358	SW  	2001	4	19	HEEA072044       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900359	20010419	00359	SW  	2001	4	19	HEEA072045       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900360	20010419	00360	SW  	2001	4	19	HEEA072046       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900361	20010419	00361	SW  	2001	4	19	HEEA072047       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900362	20010419	00362	SW  	2001	4	19	HEEA072048       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900363	20010419	00363	SW  	2001	4	19	HEEA072049       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900364	20010419	00364	SW  	2001	4	19	HEEA072050       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900365	20010419	00365	SW  	2001	4	19	HEEA072051       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900366	20010419	00366	SW  	2001	4	19	HEEA072052       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900367	20010419	00367	SW  	2001	4	19	HEEA072053       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900368	20010419	00368	SW  	2001	4	19	HEEA072054       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900369	20010419	00369	SW  	2001	4	19	HEEA072055       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900370	20010419	00370	SW  	2001	4	19	HEEA072056       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001041900371	20010419	00371	SW  	2001	4	19	HEEA072057       	1	20010405	G	2560	501819409	SEAT BELT       			BELL  	412   	412         	1182202	SW  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN.						1	G	7	2 	4U			 	H4SW    					 
2001041900372	20010419	00372	SW  	2001	4	19	HEEA072058       	1	20010405	G	2560	501836307	SEAT BELT       			BELL  	412   	412         	1182202	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				FRAYED. REPLACED WITH SERVICEABLE RESTRAINT.						1	G	7	2 	4U			 	H4SW    					 
2001041900373	20010419	00373		2001	4	19	HEEA072059       	4	20010405	G	2370	9806020023	CVR             			BELL  	412   	412         	1182202	SW  										COCKPIT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	30YM					36032				FAILS TO ILLUMINATE TEST LIGHT.						1	G	7	2 	4U			 	H4SW    					 
2001041900374	20010419	00374		2001	4	19	HEEA072060       	4	20010405	G	2370	9806020023	CVR             			BELL  	412   	412         	1182202	SW  										COCKPIT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5759N					33002				WILL NOT LIGHT UP TEST LIGHT ON PUSH BUTTON TEST. FOUND UNIT FAILED FSK TEST AND ROTOR SPEED TEST.						1	G	7	2 	4U			 	H4SW    					 
2001042000186	20010420	00186	SW  	2001	4	20	HEEA072061       	1	20010405	G	3212	D24911117	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				LEAKING, FAILED 6 MONTH INSPECTION.						1	G	7	2 	4U			 	H4SW    					 
2001042000187	20010420	00187	SW  	2001	4	20	HEEA072062       	1	20010405	G	3212	D24921119	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2014K					33020				AFTER ELECTRICAL INFLATION OF FLOAT SYSTEM, A LEAK AT THE REAR POP OFF VALVE WAS NOTED.  VALVE THREADS WERE STRIPPED.  V	ALVE WOULD ONLY ROTATE.					1	G	7	2 	4U			 	H4SW    					 
2001042000188	20010420	00188	SW  	2001	4	20	HEEA072063       	1	20010405	G	3212	D24921119	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				LEAKING, FAILED 6 MONTH INSPECTION. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001042000189	20010420	00189		2001	4	20	HEEA072064       	4	20010405	G	2350	M880555002	SWITCH          			BELL  	412   	412         	1182202	SW  										COMM SYSTEM	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				INTERMITTENT HOT MIKE SWITCH STICKING. REPLACED WITH SERVICEABLE SWITCH.						1	G	7	2 	4U			 	H4SW    					 
2001042000190	20010420	00190	SW  	2001	4	20	HEEA072065       	1	20010405	G	5260	PHI101741	STEP            			BELL  	412   	412         	1182202	SW  										LEFT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				LEFT HAND STEP STAYING UP. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000191	20010420	00191	SW  	2001	4	20	HEEA072066       	1	20010405	G	5260	PHI101741	STEP            			BELL  	412   	412         	1182202	SW  										RIGHT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				RIGHT HAND STEP WILL NOT GO DOWN. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000192	20010420	00192	SW  	2001	4	20	HEEA072067       	1	20010405	G	5260	PHI101741	STEP            			BELL  	412   	412         	1182202	SW  										RIGHT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				RIGHT HAND STEP WILL NOT EXTEND. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000193	20010420	00193	SW  	2001	4	20	HEEA072068       	1	20010405	G	5260	PHI101741	STEP            			BELL  	412   	412         	1182202	SW  										LEFT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WOULD NOT LET LT STEP GO DOWN. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000194	20010420	00194		2001	4	20	HEEA072069       	4	20010405	G	2312	VFS10902	ANTENNA         			BELL  	412   	412         	1182202	SW  										VHF	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				ANTENNA SPLIT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001042000195	20010420	00195	SW  	2001	4	20	HEEA072070       	1	20010405	G	3212	412050017133	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT BAG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				COVER TORN. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001042000196	20010420	00196	SW  	2001	4	20	HEEA072071       	1	20010405	G	2560	412070843105	SHOULDER BELT   			BELL  	412   	412         	1182202	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				SHOULDER HARNESS WEB FRAYED. REPLACED WITH SERVICEABLE RESTRAINT.						1	G	7	2 	4U			 	H4SW    					 
2001042000197	20010420	00197	SW  	2001	4	20	HEEA072072       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000198	20010420	00198	SW  	2001	4	20	HEEA072073       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000199	20010420	00199	SW  	2001	4	20	HEEA072074       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000200	20010420	00200	SW  	2001	4	20	HEEA072075       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000201	20010420	00201	SW  	2001	4	20	HEEA072076       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000203	20010420	00203	SW  	2001	4	20	HEEA072077       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000204	20010420	00204	SW  	2001	4	20	HEEA072078       	1	20010405	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001042000205	20010420	00205		2001	4	20	HEEA072079       	4	20010405	G	3452	066106200	TRANSPONDER     			BELL  	407   	407         	       	SW  										ATC	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	409PH					53059				LOW POWER AND WIDE PULSE WIDTH. PERFORMED PRELIMINARY INSPECTION AND FOUND F401 FUSE BLOWN AND Q415 BAD.  REPLACED F401 	FUSE AND Q415 TRANSISTOR.  FOUND UNIT WILL NOT RECEIVE.  REPLACED V101 CAVITY TUBE AND V301 PHOTOCELL.  REPAIRED.  BENCH	 CHECK GOOD.				1	G	7	1 	3U			O	H2SW    					 
2001042000206	20010420	00206	SW  	2001	4	20	HEEA072080       	1	20010405	G	3212	206050248121	FLOAT           			BELL  	206   	206L4       	1182110	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7074W					52033				L/H AFT FLOAT BAG FAILED 6 MONTH INSPECTION. SENT TO OFFSHORE HELICOPTER SUPPORT FOR WARRANTY REPAIR.						1	G	7	1 	3U			NC	H2SW    					 
2001042000207	20010420	00207	SW  	2001	4	20	HEEA072081       	1	20010405	G	6730	206076062107	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ROTOR SERVO SYS	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8594X					51531				LEAKING. REPLACED WITH SERVICEABLE FLOAT.						1	G	7	1 	3U			 	H2SW    					 
2001042000209	20010420	00209		2001	4	20	HEEA072082       	4	20010405	G	2561	3500145NL72	LIFE VEST       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				VEST WILL NOT HOLD AIR. SENT TO J.D. MANUFACTURING FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000210	20010420	00210	SW  	2001	4	20	HEEA072083       	1	20010405	G	6710	C4264215	SERVO VALVE     		206076062003	BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4282Z				RH4128A	51499				SLIDE AND SLEEVE ASSY (SERVO VALVE) HAS STICKY MOVEMENT. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000211	20010420	00211	SW  	2001	4	20	HEEA072084       	1	20010405	G	7120	23069751	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				ENGINE REAR MOUNT BEARING HAS PLAY. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			O	H2SW    					 
2001042000212	20010420	00212	SW  	2001	4	20	HEEA072085       	1	20010405	G	7120	206062102013	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000213	20010420	00213	SW  	2001	4	20	HEEA072086       	1	20010405	G	7120	206062103017	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000214	20010420	00214	SW  	2001	4	20	HEEA072087       	1	20010405	G	7120	206062101101	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000215	20010420	00215	SW  	2001	4	20	HEEA072088       	1	20010405	G	7120	206062101102	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000216	20010420	00216	SW  	2001	4	20	HEEA072089       	1	20010405	G	7120	206062103018	MOUNT           			BELL  	206   	206B3       	1181506	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000217	20010420	00217	SW  	2001	4	20	HEEA072090       	1	20010405	G	7120	206064107101	MOUNT           			BELL  	206   	206L1       	1182107	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2124Z					45646				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001042000218	20010420	00218		2001	4	20	HEEA072091       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				UNABLE TO TUNE AND TRANSMIT. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.  ADJUSTED C/N SQ	UELCH, CARRIER SQUELCH, MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000219	20010420	00219		2001	4	20	HEEA072092       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	31077					51520				THE LARGE OUTER CHANNEL CHANGE KNOB INTERMITTENT. PERFORMED PRELIMINARY INSPECTION AND TESTED.  REPLACED DISPLAY BOARD A	SSY.  REPAIRED PROBLEM.  ADJUSTED C/N SQUELCH AND BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000220	20010420	00220		2001	4	20	HEEA072093       	4	20010405	G	2312	064101905	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5007Y					45192				WILL NOT CHANGE FROM STANDBY TO IN USE AND VERY HARD TO CHANGE FREQUENCY FOR FIRST 20 TO 30 MINUTES OF FLIGHT. PERFORMED	 PRELIMINARY INSPECTION AND TESTED.  ADJUSTED MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.  COULD NOT DUPLICATE PROBLEM.					1	G	7	1 	3U			 	H2SW    					 
2001042000221	20010420	00221		2001	4	20	HEEA072094       	4	20010405	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7077F					52038				UNABLE TO CONTROL VOLUME. PERFORMED PRELIMINARY INSPECTION AND TESTED.  REPLACED BAD S901.  POTENTIOMETER SWITCH VOLUME 	REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	3U			NC	H2SW    					 
2001042000222	20010420	00222	SW  	2001	4	20	HEEA072095       	1	20010405	G	7810		SUPPORT BRACKET 			BELL  	412   	412         	1182202	SW  										EXHAUST STACK	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				SUPPORT BRACKET AND SHROUD CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001042000223	20010420	00223	SW  	2001	4	20	HEEA072096       	1	20010405	G	7810	212061202007	EXHAUST STACK   			BELL  	412   	412         	1182202	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				EXHAUST STACK IS CRACKED AT SEAMS OF DUCT HALVES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001042000224	20010420	00224	SW  	2001	4	20	HEEA072097       	1	20010405	G	7810	212061210001	DUCT            			BELL  	412   	412         	1182202	SW  										EXHAUST STACK	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001042000225	20010420	00225		2001	4	20	HEEA072098       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	45RP					45521				DISPLAY INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED.  FOUND DISPLAY A LITTLE WEAK.  REPLACED DS501 DISPLAY.	  REPAIRED.  ADJUSTED MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000226	20010420	00226		2001	4	20	HEEA072099       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	45RP					45521				DISPLAY FLICKERS AND MEMORY RESETS. PERFORMED PRELIMINARY INSPECTION AND COULD NOT DUPLICATE PROBLEM.  FOUND AUDIO LEVEL	 TO BE VERY LOW.  REPLACED R505 VOLUME CONTROL  AND CAPACITOR.  ADJUSTED C/N SQUELCH, MODULATION AND SIDETONE.  BENCH CH	ECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001042000227	20010420	00227		2001	4	20	HEEA072100       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3116L					51529				DISPLAY TOO DIM AND SEVERAL LED DIGITS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND FOUND DISPLAY BAD.  REPLACED AN	D ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000228	20010420	00228		2001	4	20	HEEA072101       	4	20010405	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				DISPLAY IS UNREADABLE ON HIGH HUMIDITY MORNINGS. REMOVED AND REPLACED DISPLAY.  ADJUSTED AND ALIGNED CARRIER NOISE SQUEL	CH, CARRIER SQUELCH, MODULATION AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000230	20010420	00230		2001	4	20	HEEA072102       	4	20010405	G	2312	064101922	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				WILL NOT TRANSMIT OR RECEIVE. PERFORMED PRELIMINARY INSPECTION AND ADJUSTED CARRIER NOISE SQUELCH, CARRIER SQUELCH, AND 	SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000231	20010420	00231		2001	4	20	HEEA072103       	4	20010405	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206B3       	1181506	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2277A					3630				RADIO TOTALLY INOPERATIVE.  WON''''T TURN ON. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.	  ADJUSTED SIDETONE.  REPLACED FADED DISPLAY LENS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000232	20010420	00232		2001	4	20	HEEA072104       	4	20010405	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				FLIPPING FROM USE TO STANDBY. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.  ADJUSTED FREQU	ENCY AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000234	20010420	00234	SW  	2001	4	20	HEEA072108       	1	20010406	G	6220	407310100103	DAMPER          			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				CORROSION IN SHEAR BEARING BORE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFEREN	CE:  DMR 715116.  LABOR CREDIT ACCOMPLISHED ON J0151671-WA (INVOICE AND DMR NO. 687009.					1	G	7	1 	3U			O	H2SW    					 
2001042000235	20010420	00235	SW  	2001	4	20	HEEA072109       	1	20010406	G	6220	407310101101	BEARING         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BEARING WORN.  SERIAL NUMBERS REMOVED ARE LP6967, LP6611, LP6567 AND LP6625.						1	G	7	1 	3U			O	H2SW    					 
2001042000240	20010420	00240	SW  	2001	4	20	HEEA072112       	1	20010406	G	6230		SEAL            			BELL  	407   	407         	       	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	1687 			A874	53288				SWASHPLATE HAS A BLOWN GREASE SEAL.						1	G	7	1 	3U			O	H2SW    					 
2001042000241	20010420	00241	SW  	2001	4	20	HEEA072113       	1	20010406	G	6720	407375024101	CONTROL UNIT    			BELL  	407   	407         	       	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	291  				53435				CAUSES PEDAL STOP TO ENGAGE INTERMITTENTLY WITHOUT ELECTRICAL OR MECHANICAL INPUT.						1	G	7	1 	3U			O	H2SW    					 
2001042000242	20010420	00242	SW  	2001	4	20	HEEA072114       	1	20010406	G	6320	407040006107FM	TRANSMISSION    			BELL  	407   	407         	       	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	3132 				53142				CHIP LIGHT HISTORY, POSSIBLY MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2001042000243	20010420	00243	SW  	2001	4	20	HEEA072115       	1	20010406	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										OIL COOLER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH				PHI0002	53199				OIL COOLER BLOWER BEARINGS ARE ROUGH.  SERIAL NUMBERS REMOVED ARE E99-0635 AND E99-0696.						1	G	7	1 	3U			O	H2SW    					 
2001042000250	20010420	00250	SW  	2001	4	20	HEEA072116       	1	20010406	G	6510	407340339103	BEARING         		407040302107	BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	440  			A1942	53397				WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR# 71506402.  LABOR 	CREDIT ACCOMPLISHED ON J0147760-WA (INVOICE AND DMR NO. 686974).					1	G	7	1 	3U			O	H2SW    					 
2001042000251	20010420	00251	SW  	2001	4	20	HEEA072117       	1	20010406	G	6300	407340339101	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH				PHI0014	53397				OIL COOLER BLOWER BEARINGS ARE WORN.  SERIAL NUMBERS REMOVED ARE ZV10128 AND ZV10209.						1	G	7	1 	3U			O	H2SW    					 
2001042000252	20010420	00252	SW  	2001	4	20	HEEA072118       	1	20010406	G	6510	407340339101	BEARING         		407040302107	BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	495PH				A1937	53397				TAIL ROTOR DRIVESHAFT BEARINGS OVERHEATED.						1	G	7	1 	3U			O	H2SW    					 
2001042000253	20010420	00253	SW  	2001	4	20	HEEA072119       	1	20010406	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	       	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001042000254	20010420	00254	SW  	2001	4	20	HEEA072120       	1	20010406	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				TAIL ROTOR DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001042000255	20010420	00255	SW  	2001	4	20	HEEA072121       	1	20010406	G	6300	407340339103	BEARING         		407040302101	BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	491PH				A15	53386				BEARING ON TAIL ROTOR DRIVESHAFT OVERHEATED.						1	G	7	1 	3U			O	H2SW    					 
2001042000262	20010420	00262	SW  	2001	4	20	HEEA072122       	1	20010406	G	6710	406010407101	IDLER LINK      			BELL  	407   	407         	       	SW  										COLLECTIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	1913 				53207				COLLECTIVE IDLER LINK IS EXCESSIVELY WORN.						1	G	7	1 	3U			O	H2SW    					 
2001042000263	20010420	00263	SW  	2001	4	20	HEEA072123       	1	20010406	G	6230	206010408001	PIN             			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				MAIN ROTOR PIVOT PIN IS EXCESSIVELY WORN.						1	G	7	1 	3U			O	H2SW    					 
2001042000264	20010420	00264	SW  	2001	4	20	HEEA072124       	1	20010406	G	6300	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	2066 				53038				UNIVERSAL JOINT ON MAIN ROTOR DRIVE IS EXCESSIVELY WORN.						1	G	7	1 	3U			O	H2SW    					 
2001042000265	20010420	00265	SW  	2001	4	20	HEEA072125       	1	20010406	G	7400	407375038101	GUARD           			BELL  	407   	407         	       	SW  										START SWITCH	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				START SWITCH GUARD BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2001042000266	20010420	00266	SW  	2001	4	20	HEEA072126       	1	20010406	G	6320	B4749	CHIP DETECTOR   			BELL  	407   	407         	       	SW  										ENGINE GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	402PH					53159				ENGINE GEARBOX CHIP DETECTOR IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001042000269	20010420	00269	SW  	2001	4	20	HEEA072127       	1	20010406	G	6322	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										COOLLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001042000270	20010420	00270		2001	4	20	HEEA072128       	4	20010406	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         	       	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH	28   				53457				SELECT BUTTON MISSING.						1	G	7	1 	3U			O	H2SW    					 
2001042000271	20010420	00271	SW  	2001	4	20	HEEA072130       	1	20010406	G	6510	407340339101	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										OILCOOLER BLOWER	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	402PH				PHI0032	53159				OIL COOLER BLOWER BEARINGS OVERHEATED.						1	G	7	1 	3U			O	H2SW    					 
2001042000272	20010420	00272		2001	4	20	HEEA072131       	4	20010406	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8591X					51495				RADIO FEEDS BACK INTO HEADSET WHEN TRANSMITTING ON OTHER VHF RADIO SYSTEM IN AIRCRAFT. PERFORMED PRELIMINARY INSPECTION.	  ADJUSTED CARRIER AND CARRIER/NOISE SQUELCH.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000273	20010420	00273		2001	4	20	HEEA072132       	4	20010406	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3108E					51498				VHF TRANSCEIVER DISPLAY FAILED.						1	G	7	1 	3U			 	H2SW    					 
2001042000001	20010420	00001		2001	4	20	HEEA072133       	4	20010406	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										VHF SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3904L					45597				VHF TRANSCEIVER BREAKS SQUELCH.						1	G	7	1 	3U			 	H2SW    					 
2001042000002	20010420	00002		2001	4	20	HEEA072134       	4	20010406	G	3452	066106200	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										ATC	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5745S					45491				NR F2. PULSE.  LOW OUTPUT POWER.  LOW RESPONSE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000003	20010420	00003		2001	4	20	HEEA072135       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	45RP					45521				TIME ENROUTE PAGE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM BUT FOUND UNIT 	WOULD FAIL GPS TEST.  RESET MEMORY AND REPROGRAMMED.  FOUND CRYSTAL OFFSET OUT OF SPECS.  ADJUSTED CRYSTAL FREQUENCY TO 	SPECS.  REPAIRED PROBLEM.  BENCH CHECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001042000004	20010420	00004		2001	4	20	HEEA072136       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				DROPS ALL WAYPOINTS. PERFORMED PRELIMINARY INSPECTION AND TESTED.  COULD NOT DUPLICATE PROBLEM.   REPLACED BAD ENT BUTTO	N SWITCH AND BAD KEY CAPS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001042000005	20010420	00005		2001	4	20	HEEA072137       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2135V					45657				WILL NOT COME ON LINE. PERFORMED PRELIMINARY INSPECTION AND FOUND BATTERY DEAD AGAIN.  SENT TO TRIMBLE NAVIGATION FOR IN	SPECTION AND REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001042000006	20010420	00006		2001	4	20	HEEA072138       	4	20010406	G	3457	13824020109	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2124Z					45646				INOPERATIVE WILL NOT PASS CMM5 6-11. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000007	20010420	00007		2001	4	20	HEEA072139       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	DISCHARGED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22751					3627				BATTERY WEAK. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000008	20010420	00008		2001	4	20	HEEA072140       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2270G					3610				ENTER BUTTON STICKS IN. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000009	20010420	00009		2001	4	20	HEEA072141       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2270G					3610				MUST INPUT CODE EVERYTIME UNIT IS TURNED ON.  UNIT ONLY PICKS UP ONE OR TWO SATELLITES WHEN ANOTHER UNIT WILL PICK UP SE	VEN OR EIGHT IN THE SAME AIRCRAFT.  UNIT ALSO INTERMITTENTLY RESTARTS, CHANGES MODES WHILE WAITING FOR IT TO PICK UP MOR	E SATELLITES INTERMITTENTLY. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR.				1	G	7	1 	3U			 	H2SW    					 
2001042000010	20010420	00010		2001	4	20	HEEA072142       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2753F					2729				BUTTONS HARD TO PRESS. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000011	20010420	00011		2001	4	20	HEEA072143       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	129MR					51129				FLASHES WARNING. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000012	20010420	00012		2001	4	20	HEEA072144       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5014Y					45219				CANNOT SET TIME. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000013	20010420	00013		2001	4	20	HEEA072145       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	32041					51539				WILL NOT HOLD HEADING. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000014	20010420	00014		2001	4	20	HEEA072146       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2759U					45272				NO MEMORY. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000015	20010420	00015		2001	4	20	HEEA072147       	4	20010406	G	3457	13824120234	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	49EA	1382 				51507				WILL NOT LOCATE ITSELF. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001042000016	20010420	00016	SW  	2001	4	20	HEEA072148       	1	20010406	G	6710	206001564001	WEB             			BELL  	206   	206L3       	1182108	SW  										SERVO SUPPORT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				OUTBOARD AND INBOARD FORWARD SERVO WEB MOUNT LUGS ARE BEING WORN BY THE SERVO FORWARD ROD END BEARING DUE TO ROCKING MOT	ION OF THE SERVO. REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U			 	H2SW    					 
2001042000017	20010420	00017	SW  	2001	4	20	HEEA072149       	1	20010406	G	6710	206001564001	WEB             			BELL  	206   	206L3       	1182108	SW  										SERVO MOUNT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				OUTBOARD FORWARD SERVO MOUNT LUGS ARE BEING WORN BY THE SERVO FORWARD ROD END BEARING DUE TO ROCKING MOTION OF THE SERVO	. REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U			 	H2SW    					 
2001042000018	20010420	00018	SW  	2001	4	20	HEEA072150       	1	20010406	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	53119					51575				EXHAUST ASSY CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000019	20010420	00019	SW  	2001	4	20	HEEA072151       	1	20010406	G	7120	206033201163A	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				CRACKED AT ENGINE MOUNT BOLT HOLE AREA. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000020	20010420	00020	SW  	2001	4	20	HEEA072152       	1	20010406	G	7120	206064103001	BEARING         			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	53119					51575				ENGINE MOUNT BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000021	20010420	00021	SW  	2001	4	20	HEEA072153       	1	20010406	G	7120	206064105001	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000022	20010420	00022	SW  	2001	4	20	HEEA072154       	1	20010406	G	7120	206064105002	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206LS					51070				ENGINE MOUNT CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000023	20010420	00023	SW  	2001	4	20	HEEA072155       	1	20010406	G	7120	206064105101	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	436PH					51436				ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001042000024	20010420	00024	SW  	2001	4	20	HEEA072156       	1	20010406	G	7120	206064105101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE MOUNT HAS MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000025	20010420	00025	SW  	2001	4	20	HEEA072157       	1	20010406	G	7120	206064105102	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	436PH					51436				ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001042000026	20010420	00026	SW  	2001	4	20	HEEA072158       	1	20010406	G	7120	206064105102	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE MOUNT HAS MECHANICAL AND CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000027	20010420	00027	SW  	2001	4	20	HEEA072159       	1	20010406	G	7120	206064106001	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206LS					51070				ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000028	20010420	00028	SW  	2001	4	20	HEEA072160       	1	20010406	G	7120	206064106001	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	436PH					51436				ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001042000029	20010420	00029	SW  	2001	4	20	HEEA072161       	1	20010406	G	7120	206064106101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE MOUNT HAS PITTED CORROSION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000030	20010420	00030	SW  	2001	4	20	HEEA072162       	1	20010406	G	7120	206064107001	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206LS					51070				ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000036	20010420	00036	SW  	2001	4	20	HEEA072163       	1	20010406	G	7120	206064107003	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206LS					51070				ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000037	20010420	00037	SW  	2001	4	20	HEEA072164       	1	20010406	G	7120	206064107101	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	436PH					51436				ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001042000038	20010420	00038	SW  	2001	4	20	HEEA072165       	1	20010406	G	7120	206064107101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				ENGINE MOUNT HAS CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000039	20010420	00039	SW  	2001	4	20	HEEA072166       	1	20010406	G	7120	206064107101	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE MOUNT HAS MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000040	20010420	00040	SW  	2001	4	20	HEEA072167       	1	20010406	G	7120		BEARING         			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2619					51375				LEG HAS WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000041	20010420	00041	SW  	2001	4	20	HEEA072168       	1	20010406	G	7120	206064107103	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	436PH					51436				ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001042000042	20010420	00042	SW  	2001	4	20	HEEA072169       	1	20010406	G	7120	206064107103	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE MOUNT HAS CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000043	20010420	00043	SW  	2001	4	20	HEEA072170       	1	20010406	G	7120		BEARING         			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2619					51375				LEG HAS WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000044	20010420	00044	SW  	2001	4	20	HEEA072171       	1	20010406	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				EXHAUST STACK IS CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000045	20010420	00045	SW  	2001	4	20	HEEA072172       	1	20010406	G	2560	206072841111	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				SEAT BELT REEL WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000046	20010420	00046	SW  	2001	4	20	HEEA072173       	1	20010406	G	2560	206072841111	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	81671					51301				SEAT BELT STICKS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000047	20010420	00047	SW  	2001	4	20	HEEA072174       	1	20010406	G	2560	206072841115	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				SEAT BELT REEL WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000048	20010420	00048	SW  	2001	4	20	HEEA072175       	1	20010406	G	2560	206072841115	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	81671					51301				SEAT BELT STICKS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001042000049	20010420	00049	EU  	2001	4	20	HEEA072176       	1	20010403	G	2432	RG355	BATTERY         			SNIAS 	350   	AS350B      	8680801	EU  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	972AE	225  				3234				ENGINE SLOW TO START. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H9EU    					 
2001042000050	20010420	00050	EU  	2001	4	20	HEEA072177       	1	20010403	G	6210	10581013	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB	3401 				S756				NR 1 INBOARD STRIP HAS SEPARATION ON THE OUTBOARD END OF THE ABRASION STRIP.						1	G	7	2 	3U			 	H3EU    					 
2001042000051	20010420	00051	EU  	2001	4	20	HEEA072178       	1	20010405	G	7810	10560186	EXHAUST PIPE    			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RUST PITS THROUGH STACK AT MOUNT FLANGE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2001050700548	20010507	00548	NE  	2001	5	7	HEEA072350       	1	20010409	G	2460	A1077B	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				ESSENTIAL BUSS READS LOW VOLTAGE.						1	G	7	2 	3U			 	H1NE    					 
2001050700549	20010507	00549	NE  	2001	5	7	HEEA072351       	1	20010410	G	7160	7630207028059	SCREEN          			SKRSKY	S76   	S76C        	8143008	NE  										ENGINE INTAKE	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				WIRE MESH HAS WIRE BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE SCREEN.						1	G	7	2 	3U			NC	H1NE    					 
2001050700550	20010507	00550		2001	5	7	HEEA072352       	4	20010411	G	3457	8143902240B	GPS             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				GPS INOPERATIVE. FOUND UNIT WOULD INTERMITTENLY TURN OFF BY ITSELF THEN TURN BACK ON AND SELF TEST AGAIN.						1	G	7	2 	3U			 	H1NE    					 
2001050700551	20010507	00551	NE  	2001	5	7	HEEA072353       	1	20010411	G	7921	7630807901105	OIL COOLER      			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				OIL COOLER CAUSING HIGH OIL TEMP.						1	G	7	2 	3U			 	H1NE    					 
2001051500108	20010515	00108		2001	5	15	HEEA072354       	4	20010411	G	3444	6223201001	INDICATOR       			BEECH 	200   	200BEECH    	1152920	CE  										RADIO ALTIMETER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30PH					BB635				NO INDICATIONS IN FLIGHT.						1	L	7	2 	4T			 	A24CE   					 
2001050700590	20010507	00590		2001	5	7	HEEA072355       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				BURNED OUT 3 INDICATORS. PERFORMED PRELIMINARY INSPECTION.  FOUND UNIT DOES NOT POWER UP.  FOUND Q604, Q605 BAD ON POWER	 SUPPLY.  REPLACED Q604, Q605.  REPAIRED.  ADJUSTED TO SPECS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050700591	20010507	00591		2001	5	7	HEEA072356       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				SCREEN ROLLS THEN GOES BLANK. PERFORMED PRELIMINARY INSPECTION.  FOUND UNIT DOES NOT POWER UP.  REPLACED Q604, Q605.  RE	PAIRED.  ADJUSTED TO SPECS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050700592	20010507	00592		2001	5	7	HEEA072357       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				INOPERATIVE.  NO NOISE BAND DURING TEST. PERFORMED PRELIMINARY INSPECTION.  COULD NOT DUPLICATE.  ADJUSTED STC AND GAIN 	VOLTAGE.    BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050700593	20010507	00593		2001	5	7	HEEA072358       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	SHORTED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				SHORTED INTERNALLY. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DOES NOT TURN ON.  REPLACED Q601, Q602, Q604, Q605 ON P	OWER SUPPLY.   REPAIRED.   BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050700594	20010507	00594		2001	5	7	HEEA072359       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	3893P					33012				GAPS IN TEST PATTERN. PERFORMED PRELIMINARY INSPECTION. FOUND R/T TRANSMITTING POWER OUT INTERMITTENT.  REPLACED MAGNETR	ON.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050700595	20010507	00595		2001	5	7	HEEA072360       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				PICTURE SCREEN SIZE FLUCTUATES AND ERRATIC. PERFORMED PRELIMINARY INSPECTION. TROUBLESHOT AND FOUND BAD HIGH VOLTAGES.  	REPLACED Q604 AND Q605.  REPAIRED HIGH VOLTAGE PROBLEM.  DISPLAY SLIGHTLY DISTORTED, REPLACED STABILIZATION BOARD, REPAI	RED.  BENCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001050800202	20010508	00202		2001	5	8	HEEA072361       	4	20010409	G	3445	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				UNIT WILL NOT POWER UP. PERFORMED PRELIMINARY INSPECTION. TROUBLESHOT AND REPLACED F202 FUSE.  ADJUSTED STC AND GAIN VOL	TAGE.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800203	20010508	00203		2001	5	8	HEEA072362       	4	20010409	G	3445	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				FAILS TARGETS AT HIGH RANGE SETTINGS. PERFORMED PRELIMINARY INSPECTION. FOUND MANUAL GAIN SET TOO HIGH, SHOWING FALSE TA	RGETS.  ADJUSTED ANC, MANUAL GAIN AND COLORS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800204	20010508	00204		2001	5	8	HEEA072363       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				RADAR SYSTEM WOULD NOT POWER UP. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT POWERING UP.  FOUND BURNT FOIL ON SWIT	CH PANEL.  REPAIRED FOIL AND BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800205	20010508	00205		2001	5	8	HEEA072364       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				NO INDICATION, BLANK SCREEN. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT DRAW AMPS. REPLACED Q4204, Q4205 TRANSISTO	RS ON POWER SUPPLY.  REPAIRED.  ADJUSTED UNIT TO SPECS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800206	20010508	00206		2001	5	8	HEEA072365       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				DOES NOT INDICATE. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE.  ADJUSTED COLORS, ANC AND MANUAL GAIN.  BENCH 	CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800207	20010508	00207		2001	5	8	HEEA072366       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				BLANK SCREEN. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DRAWS EXCESSIVE CURRENT.  REPLACED Q4204, Q4205 TRANSISTORS O	N POWER SUPPLY.  REPAIRED.  FOUND RED AND YELLOW COLORS IN NOISE BAND.  REPLACED IC U1402, U1403, U1406.  REPAIRED.  BEN	CH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001050800208	20010508	00208		2001	5	8	HEEA072367       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				WILL NOT COME ON BUT WILL POWER UP. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY FADES IN AND OUT.  CLEANED ALL BOARD	S AND PINS.  FOUND CORROSION ON MEMORY BOARD CONNECTOR.  CLEANED CORROSION.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800209	20010508	00209		2001	5	8	HEEA072368       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				CYCLES ON AND OFF.  FLICKERS MOST OF THE TIME AND DOES NOT BRING UP PICTURE. PERFORMED PRELIMINARY INSPECTION. COULD NOT	 VERIFY COMPLAINT.  ADJUSTED ANC AND INTENSITY.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800210	20010508	00210		2001	5	8	HEEA072369       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				LEFT SIDE OF DISPLAY WILL NOT DIM. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAINT.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050800211	20010508	00211		2001	5	8	HEEA072370       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				TOP HALF OF DISPLAY DISTORTED. PERFORMED PRELIMINARY INSPECTION. REPLACED SOCKET PINS ON VARIOUS CONNECTORS.  REPLACED C	RT ASSEMBLY.  ALIGNED TO SPECS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800212	20010508	00212		2001	5	8	HEEA072371       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				SCREEN WENT BLANK. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY SHRUNK ON SCREEN.  REPLACED R133 AND Q1318 ON VIDEO B	OARD.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800213	20010508	00213		2001	5	8	HEEA072372       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				COLORS INCORRECT ON TEST MODE.  TEST UNSTABLE INTERMITTENTLY. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAI	NT.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800214	20010508	00214		2001	5	8	HEEA072373       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				SCREEN TURNS BLUE. PERFORMED PRELIMINARY INSPECTION. FOUND HIGH VOLTAGE POWER SUPPLY CAUSING LOUD POPPING NOISE.  REPLAC	ED HIGH VOLTAGE POWER SUPPLY.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800215	20010508	00215		2001	5	8	HEEA072374       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				VIDEO IS WAVY.  SCREEN IS BLANK ON THE TOP AND BOTTOM. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY BLANKS OUT AND CO	LORS FADE IN AND OUT.  FOUND IC U1241 BAD ON TIMING BOARD.  REPLACED IC U1241.  REPAIRED.  ALSO REPLACED 30 EACH SOCKET 	PINS ON CONNECTORS.  BENCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001050800216	20010508	00216		2001	5	8	HEEA072375       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				INOPERATIVE.  NO DISPLAY ON SCREEN. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAINT.  CLEANED SLIGHT CORROS	ION ON BOARDS AND CONNECTORS.  ADJUSTED TO SPECS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800217	20010508	00217		2001	5	8	HEEA072376       	4	20010409	G	3442	MI5852013	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				DISPLAY ERRATIC. PERFORMED PRELIMINARY INSPECTION. REPLACED P1201 CONNECTOR AND CLEANED CORROSION FROM PINS ON SEVERAL C	ONNECTORS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050800218	20010508	00218		2001	5	8	HEEA072377       	4	20010409	G	3442	MI585202	ANTENNA         			BELL  	412   	412         	1182202	SW  										RADAR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WILL NOT HOLD PROPER TILT. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050800219	20010508	00219		2001	5	8	HEEA072378       	4	20010409	G	2561	PHI10090	LIFE VEST       			BELL  	412   	412         	1182202	SW  										CABIN	LEAKING         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				LEAKS. SENT TO J.D. MANUFACTURING FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001050800220	20010508	00220		2001	5	8	HEEA072379       	4	20010409	G	3442	MI585202	ANTENNA         			BELL  	412   	412         	1182202	SW  										RADAR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				WILL NOT SHOW SWEEP AND NO TARGETS DISPLAYED. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001050800221	20010508	00221	SW  	2001	5	8	HEEA072380       	1	20010409	G	5260	PHI101741	STEP            			BELL  	412   	412         	1182202	SW  										RIGHT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				RIGHT STEP STUCK IN STOW POSITION. REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001050800222	20010508	00222	SW  	2001	5	8	HEEA072381       	1	20010409	G	2510	222320823119	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	31077					51520				BAD SHOULDER HARNESS TENSION ADJUSTERS BACKWARDS AND RUB AGAINST BODY AND CANNOT BE ADJUSTED.						1	G	7	1 	3U			 	H2SW    					 
2001050800223	20010508	00223		2001	5	8	HEEA072382       	4	20010409	G	3422	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	30KH					51527				WOULD NOT ERECT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2003081500011	20030815	00011	SW  	2003	8	15	HEEA072383       	1	20010409	G	2820	206063650001	VALVE           			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5019F					45244				LEAKING FUEL VALVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800224	20010508	00224	SW  	2001	5	8	HEEA072384       	1	20010409	G	7120	206064107109	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800225	20010508	00225	SW  	2001	5	8	HEEA072385       	1	20010409	G	7810	206064203101	DUCT            			BELL  	206   	206L3       	1182108	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800226	20010508	00226	SW  	2001	5	8	HEEA072386       	1	20010409	G	2510	206072841113	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				INERTIA REEL RATCHETY AND INTERMITTENTLY STICKS WHEN EXTENDING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800227	20010508	00227	SW  	2001	5	8	HEEA072387       	1	20010409	G	2913	206076030101	PUMP            			BELL  	206   	206L3       	1182108	SW  										HYD SYSTEM	NOISY           	E			HEEA	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	03	30KH					51527				NOISE COMING FROM HYDRAULIC SYSTEM DURING CRUISE AND ON APPROACHES INTERMITTENT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800228	20010508	00228	SW  	2001	5	8	HEEA072388       	1	20010409	G	3212	206050247109	COVER           			BELL  	206   	206L1       	1182107	SW  										FLOAT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				LEFT AFT FLOAT COVER FLAP VELCRO HAS COME LOOSE FROM COVER.  STITCHING CAME OUT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800229	20010508	00229	SW  	2001	5	8	HEEA072389       	1	20010409	G	3210	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				CORROSION PITS UNDER SADDLE MOUNTS. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001050800230	20010508	00230	SW  	2001	5	8	HEEA072390       	1	20010409	G	2824	205060612003	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	BYPASSING       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ALLOWS FUEL TO BYPASS IN THE CLOSED POSITION. SENT TO ITT AEROSPACE FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001050800231	20010508	00231	SW  	2001	5	8	HEEA072391       	1	20010409	G	2844	209062003001	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				LOW PRESSURE LIGHT WILL NOT COME ON. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800232	20010508	00232	SW  	2001	5	8	HEEA072392       	1	20010409	G	2844	209062003001	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3893L					33006				LEAKING THROUGH SWITCH BODY. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800233	20010508	00233	SW  	2001	5	8	HEEA072393       	1	20010409	G	2844	209062003001	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				C-BOX PRESSURE LIGHT ILLUMINATES INTERMITTENTLY AND REMAINS ON 1 TO 2 MINUTES, THEN GOES OUT.  C-BOX OIL PRESSURE REMAIN	S STEADY. SCRAPPED AND REPLACED WITH SERVICEABLE PART.					1	G	7	2 	4U			 	H4SW    					 
2001050800234	20010508	00234	SW  	2001	5	8	HEEA072394       	1	20010409	G	7810	212061201011	EJECTOR         			BELL  	412   	412         	1182202	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800235	20010508	00235	SW  	2001	5	8	HEEA072395       	1	20010409	G	7810	212061201012	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				CRACKED AT MOUNTING PADS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800236	20010508	00236	SW  	2001	5	8	HEEA072396       	1	20010409	G	7810	212061210001	DUCT            			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800237	20010508	00237		2001	5	8	HEEA072397       	4	20010409	G	3413	212070239001	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT VSI	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ERRATIC READINGS FAILED STATIC CHECK.						1	G	7	2 	4U			 	H4SW    					 
2001050800238	20010508	00238		2001	5	8	HEEA072398       	4	20010409	G	3413	212070239001	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT VSI	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ERRATIC ABOVE 2000 FEET MSL.						1	G	7	2 	4U			 	H4SW    					 
2001050800239	20010508	00239	SW  	2001	5	8	HEEA072399       	1	20010409	G	5260	212070418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				STEP ACTUATOR DOES NOT FUNCTION. 						1	G	7	2 	4U			 	H4SW    					 
2001050800240	20010508	00240	SW  	2001	5	8	HEEA072400       	1	20010409	G	7714	212075037101	INDICATOR       			BELL  	412   	412         	1182202	SW  										N1	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				BOUNCES ERRATICALLY.						1	G	7	2 	4U			 	H4SW    					 
2001050800241	20010508	00241	SW  	2001	5	8	HEEA072401       	1	20010409	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ROD BROKEN ON ACTUATOR AND IS  INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001050800242	20010508	00242	SW  	2001	5	8	HEEA072402       	1	20010409	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				STEP WILL NOT RETRACT.						1	G	7	2 	4U			 	H4SW    					 
2001050800243	20010508	00243	SW  	2001	5	8	HEEA072403       	1	20010409	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				STEP ACTUATOR FROZEN.						1	G	7	2 	4U			 	H4SW    					 
2001050800244	20010508	00244	SW  	2001	5	8	HEEA072404       	1	20010409	G	2510	214070966101	SEAT BELT       			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				END UNSTITCHED.						1	G	7	2 	4U			 	H4SW    					 
2001050800245	20010508	00245	SW  	2001	5	8	HEEA072405       	1	20010409	G	2510	214070966101	SEAT BELT       			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				END UNSTITCHED. 						1	G	7	2 	4U			 	H4SW    					 
2001050800246	20010508	00246	SW  	2001	5	8	HEEA072406       	1	20010409	G	6420	412010418105	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										PITTING ON RACE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.						1	G	7	2 	4U			 	H4SW    					 
2001050800247	20010508	00247	SW  	2001	5	8	HEEA072407       	1	20010409	G	5320	206033201167S	STIFFENER       			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	BENT            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										STIFFENER CHANNELS ARE NOT BENT CORRECTLY.  U-CHANNEL VERTICAL FLANGES ARE SUPPOSED TO BE BENT UP 90 DEGREES.  THE FLANG	ES ON THESE TWO CHANNELS ARE 85 DEGREES AND 95 DEGREES.  THIS CAUSES THE FITTING, P/N 206-031-629-103 TO BE INSTALLED AT	 AN ANGLE, AND WILL CAUSE THE ENGINE MOUNT BOLT TO BE INSTALLED AT AN ANGLE THROUGH THE BULKHEAD. SENT TO BELL HELICOPTE	R TEXTRON FOR CREDIT.			1	G	7	1 	3U			 	H2SW    					 
2001050800248	20010508	00248	SW  	2001	5	8	HEEA072408       	1	20010409	G	7714	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				RPM WARNING LIGHT FLICKERS ON AND OFF AROUND 75 PERCENT N2.						1	G	7	2 	4U			 	H4SW    					 
2001050800249	20010508	00249		2001	5	8	HEEA072409       	4	20010409	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										TURN RATE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				TURN NEEDLE OSCILLATES.						1	G	7	2 	4U			 	H4SW    					 
2001050800250	20010508	00250	SW  	2001	5	8	HEEA072410       	1	20010409	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				DOES NOT WORK.						1	G	7	2 	4U			 	H4SW    					 
2001050800251	20010508	00251	SW  	2001	5	8	HEEA072411       	1	20010409	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R					36007				STEP WILL NOT EXTEND.						1	G	7	2 	4U			 	H4SW    					 
2001050800252	20010508	00252		2001	5	8	HEEA072412       	4	20010409	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										RATE OF TURN	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				NO RATE OF TURN INDICATION.						1	G	7	2 	4U			 	H4SW    					 
2001050800253	20010508	00253		2001	5	8	HEEA072413       	4	20010409	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										RATE OF TURN	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				TURN NEEDLE IS INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001050800254	20010508	00254	SW  	2001	5	8	HEEA072414       	1	20010409	G	5230	2353	HANDLE          			BELL  	412   	412         	1182202	SW  										CARGO DOOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				HEAT COATING WORN OFF BAGGAGE DOOR HANDLE.  HANDLE LOOSE ON IT''S SHAFT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800255	20010508	00255	NE  	2001	5	8	HEEA072415       	2	20010409	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FREE TURBINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				N2 WILL NOT REACH 100 PERCENT. FOUND INTERIOR OF UNIT VERY DIRTY.  TEFLON TUBE WAS WORN.  REPLACED TEFLON TUBE WITH NEW 	PART AND CLEANED INTERIOR PARTS.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800256	20010508	00256	NE  	2001	5	8	HEEA072416       	2	20010409	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FREE TURBINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				N2 WENT HIGH WITH THROTTLE AT IDLE. FOUND UNIT TO BE SLIGHTLY HANGING.  SPLIT UNIT AND FOUND INTERIOR OF UNIT TO BE DIRT	Y, WITH FLYWEIGHTS STICKING.  THIS WAS THE CAUSE OF THE HANGING ON BENCH.  CLEANED INTERIOR OF UNIT AND GOVERNOR TESTED 	OK.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800257	20010508	00257	NE  	2001	5	8	HEEA072417       	2	20010409	G	7320	2526385	BELLOWS         		324473514   	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FUEL CONTROL	DEFECTIVE       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N	212  			A34690	33010				IDLES AT 45 PERCENT N1 AND WILL NOT ACCELERATE. FOUND ALL FLOWS TO BE VERY LOW AND UNADJUSTABLE.  SPLIT UNIT AND FOUND B	ELLOWS TO BE DEFECTIVE.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800258	20010508	00258	NE  	2001	5	8	HEEA072418       	2	20010409	G	7320	324473514	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				ENGINE SLOW TO START.  SMOKES ON START CYCLE. RAN UNIT AS RECEIVED ON TEST BENCH.  COULD NOT DUPLICATE PROBLEM.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800259	20010508	00259	NE  	2001	5	8	HEEA072419       	2	20010409	G	7320	324473514	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				ENGINE SLOW TO START.  SMOKES ON START CYCLE. RAN UNIT AS RECEIVED ON TEST BENCH.  COULD NOT DUPLICATE PROBLEM.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800260	20010508	00260	NE  	2001	5	8	HEEA072420       	2	20010409	G	7320	324473514	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				7 PERCENT TORQUE SURGE AT FLAT PITCH. RAN UNIT AS RECEIVED ON TEST BENCH.  COULD NOT DUPLICATE PROBLEM.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800261	20010508	00261	NE  	2001	5	8	HEEA072421       	2	20010409	G	7320	32447368	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				7 PERCENT N1 OSCILLATION, TOO MUCH CUSHION ON THE HIGH SIDE, UNABLE TO ADJUST. RAN UNIT AS RECEIVED ON TEST BENCH.  COUL	D NOT DUPLICATE PROBLEM.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2003081500012	20030815	00012	SW  	2003	8	15	HEEA072422       	1	20010409	G	6730	41005496101	SERVO           			BELL  	412   	412         	1182202	SW  										FLT CONTROLS	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03										SERVO CAUSING EXCESSIVE INTERNAL LEAKAGE DURING TESTING.						1	G	7	2 	4U			 	H4SW    					 
2001050800262	20010508	00262	SW  	2001	5	8	HEEA072423       	1	20010409	G	6710	212076005105	CYLINDER        			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	BYPASSING       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										CAUSING EXCESSIVE BYPASS DURING TESTING.						1	G	7	2 	4U			 	H4SW    					 
2001050800263	20010508	00263	SW  	2001	5	8	HEEA072424       	1	20010409	G	3213	412050010111A	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3911L					33023				AFT CROSSTUBE SPREAD BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800264	20010508	00264	SW  	2001	5	8	HEEA072425       	1	20010409	G	3213	412015060102	SKID SHOE       			BELL  	412   	412         	1182202	SW  										MAIN SKID	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				SHOE TORN AT MOUNT POINTS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800265	20010508	00265	SW  	2001	5	8	HEEA072426       	1	20010409	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MLG	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				RUBBER ON CAP DETERIORATED.						1	G	7	2 	4U			 	H4SW    					 
2001050800266	20010508	00266	SW  	2001	5	8	HEEA072427       	1	20010409	G	3213	412050016102	SHOE            			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800267	20010508	00267	SW  	2001	5	8	HEEA072428       	1	20010409	G	3213	412050016102	SHOE            			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800268	20010508	00268	SW  	2001	5	8	HEEA072429       	1	20010409	G	3212	412050017133	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				FLOAT COVER TORN.						1	G	7	2 	4U			 	H4SW    					 
2001050800269	20010508	00269	SW  	2001	5	8	HEEA072430       	1	20010409	G	3212	412050017133	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				FLOAT COVER TORN. REPLACED WITH SERVICEABLE COVER.						1	G	7	2 	4U			 	H4SW    					 
2001050800270	20010508	00270	SW  	2001	5	8	HEEA072431       	1	20010409	G	3212	412050017135	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				WORN VELCRO.						1	G	7	2 	4U			 	H4SW    					 
2001050800271	20010508	00271	SW  	2001	5	8	HEEA072432       	1	20010409	G	3213	412050045107	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										UPON REMOVING CENTER PIVOT SADDLE; IT WAS FOUND THAT THERE WAS NO HOT BOND AGENT UNDER PIVOT. REPAIRED.						1	G	7	2 	4U			 	H4SW    					 
2001050800272	20010508	00272	SW  	2001	5	8	HEEA072433       	1	20010409	G	2510	412070843105	STRAP           			BELL  	412   	412         	1182202	SW  										COCKPIT	FRAYED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				STRAPS FRAYED. REPLACED RESTRAINTS.						1	G	7	2 	4U			 	H4SW    					 
2001050800273	20010508	00273	SW  	2001	5	8	HEEA072434       	1	20010409	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS LOW       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				NUMBER TWO NEEDLE READS LOW. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800274	20010508	00274		2001	5	8	HEEA072435       	4	20010409	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INACCURATE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				13 KNOT DIFFERENCE BETWEEN PILOTS AND COPILOTS INSTRUMENTS.						1	G	7	2 	4U			 	H4SW    					 
2001050800275	20010508	00275	SW  	2001	5	8	HEEA072436       	1	20010409	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS LOW       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R					36007				INDICATES 2 PERCENT LOW. SENT TO MASCO FOR WARRANTY REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001050800276	20010508	00276	SW  	2001	5	8	HEEA072437       	1	20010409	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R					36007				N2 NEEDLES STICK WHEN POWER IS CHANGED.						1	G	7	2 	4U			 	H4SW    					 
2001050800277	20010508	00277	SW  	2001	5	8	HEEA072438       	1	20010409	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				NR 1 TACH NEEDLE STOPPED ALL INDICATING.						1	G	7	2 	4U			 	H4SW    					 
2001050800278	20010508	00278	SW  	2001	5	8	HEEA072439       	1	20010409	G	2436	51539002N	GCU             			BELL  	412   	412         	1182202	SW  										NR 1 GENERATOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				NR 2 GENERATOR FAILED IN FLIGHT, WOULD NOT RESET.						1	G	7	2 	4U			 	H4SW    					 
2001050800279	20010508	00279	SW  	2001	5	8	HEEA072440       	1	20010409	G	3213	AB412050016101	SKID SHOE       			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				SKID SHOE WORN THROUGH. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800280	20010508	00280	SW  	2001	5	8	HEEA072441       	1	20010410	G	6720	PHI41294	BUSHING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				BUSHINGS AND ROD ENDS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2003081500013	20030815	00013	SW  	2003	8	15	HEEA072442       	1	20010410	G	6420	PHI41294	ROTOR HEAD      			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	VIBRATION       	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	108X					33115				TAIL ROTOR PRODUCING A HIGH FREQ VIBRATION. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800281	20010508	00281		2001	5	8	HEEA072443       	4	20010410	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	NOISY           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				A LOT OF BACKGROUND NOISE IN RECEPTION MODE. PERFORMED PRELIMINARY INSPECTION AND FOUND CARRIER SQUELCH INTERMITTENT, AD	JUSTED R184.					1	G	7	1 	3U			 	H2SW    					 
2001050800282	20010508	00282		2001	5	8	HEEA072444       	4	20010410	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				DISPLAY BLINKS ON AND OFF. PERFORMED PRELIMINARY INSPECTION.  SWAPPED OUT DISPLAY.  NO HELP.  REPLACED BAD VOLUME POTENT	IOMETER, CRACKED TRANSFER SWITCH AND PUSH BUTTON AND IC I901.  FOUND BRIGHT DASHES TO APPEAR ACROSS MIDDLE OF USE FREQUE	NCY.  REPLACED IC I505 AND I506.  NO HELP.				1	G	7	1 	3U			 	H2SW    					 
2001050800283	20010508	00283	SW  	2001	5	8	HEEA072445       	1	20010410	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				BEARINGS WORN. REPLACED WITH SERVICEABLE RESTRAINT.						1	G	7	1 	3U			 	H2SW    					 
2001050800284	20010508	00284	SW  	2001	5	8	HEEA072446       	1	20010410	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C					51425				BEARINGS WORN. REPLACED WITH SERVICEABLE RESTRAINT.						1	G	7	1 	3U			 	H2SW    					 
2001050800285	20010508	00285		2001	5	8	HEEA072447       	4	20010410	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2135V					45657				WILL NOT TRANSMIT ON ALL FREQUENCIES AND WILL NOT SWITCH. PERFORMED PRELIMINARY INSPECTION.  COULD NOT DUPLICATE PROBLEM	.  ADJUSTED FREQUENCY.  FOUND DISPLAY STAYING DIM ALL THE TIME.  REPLACED BAD V901 PHOTOCELL.  REPAIRED PROBLEM.  BENCH 	CHECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001050800286	20010508	00286	SW  	2001	5	8	HEEA072448       	1	20010410	G	7933	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	READS HIGH      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				INDICATES ABOVE RED LINE.						1	G	7	2 	4U			 	H4SW    					 
2001050800287	20010508	00287	SW  	2001	5	8	HEEA072449       	1	20010410	G	7933	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	READS HIGH      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3911L					33023				INDICATES ABOVE RED LINE.						1	G	7	2 	4U			 	H4SW    					 
2001050800288	20010508	00288	SW  	2001	5	8	HEEA072450       	1	20010410	G	7933	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				STICKS WHEN ENGINE IS FIRST RUN UP.						1	G	7	2 	4U			 	H4SW    					 
2001050800289	20010508	00289	SW  	2001	5	8	HEEA072451       	1	20010410	G	6720	PHI41294	BUSHING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN BEARINGS/BUSHINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800290	20010508	00290		2001	5	8	HEEA072452       	4	20010410	G	3421	PHI4121017601	CONNECTOR       			BELL  	412   	412         	1182202	SW  										ATTITIUDE GYRO	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CONNECTOR PLUG RECEPTACLE LOOSE IN HOUSING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800291	20010508	00291	SW  	2001	5	8	HEEA072453       	1	20010410	G	2821	AC985F10	FUEL FILTER     			BELL  	214   	214ST       	1182106	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	3897N					28106				FUEL FILTER LIGHT. REPLACED WITH SERVICEABLE PART.						2	G	7	2 	4U			 	H10SW   					 
2001050800292	20010508	00292	SW  	2001	5	8	HEEA072454       	1	20010410	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TORQUE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				NR 1 NEEDLE IS INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001050800293	20010508	00293	SW  	2001	5	8	HEEA072455       	1	20010410	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TORQUE	SPLIT           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				HAS A 10 PERCENT SPLIT.  ALSO NOTICED WITH JUST THE NR 1 ENGINE RUNNING THE TRANSMISSION NEEDLE FLUCTUATING AND BRINGING	 THE NR 2 NEEDLE WITH IT.					1	G	7	2 	4U			 	H4SW    					 
2001050800294	20010508	00294	SW  	2001	5	8	HEEA072456       	1	20010410	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				NR 1 ENGINE READING LOW.						1	G	7	2 	4U			 	H4SW    					 
2001050800295	20010508	00295	SW  	2001	5	8	HEEA072457       	1	20010410	G	7714	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				NR 1 NEEDLE INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001050800296	20010508	00296	SW  	2001	5	8	HEEA072458       	1	20010410	G	3213	AB205050403031	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				CORRODED BEYOND LIMITS UNDER BOTH SADDLE MOUNTS. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001050800297	20010508	00297	SW  	2001	5	8	HEEA072459       	1	20010410	G	5260	PHI101741	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WILL NOT OPERATE LEFT STEP ACTUATOR. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800298	20010508	00298	SW  	2001	5	8	HEEA072460       	1	20010410	G	5260	PHI101741	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				LEFT STEP WILL NOT RAISE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800299	20010508	00299	SW  	2001	5	8	HEEA072461       	1	20010410	G	5260	PHI101741	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				LT STEP WILL NOT EXTEND. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800300	20010508	00300	SW  	2001	5	8	HEEA072462       	1	20010410	G	5260	PHI101741	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				LT STEP WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050800301	20010508	00301	GL  	2001	5	8	HEEA072463       	2	20010410	G	7320	25490924	FUEL CONTROL    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2133X					45634	CAE890024			FUEL LEAKING FROM AROUND BYPASS COVER. DURING OVERHAUL FOUND EXCESSIVE CORROSION AND PITTING AROUND BYPASS COVER AND BOR	E.  THIS CONDITION WILL CAUSE LEAKING FROM THE BYPASS COVER.  REPLACED COMPLETE MAIN FLOW BODY ASSY.  UNIT TESTED SATISF	ACTORY.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050800302	20010508	00302	GL  	2001	5	8	HEEA072464       	2	20010410	G	7320	252464430	FUEL CONTROL    			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2753F					2729				GOING HOT AND WOULD NOT RESPOND TO ADJUSTMENTS. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050800303	20010508	00303	GL  	2001	5	8	HEEA072465       	2	20010410	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	ERRATIC         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8589X					51487				INCONSISTENT STARTS.  SOME STARTS NORMAL.  OTHERS DELAYED AND TENDED TO HAVE HIGH TOT. REPLACED WITH SERVICEABLE FUEL CO	NTROL.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050800304	20010508	00304		2001	5	8	HEEA072466       	4	20010410	G	3421	5040017901	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	45RP					45521				EXCESSIVE PRECESSING. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR.						1	G	7	1 	3U			 	H2SW    					 
2001050800305	20010508	00305		2001	5	8	HEEA072467       	4	20010410	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				INDICATES 7-8 DEGREE LEFT TURN IN LEVEL FLIGHT. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR.						1	G	7	1 	3U			 	H2SW    					 
2001050800306	20010508	00306		2001	5	8	HEEA072468       	4	20010410	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8591X					51495				ROLLING AND WILL NOT HOLD A LEVEL ATTITUDE. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR.						1	G	7	1 	3U			 	H2SW    					 
2001050800307	20010508	00307		2001	5	8	HEEA072469       	4	20010410	G	3422	5050010902	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6251X					51552				LAGS 40 DEGREE IN 180 DEGREE TURN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800308	20010508	00308	SW  	2001	5	8	HEEA072470       	1	20010410	G	6520	PHI2062003	HOUSING         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	21497					51518				TAIL ROTOR GEARBOX INPUT SEAL LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800309	20010508	00309	GL  	2001	5	8	HEEA072471       	2	20010410	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	4835					51131				STARTS STAGNATES AT 33 PERCENT N1. RAN UNIT ON TEST BENCH AND COULD NOT DUPLICATE PROBLEM.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050800310	20010508	00310	SW  	2001	5	8	HEEA072472       	1	20010410	G	6210	200578S69D	BOLT            			BELL  	206   	206L1       	1182107	SW  										M/R BLADE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				AREA OF SHANK BEHIND THREADS, IS OVERSIZED AND WILL NOT ALLOW BOLT TO GO THROUGH BUSHING. REPLACED WITH SERVICEABLE PART	.					1	G	7	1 	3U			 	H2SW    					 
2001050800311	20010508	00311	SW  	2001	5	8	HEEA072473       	1	20010410	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				LT STEP WILL NOT RETRACT.						1	G	7	2 	4U			 	H4SW    					 
2001050800312	20010508	00312	SW  	2001	5	8	HEEA072474       	1	20010410	G	7332	206061535007	TRANSDUCER      			BELL  	206   	206L1       	1182107	SW  										FUEL PRESSURE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	03	513EH					45421				WHILE IN CRUISE FLIGHT THE FUEL PRESSURE INDICATOR SHOWED A DECREASE IN FUEL PRESSURE. REPLACED PRESSURE TRANSMITTER.						1	G	7	1 	3U			 	H2SW    					 
2001050800313	20010508	00313	SW  	2001	5	8	HEEA072475       	1	20010410	G	5610	222180109	WINDOW          			BELL  	430   	430         	1182150	SW  										COCKPIT	SEPARATED       	E			HEEA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	430X					49058				ENROUTE TO MP283 AT 3000 FEET AT 135 KNOTS, THE CO-PILOT''S DOOR WINDOW DEPARTED THE AIRCRAFT. INSPECTED AND FOUND NO DA	MAGE TO AIRCRAFT.					1	G	7	2 	3U			RT	H9SW    					 
2001050800314	20010508	00314		2001	5	8	HEEA072476       	4	20010411	G	3457	8143902240B	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				WILL NOT RECEIVE SATELLITES. COULD NOT DUPLICATE PROBLEM.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050800315	20010508	00315		2001	5	8	HEEA072477       	4	20010411	G	3457	8143902240B	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				GPS WENT OFF LINE/ON LINE. COULD NOT DUPLICATE PROBLEM.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050800316	20010508	00316		2001	5	8	HEEA072478       	4	20010411	G	3457	8143902240B	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				CDI (EXTERNAL) DOES NOT INDICATE PROPERLY.  DOES NOT AGREE WITH GPS CDI REMAINS 2 DIVISIONS DIFFERENT. SENT TO TRIMBLE N	AVIGATION FOR INSPECTION AND REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001050800317	20010508	00317		2001	5	8	HEEA072480       	4	20010411	G	3457	8143802240D	GPS             			BELL  	407   	407         	       	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	492PH					53390				FALLS OFF LINE.						1	G	7	1 	3U			O	H2SW    					 
2001050800318	20010508	00318		2001	5	8	HEEA072481       	4	20010411	G	3457	8143802240D	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22743					3624				LOCKS ON ONE LOCATION, WILL NOT UPDATE IN FLIGHT. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800319	20010508	00319		2001	5	8	HEEA072482       	4	20010411	G	3442	80510800001	CONTROL BOX     			BELL  	206   	206L3       	1182108	SW  										RADAR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6610Y					51419				NO TARGETS DISPLAYED.						1	G	7	1 	3U			 	H2SW    					 
2001050800320	20010508	00320		2001	5	8	HEEA072483       	4	20010411	G	3443	80510890001	CONTROL BOX     			BELL  	206   	206L3       	1182108	SW  										RADAR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6610Y					51419				WOULD NOT TRACK AIRCRAFT PROPERLY.						1	G	7	1 	3U			 	H2SW    					 
2001050800321	20010508	00321	SW  	2001	5	8	HEEA072484       	1	20010411	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1202T					33112				LEAKING FROM CENTER CORE AREA.						1	G	7	2 	4U			 	H4SW    					 
2001050800322	20010508	00322	SW  	2001	5	8	HEEA072485       	1	20010411	G	2820	869A6TT	CHECK VALVE     			BELL  	206   	206L1       	1182107	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3178K					45765				CHECK VALVES POSSIBLY CAUSING ENGINE FLAME OUT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800323	20010508	00323	SW  	2001	5	8	HEEA072486       	1	20010411	G	2820	869A6TT	VALVE           			BELL  	206   	206L1       	1182107	SW  										ENGINE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				STICKING OPEN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800324	20010508	00324		2001	5	8	HEEA072487       	4	20010411	G	2214	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				NR 2 HELIPILOT WOULD NOT COME ON.						1	G	7	2 	4U			 	H4SW    					 
2001050800325	20010508	00325		2001	5	8	HEEA072488       	4	20010411	G	2212	7000299901	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				NR 2 HELIPILOT WILL NOT CYCLE AFCS CAUTION LIGHT WITH HELIPILOT ON AND TURNING HELIPILOT NR 2 ON AND OFF.						1	G	7	2 	4U			 	H4SW    					 
2001050800326	20010508	00326		2001	5	8	HEEA072489       	4	20010411	G	3444	7000839901	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	108X					33115				FLAG WILL NOT PULL. 						1	G	7	2 	4U			 	H4SW    					 
2001050800327	20010508	00327		2001	5	8	HEEA072490       	4	20010411	G	3444	7000839904	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				READS LOW AND DH LIGHT DOES NOT COME ON AT SET ALTITUDE.						1	G	7	2 	4U			 	H4SW    					 
2001050800328	20010508	00328	SW  	2001	5	8	HEEA072491       	1	20010411	G	2910	70066L000R230	HOSE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				LEAKING THROUGH STEEL BRAIDED SLEEVE. REPLACED WITH SERVICEABLE HOSE.						1	G	7	2 	4U			 	H4SW    					 
2001050800329	20010508	00329	SW  	2001	5	8	HEEA072492       	1	20010411	G	3110	78805059008	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4282Z					51499				INTERMITTENT DISPLAY.						1	G	7	1 	3U			 	H2SW    					 
2001050800330	20010508	00330		2001	5	8	HEEA072493       	4	20010411	G	3416	6221205004	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				TESTS AT 42 INSTEAD OF 50 +/-5.						1	G	7	2 	4U			 	H4SW    					 
2001050800331	20010508	00331	SW  	2001	5	8	HEEA072494       	1	20010411	G	6730	6225194001	SERVO           			BELL  	206   	206L1       	1182107	SW  										AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5744Y					45465				INTERMITTENT FEEDBACK (KICKING) IN AUTOPILOT SYSTEM. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800332	20010508	00332	SW  	2001	5	8	HEEA072495       	1	20010411	G	6730	6225194001	SERVO           			BELL  	206   	206L1       	1182107	SW  										AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5744Y					45465				CAUSES AUTOPILOT SYSTEM TO DISENGAGE AND FEEDBACK IN CONTROLS (KICKING). REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800333	20010508	00333	SW  	2001	5	8	HEEA072496       	1	20010411	G	6730	6225194001	SERVO           			BELL  	206   	206L1       	1182107	SW  										AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5744Y					45465				SERVO CAUTION LIGHT ILLUMINATES AND AUTOPILOT SYSTEM DISENGAGES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800334	20010508	00334	SW  	2001	5	8	HEEA072497       	1	20010411	G	6730	6225194001	SERVO           			BELL  	206   	206L1       	1182107	SW  										AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5744Y					45465				AUTOPILOT SYSTEM INTERMITTENTLY DISENGAGES AND SERVO CAUSES KICKING IN PILOT''''S CYCLIC STICK. REPLACED WITH SERVICEABL	E PART.					1	G	7	1 	3U			 	H2SW    					 
2001050800335	20010508	00335	SW  	2001	5	8	HEEA072498       	1	20010411	G	3110	65013008	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				STICKS.  FACEPLATE CAME OFF DURING REMOVAL OF INDICATOR. SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800336	20010508	00336	GL  	2001	5	8	HEEA072499       	2	20010411	G	7240	6854255	VALVE           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206FS					51506				THREADS DAMAGED THAT GO INTO COMBUSTION CASE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	T	 	H2SW    	E10CE				 
2001050800337	20010508	00337	SW  	2001	5	8	HEEA072500       	1	20010411	G	7120		BEARING         			BELL  	407   	407         	       	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				REAR ENGINE MOUNT BEARING UNSTAKED. SENT TO DALLAS AIRMOTIVE FOR OVERHAUL.						1	G	7	1 	3U			O	H2SW    					 
2001050800338	20010508	00338	SW  	2001	5	8	HEEA072501       	1	20010411	G	7100	6892836	TUBE            			BELL  	206   	206L3       	1182108	SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6610C					51425				TUBE ASSY LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800339	20010508	00339	GL  	2001	5	8	HEEA072502       	2	20010411	G	7420	6893283	IGNITION LEAD   			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077F					52038				IGNITION LEAD INOPERATIVE.						1	G	7	1 	3U	3	T	NC	H2SW    	E10CE				 
2001050900093	20010509	00093	GL  	2001	5	9	HEEA072505       	2	20010411	G	7532	6894063	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				WOULD NOT ACTUATE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	T	 	H2SW    	E10CE				 
2001050800340	20010508	00340		2001	5	8	HEEA072506       	4	20010411	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8591X					51495				ROLLING, WILL NOT HOLD A LEVEL ALTITUDE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800341	20010508	00341		2001	5	8	HEEA072507       	4	20010411	G	3421	5040017901	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ATTITUDE	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				PRECESSES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800342	20010508	00342		2001	5	8	HEEA072508       	4	20010411	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ATTITUDE	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				PILOT REPORTS THAT AFTER INSTRUMENT SLOWLY STARTED TO PRECESS THE CARD WAS CORRECTED AND INSTRUMENT FROZE UP IN WINGS LE	VEL AND NOSE ON HORIZON POSITION. REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U			 	H2SW    					 
2001050800343	20010508	00343		2001	5	8	HEEA072509       	4	20010411	G	3421	5040017901	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ATTITUDE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5019F					45244				PILOT REPORTED INDICATOR INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800344	20010508	00344		2001	5	8	HEEA072510       	4	20010411	G	3422	5050010902	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	SMOKE           	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	03	41791					51465				SMOKING AND POPS CIRCUIT BREAKER. REPLACED TRANSFORMER, RESISTORS AND BEARINGS.  BENCH CHECK GOOD.						1	G	7	1 	3U			 	H2SW    					 
2001050800345	20010508	00345		2001	5	8	HEEA072511       	4	20010411	G	3422	5050010902	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				PRECESSES 2 DEGREES EVERY 5 MINUTES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800346	20010508	00346	SW  	2001	5	8	HEEA072512       	1	20010411	G	6320	50501008380401	SEAL            			BELL  	206   	206L3       	1182108	SW  										OIL PUMP	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6160Y					51609				OIL LEAKING FROM TRANSMISSION OIL PUMP DRIVE SHAFT SEAL. REPLACED TRANSMISSION OIL PUMP.						1	G	7	1 	3U			 	H2SW    					 
2001050800347	20010508	00347		2001	5	8	HEEA072514       	4	20010411	G	2562	569880101	SWITCH          			BELL  	206   	206L4       	1182110	SW  										ELT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7077F					52038				RED LIGHT STAYS ON DIM. REPLACED WITH SERVICEABLE SWITCH.						1	G	7	1 	3U			NC	H2SW    					 
2001050800348	20010508	00348	NE  	2001	5	8	HEEA072515       	2	20010411	G	7420	3029107	LEAD            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					IGNITER	FRAYED          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				FRAYED. REPLACED WITH SERVICEABLE CABLE.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800349	20010508	00349	SW  	2001	5	8	HEEA072516       	1	20010411	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										TRIM	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				ITT FLUCTUATES IN FLIGHT AT OR ABOVE 2500 FEET ALTITUDE.						1	G	7	2 	4U			 	H4SW    					 
2001050800350	20010508	00350	NE  	2001	5	8	HEEA072517       	2	20010411	G	7321	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				TORQUE OSCILLATIONS DURING POWER CHANGES. TESTED UNIT AND COULD NOT DUPLICATE PROBLEM.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800351	20010508	00351	NE  	2001	5	8	HEEA072518       	2	20010411	G	7321	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	CONTAMINATED    	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	3893N					33010				DROOPING IN FLIGHT, FOUND TURCO IN FITTINGS. CLEANED AND POLISHED SERVO VALVE, LEVERS AND FITTINGS.  UNIT TESTED OK.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050800352	20010508	00352	SW  	2001	5	8	HEEA072519       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L3       	1182108	SW  										T/R SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800353	20010508	00353	SW  	2001	5	8	HEEA072520       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				PITTED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800354	20010508	00354	SW  	2001	5	8	HEEA072521       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE SHAFT	FRETTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				FRETTING BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800355	20010508	00355	SW  	2001	5	8	HEEA072522       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L1       	1182107	SW  										T/R DRIVE SHAFT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				CRACKED. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800356	20010508	00356	SW  	2001	5	8	HEEA072523       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L1       	1182107	SW  										T/R DRIVE SHAFT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				CRACKED. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800357	20010508	00357	SW  	2001	5	8	HEEA072524       	1	20010411	G	6510	327211	DISC PACK       			BELL  	407   	407         	       	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	436PH					51436				CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			O	H2SW    					 
2001050800358	20010508	00358	SW  	2001	5	8	HEEA072525       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L1       	1182107	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800359	20010508	00359	SW  	2001	5	8	HEEA072526       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			 	H2SW    					 
2001050800360	20010508	00360	SW  	2001	5	8	HEEA072527       	1	20010411	G	6510	327211	DISC PACK       			BELL  	206   	206L4       	1182110	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077F					52038				CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW    					 
2001050800361	20010508	00361		2001	5	8	HEEA072528       	4	20010411	G	2330	002000002	AMPLIFIER       			BELL  	206   	206L3       	1182108	SW  										PA SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				INOPERATIVE.  WILL NOT TURN ON. PERFORMED PRELIMINARY INSPECTION.  FOUND Q3204 BAD.  REPLACED.  CLEANED RUST ON HOUSING 	AND PAINTED.  FUNCTION CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001050800362	20010508	00362		2001	5	8	HEEA072529       	4	20010411	G	3457	0110005400	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5007Q					45187				LOOSES SATELLITES DURING FLIGHT.						1	G	7	1 	3U			 	H2SW    					 
2001050800363	20010508	00363		2001	5	8	HEEA072530       	4	20010411	G	3457	0110005400	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				WILL NOT ACQUIRE SATELLITE SIGNAL.						1	G	7	1 	3U			 	H2SW    					 
2001050800364	20010508	00364		2001	5	8	HEEA072531       	4	20010411	G	3457	0110005400	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21240					45647				DROPPING OFF.						1	G	7	1 	3U			 	H2SW    					 
2001050800365	20010508	00365		2001	5	8	HEEA072532       	4	20010411	G	3457	0110005400	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5007Y					45192				WILL NOT COME ON LINE FOR 20-40 MINUTES.						1	G	7	1 	3U			 	H2SW    					 
2001050800366	20010508	00366		2001	5	8	HEEA072533       	4	20010411	G	3457		BATTERY         			BELL  	206   	206L3       	1182108	SW  										GPS	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6748D				81509251	51106				INTERNAL BATTERY WEAK. SENT TO GARMIN INTERNATIONAL FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800367	20010508	00367		2001	5	8	HEEA072534       	4	20010411	G	3457	0110005400	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	UNRELIABLE      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	979BH					51403				GPS UNRELIABLE. SENT TO GARMIN INTERNATIONAL FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800368	20010508	00368	GL  	2001	5	8	HEEA072535       	2	20010411	G	7261	03808808	ELEMENT         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENG OIL SYSTEM	BYPASSING       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				BYPASSED EARLY. SCRAPPED LOCALLY AND REPLACED WITH NEW FILTER.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050800369	20010508	00369		2001	5	8	HEEA072536       	4	20010411	G	3457	0845000000	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2775A					45297				1ST DIGIT OF DISPLAY INOPERATIVE. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800370	20010508	00370		2001	5	8	HEEA072537       	4	20010411	G	3457	0845000000	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	81671					51301				WILL NOT KEEP USER WAYPOINTS WHEN POWER IS CYCLED. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800371	20010508	00371		2001	5	8	HEEA072538       	4	20010411	G	3457	0845000000	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	81671					51301				POWER BUTTON IS INOPERATIVE. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800372	20010508	00372	SW  	2001	5	8	HEEA072539       	1	20010411	G	6510	406040340101	DISC PACK       			BELL  	206   	206L3       	1182108	SW  										T/R DRIVE SHAFT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				PITTED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800373	20010508	00373	SW  	2001	5	8	HEEA072540       	1	20010411	G	6720	206001058101	CONTROL ROD     			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				CORROSION UNDER NYLATRON SLEEVE FOUND TO BE .020 INCH DEEP. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800374	20010508	00374	SW  	2001	5	8	HEEA072541       	1	20010411	G	6720	206001058101	CONTROL ROD     			BELL  	206   	206L4       	1182110	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001050800375	20010508	00375	SW  	2001	5	8	HEEA072542       	1	20010411	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				WORN SPHERICAL BEARINGS.						1	G	7	1 	3U			 	H2SW    					 
2001050800376	20010508	00376	SW  	2001	5	8	HEEA072543       	1	20010411	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2619					51375				BEARING IN TRANSMISSION RESTRAINT CAME UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800377	20010508	00377	SW  	2001	5	8	HEEA072544       	1	20010411	G	6330	206033506103	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800378	20010508	00378	SW  	2001	5	8	HEEA072545       	1	20010411	G	6330	206033506103	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				BOTH RESTRAINT ARM BEARINGS HAS EXCESSIVE WEAR IN BEARINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800379	20010508	00379	SW  	2001	5	8	HEEA072546       	1	20010411	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				BEARING WORN AND ONE BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800380	20010508	00380	SW  	2001	5	8	HEEA072547       	1	20010411	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050800381	20010508	00381	SW  	2001	5	8	HEEA072548       	1	20010411	G	2810	206064611001	FUEL CELL       			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				LEAKING, FOUND SMALL TEAR AT FRONT OF CELL.						1	G	7	1 	3U			 	H2SW    					 
2001050800382	20010508	00382	SW  	2001	5	8	HEEA072549       	1	20010411	G	2810	206064611001	FUEL CELL       			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3178K					45765				MAIN FUEL CELL LEAKS.						1	G	7	1 	3U			 	H2SW    					 
2001050800383	20010508	00383	SW  	2001	5	8	HEEA072550       	1	20010411	G	7714	206075681101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	3178K					45765				DUAL TACH HAS NO LIGHT.						1	G	7	1 	3U			 	H2SW    					 
2001050800384	20010508	00384	SW  	2001	5	8	HEEA072551       	1	20010411	G	7714	206075681101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	SPLIT           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				2 PERCENT SPLIT IN NEEDLE INDICATION.						1	G	7	1 	3U			 	H2SW    					 
2001050800385	20010508	00385	SW  	2001	5	8	HEEA072552       	1	20010411	G	7714	206075681117	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				TURBINE NEEDLE STAYING AT ZERO AT TIMES AND VERY UNRELIABLE.						1	G	7	1 	3U			 	H2SW    					 
2001050800386	20010508	00386	SW  	2001	5	8	HEEA072553       	1	20010411	G	7712	206075739103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TORQUEMETER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				INDICATOR FLUCTUATES 4 TO 5 PERCENT AT ALL TIMES.						1	G	7	1 	3U			 	H2SW    					 
2001050800387	20010508	00387	SW  	2001	5	8	HEEA072554       	1	20010411	G	7712	206075739103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TORQUEMETER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				FLUCTUATES 3 TO 5 PERCENT ABOVE 80 PERCENT TORQUE.						1	G	7	1 	3U			 	H2SW    					 
2001050800388	20010508	00388	SW  	2001	5	8	HEEA072555       	1	20010411	G	7712	206075739103	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TORQUEMETER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				TORQUE NEEDLE BOUNCES 2 TO 4 PERCENT.						1	G	7	1 	3U			 	H2SW    					 
2001050800389	20010508	00389	SW  	2001	5	8	HEEA072556       	1	20010411	G	7712	206075739103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TORQUEMETER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				FLUCTUATES 10 PERCENT AND INTERMITTENTLY STICKS AT 6 PERCENT AFTER SHUTDOWN.						1	G	7	1 	3U			 	H2SW    					 
2001050800390	20010508	00390	SW  	2001	5	8	HEEA072557       	1	20010411	G	6730	206076062003	CYLINDER        			BELL  	206   	206L3       	1182108	SW  										SERVO	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				THE PILOT VALVE THROUGH BOLTS (2 EA) ARE VERY STIFF AND CANNOT BE MOVED BY HAND.  STIFF FLIGHT CONTROLS. REPLACED WITH S	ERVICEABLE SERVO.					1	G	7	1 	3U			 	H2SW    					 
2001050800391	20010508	00391	SW  	2001	5	8	HEEA072558       	1	20010411	G	6730	206076062003	CYLINDER        			BELL  	206   	206L3       	1182108	SW  										SERVO	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6610Y					51419				LEAKING AT REAR SEAL. REPLACED WITH SERVICEABLE SERVO.						1	G	7	1 	3U			 	H2SW    					 
2001050800392	20010508	00392	SW  	2001	5	8	HEEA072559       	1	20010411	G	3212	206369002	FLOAT           			BELL  	206   	206L1       	1182107	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				HAS HOLE ON FRONT END.						1	G	7	1 	3U			 	H2SW    					 
2001050800393	20010508	00393	SW  	2001	5	8	HEEA072560       	1	20010411	G	2821	222366621101	FUEL FILTER     			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	30KH					51527				LIGHT WILL NOT COME ON.						1	G	7	1 	3U			 	H2SW    					 
2001050800394	20010508	00394	SW  	2001	5	8	HEEA072561       	1	20010411	G	2821	222366621101	FUEL FILTER     			BELL  	206   	206L4       	1182110	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	7074W					52033				LIGHT STAYS ON.						1	G	7	1 	3U			NC	H2SW    					 
2001050800395	20010508	00395	SW  	2001	5	8	HEEA072562       	1	20010411	G	2821	222366621101	FUEL FILTER     			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3178K					45765				BYPASS BUTTON STICKS. SENT TO PUROFLOW CORP. FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050800396	20010508	00396	SW  	2001	5	8	HEEA072563       	1	20010411	G	2821	222366621101	FUEL FILTER     			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SW	03	45RP					45521				ELECTRICAL PIN IN FILTER HEAD BROKEN. REPLACED WITH SERVICEABLE FUEL FILTER ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001050800397	20010508	00397	GL  	2001	5	8	HEEA072564       	2	20010411	G	7420	23060816	LEAD            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					IGNITER	SHORTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				ONE OF THE FOUR TANGS ON B RECEPTACLE END BROKEN.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050800398	20010508	00398	GL  	2001	5	8	HEEA072565       	2	20010411	G	7323	252467711	GOVERNOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	DIRTY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				WILL NOT RECOVER RPM AFTER COLLECTIVE POWER CHANGES. FOUND INTERIOR OF UNIT TO BE DIRTY WHICH COULD HAVE CAUSED GOVERNOR	 TO HANG AND HAVE HYSTERSIS PROBLEMS.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900094	20010509	00094	GL  	2001	5	9	HEEA072566       	2	20010411	G	7323	252469211	GOVERNOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				AIRCRAFT EXPERIENCES OVERSPEEDS ON LANDINGS AND DROOPS DURING TAKE OFF. REPLACED GOVERNOR ASSY.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900095	20010509	00095	GL  	2001	5	9	HEEA072567       	2	20010411	G	7323	252469211	GOVERNOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C	8138 				51425				N2 SLOW TO RECOVER AFTER POWER CHANGES. GOVERNOR RESPONDED POORLY ON TEST BENCH.  SLOPE RESPONDED SLOWLY.  CLEANED INTER	IOR AND UNIT TESTED OK.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900096	20010509	00096	GL  	2001	5	9	HEEA072568       	2	20010411	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				TORQUE FLUCTUATING 10 PERCENT ON TAKE OFF. PERFORMED PRELIMINARY INSPECTION AND FOUND EXCESSIVE SIDE PLAY AT THE CUTOFF 	LINKAGE.  REPLACED AND UNIT TESTED OK.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900097	20010509	00097	GL  	2001	5	9	HEEA072569       	2	20010411	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				STARTING PROBLEMS AND OSCILLATIONS ABOVE 80 PERCENT TORQUE. PERFORMED PRELIMINARY INSPECTION AND COULD NOT DUPLICATE PRO	BLEM.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900098	20010509	00098	GL  	2001	5	9	HEEA072570       	2	20010411	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				HUNG STARTS IN THE 40 TO 50 PERCENT N1 RANGE. PERFORMED PRELIMINARY INSPECTION AND FOUND NO DISCREPANCIES.  UNIT TESTED 	OK.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900099	20010509	00099	GL  	2001	5	9	HEEA072571       	2	20010411	G	7320	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				ENGINE LIGHTS OFF VERY HOT ON ALL STARTS AND THERE IS NO MORE ADJUSTMENT LEFT FOR LIGHTOFF DERICHMENT.  IF ACCELERATION 	IS MOVED BACK, START IS STILL HOT AND ACCELERATION SLOW. PERFORMED PRELIMINARY INSPECTION AND FOUND NO DISCREPANCIES.  U	NIT TESTED OK.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050800399	20010508	00399	SW  	2001	5	8	HEEA072572       	1	20010412	G	6322	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				PART IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001050800400	20010508	00400	SW  	2001	5	8	HEEA072573       	1	20010412	G	7810	407062021101	DUCT            			BELL  	407   	407         	       	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				PART IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001050800401	20010508	00401	SW  	2001	5	8	HEEA072574       	1	20010412	G	2840	407362005103	SWITCH          			BELL  	407   	407         	       	SW  										LIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				LOW LEVEL LIGHT WILL NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2001050900100	20010509	00100	SW  	2001	5	9	HEEA072576       	1	20010412	G	3212	206373902103	RELIEF VALVE    			BELL  	407   	407         	       	SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				RELIEF VALVE ON FLOAT LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001050900101	20010509	00101	SW  	2001	5	9	HEEA072577       	1	20010412	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										T/R HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				53198	53142				TAIL ROTOR HUB BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001050900102	20010509	00102	SW  	2001	5	9	HEEA072578       	1	20010412	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										T/R HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				53198	53142				TAIL ROTOR HUB BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001050900103	20010509	00103	SW  	2001	5	9	HEEA072579       	1	20010412	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										T/R HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				53198	53142				TAIL ROTOR HUB BEARINGWORN.						1	G	7	1 	3U			O	H2SW    					 
2001050900104	20010509	00104	SW  	2001	5	9	HEEA072580       	1	20010412	G	2510	222320823130	SEAT BELT       			BELL  	407   	407         	       	SW  										COCKPIT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				SEAT BELT TAG TORN.						1	G	7	1 	3U			O	H2SW    					 
2001050900105	20010509	00105	SW  	2001	5	9	HEEA072581       	1	20010412	G	2820	AV23B11754	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	7128R					36007				LEAKING SHAFT SEAL. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001051000167	20010510	00167	EU  	2001	5	10	HEEA072582       	1	20010409	G	5531	350A1400200802	SPAR            			SNIAS 	350   	AS350B2     	8680813	EU  										STABILIZER	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				SPAR INSIDE CHAFED FROM CONDUIT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001051000168	20010510	00168	EU  	2001	5	10	HEEA072583       	1	20010409	G	3213	350A41108602	CROSSTUBE       			SNIAS 	350   	AS350B2     	8680813	EU  										MLG	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				CHAFED BY FLOAT ASSEMBLY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001051000169	20010510	00169	EU  	2001	5	10	HEEA072584       	1	20010409	G	3213	350A41108702	CROSSTUBE       			SNIAS 	350   	AS350B2     	8680813	EU  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				SURFACE CORROSION EXCEEDS COVERAGE AREA AND DEPTH LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001051000170	20010510	00170		2001	5	10	HEEA072585       	4	20010411	G	3457	8143802240D	GPS             			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE					3229				LOST POSITION.  CANT FIND ITSELF.						1	G	7	1 	3U			 	H9EU    					 
2001051000171	20010510	00171		2001	5	10	HEEA072586       	4	20010411	G	3457	8143802240D	GPS             			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	970AE					3235				FACE PLATE DELAMINATED.						1	G	7	1 	3U			 	H9EU    					 
2001051000172	20010510	00172		2001	5	10	HEEA072587       	4	20010411	G	3421	504001790116	GYRO            			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				WOULD NOT FAST ERECT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001051000173	20010510	00173	EU  	2001	5	10	HEEA072588       	1	20010411	G	6510	552200	BEARING         			BOLKMS	105   	BO105S      	5626006	EU  										T/R DRIVESHAFT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				WHILE ROTATING M/R HEAD, NOTICED CLICKING SOUND COMING FROM BEARING ON TAILBOOM. REMOVED T/R DRIVESHAFT AND REPLACED ROU	GH BEARING.					1	G	7	2 	3U			 	H3EU    					 
2001050700556	20010507	00556		2001	5	7	HEEA072594       	4	20010417	G	3450	071106603	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546G					760076				WILL NOT GIVE BEARING INFO OR AUDIO. PERFORMED PRELIMINARY INSPECTION AND FOUND HUNDREDS SECTION S101 TERMINAL #26 HAS B	ROKEN WIRE AND VOLUME CONTROL NOISY.  RESOLDERED WIRE ON S101 TERMINAL 26 AND CLEANED VOLUME CONTROL.  REPAIRED.  BENCH 	CHECK GOOD.				1	G	7	2 	3U			 	H1NE    					 
2001050700557	20010507	00557		2001	5	7	HEEA072595       	4	20010417	G	3451	066106602	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										DME	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	761PH					760224				WEAK RECEIVE AND TRANSMIT.						1	G	7	2 	3U			 	H1NE    					 
2001050700558	20010507	00558		2001	5	7	HEEA072596       	4	20010417	G	3454	066400700	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										VOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5435V					760158				CAUSES VOR GREEN NEEDLE TO INDICATE 15-20 DEGREES OFF. REPLACED I404, I406, I403, I407, C413, C430 AND C438.  NO HELP.  	REPLACED I408 AND C438, I406.  TROUBLESHOT AND REPAIRED A BROKEN FOIL UNDER I404.  REPAIRED PROBLEM.  RMI AND VOR BEARIN	GS OUT OF TOLERANCE.  ALIGNED THE VOR AND RMI BOARDS.  BENCH CHECK GOOD.				1	G	7	2 	3U			 	H1NE    					 
2001050700559	20010507	00559		2001	5	7	HEEA072597       	4	20010419	G	2312	VFS10902	ANTENNA         			SKRSKY	S76   	S76A        	8143006	NE  										VHF	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911MJ					760231				REPORTED TO TRANSMIT GARBLED. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U			 	H1NE    					 
2001050700560	20010507	00560		2001	5	7	HEEA072598       	4	20010419	G	2340	A3016W	INTERPHONE      			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5128					760181				AFTER UNIT WARMS UP, TRANSMITS AND RECEIVES BROKEN. PERFORMED PRELIMINARY INSPECTION.  FOUND AMP BOARD AR1 AND TRANSISTO	R Q8 BAD, REPLACED SAME.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2001050700561	20010507	00561	NE  	2001	5	7	HEEA072599       	1	20010419	G	2510	A1077B	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4253S					760035				WOULD NOT PULL WITH GENERATORS ON THE LINE, FOUND LOW RESISTANCE BETWEEN X1 AND X2. SENT TO PRECISION AVIONICS & INSTR. 	INC. FOR INSPECTION AND REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001050700562	20010507	00562	SW  	2001	5	7	HEEA072600       	1	20010419	G	3340	ACR4F	LIGHT           			BELL  	412   	412         	1182202	SW  										EXTERNAL	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893N					33010				NOT WORKING. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001050900106	20010509	00106	SW  	2001	5	9	HEEA072601       	1	20010416	G	2822	205061635005	SWITCH          			BELL  	412   	412         	1182202	SW  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BOOST PUMP LIGHT WILL NOT GO OUT.						1	G	7	2 	4U			 	H4SW    					 
2001050900107	20010509	00107	NE  	2001	5	9	HEEA072602       	2	20010416	G	7532	3043023	BLEED VALVE     			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	3893P					33012	CPPS62415			IN CRUISE FLIGHT OBSERVED A 6 PERCENT TORQUE SPLIT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050900108	20010509	00108	SW  	2001	5	9	HEEA072603       	1	20010416	G	2435	200SGL132Q	STARTER GEN     			BELL  	206   	206L1       	1182107	SW  										ENGINE	VIBRATION       	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	03	2761N	2032 				45277				HIGH FREQUENCY VIBRATION.  ALSO THERE IS A CONSIDERABLE AMOUNT OF RUST COLORED RESIDUE OR DUST COMING FROM THE FRONT BEA	RING. REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U			 	H2SW    					 
2001050900109	20010509	00109	NE  	2001	5	9	HEEA072604       	2	20010416	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1 ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				NR 1 ENGINE OSCILLATES DURING POWER TRANSITION AT APPROX. 80 PERCENT TORQUE. FOUND GOVERNOR WAS HANGING.  FOUND INTERIOR	 OF UNIT VERY DIRTY WHICH CAUSED THE FLYWEIGHTS TO STICK.  CLEANED FLYWEIGHTS AND REPLACED FLYWEIGHT PINS DUE TO WEAR.  	UNIT TESTED OK.				1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050900110	20010509	00110	SW  	2001	5	9	HEEA072605       	1	20010416	G	6710	C4264215	SLEEVE          			BELL  	206   	206L3       	1182108	SW  										M/R CONTROL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8587X					51464				CAUSING EXCESSIVE INTERNAL LEAKAGE DURING TESTING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050900111	20010509	00111	GL  	2001	5	9	HEEA072606       	2	20010416	G	7421	CH34187A	IGNITER         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610C					51425				AIRCRAFT HAS DELAYED LIGHT OFF AFTER ENGINE WASH. REPLACED WITH SERVICEABLE IGNITER.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900112	20010509	00112	SW  	2001	5	9	HEEA072607       	1	20010416	G	6730	206076031023	SERVO           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										SPOOL STICKS IN SLEEVE OF LAP ASSY.  SUSPECT DEFECTIVE LAPPING.						1	G	7	1 	3U			 	H2SW    					 
2001050900113	20010509	00113	SW  	2001	5	9	HEEA072608       	1	20010416	G	6730	C4264113	PLUG            		206076062003	BELL  	206   	206L3       	1182108	SW  										CYLINDER	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	937S				RH3037A	51258				FOUND PLUG STICKS IN SLEEVE AND SPRING STICKS ON SPOOL. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050900114	20010509	00114	SW  	2001	5	9	HEEA072609       	1	20010416	G	6730		SERVO           		206076062003	BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03					RH0958					CAUSING EXTERNAL LEAKAGE OF SERVO DURING TESTING.  FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR 	WARRANTY REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001050900115	20010509	00115	SW  	2001	5	9	HEEA072610       	1	20010416	G	6730		SERVO           		206076062003	BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	49EA				RH3886A	51507				CAUSING EXCESSIVE INTERNAL LEAKAGE.    FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REP	AIR.					1	G	7	1 	3U			 	H2SW    					 
2001050900116	20010509	00116	SW  	2001	5	9	HEEA072611       	1	20010416	G	6730		SERVO           		206076062003	BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	206FS				RH1092	51506				CAUSING EXCESSIVE INTERNAL LEAKAGE.    FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REP	AIR.					1	G	7	1 	3U			 	H2SW    					 
2001050900117	20010509	00117		2001	5	9	HEEA072612       	4	20010417	G	3444	071111400	CONNECTOR       			BELL  	206   	206L1       	1182107	SW  										ALTIMETER	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5744Y					45465				ANTENNA CABLE CONNECTOR LOOSE FROM CABLE. INSPECTED ANTENNA AND FOUND BROKEN BEYOND REPAIR.  SCRAPPED ANTENNA.						1	G	7	1 	3U			 	H2SW    					 
2001050900118	20010509	00118		2001	5	9	HEEA072613       	4	20010417	G	3444	071111401	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	UNRELIABLE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141BH					51303				INTERMITTENT AND UNRELIABLE.						1	G	7	1 	3U			 	H2SW    					 
2001050900119	20010509	00119		2001	5	9	HEEA072614       	4	20010417	G	3444	071111401	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				ANTENNA HAS A 50 FOOT ERROR.						1	G	7	1 	3U			 	H2SW    					 
2001050900120	20010509	00120		2001	5	9	HEEA072615       	4	20010417	G	3442		WIRE            			BELL  	206   	206L3       	1182108	SW  										ANTENNA	SEPARATED       	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X				13278	51495				ANTENNA CABLE PULLED OUT.						1	G	7	1 	3U			 	H2SW    					 
2001050900121	20010509	00121		2001	5	9	HEEA072616       	4	20010417	G	3452	071119208	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				DISPLAY BLANKS OUT WHEN CHANGING DIGITS. PERFORMED PRELIMINARY INSPECTION AND REPLACED DISPLAY LENS AND I203, I204, I205	 AND I206 IC CHIPS.  NO HELP.  FOUND J303 FLEX CABLE BAD.  REPLACED J303 CABLE, I303 IC CHIP, I306 IC CHIP AND I202 IC C	HIP.  NO HELP.				1	G	7	2 	4U			 	H4SW    					 
2001050900122	20010509	00122		2001	5	9	HEEA072617       	4	20010417	G	3454	069102505	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										VOR SYSTEM	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077B					52037				WEAK RECEIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND MODULATION LOW AND WILL NOT ADJUST.  REPLACED Q313, Q312 AND R505	.  ALSO FOUND NAV RECEIVER WEAK.  TROUBLESHOT AND FOUND SEVERAL COIL AND INDUCTORS FROZEN.  REPLACED L202, L206, L300, L	301, L303 AND L304. ALSO REPLACED T205.  COMM RECEIVER SENSITIVITY VERY WEAK AND WILL NOT ADJUST.				1	G	7	1 	3U			NC	H2SW    					 
2001050900123	20010509	00123		2001	5	9	HEEA072618       	4	20010417	G	2312	064100900	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				ON INITIAL INSTALLATION UNIT WOULD NOT TRANSMIT DURING FUNCTIONAL TEST. FOUND MODULATION WEAK WHEN UNIT WAS COOL AND WOU	LD GO UP AS UNIT WARMED UP.  REPLACED CR325 DIODE AND REALIGNED TRANSMITTER.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	4U			 	H4SW    					 
2001050900124	20010509	00124		2001	5	9	HEEA072619       	4	20010417	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WILL NOT RECEIVE. REMOVED BROKEN PIN FROM RF CONNECTOR.  REMOVED CORROSION FROM CHASIS.  ADJUSTED C/N SQUELCH, CARRIER S	QUELCH, MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900125	20010509	00125		2001	5	9	HEEA072620       	4	20010417	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	OUT OF ADJ      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				TRANSMIT SCRATCHY.  FOUND RF CONNECTOR LOOSE ON UNIT. TIGHTENED RF CONNECTOR.  ALIGNED TRANSMITTER.  REPAIRED.  ADJUSTED	 CARRIER SQUELCH.  REMOVED CORROSION FROM CHASIS.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900126	20010509	00126		2001	5	9	HEEA072621       	4	20010417	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				INOPERATIVE, WILL NOT COME ON. FOUND FUSE OPEN.  REPLACED HEADER AND APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL.  	ADJUSTED C/N SQUELCH, MIC GAIN, AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900127	20010509	00127		2001	5	9	HEEA072622       	4	20010417	G	2312	064102302	RECEIVER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				SQUELCH STAYS ON. ALIGNED RECEIVER SEVERAL TIMES.  SWAPPED Q317 AND Q319 TRANSISTORS.  REALIGNED RECEIVER BOARD.  REPLAC	ED Q304, Q305, Q306, Q307, Q308, Q317, Q318, Q319, Q320 AND Q321 TRANSISTORS AND I301 IC CHIP.  ALSO REPLACED BROKEN NAM	EPLATE.  ADJUSTED VCO VOLTAGE AND REALIGNED RECEIVER.  REPLACED RECEIVER BOARD.  BENCH CHECK GOOD.				2	G	7	2 	4U			 	H10SW   					 
2001050900128	20010509	00128		2001	5	9	HEEA072623       	4	20010417	G	2312	064105430	TRANSCEIVER     			BELL  	407   	407         	       	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				INTERMITTENT RADIO WOULD NOT BREAK SQUELCH. FOUND LENS BAD AND MHZ SWITCH HOUSING BAD.  REPLACED SWITCH HOUSING, LENS AN	D FOUND POWER OUT LOW.  ADJUSTED.  REPLACED COIL T604.  REPAIRED.  ALSO FOUND MODULATION DISTORTED.  REPLACED TRANSISTOR	 KIT Q124, Q130.  REPAIRED.  BENCH CHECK GOOD.				1	G	7	1 	3U			O	H2SW    					 
2001050900129	20010509	00129		2001	5	9	HEEA072624       	4	20010417	G	3422	060001500	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				D.G. DOES NOT TRACK IN TURNS.						1	G	7	1 	3U			 	H2SW    					 
2001050900130	20010509	00130		2001	5	9	HEEA072625       	4	20010417	G	3422	060001500	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				CAUSES HIS TO STICK AND BE ERRATIC.						1	G	7	1 	3U			 	H2SW    					 
2001050900131	20010509	00131		2001	5	9	HEEA072626       	4	20010417	G	3444	066106103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				ERRATIC AND INACCURATE READINGS.						1	G	7	1 	3U			 	H2SW    					 
2001050900132	20010509	00132		2001	5	9	HEEA072627       	4	20010417	G	3444	066106103	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										RADAR ALTIMETER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				RADAR ALTIMETER ERRATIC.						1	G	7	1 	3U			 	H2SW    					 
2001050900133	20010509	00133		2001	5	9	HEEA072628       	4	20010417	G	3444	066106103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141BH					51303				WILL NOT INDICATE CORRECT ALTITUDE.						1	G	7	1 	3U			 	H2SW    					 
2001050900134	20010509	00134		2001	5	9	HEEA072629       	4	20010417	G	3444	066106103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8587X					51464				ABOVE 300 FEET READINGS ARE ERRATIC OVER ROUGH TERRAIN.						1	G	7	1 	3U			 	H2SW    					 
2001050900135	20010509	00135		2001	5	9	HEEA072631       	4	20010417	G	3444	066106103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				50 FOOT INDICATING ERROR.						1	G	7	1 	3U			 	H2SW    					 
2001050900136	20010509	00136		2001	5	9	HEEA072632       	4	20010417	G	3452	066106200	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				KNOB DEFECTIVE. PERFORMED PRELIMINARY INSPECTION.  REPLACED KNOB SHAFT.  TRANSMIT POWER WEAK.  INSTALLED V101 REPAIRED. 	 FOUND UNIT MISSING IDENT BUTTON.  INSTALLED BUTTON.  ADJUSTED PULSE WIDTH.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001050900137	20010509	00137		2001	5	9	HEEA072633       	4	20010417	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				TRANSPONDER WILL NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION.  FOUND UNIT NOT RECEIVING OR TRANSMITTING.  FOUND V101 	TUBE BAD.  REPLACED V101 TUBE.  REPAIRED.  ALSO FOUND SWITCH PANEL BAD.  REPLACED.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001050900138	20010509	00138		2001	5	9	HEEA072634       	4	20010417	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L4       	1182110	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077F					52038				REPLY LIGHT INOPERATIVE.						1	G	7	1 	3U			NC	H2SW    					 
2001050900139	20010509	00139		2001	5	9	HEEA072635       	4	20010417	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				WILL NOT COME ON.						1	G	7	1 	3U			 	H2SW    					 
2001050900140	20010509	00140		2001	5	9	HEEA072636       	4	20010417	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31821					51076				TRANSMITS INTERMITTENTLY.  MTL LOW.  CANNOT MEASURE FREQUENCY.						1	G	7	1 	3U			 	H2SW    					 
2001050900141	20010509	00141		2001	5	9	HEEA072637       	4	20010417	G	3451	066106600	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										DME	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5009N					30936				NO OUTPUT TO THE INDICATOR.						1	G	7	1 	4U			 	H4SW    					 
2001050900142	20010509	00142		2001	5	9	HEEA072638       	4	20010417	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										VOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				MARKER BEACON WOULD NOT TEST. PERFORMED PRELIMINARY INSPECTION AND REPLACED FRONT CONNECTOR J6341 BECAUSE OF A BAD PIN. 	 REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900143	20010509	00143		2001	5	9	HEEA072639       	4	20010417	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										GLIDE SLOPE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				GLIDE SLOPE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND REPLACED TRANSISTOR Q311.  REPAIRED.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050900144	20010509	00144		2001	5	9	HEEA072640       	4	20010417	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										GLIDE SLOPE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				GLIDE SLOPE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND FOUND GS NEEDLE PEGS OUT WHEN VIBRATED.  REPLACED RECEPTAC	LES I-5 ON GLIDESLOPE BOARD.  REPAIRED.  ADJUSTED VOR HEADING.  ADJUSTED HI/LOW SENSE ON MARKER BEACON.  BENCH CHECK GOO	D.				1	G	7	2 	4U			 	H4SW    					 
2001050900145	20010509	00145		2001	5	9	HEEA072641       	4	20010417	G	3444	066304400	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ERRATIC IN FLIGHT.						1	G	7	2 	4U			 	H4SW    					 
2001050900146	20010509	00146		2001	5	9	HEEA072642       	4	20010417	G	3444	066305401	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				ERRATIC AND INACCURATE.						1	G	7	1 	3U			 	H2SW    					 
2001050900147	20010509	00147		2001	5	9	HEEA072643       	4	20010417	G	3444	066305401	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8593X					51509				WILL NOT INDICATE OR POWER UP.						1	G	7	1 	3U			 	H2SW    					 
2001050900148	20010509	00148		2001	5	9	HEEA072644       	4	20010417	G	3444	066305401	INDICATOR       			BELL  	407   	407         	       	SW  										RADAR ALTIMETER	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				INTERMITTENT..						1	G	7	1 	3U			O	H2SW    					 
2001050900149	20010509	00149		2001	5	9	HEEA072645       	4	20010417	G	3444	066305401	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				NEEDLE READS LOW. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050900150	20010509	00150		2001	5	9	HEEA072646       	4	20010417	G	3444	066305401	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141BH					51303				INTERMITTENT, UNRELIABLE WHEN WORKING. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001050900151	20010509	00151		2001	5	9	HEEA072647       	4	20010417	G	3432	066400700	RECEIVER        			BELL  	412   	412         	1182202	SW  										VOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				WILL NOT RECEIVE. PERFORMED PRELIMINARY INSPECTION.  REPLACED OPEN FUSE F501.  REPAIRED PROBLEM.  ADJUSTED LOCALIZER DEV	IATION.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900152	20010509	00152		2001	5	9	HEEA072648       	4	20010417	G	3453	066402600	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										LORAN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X					51494				UNABLE TO PUT IN A DIFFERENT WAYPOINT DUE TO KNOB OUT. PERFORMED PRELIMINARY INSPECTION.  FOUND S202 SWITCH BROKEN AND R	ETAINER RING MISSING FROM END OF PULL SCAN KNOB SHAFT.  REPLACED S202 SWITCH AND RETAINER RING.  REPAIRED.  BENCH CHECK 	GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001050900153	20010509	00153		2001	5	9	HEEA072649       	4	20010417	G	3453	066402600	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										LORAN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				INOPERATIVE.  NO DISPLAY.						1	G	7	1 	3U			 	H2SW    					 
2001050900154	20010509	00154		2001	5	9	HEEA072651       	4	20010418	G	3453	066402600	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										LORAN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				SCREEN GOES BLANK AFTER EXTENDED USE.  SUSPECT OVERHEATING DUE TO FAULTY COOLING FAN.						1	G	7	1 	3U			 	H2SW    					 
2001050900155	20010509	00155	SW  	2001	5	9	HEEA072652       	1	20010418	G	2436	163404751	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				GENERATOR KICKS OFF LINE.						1	G	7	1 	3U			 	H2SW    					 
2001050900156	20010509	00156	GL  	2001	5	9	HEEA072653       	2	20010418	G	7261	174000101	FILTER          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5007Q					45187				COULD NOT GET FACET FILTER TO STOP LEAKING.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900157	20010509	00157	GL  	2001	5	9	HEEA072654       	2	20010418	G	7261	174000103	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	6610C					51425				UNABLE TO STOP FILTER HOUSING FROM LEAKING. SENT TO PUROLATOR FACETS FOR INSPECTION AND REPAIR.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2003081500050	20030815	00050	SW  	2003	8	15	HEEA072655       	1	20010418	G	7910	1740352	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				BUTTON WOULD NOT EXTEND DURING BYPASS CHECK. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050900158	20010509	00158	NE  	2001	5	9	HEEA072657       	2	20010418	G	7412	103815504	EXCITER         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WEAK.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050900159	20010509	00159		2001	5	9	HEEA072658       	4	20010418	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				CDI OFF FLAG DISPLAYS INTERMITTENTLY. SENT TO MASCO FOR WARRANTY REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001050900160	20010509	00160		2001	5	9	HEEA072659       	4	20010418	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				PRECESSES.						1	G	7	2 	4U			 	H4SW    					 
2001050900161	20010509	00161		2001	5	9	HEEA072660       	4	20010418	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				RT FLAG STICKS TO THE RIGHT.						1	G	7	2 	4U			 	H4SW    					 
2001050900162	20010509	00162		2001	5	9	HEEA072661       	4	20010418	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				ADI TUMBLES WHEN POWER IS APPLIED.						1	G	7	2 	4U			 	H4SW    					 
2001050900163	20010509	00163	GL  	2001	5	9	HEEA072662       	2	20010418	G	7261	174000101	FILTER          			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3116P					51530				LEAKING.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001050900164	20010509	00164		2001	5	9	HEEA072663       	4	20010418	G	2300	122024102	CONTROL UNIT    			BELL  	407   	407         	       	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	495PH					53397				INOPERATIVE.  LIGHTS WONT PULSE AND WONT ILLUMINATE.						1	G	7	1 	3U			O	H2SW    					 
2001050900165	20010509	00165	SW  	2001	5	9	HEEA072664       	1	20010418	G	3340	122024102	CONTROL UNIT    			BELL  	407   	407         	       	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	719PH					53266				WHEN BATTERY SWITCH IS TURNED ON, FWD LANDING WOULD NOT TURN OFF.  ALSO FWD LIGHT WOULD NOT PULSATE.						1	G	7	1 	3U			O	H2SW    					 
2001050900166	20010509	00166		2001	5	9	HEEA072666       	4	20010418	G	2311	4000038	TRANSMITTER     			BELL  	206   	206L4       	1182110	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				CANNOT GET SQUELCH TEST OR ANY TRANSMISSION FROM ANY CHANNEL ON FM RADIO. REPLACED VOLUME CONTROL, VOLUME KNOB AND FRONT	 PANEL.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	3U			NC	H2SW    					 
2001050900167	20010509	00167		2001	5	9	HEEA072667       	4	20010418	G	2311	4000038	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				RATCHETING VOLUME KNOB. REPLACED VOLUME POTENTIOMETER.  REPAIRED PROBLEM.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001050900168	20010509	00168		2001	5	9	HEEA072668       	4	20010418	G	2311	4000038	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				INTERMITTENT. REPLACED VOLUME POTENTIOMETER, VOLUME KNOB AND CHANNEL KNOB.  REPAIRED PROBLEM.  BENCH CHECK GOOD.						1	G	7	1 	3U			 	H2SW    					 
2001050900169	20010509	00169		2001	5	9	HEEA072669       	4	20010418	G	2312	4000103000	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5744Y					45465				HIGH LEVEL OF SQUELCH BLEEDING OVER INTO ALL AUDIO SYSTEMS. FOUND CORROSION ON UNIT.  CLEANED CORROSION FROM UNIT.  FOUN	D INTERMITTENT TRANSMIT ON HIGHER FREQUENCIES 469.9875 MHZ.  ALIGNED TRANSMITTER TO SPECS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001050900170	20010509	00170		2001	5	9	HEEA072670       	4	20010418	G	2312	4000103000	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5744Y					45465				FM UHF BAND INTERMITTENTLY DOES NOT TRANSMIT OR RECEIVE.						1	G	7	1 	3U			 	H2SW    					 
2001050900171	20010509	00171		2001	5	9	HEEA072671       	4	20010418	G	2211	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				WONT HOLD ALTITUDE.						1	G	7	2 	4U			 	H4SW    					 
2001050900172	20010509	00172	SW  	2001	5	9	HEEA072672       	1	20010418	G	6710	412001300105	BELLCRANK       			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900173	20010509	00173	SW  	2001	5	9	HEEA072673       	1	20010418	G	6220	412010216105	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BEARING RETAINING RING POPPED OUT OF GROOVE.  ALSO BEARING SPINS IN HOUSING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900174	20010509	00174	SW  	2001	5	9	HEEA072674       	1	20010418	G	6220	412010216107	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BEARING FROZEN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001051000118	20010510	00118	SW  	2001	5	10	HEEA072675       	1	20010418	G	5610	412018060111	CAM             			BELL  	412   	412         	1182202	SW  										WINDOW	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WORN WINDOW. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900175	20010509	00175	SW  	2001	5	9	HEEA072676       	1	20010418	G	5310		STRUCTURE       			BELL  	412   	412         	1182202	SW  										ENGINE BAY	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				ENGINE BAY STRUCTURE DELAMINATED.						1	G	7	2 	4U			 	H4SW    					 
2001050900176	20010509	00176	SW  	2001	5	9	HEEA072677       	1	20010418	G	6220	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				RUBBER IS DAMAGED.						1	G	7	2 	4U			 	H4SW    					 
2001050900177	20010509	00177	SW  	2001	5	9	HEEA072678       	1	20010418	G	6220	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				RUBBER LORD MOUNT WEAR FROM OIL. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900178	20010509	00178	SW  	2001	5	9	HEEA072679       	1	20010418	G	6220	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				RUBBER WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900179	20010509	00179	SW  	2001	5	9	HEEA072680       	1	20010418	G	6220	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				RUBBER EXTRUDED.						1	G	7	2 	4U			 	H4SW    					 
2001050900180	20010509	00180	SW  	2001	5	9	HEEA072681       	1	20010419	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				FORCE TRIM STICKING.						1	G	7	2 	4U			 	H4SW    					 
2001050900181	20010509	00181	SW  	2001	5	9	HEEA072682       	1	20010419	G	7330	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										UNABLE TO CALIBRATE FUEL SYSTEM.						1	G	7	1 	3U			 	H2SW    					 
2001050900182	20010509	00182	SW  	2001	5	9	HEEA072683       	1	20010419	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WILL NOT ENGAGE OR SPIN.						2	G	7	2 	4U			 	H10SW   					 
2001050900183	20010509	00183	SW  	2001	5	9	HEEA072684       	1	20010419	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STICKS EXENDED.						1	G	7	2 	4U			 	H4SW    					 
2001050900184	20010509	00184		2001	5	9	HEEA072685       	4	20010419	G	3413	44600045800	INDICATOR       			BELL  	407   	407         	       	SW  										VERTICAL SPEED	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				VERTICAL SPEED INDICATOR STICKING. SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2001050900185	20010509	00185	SW  	2001	5	9	HEEA072686       	1	20010419	G	7333	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										TRANS PUMPS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				NR 1 AND 2 TRANSFER PUMPS WOULD NOT SHUT OFF AFTER FORWARD FUEL TANKS EMPTIED.						1	G	7	2 	4U			 	H4SW    					 
2001050900186	20010509	00186	SW  	2001	5	9	HEEA072687       	1	20010419	G	7333	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				CAUSES FUEL QUANTITY INDICATOR RO READ ZERO.						1	G	7	2 	4U			 	H4SW    					 
2001050900187	20010509	00187	SW  	2001	5	9	HEEA072688       	1	20010419	G	7333	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				LOW FUEL LIGHT COMES ON AT 1320 LBS.						1	G	7	2 	4U			 	H4SW    					 
2001050900188	20010509	00188	SW  	2001	5	9	HEEA072689       	1	20010419	G	7333	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				LOW FUEL LIGHT COMES ON AT 1320 LBS.						1	G	7	2 	4U			 	H4SW    					 
2001050900189	20010509	00189	SW  	2001	5	9	HEEA072690       	1	20010419	G	2140	S5008EC3	HOSE            			BELL  	206   	206L3       	1182108	SW  										HEATER	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	31077					51520				HOSE ASSY WIRE BRAIDING IS CHAFED AND HOSE IS LEAKING. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001051000119	20010510	00119	SW  	2001	5	10	HEEA072691       	1	20010419	G	2140	S5008EC3	HOSE            			BELL  	206   	206L3       	1182108	SW  										HEATER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				FERRULE CRACKED ON HOSE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900190	20010509	00190	SW  	2001	5	9	HEEA072692       	1	20010419	G	2140	S5008EC3	HOSE            			BELL  	206   	206L3       	1182108	SW  										HEATER	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	206LS					51070				HEATER HOSE LEAKING FROM FITTINGS. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900191	20010509	00191	SW  	2001	5	9	HEEA072693       	1	20010419	G	2140	S50301	VALVE           			BELL  	206   	206L3       	1182108	SW  										CABIN HEAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				BALL BEARING AND SPRING CORRODED INSIDE OF VALVE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900192	20010509	00192	SW  	2001	5	9	HEEA072694       	1	20010419	G	2140	S50301	VALVE           			BELL  	206   	206L3       	1182108	SW  										CABIN HEAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				CORRODED BALL BEARING AND SPRING. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900193	20010509	00193		2001	5	9	HEEA072695       	4	20010419	G	3418	SC628P	HORN            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				HORN HAS STEADY SOUND ONLY, MUST PULSATE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900194	20010509	00194	SW  	2001	5	9	HEEA072696       	1	20010419	G	7714	SC628P	HORN            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE UNIT.						1	G	7	1 	3U			 	H2SW    					 
2001050900195	20010509	00195	SW  	2001	5	9	HEEA072697       	1	20010419	G	2140	R02221	VENT            			BELL  	412   	412         	1182202	SW  										HEATER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				HEATER INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900196	20010509	00196		2001	5	9	HEEA072698       	4	20010419	G	3444	DMC632	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										RADAR ALTIMETER	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8594X					51531				CORRODED CAUSING WEAK RECEPTION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050900197	20010509	00197		2001	5	9	HEEA072699       	4	20010419	G	3444	DMC634A	ANTENNA         			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				BASE IS DAMAGED. BASE IS CRACKED.  SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900198	20010509	00198		2001	5	9	HEEA072700       	4	20010419	G	2562	ELT910	ELT             			BELL  	206   	206L4       	1182110	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077F					52038				WOULD NOT SHUT OFF. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001050900199	20010509	00199	SW  	2001	5	9	HEEA072701       	1	20010419	G	2844	BSE20630G	TRANSDUCER      			BELL  	206   	206L3       	1182108	SW  										FUEL PRESSURE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				FUEL PRESSURE GAUGE INTERMITTENTLY PEGS OUT.						1	G	7	1 	3U			 	H2SW    					 
2001050900200	20010509	00200	NE  	2001	5	9	HEEA072702       	2	20010419	G	7420	CH5339901	LEAD            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					IGNITER	BURNED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				BURN HOLE IN LEAD.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001050900201	20010509	00201		2001	5	9	HEEA072703       	4	20010419	G	3423	CB2100T6C	COMPASS         			BELL  	412   	412         	1182202	SW  										COCKPIT	LOW             	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				LOW ON FLUID.						1	G	7	2 	4U			 	H4SW    					 
2001050900202	20010509	00202		2001	5	9	HEEA072704       	4	20010419	G	3423	C2300DL4B	COMPASS         			BELL  	206   	206L1       	1182107	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3178K					45765				INDICATES 25 DEGREES OFF FROM ACTUAL COURSE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001050900203	20010509	00203		2001	5	9	HEEA072705       	4	20010419	G	3423	CB2100T6D	COMPASS         			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				HAS FRICTION LIGHT INTERMITTENT, WILL NOT CALIBRATE.						2	G	7	2 	4U			 	H10SW   					 
2001050900204	20010509	00204		2001	5	9	HEEA072706       	4	20010419	G	3442	MI5851345	INDICATOR       			BELL  	212   	212         	1181420	SW  										RADAR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				DOES NOT PAINT TARGETS. FOUND UNIT HAS NO NOISE, ADJUSTED AUTOMATIC NOISE CONTROL.  TROUBLESHOT VIDEO BOARD AND REPLACED	 R1450 RESISTOR.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	4U			 	H4SW    					 
2001050900205	20010509	00205		2001	5	9	HEEA072707       	4	20010419	G	3442	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				PAINTS FALSE TARGETS AND BAD TEST PATTERN. PERFORMED PRELIMINARY INSPECTION AND ADJUSTED ANC AND INTENSITY.  BENCH CHECK	 GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900206	20010509	00206		2001	5	9	HEEA072708       	4	20010419	G	3442	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WOULD NOT GO INTO TEST MODE.  ALSO HAD FALSE TARGETS ON HIGH RANGE SETTINGS. FOUND DISPLAY TEST PATTERN INTERMITTENTLY D	ROPPING OFF.  FOUND LOGIC NR 1 BOARD CAUSING PROBLEM.  REPLACED LOGIC #1 BOARD FROM P40 INDICATOR.  REPAIRED.  BENCH CHE	CK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001050900207	20010509	00207		2001	5	9	HEEA072709       	4	20010419	G	3442	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				NOT PAINTING PROPER PICTURE. PERFORMED PRELIMINARY INSPECTION.  FOUND SPIKES ON TEST PATTERN.  TROUBLESHOT AND FOUND C12	20 ON LOGIC NR 1 BOARD BAD.  REPLACED C1220.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900208	20010509	00208		2001	5	9	HEEA072710       	4	20010419	G	3442	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WHEN RADAR IS IN STANDBY MODE AZIMUTH LINES ARE VISIBLE. PERFORMED PRELIMINARY INSPECTION.  FOUND LOGIC NR 2 BOARD IC U1	346 HAS COLD SOLDER JOINT ON PIN 9.  RESOLDERED IC.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900209	20010509	00209		2001	5	9	HEEA072711       	4	20010419	G	2561	PHI10090	LIFE VEST       			BELL  	206   	206L4       	1182110	SW  										CABIN	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7074W					52033				FAILED TO PASS 3 MONTH INFLATION TEST.						1	G	7	1 	3U			NC	H2SW    					 
2001050900211	20010509	00211		2001	5	9	HEEA072713       	4	20010419	G	2340	AA34300	INTERPHONE      			BELL  	412   	412         	1182202	SW  										CABIN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				INOPERATIVE - LOW RECEIVE AUDIO.						1	G	7	2 	4U			 	H4SW    					 
2001050900212	20010509	00212		2001	5	9	HEEA072714       	4	20010419	G	2340	AA34300	INTERPHONE      			BELL  	206   	206L1       	1182107	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27766					45312				SENSITIVITY TOO LOW.						1	G	7	1 	3U			 	H2SW    					 
2001050900213	20010509	00213		2001	5	9	HEEA072715       	4	20010419	G	2340	AA95759	CONTROLLER      			SNIAS 	350   	AS350B      	8680801	EU  										AUDIO	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE					3230				MIC STAYS HOT IN VOX POSITION. SENT TO NORTHERN AIRBORNE TECHNOLOGY FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H9EU    					 
2001050900214	20010509	00214		2001	5	9	HEEA072716       	4	20010419	G	2340	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										CABIN	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				BOTH VHF RADIOS WEAK AND GARBLED. PERFORMED PRELIMINARY INSPECTION.  FOUND TRANSMIT LEVELS R36-R41 SET TOO LOW.  SET LEV	ELS TO 9V.  REPAIRED.  ALSO FOUND LIGHT PANEL AND VOLUME AND TRANSMIT KNOBS BAD.  REPLACED.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001050900215	20010509	00215		2001	5	9	HEEA072717       	4	20010419	G	2340	A3016W	INTERPHONE      			BELL  	212   	212         	1181420	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1074C					30989				NO AUDIO OUT AT ANY POSITION ON ROTARY SELECTOR. FOUND R36-R41 TRANSMIT LEVELS ADJUSTED ALL THE WAY DOWN.  ALSO FOUND SW	ITCHES S1, S2, S3, S11, LIGHT PANEL, TRANSMIT AND VOLUME KNOBS ALL BAD.  ADJUSTED TRANSMIT LEVELS ON R36-R41 AND REPLACE	D ALL BAD PARTS.  REPAIRED.  BENCH CHECK GOOD.				1	G	7	1 	4U			 	H4SW    					 
2001050900216	20010509	00216		2001	5	9	HEEA072718       	4	20010419	G	2564	ACR108BP	LIFE RAFT       			BELL  	206   	206L3       	1182108	SW  										EMERGENCY EQUIP	DISLODGED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				DURING POSTFLIGHT INSPECTION, NOTICED THAT LIFE RAFT WAS COMING OUT OF COVER.  FURTHER INVESTIGATION FOUND THAT INFLATIO	N BOTTLE VALVE WAS SLOWLY LEAKING GAS INTO THE RAFT. SENT TO OFFSHORE HELICOPTER SUPPORT FOR WARRANTY REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001050900217	20010509	00217	SW  	2001	5	9	HEEA072719       	1	20010419	G	3030		HEATER          			BELL  	412   	412         	1182202	SW  										PITOT TUBE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				HEATER INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900218	20010509	00218	SW  	2001	5	9	HEEA072720       	1	20010419	G	2422	ASH5845	INVERTER        			BELL  	212   	212         	1181420	SW  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	102PH					30899				NO VOLTAGE OUTPUT.						1	G	7	1 	4U			 	H4SW    					 
2001050900219	20010509	00219	SW  	2001	5	9	HEEA072721       	1	20010419	G	6320	412040123101	QUILL ASSY      			BELL  	412   	412         	1182202	SW  										ROTOR BRAKE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				ROTORBRAKE QUILL LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900220	20010509	00220	SW  	2001	5	9	HEEA072722       	1	20010419	G	5320	412060802117	BRACKET         			BELL  	412   	412         	1182202	SW  										FUSELAGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900221	20010509	00221	SW  	2001	5	9	HEEA072723       	1	20010419	G	5210		BEARING         			BELL  	412   	412         	1182202	SW  										HINGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				BEARINGS WORN AND MAKING MUD. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900222	20010509	00222	SW  	2001	5	9	HEEA072724       	1	20010419	G	5210	412060804101	HINGE           			BELL  	412   	412         	1182202	SW  										PAX DOOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				BROKEN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900223	20010509	00223	SW  	2001	5	9	HEEA072725       	1	20010419	G	5330	412070528107	PANEL           			BELL  	412   	412         	1182202	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900224	20010509	00224	SW  	2001	5	9	HEEA072727       	1	20010419	G	2422	412075101103	INVERTER        			BELL  	412   	412         	1182202	SW  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WOULD NOT TURN ON.						1	G	7	2 	4U			 	H4SW    					 
2001050900225	20010509	00225		2001	5	9	HEEA072728       	4	20010419	G	3442		PLATE           			BELL  	412   	412         	1182202	SW  										ANTENNA	MISSING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				FACE PLATE MISSING.						1	G	7	2 	4U			 	H4SW    					 
2001050900226	20010509	00226		2001	5	9	HEEA072729       	4	20010419	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3911L					33023				KICK OFF IN FLIGHT AND WANDERS AFTER SET IN CRUISE FLIGHT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001050900227	20010509	00227	SW  	2001	5	9	HEEA072730       	1	20010419	G	6220	407010101101	YOKE            			BELL  	407   	407         	       	SW  										MAIN ROTOR HEAD	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH	2481 				53327				AT 2500 HOUR INSPECTION FOUND YOKE DAMAGED IN WEB AREA.  ITEM WAS SENT ON  FOR ULTRASONIC INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2001051000174	20010510	00174		2001	5	10	HEEA072731       	4	20010416	G	3457	8143902240B	GPS             			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	03	855PH					3351				ON CLIMB, GPS SCREEN WENT BLANK AND COCKPIT FILLED WITH A BURNT ELECTRICAL ODOR. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001051000175	20010510	00175		2001	5	10	HEEA072732       	4	20010417	G	2312	069102525	TRANSCEIVER     			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				DOES NOT TRANSMIT OR RECEIVE. FOUND VCO TO BE BAD.						1	G	7	1 	3U			 	H9EU    					 
2001051000176	20010510	00176		2001	5	10	HEEA072733       	4	20010417	G	3444	066106103	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										RADAR ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				WILL NOT SELF TEST PROPERLY.						1	G	7	1 	3U			 	H9EU    					 
2001051000177	20010510	00177	EU  	2001	5	10	HEEA072734       	1	20010419	G	2422	SS50	INVERTER        			SNIAS 	350   	AS350B      	8680801	EU  										ELELCTRICAL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	970AE	689  				3235				NOT CHARGING MEDICAL EQUIPMENT.						1	G	7	1 	3U			 	H9EU    					 
2001050900228	20010509	00228	SW  	2001	5	9	HEEA072746       	1	20010423	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	       	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	276  				53435				FAILED 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2001050900229	20010509	00229	SW  	2001	5	9	HEEA072747       	1	20010423	G	6720	C807382	CONTROL ROD     			BELL  	407   	407         	       	SW  										TAIL ROTOR	INTERFERENCE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	998SP	127  				53403				INSPECTION OF INTERFERENCE BETWEEN T/R CONTROL TUBE AND N1 TELEFLEX CABLE IN ROOF BEAM.  INSPECTION DUE TO FINDING A N1 	TELEFLEX CABLE ROUTED THROUGH THE WRONG LIGHTENING HOLE AND INTERFERING WITH THE T/R CONTROL TUBE.					1	G	7	1 	3U			O	H2SW    					 
2001050900230	20010509	00230	SW  	2001	5	9	HEEA072748       	1	20010423	G	2913	214076334101	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYD SYSTEM	LEAKING         	E			HEEA	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	03	59806					28140				WHILE IN CRUISE FLIGHT, LOST UTILITY HYDRAULIC POWER. RETURNED TO BASE FOR MAINTENANCE.						2	G	7	2 	4U			 	H10SW   					 
2001050900231	20010509	00231	SW  	2001	5	9	HEEA072749       	1	20010424	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										KICKING OFF AT START.						2	G	7	2 	4U			 	H10SW   					 
2001050900232	20010509	00232	SW  	2001	5	9	HEEA072751       	1	20010424	G	6300	214030603111	SUPPORT BRACKET 			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BEARING DOES NOT FIT IN BEARING BORE.						2	G	7	2 	4U			 	H10SW   					 
2001051000120	20010510	00120	SW  	2001	5	10	HEEA072752       	1	20010424	G	6300	214030603111	SUPPORT         			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BEARING DOES NOT FIT IN BEARING BORE.						2	G	7	2 	4U			 	H10SW   					 
2001051000121	20010510	00121	SW  	2001	5	10	HEEA072753       	1	20010424	G	2730	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										NR 1 ELEVATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NR 1 ELEVATOR WONT STAY ON LINE.						2	G	7	2 	4U			 	H10SW   					 
2001051000122	20010510	00122	SW  	2001	5	10	HEEA072754       	1	20010424	G	6300	206001364001	TRUNNION        			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR DR	RATCHETING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARING RATCHETING.						1	G	7	1 	3U			 	H2SW    					 
2001051000123	20010510	00123	SW  	2001	5	10	HEEA072762       	1	20010427	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ROTARY	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STICKS INTERMITTENTLY.						2	G	7	2 	4U			 	H10SW   					 
2001051000124	20010510	00124	SW  	2001	5	10	HEEA072763       	1	20010427	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WILL NOT START ON AIRCRAFT BATTERIES.						2	G	7	2 	4U			 	H10SW   					 
2001051000125	20010510	00125	SW  	2001	5	10	HEEA072764       	1	20010427	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WILL NOT START ON AIRCRAFT BATTERIES.						2	G	7	2 	4U			 	H10SW   					 
2001051000126	20010510	00126	SW  	2001	5	10	HEEA072765       	1	20010427	G	2730	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ELEVATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NR 1 ELEVATOR KICKS OFF LINE.						2	G	7	2 	4U			 	H10SW   					 
2001051000127	20010510	00127	SW  	2001	5	10	HEEA072766       	1	20010427	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WILL NOT ENGAGE.						2	G	7	2 	4U			 	H10SW   					 
2001051000178	20010510	00178	EU  	2001	5	10	HEEA072767       	1	20010423	G	5510		STRUCTURE       			SNIAS 	350   	AS350B      	8680801	EU  										STABILIZER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH	887  				3248				CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2001051500433	20010515	00433	NE  	2001	5	15	HEEA072890       	2	20010501	G	7200	70BM041720	TURBINE         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE	831  				3229	22126			HIGH OIL CONSUMPTION. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001051500434	20010515	00434	NE  	2001	5	15	HEEA072891       	2	20010501	G	7200	70BM041720	TURBINE         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	685  				3230	22072			HIGH OIL CONSUMPTION. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001051500442	20010515	00442	SW  	2001	5	15	HEEA072893       	1	20010430	G	6210	206015001115	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X	120  				51508				NUMBER ONE FINGER ON UPPER SURFACE TRAILING EDGE HAS 7 INCHES OF THE FINGER MISSING. SENT TO BELL HELICOPTER TEXTRON FOR	 CREDIT.					1	G	7	1 	3U			 	H2SW    					 
2001051500443	20010515	00443	SW  	2001	5	15	HEEA072894       	1	20010430	G	6300	214040844109	RETAINER        			BELL  	214   	214ST       	1182106	SW  										M/R DRIVE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PITTING ON SPRAGS. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.						2	G	7	2 	4U			 	H10SW   					 
2001051500444	20010515	00444	SW  	2001	5	15	HEEA072895       	1	20010501	G	2910	212076176001	TUBE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	CRACKED         	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	3911L					33023				DURING CRUISE FLIGHT THE NR 1 HYDRAULIC SYSTEM LIGHT CAME ON. MAINTENANCE FOUND A CRACKED TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001051500445	20010515	00445	SW  	2001	5	15	HEEA072896       	1	20010501	G	2910	M832481906	O-RING          			BELL  	214   	214ST       	1182106	SW  										HYD MOTOR	LEAKING         	E			HEEA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	59806					28140				THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED LEAKING O-RINGS ON HYDRAULIC MOTOR.						2	G	7	2 	4U			 	H10SW   					 
2001051500446	20010515	00446	SW  	2001	5	15	HEEA072897       	1	20010501	G	2910	M832481904	O-RING          			BELL  	214   	214ST       	1182106	SW  										HYD MOTOR	LEAKING         	E			HEEA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	59806					28140				THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED LEAKING O-RINGS ON HYDRAULIC MOTOR.						2	G	7	2 	4U			 	H10SW   					 
2001051500447	20010515	00447	SW  	2001	5	15	HEEA072898       	1	20010501	G	2910	214076333103	MOTOR           			BELL  	214   	214ST       	1182106	SW  										HYD SYSTEM	SEIZED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED SEIZED HYDRAULIC MOTOR.						2	G	7	2 	4U			 	H10SW   					 
2001051500448	20010515	00448	SW  	2001	5	15	HEEA072899       	1	20010501	G	6230	2005712103D	BOLT            			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				CORROSION PITTING ON SURFACE OF BOLTS. REPLACED WITH SERVICEABLE BOLTS.						1	G	7	1 	3U			 	H2SW    					 
2001051500449	20010515	00449	SW  	2001	5	15	HEEA072900       	1	20010501	G	3040	204070907001	CONVERTER       			BELL  	412   	412         	1182202	SW  										WINDSHIELD WIPER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				CONVERTER INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001051500450	20010515	00450	SW  	2001	5	15	HEEA072901       	1	20010501	G	2140	205072277009	VALVE           			BELL  	412   	412         	1182202	SW  										HEATER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WILL NOT REGULATE TEMPERATURE, STAYS FULL HOT.						1	G	7	2 	4U			 	H4SW    					 
2001051500451	20010515	00451	SW  	2001	5	15	HEEA072902       	1	20010501	G	5230		STRUCTURE       			BELL  	206   	206L3       	1182108	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				CRACKED IN SEVERAL PLACES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500452	20010515	00452	SW  	2001	5	15	HEEA072903       	1	20010501	G	6710	206001343001	ELBOW           			BELL  	206   	206L1       	1182107	SW  										CYCLIC	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500453	20010515	00453	SW  	2001	5	15	HEEA072904       	1	20010501	G	6710	206001344001	CYCLIC STICK    			BELL  	206   	206L1       	1182107	SW  										COCKPIT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500454	20010515	00454	SW  	2001	5	15	HEEA072905       	1	20010501	G	6710	206001396001	SHAFT           			BELL  	206   	206L3       	1182108	SW  										CYCLIC STICK	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				THREADS STRIPPED ON SHAFT;  PILOT WAS UNABLE TO FRICTION DOWN CYCLIC STICK. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500455	20010515	00455	SW  	2001	5	15	HEEA072906       	1	20010501	G	6710	206001397101	PIVOT SUPPORT   			BELL  	206   	206L3       	1182108	SW  										CYCLIC	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				BORE FOR BARREL NUTS DAMAGED BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500456	20010515	00456	SW  	2001	5	15	HEEA072907       	1	20010501	G	6710		BEARING         			BELL  	206   	206L1       	1182107	SW  										BELLCRANK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F				RE1927	45244				BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500457	20010515	00457	SW  	2001	5	15	HEEA072908       	1	20010501	G	6710		BEARING         			BELL  	206   	206L1       	1182107	SW  										BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP				RE1303	45521				WORN BEARINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500458	20010515	00458	SW  	2001	5	15	HEEA072909       	1	20010501	G	6710		BEARING         			BELL  	206   	206L1       	1182107	SW  										BELLCRANK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP				RE3050	45521				CENTER BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500459	20010515	00459	SW  	2001	5	15	HEEA072910       	1	20010501	G	6710		BEARING         			BELL  	206   	206L1       	1182107	SW  										BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500460	20010515	00460	SW  	2001	5	15	HEEA072911       	1	20010501	G	6710		BEARING         			BELL  	206   	206L3       	1182108	SW  										BELLCRANK	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500461	20010515	00461	SW  	2001	5	15	HEEA072912       	1	20010501	G	6710		WASHER          			BELL  	206   	206L4       	1182110	SW  										BELLCRANK	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077F					52038				WASHER UNBONDED AND BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001051500462	20010515	00462	SW  	2001	5	15	HEEA072913       	1	20010501	G	6710		BEARING         			BELL  	206   	206L1       	1182107	SW  										BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				WORN BEARINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001051500463	20010515	00463	SW  	2001	5	15	HEEA072914       	1	20010501	G	6710		PAD             			BELL  	206   	206L3       	1182108	SW  										BELLCRANK	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				BUFFER PADS NEAR BEARINGS UNBONDED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001072600082	20010726	00082	GL  	2001	7	26	HEEA073007       	2	20010511	G	7261	6892846	LINE            			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					COMPRESSOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038	CAE847194			LINE IS CHAFED. REPLACED LINE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001072600084	20010726	00084	NE  	2001	7	26	HEEA073008       	1	20010511	G	2435	6854424	SEAL            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					STARTER GEN	DISLODGED       	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	1546K					760082	CAE890071S			IN CRUISE FLIGHT, NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE BETWEEN GREEN ARC AND LOWER RED ARC. MAINTENANCE FOUND STA	RTER GENERATOR SEAL UNSEATED.  REPLACED, SERVICED ENGINE OIL SYSTEM AND RETURNED AIRCRAFT TO SERVICE.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001072600086	20010726	00086	NE  	2001	7	26	HEEA073009       	1	20010511	G	3212		VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										FLOAT BOTTLE	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1545K					760047				WHILE IN FLIGHT THE LT NOSE FLOAT ASSEMBLY STARTED TO DEPLOY. MAINTENANCE FOUND FLOAT VALVE LEAKING INTERNALY AND STARTE	D TO INFLATE BAG.					1	G	7	2 	3U			 	H1NE    					 
2001080300087	20010803	00087		2001	8	3	HEEA073010       	4	20010514	G	3140		LIGHT           																	COCKPIT	ILLUMINATED     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										INSTRUMENT PANEL LIGHT WILL NOT EXTINGUISH.																			 
2001072600090	20010726	00090	NE  	2001	7	26	HEEA073011       	2	20010518	G	7230		BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					COMPRESSOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	720  				3230	22072			CRACKED COMPRESSOR BLADE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001072600096	20010726	00096	NE  	2001	7	26	HEEA073012       	2	20010518	G	7230		BLADE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					COMPRESSOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	720  				3230	22072			CRACKED COMPRESSOR BLADE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001072600102	20010726	00102	SW  	2001	7	26	HEEA073013       	1	20010507	G	2450		HARNESS         			BELL  	412   	412         	1182202	SW  										COCKPIT	CHAFED          	E			HEEA	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	03	142PH					33150				WHILE IN CRUISE FLIGHT THE 115 VOLT AFCS CIRCUIT BREAKER POPPED. MAINTENANCE TURNED BATTERY POWER ON AND THE MASTER CAUT	ION PANEL CIRCUIT BREAKER POPPED ALSO, WITH VISIBLE SMOKE.  FOUND CHAFED WIRE BUNDLE WHERE IT EXITS WINDSHIELD POST AREA	 AT FORWARD EDGE OF R/H PANEL.				1	G	7	2 	4U			 	H4SW    					 
2001072600113	20010726	00113	SW  	2001	7	26	HEEA073014       	1	20010507	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	740PH					53435				READS HIGH 150+ AT TIMES THEN GOES TO 130 WHICH IS STILL 5 TO 10 PSI HIGH PER DIRECT READING GAUGE. SENT TO BELL HELICOP	TER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#715195.					1	G	7	1 	3U			O	H2SW    					 
2001072600120	20010726	00120	SW  	2001	7	26	HEEA073015       	1	20010507	G	6300	407310203101	MOUNT           			BELL  	407   	407         	       	SW  										MAIN ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH	991  				53386				MOUNT SEPARATED.						1	G	7	1 	3U			O	H2SW    					 
2001072600131	20010726	00131	SW  	2001	7	26	HEEA073016       	1	20010507	G	2424	206075447101	VOLT REGULATOR  			BELL  	407   	407         	       	SW  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				WILL NOT PICK UP LOAD.						1	G	7	1 	3U			O	H2SW    					 
2001072600137	20010726	00137	SW  	2001	7	26	HEEA073017       	1	20010507	G	6321	206340301101	DISK            			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	3135 				53142				WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#715175.						1	G	7	1 	3U			O	H2SW    					 
2001072600145	20010726	00145	SW  	2001	7	26	HEEA073022       	1	20010507	G	6730	212076005105	CYLINDER        			BELL  	412   	412EP       	1182205	SW  										M/R CONTROL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6106C	196  				36257				LEAKING FROM BOTTOM WEEP HOLE.						1	G	7	2 	4U			 	H4SW    					 
2001072600146	20010726	00146	SW  	2001	7	26	HEEA073023       	1	20010507	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										BOOST PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				LEFT HAND BOOST PUMP LIGHT WOULD NOT COME ON.						1	G	7	1 	3U			O	H2SW    					 
2001072600148	20010726	00148	SW  	2001	7	26	HEEA073024       	1	20010507	G	7921	406360500101	COOLER          			BELL  	407   	407         	       	SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	510PH					53209				COOLER LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600150	20010726	00150	SW  	2001	7	26	HEEA073025       	1	20010507	G	6410	406016100119	BLADE           			BELL  	407   	407         	       	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				VOID BETWEEN SKIN AND BLOCK.						1	G	7	1 	3U			O	H2SW    					 
2001072600151	20010726	00151	SW  	2001	7	26	HEEA073026       	1	20010507	G	3246	407050201101	CROSSTUBE       			BELL  	407   	407         	       	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	409PH	4056 				53059				CORROSION, SENDING IN FOR EVALUATION DUE TO POSSIBLE MFG. DEFECT.						1	G	7	1 	3U			O	H2SW    					 
2001072600153	20010726	00153	SW  	2001	7	26	HEEA073027       	1	20010507	G	6520	406040400117FM	GEARBOX         			BELL  	407   	407         	       	SW  										TAIL ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH	2282 				53277				TAIL ROTOR GEARBOX MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2001072600154	20010726	00154	SW  	2001	7	26	HEEA073028       	1	20010507	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	       	SW  										MAIN ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	1231 				53378				SWASHPLATE BEARING HAS A ROUGH SOUND WHEN ROTATED.						1	G	7	1 	3U			O	H2SW    					 
2001072600155	20010726	00155	SW  	2001	7	26	HEEA073029       	1	20010507	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	       	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				ROTOR NEEDLE INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001072600156	20010726	00156	SW  	2001	7	26	HEEA073030       	1	20010507	G	7921	406360500101	COOLER          			BELL  	407   	407         	       	SW  										ENGINE OIL	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	409PH					53059				OIL COOLER OVERHEATING.						1	G	7	1 	3U			O	H2SW    					 
2001072600157	20010726	00157	SW  	2001	7	26	HEEA073031       	1	20010507	G	6220	407010103101	PITCH HORN      			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH	2481 				53327				CORROSION BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2001072600158	20010726	00158	SW  	2001	7	26	HEEA073032       	1	20010507	G	6220	406010107105	ADAPTER         			BELL  	407   	407         	       	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				MAIN ROTOR HUB ADAPTER CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2001072600161	20010726	00161	SW  	2001	7	26	HEEA073036       	1	20010507	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	       	SW  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				BOOST PUMP CARTRIDGE INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001072600162	20010726	00162	SW  	2001	7	26	HEEA073037       	1	20010507	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				BLOWER HOUSING CRACKED AND POPPED RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2001072600164	20010726	00164	SW  	2001	7	26	HEEA073038       	1	20010507	G	6500	407040316101	FLYWHEEL        			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FLYWHEEL HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001072600165	20010726	00165	SW  	2001	7	26	HEEA073039       	1	20010507	G	6720		BOLT            			BELL  	407   	407         	       	SW  										TAIL ROTOR	SEIZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				LINK BOLT FROZEN IN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001072600166	20010726	00166	SW  	2001	7	26	HEEA073040       	1	20010507	G	3212	206050247137	COVER           			BELL  	407   	407         	       	SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				FLOAT COVER HAS TORN END CAPS.						1	G	7	1 	3U			O	H2SW    					 
2001072600167	20010726	00167	SW  	2001	7	26	HEEA073041       	1	20010507	G	3212	212073905001	INDICATOR       			BELL  	407   	407         	       	SW  										FLOAT BOTTLE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				FLOAT BOTTLE INDICATOR FULL OF WATER, NOT READABLE.						1	G	7	1 	3U			O	H2SW    					 
2001072600168	20010726	00168	SW  	2001	7	26	HEEA073042       	1	20010507	G	6220	407010105101	STUD            		407010100115	BELL  	407   	407         	       	SW  										DROOP STOP	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH				A351	53327				STUD CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600169	20010726	00169	SW  	2001	7	26	HEEA073043       	1	20010507	G	6710		BEARING         			BELL  	407   	407         	       	SW  										UNIVERSAL	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	610  				53397				UNIVERSAL UPPER BEARING LOOSE.						1	G	7	1 	3U			O	H2SW    					 
2001072600170	20010726	00170	SW  	2001	7	26	HEEA073044       	1	20010507	G	7120	407060111101	MOUNT           			BELL  	407   	407         	       	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				WORN BEARING IN ENGINE MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2001072600176	20010726	00176	SW  	2001	7	26	HEEA073045       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				TAG UNREADABLE ON SEAT BELT.						1	G	7	1 	3U			O	H2SW    					 
2001072600177	20010726	00177	SW  	2001	7	26	HEEA073046       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TAG TORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600184	20010726	00184	SW  	2001	7	26	HEEA073047       	1	20010507	G	2840	407362005103	SWITCH          			BELL  	407   	407         	       	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				SWITCH STICKS IN CLOSED POSITION.						1	G	7	1 	3U			O	H2SW    					 
2001072600186	20010726	00186	SW  	2001	7	26	HEEA073048       	1	20010507	G	3212	206050247135	COVER           			BELL  	407   	407         	       	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FLOAT COVER IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600188	20010726	00188	SW  	2001	7	26	HEEA073049       	1	20010507	G	3212	206050247135	COVER           			BELL  	407   	407         	       	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				FLOAT COVER WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600189	20010726	00189	SW  	2001	7	26	HEEA073050       	1	20010507	G	6420	407340339101	BEARING         			BELL  	407   	407         	       	SW  										COOLER BLOWER	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	181  				53396				BEARING MAKING NOISE.						1	G	7	1 	3U			O	H2SW    					 
2001072600190	20010726	00190	SW  	2001	7	26	HEEA073051       	1	20010507	G	3212	70079H100F210	HOSE            			BELL  	407   	407         	       	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				SLIGHT DAMAGE NEAR FITTING.						1	G	7	1 	3U			O	H2SW    					 
2001072600191	20010726	00191	SW  	2001	7	26	HEEA073052       	1	20010507	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				NUT PLATES BAD.						1	G	7	1 	3U			O	H2SW    					 
2001072600194	20010726	00194	SW  	2001	7	26	HEEA073053       	1	20010507	G	6300	407310203101	MOUNT           			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	2481 				53267				WORN RUBBER ON MAIN ROTOR DRIVE MOUNT.						1	G	7	1 	3U			O	H2SW    					 
2001072600196	20010726	00196	SW  	2001	7	26	HEEA073054       	1	20010507	G	6710	406010425107	LEVER           			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	2366 				53159				LEVER WORN AND SLOPPY.						1	G	7	1 	3U			O	H2SW    					 
2001072600197	20010726	00197	SW  	2001	7	26	HEEA073055       	1	20010507	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	2332 				53147				UNIVERSAL ON MAIN ROTOR DRIVE, WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600202	20010726	00202	SW  	2001	7	26	HEEA073056       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				BAD LABELS.						1	G	7	1 	3U			O	H2SW    					 
2001072600203	20010726	00203	SW  	2001	7	26	HEEA073057       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				BAD LABELS.						1	G	7	1 	3U			O	H2SW    					 
2001072600204	20010726	00204	SW  	2001	7	26	HEEA073058       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				BAD LABELS.						1	G	7	1 	3U			O	H2SW    					 
2001072600205	20010726	00205	SW  	2001	7	26	HEEA073059       	1	20010507	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				BAD LABELS.						1	G	7	1 	3U			O	H2SW    					 
2001072600206	20010726	00206	SW  	2001	7	26	HEEA073060       	1	20010509	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				TAIL ROTOR OIL COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600207	20010726	00207	SW  	2001	7	26	HEEA073061       	1	20010509	G	2560		PLACARD         			BELL  	407   	407         	       	SW  										SEAT BELT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				LABEL COMING OFF BELT.						1	G	7	1 	3U			O	H2SW    					 
2001072600208	20010726	00208	SW  	2001	7	26	HEEA073062       	1	20010509	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH				53398	53277				TAIL ROTOR BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600209	20010726	00209	SW  	2001	7	26	HEEA073063       	1	20010509	G	6310	214040841101	SEAL            		406040500123	BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				A3174	53142				FREEWHEEL UNIT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600210	20010726	00210	SW  	2001	7	26	HEEA073064       	1	20010509	G	6310	406340102101	CARBON SEAL     		406040500123	BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				A3174	53142				CARBON SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600211	20010726	00211	SW  	2001	7	26	HEEA073065       	1	20010509	G	3210	407040624101	TUBE            			BELL  	407   	407         	       	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				TUBE WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600212	20010726	00212	SW  	2001	7	26	HEEA073066       	1	20010509	G	3210	407040623101	LINE            			BELL  	407   	407         	       	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				LINE WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600213	20010726	00213	SW  	2001	7	26	HEEA073067       	1	20010509	G	7921	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				OIL COOLER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600214	20010726	00214	SW  	2001	7	26	HEEA073068       	1	20010509	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600215	20010726	00215	SW  	2001	7	26	HEEA073069       	1	20010509	G	5210	206064819005S	SKIN            			BELL  	407   	407         	       	SW  										CREW DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				CORRODED, SENDING IN FOR EVALUATION.  IT HAS BEEN DETERMINED, POSSIBLE MFG DEFECT.  NO PREVENTIVE MAINT BETWEEN 2 METALS	.					1	G	7	1 	3U			O	H2SW    					 
2001072600216	20010726	00216	SW  	2001	7	26	HEEA073070       	1	20010509	G	5210	206064819006S	SKIN            			BELL  	407   	407         	       	SW  										CREW DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				CORRODED, SENDING IN FOR EVALUATION.  IT HAS BEEN DETERMINED, POSSIBLE MFG DEFECT.  NO PREVENTIVE MAINT BETWEEN 2 METALS	.					1	G	7	1 	3U			O	H2SW    					 
2001072600217	20010726	00217	SW  	2001	7	26	HEEA073071       	1	20010509	G	6710	406310404101	ROD END         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	2977 				53159				ROD END ON MAIN ROTOR IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600219	20010726	00219	SW  	2001	7	26	HEEA073072       	1	20010509	G	6710	406010417101	LINER           			BELL  	407   	407         	       	SW  										BEARING	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				BEARING LINER WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072600220	20010726	00220	SW  	2001	7	26	HEEA073073       	1	20010509	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH	463  				53400				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001072600222	20010726	00222	SW  	2001	7	26	HEEA073074       	1	20010509	G	6720	407001026101	TUBE            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				TAIL ROTOR CONTROL TUBE HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001072600223	20010726	00223	SW  	2001	7	26	HEEA073075       	1	20010509	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600224	20010726	00224	SW  	2001	7	26	HEEA073076       	1	20010509	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	730  				53397				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001072600225	20010726	00225	SW  	2001	7	26	HEEA073077       	1	20010509	G	3201	206052105035	CUSHION         			BELL  	407   	407         	       	SW  										MLG	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				CUSHION UNBONDED.						1	G	7	1 	3U			O	H2SW    					 
2001072600226	20010726	00226	SW  	2001	7	26	HEEA073078       	1	20010509	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001072600227	20010726	00227	SW  	2001	7	26	HEEA073079       	1	20010509	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				CRACKED AND WORKING RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2001072600228	20010726	00228	SW  	2001	7	26	HEEA073080       	1	20010509	G	6510	406040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH				PHI0012	53207				COOLER BLOWER SHAFT HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001072600229	20010726	00229	SW  	2001	7	26	HEEA073081       	1	20010509	G	6310	406340102101	CARBON SEAL     			BELL  	407   	407         	       	SW  										TRANSMISSION	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				CARBON SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600230	20010726	00230	SW  	2001	7	26	HEEA073082       	1	20010509	G	6720	PHI407112	TRUNNION        			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				TRUNNION EAR WORN.  LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600231	20010726	00231	SW  	2001	7	26	HEEA073083       	1	20010509	G	6310	406040550101	ADAPTER         			BELL  	407   	407         	       	SW  										TRANSMISSION	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				ADAPTER SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001072600232	20010726	00232	SW  	2001	7	26	HEEA073085       	1	20010509	G	6510	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	190  			PHI0010	53397				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001072600234	20010726	00234	SW  	2001	7	26	HEEA073086       	1	20010509	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	SLOW            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RELEASES SLOW.						2	G	7	2 	4U			 	H10SW   					 
2001072600236	20010726	00236	SW  	2001	7	26	HEEA073087       	1	20010509	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FORE/AFT TRIM RELEASE STICKING.						2	G	7	2 	4U			 	H10SW   					 
2001072600237	20010726	00237	SW  	2001	7	26	HEEA073088       	1	20010509	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	SLIPPED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CLUTCH SLIPPAGE OUT OF LIMITS.						2	G	7	2 	4U			 	H10SW   					 
2001072600239	20010726	00239	SW  	2001	7	26	HEEA073089       	1	20010509	G	7120	209062105001	BEARING         			BELL  	412   	412         	1182202	SW  										MOUNT ROD END	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARINGS EXTREMELY TIGHT.  BURNISHED BEARING USING BOLT AND TURNING SLOWLY.  A SLIVER OF BEARING RACE FELL OUT.  APPAREN	TLY WHAT WAS CAUSING THE TIGHTNESS IN THE FIRST PLACE.  ONCE THIS SLIVER WAS OUT THE BEARINGS ARE TOO LOOSE AND WOULD ON	LY HAVE HALF ITS LIFE.				1	G	7	2 	4U			 	H4SW    					 
2001072600242	20010726	00242	SW  	2001	7	26	HEEA073090       	1	20010511	G	2933	222375019105	TRANSMITTER     			BELL  	214   	214ST       	1182106	SW  										HYD INDICATOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				NR 1 HYDRAULIC PRESSURE GAUGE MALFUNCTIONED. REPLACED PRESSURE GAUGE.						2	G	7	2 	4U			 	H10SW   					 
2001072600243	20010726	00243	SW  	2001	7	26	HEEA073091       	1	20010511	G	6300	407340339101	BEARING         			BELL  	407   	407         	       	SW  										BLOWER SHAFT	FAILED          	E			HEEA	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	740PH	223  				53435				AIRCRAFT DEVELOPED A VIBRATION IN FLIGHT. FOUND FWD. BEARING ON BLOWER SHAFT FAILED.						1	G	7	1 	3U			O	H2SW    					 
2001072600244	20010726	00244	SW  	2001	7	26	HEEA073092       	1	20010514	G	7740	DPUA0101	COMPUTER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	30KH					51527				INTELLASTART CAUTION LIGHTS COMES ON INTERMITTENTLY AND WILL NOT LINK TO LAPTOP COMPUTER.  SYSTEM FAILED DOWNLOAD PORT T	EST.					1	G	7	1 	3U			 	H2SW    					 
2001072600246	20010726	00246	SW  	2001	7	26	HEEA073093       	1	20010514	G	2910		ELBOW           			BELL  	214   	214ST       	1182106	SW  										HYD SYSTEM	CHAFED          	E			HEEA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			SW	03	59806					28140				ON FINAL APPROACH, THE OIL COOLER LIGHT ILLUMINATED. FOUND THE UTILITY HYDRAULIC SYSTEM LOST FLUID.  MAINTENANCE FOUND L	EAK AT ELBOW WHERE THE SUPPORT HAD CHAFED THROUGH DUE TO JAM NUT BEING LOOSE.					2	G	7	2 	4U			 	H10SW   					 
2001072600247	20010726	00247	EU  	2001	7	26	HEEA073094       	1	20010510	G	8010	845UN01Q4AA5F	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  										STARTER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE	105  				3229				VEMD RECORDING START SWITCH.						1	G	7	1 	3U			 	H9EU    					 
2001072600249	20010726	00249	EU  	2001	7	26	HEEA073095       	1	20010510	G	6321	350A32050002	BRAKE ASSY      			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	970AE	282  				3235				OIL SOAKED FROM LEAKING SEAL OF INPUT.						1	G	7	1 	3U			 	H9EU    					 
2001072600251	20010726	00251		2001	7	26	HEEA073096       	4	20010510	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				CANNOT RESET SWEEP SECOND HAND FOR ELAPSED TIMER.						1	G	7	1 	3U			 	H9EU    					 
2001072600252	20010726	00252		2001	7	26	HEEA073097       	4	20010510	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	970AE	754  				3235				PILOT REPORTS SECOND HAND DOESN'T FUNCTION.						1	G	7	1 	3U			 	H9EU    					 
2001072600253	20010726	00253	EU  	2001	7	26	HEEA073098       	1	20010510	G	6730	SC5084	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE	1976 				2653				LEAKED AT TOP SIDE OF PISTON.						1	G	7	1 	3U			 	H9EU    					 
2001072600255	20010726	00255	EU  	2001	7	26	HEEA073099       	1	20010510	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE	3045 				2653				CRACK AT TRIM TAB AREA ON TRAILING EDGE.						1	G	7	1 	3U			 	H9EU    					 
2001072600258	20010726	00258	EU  	2001	7	26	HEEA073100       	1	20010510	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	974AE	374  				2653				LEAKING AT UPPER PISTON SEAL AREA.						1	G	7	1 	3U			 	H9EU    					 
2001072600260	20010726	00260	EU  	2001	7	26	HEEA073101       	1	20010510	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE	473  				3229				SEPARATED AT EDGES.						1	G	7	1 	3U			 	H9EU    					 
2001072600263	20010726	00263		2001	7	26	HEEA073102       	4	20010510	G	3100	614764031	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				NEEDLE STICKS.						1	G	7	1 	3U			 	H9EU    					 
2001072600265	20010726	00265	EU  	2001	7	26	HEEA073103       	1	20010510	G	2910	MA12401	PRESSURE SWITCH 			SNIAS 	350   	AS350B2     	8680813	EU  										HYD SYSTEM	INACCURATE      	E			HEEA	O				OTHER                   				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	4000L					2873				INACCURATE READINGS.						1	G	7	1 	3U			 	H9EU    					 
2001072600267	20010726	00267		2001	7	26	HEEA073104       	4	20010510	G	3100	614764031	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				NOT INDICATING.						1	G	7	1 	3U			 	H9EU    					 
2001072600270	20010726	00270		2001	7	26	HEEA073105       	4	20010510	G	3160	845UN01Q4AA5F	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  										VEMD	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE					3230				FAILURE ON VEMD.						1	G	7	1 	3U			 	H9EU    					 
2001072600272	20010726	00272	EU  	2001	7	26	HEEA073107       	1	20010510	G	3252	350A75208000	DAMPER          			SNIAS 	350   	AS350B      	8680801	EU  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	972AE	295  				3234				LEAKING AROUND SHAFT SEAL.						1	G	7	1 	3U			 	H9EU    					 
2001072600285	20010726	00285	EU  	2001	7	26	HEEA073109       	1	20010510	G	7714	G300103	WARNING SYSTEM  			SNIAS 	350   	AS350B      	8680801	EU  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				ROTOR LIGHT DOES NOT FLASH AT LOWER RPMS.						1	G	7	1 	3U			 	H9EU    					 
2001072600288	20010726	00288	EU  	2001	7	26	HEEA073110       	1	20010510	G	6240	614764031	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	854PH					3248				ROTOR NEEDLE WILL NOT GO ABOVE 340 RPM.						1	G	7	1 	3U			 	H9EU    					 
2001072600290	20010726	00290	EU  	2001	7	26	HEEA073111       	1	20010510	G	6240	G300102	WARNING SYSTEM  			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4034Q					2918				ROTOR ALARM SYSTEM WILL NOT WORK PROPERLY.						1	G	7	1 	3U			 	H9EU    					 
2001072600321	20010726	00321		2001	7	26	HEEA073112       	4	20010510	G	3416	150201182	ALTIMETER       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AE					3229				150 TO 200 FEET OFF ACTUAL ALTITUDE.						1	G	7	1 	3U			 	H9EU    					 
2001072700004	20010727	00004	EU  	2001	7	27	HEEA073113       	1	20010510	G	6240	614764031	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				INDICATOR INOPERATIVE.						1	G	7	1 	3U			 	H9EU    					 
2001072700005	20010727	00005	EU  	2001	7	27	HEEA073114       	1	20010510	G	6340	50071550020	SENSOR          			SNIAS 	350   	AS350B      	8680801	EU  										ROTOR TACH	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				ROTOR TACH FLUCTUATES.  PIN B IN CONNECTOR WILL NOT SEAT.						1	G	7	1 	3U			 	H9EU    					 
2001072700006	20010727	00006	EU  	2001	7	27	HEEA073115       	1	20010510	G	6520		BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466				3811	3004				PITCH CONTROL BEARINGS CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2001072700007	20010727	00007	EU  	2001	7	27	HEEA073116       	1	20010510	G	6410	355A09103600	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TAIL ROTOR BEARINGS CRACKED.						1	G	7	1 	3U			 	H9EU    					 
2001072700012	20010727	00012	SW  	2001	7	27	HEEA073164       	1	20010523	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										CLUTCH HOUSING	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				OIL IN CLUTCH HOUSING ON 250 HOUR INSPECTION.						2	G	7	2 	4U			 	H10SW   					 
2001072700013	20010727	00013	SW  	2001	7	27	HEEA073165       	1	20010524	G	3340	6500306N	RECEPTACLE      			BELL  	407   	407         	       	SW  										TAIL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	719PH					53266				TAIL LIGHT WON'T LIGHT. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001072700016	20010727	00016	SW  	2001	7	27	HEEA073170       	1	20010524	G	7920	204040760109	FILTER ELEMENT  			BELL  	407   	407         	       	SW  										ENGINE OIL	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MAKING METAL. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001072700017	20010727	00017	SW  	2001	7	27	HEEA073172       	1	20010524	G	7932	S207A	GAUGE           			BELL  	407   	407         	       	SW  										OIL LEVEL	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				OIL LEVEL INDICATOR HAZED. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001072700049	20010727	00049	SW  	2001	7	27	HEEA073191       	1	20010524	G	6510	206061432118	INLET           			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				INLET CRACKED; WORN.						1	G	7	1 	3U			O	H2SW    					 
2001072700051	20010727	00051	SW  	2001	7	27	HEEA073192       	1	20010525	G	2841	206063633103	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										FUEL QTY	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NEEDLE STICKS THROUGHOUT SCALE INTERMITTENTLY.						1	G	7	1 	3U			 	H2SW    					 
2001072700053	20010727	00053	SW  	2001	7	27	HEEA073193       	1	20010531	G	6300	212340100103	SEAL            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DEFECTS FOUND ON SEAL LIP.						1	G	7	1 	4U			 	H4SW    					 
2001072700055	20010727	00055	SW  	2001	7	27	HEEA073194       	1	20010531	G	6300	212340105101	SEAL            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DEFECTS FOUND ON SEAL LIP.						1	G	7	1 	4U			 	H4SW    					 
2001072700056	20010727	00056	SW  	2001	7	27	HEEA073195       	1	20010531	G	6300	MS2764642	BEARING         			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	MISMARKED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MISIDENTIFIED.  PICK TICKET SHOWS P/N MS27646-42 BUT TICKET HAS A BOLT P/N UNKNOWN.						1	G	7	1 	4U			 	H4SW    					 
2001072700068	20010727	00068	SW  	2001	7	27	HEEA073197       	1	20010601	G	6300		BEARING         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	2481 				53267				WORN BEARINGS AND BOLT HOLES.  SERIAL NUMBERS REMOVED ARE LK0963 AND LK1030.						1	G	7	1 	3U			O	H2SW    					 
2001072700071	20010727	00071	SW  	2001	7	27	HEEA073198       	1	20010601	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	510PH					53209				BOOST PUMP LIGHT FAILED TO ILLUMINATE.						1	G	7	1 	3U			O	H2SW    					 
2001072700072	20010727	00072	SW  	2001	7	27	HEEA073199       	1	20010601	G	2820	222366621103	FUEL FILTER     			BELL  	407   	407         	       	SW  										ENGINE	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				FUEL FILTER CHAFED ON BOWL.						1	G	7	1 	3U			O	H2SW    					 
2001072700073	20010727	00073	SW  	2001	7	27	HEEA073200       	1	20010601	G	3110	407375001105	INDICATOR       			BELL  	407   	407         	       	SW  										MGT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	493PH					53393				NO INDICATION.						1	G	7	1 	3U			O	H2SW    					 
2001072700076	20010727	00076	SW  	2001	7	27	HEEA073201       	1	20010601	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	       	SW  										MLG FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				WOULD NOT SEAT WHEN SERVICED.						1	G	7	1 	3U			O	H2SW    					 
2001072700085	20010727	00085	SW  	2001	7	27	HEEA073202       	1	20010601	G	6710		BEARING         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH	1291 				53399				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001072700086	20010727	00086	SW  	2001	7	27	HEEA073203       	1	20010601	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	       	SW  										FADEC	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				FADEC DEGRADE LIGHT 3 LIGHTS.						1	G	7	1 	3U			O	H2SW    					 
2001072700087	20010727	00087	SW  	2001	7	27	HEEA073204       	1	20010601	G	6320	407040006107	GEARBOX         			BELL  	407   	407         	       	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	2074 				53199				MAIN ROTOR GEARBOX MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2001072700089	20010727	00089	SW  	2001	7	27	HEEA073205       	1	20010601	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	       	SW  										GENERATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				INTERMITTENT START LIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001072700091	20010727	00091	SW  	2001	7	27	HEEA073206       	1	20010601	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	       	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				INDICATES APPROX. 8% LOW.  INDICATES 0% AT FLIGHT IDLE.						1	G	7	1 	3U			O	H2SW    					 
2001072700093	20010727	00093	SW  	2001	7	27	HEEA073207       	1	20010601	G	7931	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	742PH	26   				53461				OIL PRESSURE DROPPED TO 90 PSI.						1	G	7	1 	3U			O	H2SW    					 
2001072700094	20010727	00094	SW  	2001	7	27	HEEA073210       	1	20010601	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	740PH					53435				TEMP SIDE QUIT INDICATING.						1	G	7	1 	3U			O	H2SW    					 
2001072700095	20010727	00095	SW  	2001	7	27	HEEA073214       	1	20010601	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	723PH					53283				WHEN GAUGE GETS HOT (4 TO 6 MIN) ENG OIL PRESSURE GOES TO ZERO.						1	G	7	1 	3U			O	H2SW    					 
2001072700096	20010727	00096		2001	7	27	HEEA073215       	4	20010601	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         	       	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				LIGHT WILL NOT WORK.						1	G	7	1 	3U			O	H2SW    					 
2001072700097	20010727	00097	SW  	2001	7	27	HEEA073216       	1	20010601	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	       	SW  										FADEC	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	499PH					53400				FADEC FAULT WORD IGN I FLT.						1	G	7	1 	3U			O	H2SW    					 
2001072700098	20010727	00098	SW  	2001	7	27	HEEA073217       	1	20010601	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	       	SW  										MLG FLOAT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				CANNOT SERVICE FLOAT BOTTLES.						1	G	7	1 	3U			O	H2SW    					 
2001072700099	20010727	00099	SW  	2001	7	27	HEEA073218       	1	20010601	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	       	SW  										GENERATOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				STICKING INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2001080300090	20010803	00090	SW  	2001	8	3	HEEA073351       	1	20010605	G	3150	214175122111	PANEL           			BELL  	214   	214ST       	1182106	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EXCHANGE UNIT RECEIVED INOPERATIVE.						2	G	7	2 	4U			 	H10SW   					 
2001080300092	20010803	00092	SW  	2001	8	3	HEEA073352       	1	20010606	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										CYCLIC	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										LATERAL FORCE TRIM STICKING.						2	G	7	2 	4U			 	H10SW   					 
2001080300100	20010803	00100	SW  	2001	8	3	HEEA073354       	1	20010608	G	6321	D01631	PAD             			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				WORN AND GLAZED.						1	G	7	1 	3U			O	H2SW    					 
2001080300108	20010803	00108	SW  	2001	8	3	HEEA073355       	1	20010608	G	6720	406312103101	LINK            			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS4534 AND NHFS4483.						1	G	7	1 	3U			O	H2SW    					 
2001080300109	20010803	00109	SW  	2001	8	3	HEEA073356       	1	20010608	G	3212	206050247131	COVER           			BELL  	407   	407         	       	SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				TORN AND DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2001080300114	20010803	00114	SW  	2001	8	3	HEEA073357       	1	20010608	G	7921	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				OIL COOLER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300115	20010803	00115	SW  	2001	8	3	HEEA073358       	1	20010608	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300116	20010803	00116	SW  	2001	8	3	HEEA073359       	1	20010608	G	3212	212073905001	GAUGE           			BELL  	407   	407         	       	SW  										MLG	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH					53435				WATER IN GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2001080300117	20010803	00117	SW  	2001	8	3	HEEA073360       	1	20010608	G	3260	8869K59	SWITCH          			BELL  	407   	407         	       	SW  										MLG	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				INTERMITTENT OPERATION.  NO POSITIVE MOVEMENT.						1	G	7	1 	3U			O	H2SW    					 
2001080300128	20010803	00128	SW  	2001	8	3	HEEA073361       	1	20010608	G	3310	FCB205AT4	RELAY           			BELL  	407   	407         	       	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4999					53323				INTERMITTENT IGNITION WHENEVER STARTER IS LATCHED.						1	G	7	1 	3U			O	H2SW    					 
2001080300133	20010803	00133	SW  	2001	8	3	HEEA073362       	1	20010608	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	       	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				CRACKED AT WELDED AREA.						1	G	7	1 	3U			O	H2SW    					 
2001080300137	20010803	00137	SW  	2001	8	3	HEEA073363       	1	20010608	G	6720	406012129101	LINK            			BELL  	407   	407         	       	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				RATCHETY.						1	G	7	1 	3U			O	H2SW    					 
2001080300138	20010803	00138	SW  	2001	8	3	HEEA073365       	1	20010608	G	6320	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH				PHI0012	53159				ROUGH.  SERIAL NUMBERS REMOVED ARE B01-0584 AND B01-0569.						1	G	7	1 	3U			O	H2SW    					 
2001080300139	20010803	00139	SW  	2001	8	3	HEEA073366       	1	20010608	G	3212	212073905001	GAUGE           			BELL  	407   	407         	       	SW  										MLG	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				MOISTURE IN GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2001080300140	20010803	00140	SW  	2001	8	3	HEEA073367       	1	20010608	G	3212	212073905001	GAUGE           			BELL  	407   	407         	       	SW  										MLG	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				READS LOW.						1	G	7	1 	3U			O	H2SW    					 
2001080300141	20010803	00141	SW  	2001	8	3	HEEA073368       	1	20010608	G	6720	406312103101	LINK            			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001080300142	20010803	00142	SW  	2001	8	3	HEEA073369       	1	20010608	G	6720	406312103101	LINK            			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001080300143	20010803	00143	SW  	2001	8	3	HEEA073370       	1	20010608	G	3212	206050247135	COVER           			BELL  	407   	407         	       	SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				END CAP TORN AND FRAYED.						1	G	7	1 	3U			O	H2SW    					 
2001080300144	20010803	00144	SW  	2001	8	3	HEEA073371       	1	20010608	G	6220	406310200101	ROD END         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300145	20010803	00145	SW  	2001	8	3	HEEA073372       	1	20010608	G	7100	407001026101	TUBE            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				TAIL ROTOR CONTROL TUBE HAS A BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300146	20010803	00146	SW  	2001	8	3	HEEA073373       	1	20010608	G	2400	M835362028M	RELAY           			BELL  	407   	407         	       	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				FADEC AUTO/MANUAL LIGHT COMES ON THEN GOES OUT.						1	G	7	1 	3U			O	H2SW    					 
2001080300147	20010803	00147	SW  	2001	8	3	HEEA073374       	1	20010608	G	6322	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH				PHI0034	53399				ROUGH.  SERIAL NUMBERS REMOVED ARE H99-2406 AND H99-2403.						1	G	7	1 	3U			O	H2SW    					 
2001080300148	20010803	00148	SW  	2001	8	3	HEEA073375       	1	20010608	G	6322	406040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH				PHI0034	53399				ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001080300149	20010803	00149	SW  	2001	8	3	HEEA073376       	1	20010608	G	6300	407040316101	FLYWHEEL        			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001080300159	20010803	00159	SW  	2001	8	3	HEEA073377       	1	20010608	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300160	20010803	00160	SW  	2001	8	3	HEEA073378       	1	20010608	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH				PHI0007	53059				ROUGH.  SERIAL NUMBERS REMOVED ARE K98-0736 AND H99-1758. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT	 PARTS PURCHASED.   REPLACED WITH SERIAL NUMBERS SNB01-0793 AND SNB01-0755.  REFERENCE:  DMR#71726100 AND 71726101.  LAB	OR CREDIT ACCOMPLISHED ON J0161088-WA (INVOICE AND DMR NO. 687026).				1	G	7	1 	3U			O	H2SW    					 
2001080300162	20010803	00162	SW  	2001	8	3	HEEA073379       	1	20010608	G	3212	206050247132	COVER           			BELL  	407   	407         	       	SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				TORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300163	20010803	00163	SW  	2001	8	3	HEEA073380       	1	20010608	G	2560	407370720101	RESTRAINT       			BELL  	407   	407         	       	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				LABELS DETERIORATING.						1	G	7	1 	3U			O	H2SW    					 
2001080300165	20010803	00165	SW  	2001	8	3	HEEA073381       	1	20010608	G	2560	407370721101	RESTRAINT       			BELL  	407   	407         	       	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				LABELS DETERIORATING.						1	G	7	1 	3U			O	H2SW    					 
2001080300166	20010803	00166	SW  	2001	8	3	HEEA073382       	1	20010608	G	6310	222060084101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				ANTI ICE LIGHT WILL NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2001080300167	20010803	00167	SW  	2001	8	3	HEEA073383       	1	20010608	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300168	20010803	00168	SW  	2001	8	3	HEEA073384       	1	20010608	G	3310	FCB205AT4	RELAY           			BELL  	407   	407         	       	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				CAUSED FADEC FAULT WORD IGN 1 FLT.						1	G	7	1 	3U			O	H2SW    					 
2001080300170	20010803	00170	SW  	2001	8	3	HEEA073385       	1	20010608	G	6510	406040339105	BEARING         		407040302101	BELL  	407   	407         	       	SW  										T/R DRIVESHAFT	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				A926	53142				VIBRATION ON TAILBOOM.  BEARING ROUGH. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.   	REFERENCE:  DMR#71513300.  LABOR CREDIT ACCOMPLISHED ON J0162309-WA (INVOICE AND DMR NO. 687029).					1	G	7	1 	3U			O	H2SW    					 
2001080300171	20010803	00171	SW  	2001	8	3	HEEA073386       	1	20010608	G	6300	407040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				PHI0020	53142				WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001080300173	20010803	00173	SW  	2001	8	3	HEEA073388       	1	20010608	G	7720	MS280343	BULB            			BELL  	407   	407         	       	SW  										TEMP INDICATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH					53435				PRESSURE INDICATION READS ZERO.						1	G	7	1 	3U			O	H2SW    					 
2001080300174	20010803	00174		2001	8	3	HEEA073389       	4	20010608	G	3120	602EN6026	SWITCH          			BELL  	407   	407         	       	SW  										CLOCK	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				CAUSES FLIGHT TIME MODE OF CLOCK TO NOT WORK.						1	G	7	1 	3U			O	H2SW    					 
2001080300175	20010803	00175	SW  	2001	8	3	HEEA073390       	1	20010608	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1110 				53114				EXCESSIVE PLAY.						1	G	7	1 	3U			O	H2SW    					 
2001080300176	20010803	00176	SW  	2001	8	3	HEEA073391       	1	20010608	G	6500	406040072105	SPLINE ADAPTER  			BELL  	407   	407         	       	SW  										TAIL ROTOR DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				WORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300177	20010803	00177	SW  	2001	8	3	HEEA073392       	1	20010608	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	       	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300178	20010803	00178	SW  	2001	8	3	HEEA073393       	1	20010608	G	2910	70079H000Y150	HOSE            			BELL  	407   	407         	       	SW  										MLG	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				KINKED ON 90 DEGREE END.						1	G	7	1 	3U			O	H2SW    					 
2001080300180	20010803	00180	SW  	2001	8	3	HEEA073394       	1	20010608	G	6230	406310411101	BOOT            			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				SMALL HOLE WORN IN BOOT.						1	G	7	1 	3U			O	H2SW    					 
2001080300182	20010803	00182	SW  	2001	8	3	HEEA073395       	1	20010611	G	3300	407076501109	HARNESS         			BELL  	407   	407         	       	SW  										ELECTRICAL	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				CHAFED NEAR PROBE NR 3 CONNECTOR.  HARNESS NOT SECURED PROPERLY.						1	G	7	1 	3U			O	H2SW    					 
2001080300183	20010803	00183	SW  	2001	8	3	HEEA073396       	1	20010611	G	6510	206061432119	BLOWER          			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300184	20010803	00184	SW  	2001	8	3	HEEA073397       	1	20010611	G	3212	206050247135	COVER           			BELL  	407   	407         	       	SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				FORWARD CAP-THREAD BARE AND TORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300185	20010803	00185	SW  	2001	8	3	HEEA073398       	1	20010611	G	6300		BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH				PHI0002	53435				NR 1 BEARING FAILED IN FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001080300186	20010803	00186	SW  	2001	8	3	HEEA073399       	1	20010611	G	6300		BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH				PHI0002	53435				NR 1 BEARING FAILED IN FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001080300187	20010803	00187	SW  	2001	8	3	HEEA073400       	1	20010611	G	6300	406040322101	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH				PHI0002	53435				NR 1 BEARING FAILED IN FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001080300188	20010803	00188	SW  	2001	8	3	HEEA073401       	1	20010611	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH				PHI0002	53435				NR 1 BEARING FAILED IN FLIGHT.  SERIAL NUMBERS REMOVED ARE M00-0854 AND M00-0882.						1	G	7	1 	3U			O	H2SW    					 
2001080300189	20010803	00189	SW  	2001	8	3	HEEA073402       	1	20010611	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	OVERHEATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				PHI0007	53142				DISCOLORATION OF BEARING GREASE.  SERIAL NUMBERS REMOVED ARE B01-0810 AND B01-0817.						1	G	7	1 	3U			O	H2SW    					 
2001080300190	20010803	00190	SW  	2001	8	3	HEEA073403       	1	20010611	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				WORKING RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2001080300191	20010803	00191	SW  	2001	8	3	HEEA073405       	1	20010611	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300192	20010803	00192	SW  	2001	8	3	HEEA073406       	1	20010611	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	4857 				53070				MAIN ROTOR ROD END HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001080300193	20010803	00193	SW  	2001	8	3	HEEA073407       	1	20010611	G	3212	206050247131	COVER           			BELL  	407   	407         	       	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				VELCRO ON END CAPS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300194	20010803	00194	SW  	2001	8	3	HEEA073408       	1	20010611	G	3212	206050247132	COVER           			BELL  	407   	407         	       	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				VELCRO ON END CAPS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001080300195	20010803	00195	SW  	2001	8	3	HEEA073409       	1	20010611	G	6320	407040623101	LINE            			BELL  	407   	407         	       	SW  										OIL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				LEAKING AT FLARE.						1	G	7	1 	3U			O	H2SW    					 
2001080300196	20010803	00196	SW  	2001	8	3	HEEA073410       	1	20010611	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				CRACKED IN TWO PLACES.						1	G	7	1 	3U			O	H2SW    					 
2001080300197	20010803	00197	SW  	2001	8	3	HEEA073411       	1	20010611	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	       	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				CRACKED AROUND BASE.						1	G	7	1 	3U			O	H2SW    					 
2001080300198	20010803	00198	SW  	2001	8	3	HEEA073412       	1	20010611	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH	654  				53386				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001080300199	20010803	00199	SW  	2001	8	3	HEEA073413       	1	20010611	G	6320	407040623101	LINE            			BELL  	407   	407         	       	SW  										OIL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	408PH					53228				FLARE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001080300216	20010803	00216	SW  	2001	8	3	HEEA073414       	1	20010611	G	6220	407310101101	BEARING         			BELL  	407   	407         	       	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH	2331 				53277				SHIM CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001080300219	20010803	00219	SW  	2001	8	3	HEEA073416       	1	20010611	G	6230	406310411101	BOOT            			BELL  	407   	407         	       	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				CRACKED. SCRAPPED ON SITE.						1	G	7	1 	3U			O	H2SW    					 
2001080300220	20010803	00220	SW  	2001	8	3	HEEA073417       	1	20010611	G	6321		PAD             			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				WORN PADS.						1	G	7	1 	3U			O	H2SW    					 
2001080300222	20010803	00222	SW  	2001	8	3	HEEA073418       	1	20010611	G	6710	407030211101	COVER           			BELL  	407   	407         	       	SW  										COLLECTIVE	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BROKEN. SCRAPPED ON SITE.  PHI REQUESTS FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#711790.						1	G	7	1 	3U			O	H2SW    					 
2001080300229	20010803	00229	SW  	2001	8	3	HEEA073419       	1	20010611	G	6710	407030211101	COVER           			BELL  	407   	407         	       	SW  										COLLECTIVE	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BROKEN. SCRAPPED ON SITE.						1	G	7	1 	3U			O	H2SW    					 
2001080300231	20010803	00231	SW  	2001	8	3	HEEA073422       	1	20010611	G	6310	214040841101	SEAL            			BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407PH					53003				LEAKING. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001080300232	20010803	00232	SW  	2001	8	3	HEEA073423       	1	20010611	G	2910	70079H000Y150	HOSE            			BELL  	407   	407         	       	SW  										MLG	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				FRAYED. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001080300255	20010803	00255	EU  	2001	8	3	HEEA073433       	1	20010611	G	2560	AFG0348056	HARNESS         			SNIAS 	350   	AS350B2     	8680813	EU  										SEAT BELT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4034Q					2918				REEL INOPERATIVE.						1	G	7	1 	3U			 	H9EU    					 
2001080300259	20010803	00259	EU  	2001	8	3	HEEA073434       	1	20010611	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B      	8680801	EU  										FUEL SYSTEM	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	973AE	691  				3229				PUMP INTERMITTENTLY NOT COMING ON.						1	G	7	1 	3U			 	H9EU    					 
2001080300260	20010803	00260		2001	8	3	HEEA073437       	4	20010611	G	3421	5040111916	GYRO            			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	972AE					3234				TUMBLES WHEN POWER APPLIED.						1	G	7	1 	3U			 	H9EU    					 
2001080300261	20010803	00261	EU  	2001	8	3	HEEA073515       	1	20010619	G	2612	9560132140	FIRE DETECTOR   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4034Q					2918	9432			INTERMITTENT.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001080300292	20010803	00292	NE  	2001	8	3	HEEA073516       	2	20010619	G	7412	9550173220	EXCITER         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				INOPERATIVE.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080600006	20010806	00006	NE  	2001	8	6	HEEA073517       	2	20010619	G	7310	0292958050	VALVE           			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	LEAKING         	E			HEEA	O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	03	505PH	1441 				760505	20017			FUEL SMELL IN COCKPIT DURING START.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080600008	20010806	00008	NE  	2001	8	6	HEEA073518       	2	20010619	G	7200	9560115450	MAGNETIC SEAL   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	856PH					3352	9728			LEAKING.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001080600009	20010806	00009	NE  	2001	8	6	HEEA073519       	2	20010619	G	7200	9560137520	MAGNETIC SEAL   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	856PH					3352	9728			LEAKING.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001080600011	20010806	00011	NE  	2001	8	6	HEEA073520       	2	20010619	G	7200	0292005310	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NACELLE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH	1622 				760505				HIGH OIL CONSUMPTION.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080600016	20010806	00016	NE  	2001	8	6	HEEA073521       	1	20010619	G	6730	30006762102	MANIFOLD        		766500980511	SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03					1002					CAUSING LEAKAGE BETWEEN MAIN AND BYPASS SERVO VALVES ON SYSTEM ONE ON FINAL TEST.  FOUND MISSING LEE PLUG IN DRILLED PAS	SAGE ON SYSTEM ONE BETWEEN MAIN AND BYPASS SERVO VALVES. SENDING TO VENDOR FOR REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001080600022	20010806	00022		2001	8	6	HEEA073522       	4	20010619	G	3442	7021450601	COMPUTER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	760PH					760078				WX RADAR SYSTEM INOPERATIVE.						1	G	7	2 	3U			 	H1NE    					 
2001080600023	20010806	00023	NE  	2001	8	6	HEEA073523       	1	20010619	G	6230	7610408020047	SCISSORS        			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4253S					760035				WORN BUSHINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001080600025	20010806	00025	NE  	2001	8	6	HEEA073524       	1	20010619	G	2435	7630007661043	DUCT            			SKRSKY	S76   	S76C        	8143008	NE  										STARTER GEN	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				CRACKED. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600027	20010806	00027	NE  	2001	8	6	HEEA073525       	1	20010619	G	6300	7635109045102	GEAR            			SKRSKY	S76   	S76A        	8143006	NE  										M/R DRIVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										NO RIVET IN CENTER OF GEAR. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001080600029	20010806	00029		2001	8	6	HEEA073526       	4	20010619	G	3160	7645001098105	DISPLAY         			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	505PH					760505				CENTER DISPLAY UNIT SHOWING AN INTERMITTENT FAIL FAULT ALONG WITH GIVING INTERMITTENT INCORRECT INFORMATION AND CAUSING 	INTERMITTENT NR 1 AND 2 ENGINE OUT WARNING LIGHTS TO COME ON IN FLIGHT. SENT TO VENDOR FOR REPAIR.					1	G	7	2 	3U			NC	H1NE    					 
2001080600031	20010806	00031	NE  	2001	8	6	HEEA073527       	1	20010619	G	2120	7650007901103	BLOWER          			SKRSKY	S76   	S76C        	8143008	NE  										CABIN	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				OPEN BETWEEN PINS A AND C. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600034	20010806	00034		2001	8	6	HEEA073529       	4	20010619	G	2215	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				FULL RIGHT HARD OVER. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600036	20010806	00036		2001	8	6	HEEA073530       	4	20010619	G	2215	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				SHOWS NO MOVEMENT ON INDICATOR. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600038	20010806	00038		2001	8	6	HEEA073531       	4	20010619	G	2215	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				AFCS SYSTEM SHOWS NO MOVEMENT ON INDICATOR. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600040	20010806	00040	NE  	2001	8	6	HEEA073532       	1	20010619	G	6730	7826002	SERVO           			SKRSKY	S76   	S76C        	8143008	NE  										TAIL ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	505PH					760505				LEAKING PAST SERVO ACTUATOR PISTON. SENT TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001080600041	20010806	00041		2001	8	6	HEEA073533       	4	20010619	G	3457	81439000232	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										GPS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122G					760232				WILL NOT RECOGNIZE DATA CARD. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001080600044	20010806	00044	GL  	2001	8	6	HEEA073534       	2	20010620	G	7261	23066681	FILTER HOUSING  			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					OIL FILTER BOWL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				OIL FILTER BOWL BYPASS BUTTON POPS CONTINUOUSLY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080600049	20010806	00049	SW  	2001	8	6	HEEA073535       	1	20010620	G	2821	23066697	FILTER          			BELL  	407   	407         	       	SW  										FUEL SYSTEM	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				POPPED BYPASS BUTTON. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001080600051	20010806	00051	GL  	2001	8	6	HEEA073537       	2	20010620	G	7320	23072725	HMU             			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				LOUD HUMMING NOISE IN ENGINE COMPARTMENT WITH BOOST PUMPS ON. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080600052	20010806	00052	NE  	2001	8	6	HEEA073538       	2	20010620	G	7200	0292005310	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE BAY	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH	1734 				760505				FOUND OIL SAMPLE HAS HIGH IRON.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080600053	20010806	00053	NE  	2001	8	6	HEEA073539       	2	20010620	G	7200	70BMA01030	ECU             			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					NR 1 ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH	2021 				760505				REVERSION LIGHT ON NR 1 THROTTLE STAYS ON.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080600054	20010806	00054	NE  	2001	8	6	HEEA073540       	1	20010620	G	2820	PT06CE84SSR	CONNECTOR       			SKRSKY	S76   	S76A        	8143006	NE  										NR 2 ENGINE	DIRTY           	E			HEEA	O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			SW	03	1546K					760082				WHILE IN CRUISE FLIGHT, THE NR 2 ENGINE FUEL FLOW INDICATOR BEGAN TO FLUCTUATE. CLEANED CANNON PLUG AT TRANSMITTER.						1	G	7	2 	3U			 	H1NE    					 
2001080600055	20010806	00055	SW  	2001	8	6	HEEA073558       	1	20010615	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										SLOW TO START.						2	G	7	2 	4U			 	H10SW   					 
2001080600056	20010806	00056	SW  	2001	8	6	HEEA073559       	1	20010615	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DISENGAGES DURING BATTERY START.						2	G	7	2 	4U			 	H10SW   					 
2001080600057	20010806	00057	SW  	2001	8	6	HEEA073563       	1	20010618	G	6700	206001552001	BELLCRANK       			BELL  	206   	206L3       	1182108	SW  										FLIGHT CONTROLS	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6160Y					51609				PIVOT BUSHING WORN AND BEARINGS WORN. REPLACED WITH SERVICEABLE BELLCRANK ASSEMBLY.						1	G	7	1 	3U			 	H2SW    					 
2001080600058	20010806	00058	SW  	2001	8	6	HEEA073564       	1	20010618	G	6700	206001554001	SUPPORT FITTING 			BELL  	206   	206L3       	1182108	SW  										CYCLIC BELLCRANK	WARPED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206LS					51070				CYCLIC BELLCRANK SUPPORT ASSY. WARPED. SCRAPPED AND REPLACED WITH SERVICEABLE SUPPORT ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600059	20010806	00059	SW  	2001	8	6	HEEA073565       	1	20010618	G	6710	206001713101	SUPPORT BRACKET 			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5014V					45217				EXCESSIVE CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE SUPPORT ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600060	20010806	00060	SW  	2001	8	6	HEEA073566       	1	20010618	G	6220	206010003007	CONE SET        			BELL  	206   	206L1       	1182107	SW  										M/R HEAD	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5014V					45217				CORROSION PITTING ON SURFACE OF CONES. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600064	20010806	00064	SW  	2001	8	6	HEEA073567       	1	20010618	G	6420	206010795103	PITCH LINK      			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				WORN. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600065	20010806	00065	SW  	2001	8	6	HEEA073568       	1	20010618	G	6420	206010795105	PITCH LINK      			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				WORN. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600066	20010806	00066	SW  	2001	8	6	HEEA073569       	1	20010618	G	6420	206010802101	BUSHING         			BELL  	206   	206L1       	1182107	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5007Q					45187				WORN. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600067	20010806	00067	SW  	2001	8	6	HEEA073570       	1	20010618	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										FLAP	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				SPRINGS WEAK AND STICKING ARMS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600068	20010806	00068	SW  	2001	8	6	HEEA073571       	1	20010618	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L1       	1182107	SW  										FLAP	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5019F					45244				YELLOW BLADE RESTRAINT STICKING IN STOWED POSITION. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600069	20010806	00069	SW  	2001	8	6	HEEA073572       	1	20010618	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L4       	1182110	SW  										FLAP	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7077F					52038				STICKING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			NC	H2SW    					 
2001080600070	20010806	00070	SW  	2001	8	6	HEEA073573       	1	20010618	G	6200	206011135007	BOLT            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2619					51375				END CAP CRACKED. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600071	20010806	00071	SW  	2001	8	6	HEEA073574       	1	20010618	G	6400	206011725001	ROD             			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	BINDING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				BINDING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600073	20010806	00073	SW  	2001	8	6	HEEA073575       	1	20010618	G	6400	206011725001	ROD             			BELL  	206   	206L1       	1182107	SW  										TAIL ROTOR	ROUGH           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	45RP					45521				ROUGH BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600074	20010806	00074	SW  	2001	8	6	HEEA073576       	1	20010618	G	6400	206011725001	ROD             			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6160Y					51609				WORN BEARING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600075	20010806	00075	SW  	2001	8	6	HEEA073577       	1	20010618	G	5302	206032308003	FRAME           			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41791					51465				CRACKED TAILBOOM MOUNTING RING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600077	20010806	00077	SW  	2001	8	6	HEEA073578       	1	20010618	G	5302	206032308103	FRAME           			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				TAILBOOM RING CRACKED AT ATTACHMENT HOLE. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600079	20010806	00079	SW  	2001	8	6	HEEA073579       	1	20010618	G	5312	206033107107B	BULKHEAD        			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				SEVERE CORROSION AT LATCH AREA WHERE SHIM WAS BONDED WITH ADHESIVE. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600081	20010806	00081	SW  	2001	8	6	HEEA073580       	1	20010618	G	5320	206033302101	CHANNEL         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				BULKHEAD CRACKED AT LT FWD ENGINE MOUNT HOLE IN UPPER FLANGE RADIUS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600082	20010806	00082	SW  	2001	8	6	HEEA073581       	1	20010618	G	5330	206033310139	ACCESS PANEL    			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				CORRODED AT ACCESS PANEL AREA BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600084	20010806	00084	SW  	2001	8	6	HEEA073582       	1	20010618	G	5302	206033407101	COWLING         			BELL  	206   	206L4       	1182110	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7074W					52033				CRACKED AND CHAFED. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			NC	H2SW    					 
2001080600086	20010806	00086	SW  	2001	8	6	HEEA073583       	1	20010618	G	3212	206030104023	FITTING         			BELL  	206   	206L3       	1182108	SW  										FLOAT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				RUBBER MISSING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600088	20010806	00088	SW  	2001	8	6	HEEA073584       	1	20010618	G	2730		BELLCRANK       			BELL  	206   	206L3       	1182108	SW  										ELEVATOR ASSY	BINDING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				BELLCRANK BEARING BINDING AT TIMES. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600092	20010806	00092	SW  	2001	8	6	HEEA073585       	1	20010618	G	3212	206030104023	FITTING         			BELL  	206   	206L3       	1182108	SW  										FLOAT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				RUBBER MISSING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001080600094	20010806	00094	SW  	2001	8	6	HEEA073586       	1	20010618	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	45RP					45521				WORN BEARINGS.						1	G	7	1 	3U			 	H2SW    					 
2001080600097	20010806	00097	SW  	2001	8	6	HEEA073587       	1	20010618	G	6330	206033516101	FLEXURE         			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				RUBBER DETERIORATED.						1	G	7	1 	3U			 	H2SW    					 
2001080600139	20010806	00139	SW  	2001	8	6	HEEA073588       	1	20010618	G	6300	206033518007	STOP            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				WORN BEARING.						1	G	7	1 	3U			 	H2SW    					 
2001080600141	20010806	00141	SW  	2001	8	6	HEEA073589       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/ROTOR DRIVE	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				BEARINGS SEPARATED AND DETERIORATED BEYOND LIMITS.						1	G	7	1 	3U			 	H2SW    					 
2001080600146	20010806	00146	SW  	2001	8	6	HEEA073590       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				BEARINGS SEPARATED AND DETERIORATED BEYOND LIMITS.						1	G	7	1 	3U			 	H2SW    					 
2001080600147	20010806	00147	SW  	2001	8	6	HEEA073591       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				MECHANICAL DAMAGE BEYOND LIMITS.						1	G	7	1 	3U			 	H2SW    					 
2001080600149	20010806	00149	SW  	2001	8	6	HEEA073592       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										LT PYLON	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8591X					51495				LT AFT PYLON LINK UPPER BEARING EXTRUDING.						1	G	7	1 	3U			 	H2SW    					 
2001080600150	20010806	00150	SW  	2001	8	6	HEEA073593       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251Y					51556				ELASTOMERIC BEARING SEPARATED.						1	G	7	1 	3U			 	H2SW    					 
2001080600151	20010806	00151	SW  	2001	8	6	HEEA073594       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8591X					51495				RT FWD PYLON LINK UPPER BEARING EXTRUDING.						1	G	7	1 	3U			 	H2SW    					 
2001080600152	20010806	00152	SW  	2001	8	6	HEEA073595       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				ELASTOMERIC BEARING AT UPPER END HAS RUBBER COMING UNBONDED.						1	G	7	1 	3U			 	H2SW    					 
2001080600158	20010806	00158	SW  	2001	8	6	HEEA073596       	1	20010618	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										M/R DRIVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	92MT					51175				ELASTOMERIC DEBONDED.						1	G	7	1 	3U			 	H2SW    					 
2001080600159	20010806	00159	SW  	2001	8	6	HEEA073597       	1	20010618	G	7600	206062721103	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										ENGINE CONTROLS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										SPREAD WILL NOT WORK.						1	G	7	1 	3U			 	H2SW    					 
2001080600160	20010806	00160	SW  	2001	8	6	HEEA073598       	1	20010618	G	7600	206062721105	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE CONTROLS	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				INTERMITTENT.						1	G	7	1 	3U			 	H2SW    					 
2001080600161	20010806	00161	SW  	2001	8	6	HEEA073599       	1	20010618	G	7600	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE CONTROLS	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8588X					51486				STICKING, WILL NOT ACTUATE.						1	G	7	1 	3U			 	H2SW    					 
2001080600162	20010806	00162	SW  	2001	8	6	HEEA073600       	1	20010618	G	7600	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE CONTROLS	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8594X					51531				STICKING, WILL NOT ACTUATE.						1	G	7	1 	3U			 	H2SW    					 
2001080600163	20010806	00163	SW  	2001	8	6	HEEA073601       	1	20010618	G	7600	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE CONTROLS	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3116P					51530				STICKING.						1	G	7	1 	3U			 	H2SW    					 
2001080600164	20010806	00164	SW  	2001	8	6	HEEA073602       	1	20010618	G	2121	206070475005	BLOWER          			BELL  	412   	412         	1182202	SW  										CABIN	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001080600165	20010806	00165	SW  	2001	8	6	HEEA073603       	1	20010618	G	2424	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										GENERATOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6610C					51425				GENERATOR DROPS OFF LINE.						1	G	7	1 	3U			 	H2SW    					 
2001080600166	20010806	00166	SW  	2001	8	6	HEEA073604       	1	20010618	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3178K					45765				CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600167	20010806	00167	SW  	2001	8	6	HEEA073605       	1	20010618	G	3246	206323018	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3178K					45765				CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600168	20010806	00168	SW  	2001	8	6	HEEA073606       	1	20010618	G	3246	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600169	20010806	00169	SW  	2001	8	6	HEEA073607       	1	20010618	G	2842	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL INDICATOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				WILL NOT INDICATE FUEL QUANTITY IN FORWARD CELLS.						1	G	7	1 	3U			 	H2SW    					 
2001080600212	20010806	00212	SW  	2001	8	6	HEEA073609       	1	20010618	G	2437	209070263003	INDICATOR       			BELL  	412   	412         	1182202	SW  										DUAL VOLT	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				NEEDLE STICKS, AMP METER SIDE.						1	G	7	2 	4U			 	H4SW    					 
2001080600215	20010806	00215	SW  	2001	8	6	HEEA073610       	1	20010618	G	6720	212001705001	BELLCRANK       			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				BEARING UNSTAKED. REPLACED WITH SERVICEABLE BELLCRANK.						1	G	7	2 	4U			 	H4SW    					 
2001080600218	20010806	00218	SW  	2001	8	6	HEEA073611       	1	20010618	G	6720	212001705001	BELLCRANK       			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				WORN BEARINGS. REPLACED WITH SERVICEABLE BELLCRANK.						1	G	7	2 	4U			 	H4SW    					 
2001080600220	20010806	00220	SW  	2001	8	6	HEEA073612       	1	20010618	G	6720	212001710001	BELLCRANK       			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				SNAP RING MISSING FROM BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001080600221	20010806	00221	SW  	2001	8	6	HEEA073613       	1	20010618	G	6720	212060740001	BELLCRANK       			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001080600222	20010806	00222	SW  	2001	8	6	HEEA073614       	1	20010618	G	6720	212060740001	BELLCRANK       			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001080600224	20010806	00224	SW  	2001	8	6	HEEA073615       	1	20010618	G	7600	212061101001	BEARING         			BELL  	412   	412         	1182202	SW  										ENGINE CONTROLS	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	108X					33115				BEARING WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001080600225	20010806	00225	SW  	2001	8	6	HEEA073616       	1	20010618	G	7600	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										ENGINE CONTROLS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2124Z					45646				BEEP ACTUATOR INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001080600227	20010806	00227	SW  	2001	8	6	HEEA073617       	1	20010618	G	2810	206063632101	FUEL CELL       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3116P					51530				FILLED CELL WITH FUEL AND LT FWD FUEL CELL STARTING LEAKING AT WEEP HOLE.						1	G	7	1 	3U			 	H2SW    					 
2001080600228	20010806	00228	SW  	2001	8	6	HEEA073618       	1	20010618	G	2840	206064635101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL INDICTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				CAUSES NEEDLE TO DROP TO ZERO IN FLIGHT.						1	G	7	1 	3U			 	H2SW    					 
2001080600229	20010806	00229	SW  	2001	8	6	HEEA073619       	1	20010618	G	3110	206070266007	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	5007Q					45187				INSTRUMENT INDICATES 3-4 PERCENT WHEN SYSTEMS ARE SHUT DOWN AND TAKES 5-6 SECONDS TO START INDICATING DURING STARTS.						1	G	7	1 	3U			 	H2SW    					 
2001080600232	20010806	00232	SW  	2001	8	6	HEEA073620       	1	20010618	G	2436	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										GENERATOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				GENERATOR WENT OFF LINE AND WON'T RESET.						1	G	7	1 	3U			 	H2SW    					 
2001080600233	20010806	00233	SW  	2001	8	6	HEEA073621       	1	20010618	G	2436	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										GENERATOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				ON FIRST START OF THE DAY, GENERATOR WILL NOT COME ON LINE.						1	G	7	1 	3U			 	H2SW    					 
2001080600236	20010806	00236	SW  	2001	8	6	HEEA073622       	1	20010618	G	7714	206075545005	SENSOR          			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				LOW RPM AUDIO COMES ON INTERMITTENTLY AT IDLE AFTER MUTE BUTTON HAS BEEN DEPRESSED.  AUDIO AND LIGHT FLICKER AT 100 PERC	ENT N2.					1	G	7	1 	3U			 	H2SW    					 
2001080600240	20010806	00240	SW  	2001	8	6	HEEA073623       	1	20010618	G	7933	206075678107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										OIL TEMP	FAILED          	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	6603X					51412				OIL TEMPERATURE WOULD NOT COME UP OFF BOTTOM OF IND.						1	G	7	1 	3U			 	H2SW    					 
2001080600242	20010806	00242	SW  	2001	8	6	HEEA073624       	1	20010618	G	7714	206075681105	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				ROTOR NEEDLE DOESN'T ENGAGE UNTIL ALMOST 100 PERCENT ENGINE RPM.						1	G	7	1 	3U			 	H2SW    					 
2001080600244	20010806	00244	SW  	2001	8	6	HEEA073625       	1	20010618	G	7714	206075682103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE TACH	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6160Y					51609				UNRELIABLE AT LOW RPM DURING STARTS.						1	G	7	1 	3U			 	H2SW    					 
2001080600246	20010806	00246	SW  	2001	8	6	HEEA073626       	1	20010618	G	7714	206075682107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE TACH	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	141BH					51303				INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001080600247	20010806	00247	SW  	2001	8	6	HEEA073627       	1	20010618	G	3246	206323002M	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600250	20010806	00250	SW  	2001	8	6	HEEA073628       	1	20010618	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				FWD CROSSTUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600251	20010806	00251	SW  	2001	8	6	HEEA073629       	1	20010618	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600252	20010806	00252	SW  	2001	8	6	HEEA073630       	1	20010618	G	3246	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				AFT CROSSTUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600253	20010806	00253	SW  	2001	8	6	HEEA073631       	1	20010618	G	3246	206323018	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5019F					45244				CORROSION NEAR OR AT CROSSTUBE SADDLE MOUNTING AREA. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600254	20010806	00254	SW  	2001	8	6	HEEA073632       	1	20010618	G	3246	206324003	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41128					51134				LT SKID TUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600255	20010806	00255	SW  	2001	8	6	HEEA073633       	1	20010618	G	3246	206324007	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001080600257	20010806	00257	SW  	2001	8	6	HEEA073634       	1	20010618	G	3246	206324008	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001080600258	20010806	00258	SW  	2001	8	6	HEEA073635       	1	20010618	G	7933	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	FLUCTUATES      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3905B					45598				FLUCTUATES WHEN VHF IS KEYED. SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600260	20010806	00260	SW  	2001	8	6	HEEA073636       	1	20010618	G	7933	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8593X					51509				NEEDLE WENT TO ZERO.						1	G	7	1 	3U			 	H2SW    					 
2001080600276	20010806	00276	SW  	2001	8	6	HEEA073637       	1	20010618	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										AIR INTAKE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001080600277	20010806	00277	SW  	2001	8	6	HEEA073638       	1	20010618	G	7923	209072433101	VALVE           			BELL  	412   	412         	1182202	SW  										ENGINE OIL	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				WILL NOT OPEN - STICKS.						1	G	7	2 	4U			 	H4SW    					 
2001080600279	20010806	00279	SW  	2001	8	6	HEEA073639       	1	20010618	G	7923	209072433101	VALVE           			BELL  	412   	412         	1182202	SW  										ENGINE OIL	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				CANNON PLUG WAS CORRODED TO CONNECTOR AND WHEN CANNON PLUG WAS REMOVED VALVE CONNECTOR CAME OFF WITH CANNON PLUG.						1	G	7	2 	4U			 	H4SW    					 
2001080600286	20010806	00286		2001	8	6	HEEA073641       	4	20010619	G	3454	066107810	RECEIVER        			BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	14UH					23028				CAUSES DISPLAY TO FLICKER AND TURN OFF. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			NC	H9SW    					 
2001080600290	20010806	00290	SW  	2001	8	6	HEEA073642       	1	20010619	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T					28101				FUNCTIONAL CHECKED GOOD AND FOUND STARTER WOULD NOT STAY ENGAGED.  IT WOULD KICK OFF AFTER APPROX. 5 TO 6 SECONDS. SENDI	NG TO VENDOR FOR REPAIR.					2	G	7	2 	4U			 	H10SW   					 
2001080600296	20010806	00296	SW  	2001	8	6	HEEA073643       	1	20010619	G	6322	6038T59P02	BLOWER          			BELL  	214   	214ST       	1182106	SW  										COOLING	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				SHAFT SHEARED. SENDING TO VENDOR FOR REPAIR.						2	G	7	2 	4U			 	H10SW   					 
2001080600298	20010806	00298		2001	8	6	HEEA073644       	4	20010619	G	3457	0110010600	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347					36005				CANNOT FIND ITSELF. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600301	20010806	00301		2001	8	6	HEEA073645       	4	20010619	G	3416	066104800	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				DISPLAYS ERRATIC ALTITUDE. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600303	20010806	00303		2001	8	6	HEEA073646       	4	20010619	G	3451	066106900	INDICATOR       			BELL  	412   	412         	1182202	SW  										DME/ TACAN	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				DIGITS OUT. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600305	20010806	00305		2001	8	6	HEEA073647       	4	20010619	G	3451	066106900	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				SEGMENT LIGHT INTERMITTENTLY GOES BLANK IN NR 2 POSITION. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600306	20010806	00306		2001	8	6	HEEA073648       	4	20010619	G	3451	066106902	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				DISPLAY FLASHES ON/OFF INTERMITTENTLY. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600307	20010806	00307		2001	8	6	HEEA073649       	4	20010619	G	3416	13012001	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS HIGH      	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	107X					33113				READS 90 FEET HIGH. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600308	20010806	00308	SW  	2001	8	6	HEEA073650       	1	20010619	G	2121	206070475005	BLOWER          			BELL  	412   	412         	1182202	SW  										CABIN	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				BURNT OUT. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600309	20010806	00309	SW  	2001	8	6	HEEA073651       	1	20010619	G	7921	209011710005	TUBE            			BELL  	412   	412         	1182202	SW  										OIL COOLER	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				WORN AT LOCATION WHERE EXCLUDER SEAL RIDES. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600310	20010806	00310	SW  	2001	8	6	HEEA073652       	1	20010619	G	7921		BEARING         			BELL  	412   	412         	1182202	SW  										OIL COOLER	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z				51009046	33077				BEARING RACE SPINNING. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600311	20010806	00311	SW  	2001	8	6	HEEA073653       	1	20010619	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										XMSN OIL	READS LOW       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				READS LOW. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600312	20010806	00312		2001	8	6	HEEA073654       	4	20010619	G	3100	212075067119	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6106C					36257				I.T.T WOULD NOT INDICATE ANY TEMP. AT ALL; NEEDLES DID NOT MOVE. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600314	20010806	00314	SW  	2001	8	6	HEEA073655       	1	20010619	G	2910	212076006007	VALVE           			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	BYPASSING       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				BYPASS BUTTON POPPED. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600315	20010806	00315	SW  	2001	8	6	HEEA073656       	1	20010619	G	3246	212321103	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				FOUND CORROSION UNDER SADDLE TO A DEPTH OF .022 BEFORE TOTAL CLEAN UP. SENDING TO VENDOR FOR CREDIT.						1	G	7	2 	4U			 	H4SW    					 
2001080600322	20010806	00322	GL  	2001	8	6	HEEA073657       	2	20010619	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	ALLSN 	250C  	250C*       	 	GL  					FREE TURBINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				ACCELERATES VERY FAST. IN SHOP REPAIR.						1	G	7	2 	4U	3	U	 	H4SW    	E4CE				 
2001080600325	20010806	00325		2001	8	6	HEEA073658       	4	20010619	G	2210	2593996333	TARSYN          			BELL  	412   	412         	1182202	SW  										AFCS	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				INTERMITTENT KICK IN THE AFCS SYSTEM WHEN SWITCHING BETWEEN SAS AND ATT MODES. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600327	20010806	00327	SW  	2001	8	6	HEEA073659       	1	20010619	G	7100	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										NR 1 ENGINE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N	2510 				33002				TRANSFERRING OIL FROM C-BOX TO NR 1 ENGINE. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600328	20010806	00328	GL  	2001	8	6	HEEA073660       	2	20010619	G	7532	312320301	BLEED VALVE     			BELL  	412   	412         	1182202	SW  	ALLSN 	250C  	250C*       	 	GL  					COMPRESSOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2298Z					33077				CAUSED COMPRESSOR STALL AT 84 PERCENT N1. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U	3	U	 	H4SW    	E4CE				 
2001080600329	20010806	00329	SW  	2001	8	6	HEEA073661       	1	20010619	G	7714	32005007	TACH GENERATOR  			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				NR 2 ENGINE N1 INDICATOR WENT TO ZERO IN FLIGHT. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600331	20010806	00331	SW  	2001	8	6	HEEA073662       	1	20010619	G	7712	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TORQUE	ERRATIC         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				ERRATIC TORQUE LIMITING, N2 DROOPING EARLY. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600333	20010806	00333	SW  	2001	8	6	HEEA073663       	1	20010619	G	7712	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				AIRCRAFT HAS 6 PERCENT TORQUE SPLIT AT HIGH POWER SETTINGS. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600334	20010806	00334	SW  	2001	8	6	HEEA073664       	1	20010619	G	7712	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				10 PERCENT TORQUE SPLIT. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600336	20010806	00336		2001	8	6	HEEA073665       	4	20010619	G	3442	4000038	KNOB            			BELL  	412   	412         	1182202	SW  										CONTROL HEAD	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				BROKEN KNOB. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600338	20010806	00338		2001	8	6	HEEA073666       	4	20010619	G	3422	4020936903	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				SHOWS 30 DEGREE CLIMB WITH ACFT LEVEL. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600342	20010806	00342		2001	8	6	HEEA073667       	4	20010619	G	2210	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				CAUSES DECOUPLE LIGHT TO COME ON INTERMITTENTLY. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600344	20010806	00344	SW  	2001	8	6	HEEA073668       	1	20010619	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K	14262				36001				OUTBOARD ABRASION STRIP HAS SEVERAL HOLES FROM EROSION. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600345	20010806	00345	SW  	2001	8	6	HEEA073669       	1	20010619	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				HAS SMALL SECTION OF SKIN MISSING NEAR OUTBOARD TAB. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600346	20010806	00346	SW  	2001	8	6	HEEA073670       	1	20010619	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				SCARF JOINT SEPARATED AND LOOSE. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600348	20010806	00348	SW  	2001	8	6	HEEA073671       	1	20010619	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				CRACKED LEADING EDGE ABRASION STRIP. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600350	20010806	00350	SW  	2001	8	6	HEEA073672       	1	20010619	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				COPILOT READS 3 PERCENT HIGHER THAN PILOTS AND ENG TORQUE SHOW 4 PERCENT SPLIT WHERE AS THE PILOTS SHOW ONLY A 1%. IN SH	OP FOR REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2001080600352	20010806	00352	SW  	2001	8	6	HEEA073673       	1	20010619	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS LOW       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				NR 2 ENGINE AND N2 ROTOR NEEDLE READS 2 PERCENT LOW. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600356	20010806	00356		2001	8	6	HEEA073674       	4	20010619	G	3460	5205160006	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				NAV FLAG WILL NOT PULL. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600357	20010806	00357		2001	8	6	HEEA073675       	4	20010619	G	2340	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				FM AUDIO BLEEDS OVER WHEN FM NR 1 SELECTOR SWITCH IS SET TO DOWN POSITION. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600359	20010806	00359		2001	8	6	HEEA073676       	4	20010619	G	2340	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										COCKPIT	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				VERY WEAK ON RADIO CHANNELS. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600361	20010806	00361		2001	8	6	HEEA073677       	4	20010619	G	3443	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				RADAR WILL NOT INDICATE TARGETS, ALSO WILL NOT SHOW TEST BAND. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600363	20010806	00363		2001	8	6	HEEA073678       	4	20010619	G	3442	MI5851345	DISPLAY         			BELL  	412   	412         	1182202	SW  										RADAR SYS	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600366	20010806	00366		2001	8	6	HEEA073679       	4	20010619	G	3442	MI5851352	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600367	20010806	00367		2001	8	6	HEEA073680       	4	20010619	G	3442	MI585136	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600371	20010806	00371		2001	8	6	HEEA073682       	4	20010619	G	3442	MI585200	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	2261D					33076				RF BAND BROKEN AND TEST PATTERN BREAKS UP. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600373	20010806	00373	SW  	2001	8	6	HEEA073683       	1	20010619	G	6720	PHI41294	BUSHING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				WORN. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600375	20010806	00375	SW  	2001	8	6	HEEA073684       	1	20010619	G	6730	212076005105	CYLINDER        			BELL  	412   	412         	1182202	SW  										ROTOR SERVO	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2261D					33076				LEAKING. IN SHOP FOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001080600376	20010806	00376		2001	8	6	HEEA073685       	4	20010619	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				DISPLAY NUMBERS DON'T COME ON. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600377	20010806	00377		2001	8	6	HEEA073686       	4	20010619	G	2312	069102435	RADIO           			BELL  	206   	206L3       	1182108	SW  										VHF SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				VHF RADIO WILL NOT POWER UP. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600378	20010806	00378	SW  	2001	8	6	HEEA073687       	1	20010619	G	2821	1110900	FILTER          			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	BYPASSING       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5019F					45244				BUTTON POPS FOR NO REASON, INTERMITTENTLY. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600379	20010806	00379	SW  	2001	8	6	HEEA073688       	1	20010619	G	2510	206033105115	SEAT            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MISMARKED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3108E					51498				PANEL IS MISIDENTIFIED. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600380	20010806	00380	SW  	2001	8	6	HEEA073689       	1	20010619	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				WORN AND UNSTAKED BEARINGS. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600381	20010806	00381	SW  	2001	8	6	HEEA073690       	1	20010619	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				BOTH BEARINGS UNSTAKED. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600382	20010806	00382	SW  	2001	8	6	HEEA073691       	1	20010619	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										TRANSMISSION	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				BEARINGS WORN. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600383	20010806	00383	SW  	2001	8	6	HEEA073692       	1	20010619	G	6330	206033506103	RESTRAINT       			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7074W					52033				BEARINGS WORN. IN SHOP FOR REPAIR.						1	G	7	1 	3U			NC	H2SW    					 
2001080600384	20010806	00384	SW  	2001	8	6	HEEA073693       	1	20010619	G	7933	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6160Z					51610				DURING START TOT INDICATOR DID NOT INDICATE TEMPERATURE. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600385	20010806	00385	SW  	2001	8	6	HEEA073694       	1	20010619	G	2435	23081018	STARTER GEN     			BELL  	206   	206L3       	1182108	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				TROUBLESHOOTING GENERATOR PROBLEM. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600386	20010806	00386	GL  	2001	8	6	HEEA073695       	2	20010619	G	7323	252469211	GOVERNOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	30KH					51527				WILL NOT HOLD 100 PERCENT N2 SETTING. IN SHOP FOR REPAIR.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080600387	20010806	00387	GL  	2001	8	6	HEEA073696       	2	20010619	G	7321	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31073					51519				ENGINE WOULD HIT 850 DEGREE ON START.  ADJUSTING START/DERICH AND START/ACCELERATION TO MINIMUM WOULD NOT BRING THE ENGI	NE TO AN ACCEPTABLE START TEMPERATURE. IN SHOP FOR REPAIR.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001080600388	20010806	00388	SW  	2001	8	6	HEEA073697       	1	20010619	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L3       	1182108	SW  										BOOST PUMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				BOOST PUMP QUIT RUNNING IN FLIGHT. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600389	20010806	00389		2001	8	6	HEEA073698       	4	20010619	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				SLOW TO ERECT. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600391	20010806	00391		2001	8	6	HEEA073700       	4	20010619	G	3457	8143802240D	GPS             			BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22743					3624				LOSES MEMORY. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600392	20010806	00392		2001	8	6	HEEA073701       	4	20010619	G	2350	AA34200	RADIO           			BELL  	206   	206L4       	1182110	SW  										COCKPIT	LOW             	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7077B					52037				VOLUME TOO LOW AND WOULD NOT ADJUST. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			NC	H2SW    					 
2001080600393	20010806	00393		2001	8	6	HEEA073703       	4	20010619	G	2350	PHI001200001201	MIXER BOX       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3116P					51530				WILL NOT RECEIVE ON PILOT'S SIDE. IN SHOP FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600394	20010806	00394		2001	8	6	HEEA073704       	4	20010619	G	2561		BOTTLE          			BELL  	206   	206L3       	1182108	SW  										LIFE VEST	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				"JERK TO INFLATE" TAG ON C02 BOTTLE ASSEMBLY BROKEN. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600395	20010806	00395	SW  	2001	8	6	HEEA073705       	1	20010619	G	6320	206033518007	STOP            			BELL  	206   	206L3       	1182108	SW  										M/R GEARBOC	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21497					51518				RUBBER DETERIORATED. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001080600396	20010806	00396	SW  	2001	8	6	HEEA073706       	1	20010619	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										BATTERY BAY	DISCHARGED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T	485  				28101				BATTERY WEAK.  WON'T HOLD A CHARGE.						2	G	7	2 	4U			 	H10SW   					 
2001080600397	20010806	00397	SW  	2001	8	6	HEEA073707       	1	20010619	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										BATTERY BAY	DISCHARGED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T	485  				28101				BATTERY WEAK.  WON'T HOLD A CHARGE.						2	G	7	2 	4U			 	H10SW   					 
2001080600398	20010806	00398		2001	8	6	HEEA073708       	4	20010619	G	3452	066106200	TRANSCEIVER     			BELL  	407   	407         	       	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				COULD NOT BE PICKED UP BY TOWER. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2001080600399	20010806	00399	SW  	2001	8	6	HEEA073709       	1	20010620	G	6210	206015001115	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH	903  				51403				CORRODED AT BLADE TIP AND LATCH PLATE UNBONDED.						1	G	7	1 	3U			 	H2SW    					 
2001080600400	20010806	00400	SW  	2001	8	6	HEEA073710       	1	20010620	G	6210	206015001115	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH	903  				51403				CORRODED AT BLADE TIP.						1	G	7	1 	3U			 	H2SW    					 
2001080600401	20010806	00401	SW  	2001	8	6	HEEA073712       	1	20010620	G	5302		STRUCTURE       			BELL  	407   	407         	       	SW  										VERTICAL FIN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH				BP1875	53207				VERTICAL FIN CORRODED.						1	G	7	1 	3U			O	H2SW    					 
2001080600402	20010806	00402	SW  	2001	8	6	HEEA073713       	1	20010620	G	3212	206050247131	COVER           			BELL  	407   	407         	       	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH					53396				AFT END CAP IS WORN AND TORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080600403	20010806	00403	SW  	2001	8	6	HEEA073714       	1	20010620	G	3212	206050247138	COVER           			BELL  	407   	407         	       	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				COVER WORN AND END CAP LOOSE. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700005	20010807	00005	SW  	2001	8	7	HEEA073715       	1	20010620	G	6510	206061432118	INLET           			BELL  	407   	407         	       	SW  										T/R OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				OIL COOLER INLET COVER CRACKED. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700006	20010807	00006	SW  	2001	8	7	HEEA073716       	1	20010620	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										T/R BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BLOWER HOUSING HAS CRACKS. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700007	20010807	00007	SW  	2001	8	7	HEEA073717       	1	20010620	G	6510	206061432121	HOUSING         			BELL  	407   	407         	       	SW  										T/R BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				BLOWER HOUSING HAS CRACKS. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700008	20010807	00008	SW  	2001	8	7	HEEA073718       	1	20010620	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	       	SW  										ENGINE	ARCED           	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	741PH	357  				53457				ARCING						1	G	7	1 	3U			O	H2SW    					 
2001080700009	20010807	00009	SW  	2001	8	7	HEEA073719       	1	20010620	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	       	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1558 				53114				STARTER GENERATOR BRUSHES WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2001080700010	20010807	00010	SW  	2001	8	7	HEEA073721       	1	20010620	G	2435		SHAFT           			BELL  	407   	407         	       	SW  										STARTER GEN	BENT            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	1190 			99405	53038				SHAFT BENT.						1	G	7	1 	3U			O	H2SW    					 
2001080700011	20010807	00011	SW  	2001	8	7	HEEA073722       	1	20010620	G	2435		BRUSHES         			BELL  	407   	407         	       	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	3794 			1828	53435				BRUSHES WORN BEYOND LIMITS. REPAIRED BY PHI.  (BELL WILL BE INVOICED)						1	G	7	1 	3U			O	H2SW    					 
2001080700012	20010807	00012	SW  	2001	8	7	HEEA073723       	1	20010620	G	6321		PAD             			BELL  	407   	407         	       	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH				337	53038				WORN PAD. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700013	20010807	00013	SW  	2001	8	7	HEEA073724       	1	20010620	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	       	SW  										FLOAT BOTTLE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	722PH					53288				AFTER FLOAT BOTTLE CHANGE VALVE ASSY LEAKED NITROGEN FROM SOLENOID OPENING ADJUSTMENT CAP. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700014	20010807	00014	SW  	2001	8	7	HEEA073725       	1	20010620	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	       	SW  										OIL PRESSURE	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				ENGINE OIL PRESSURE READING LOW. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700015	20010807	00015	SW  	2001	8	7	HEEA073726       	1	20010620	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	       	SW  										OIL PRESSURE	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH					53461				ENGINE OIL PRESSURE INDICATING 30 PSI LOW IN CRUISE FLIGHT. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700018	20010807	00018	GL  	2001	8	7	HEEA073727       	2	20010620	G	7412	23064130	IGNITER BOX     			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				WORKS INTERMITTENTLY.  AIRCRAFT WOULD NOT LIGHT OFF. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080700019	20010807	00019	SW  	2001	8	7	HEEA073728       	1	20010620	G	6520	406040453101	SEAL            			BELL  	407   	407         	       	SW  										T/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	228  				53199				SEAL LEAKING OIL. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700023	20010807	00023	SW  	2001	8	7	HEEA073729       	1	20010620	G	6310	406040500123B	FREEWHEEL UNIT  			BELL  	407   	407         	       	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	2236 				53207				FRONT SEAL LEAKING. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700025	20010807	00025	SW  	2001	8	7	HEEA073730       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				BLUE MAIN ROTOR PITCH CHANGE BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700026	20010807	00026	SW  	2001	8	7	HEEA073731       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700028	20010807	00028	SW  	2001	8	7	HEEA073732       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH	1201 				53386				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700029	20010807	00029	SW  	2001	8	7	HEEA073733       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700030	20010807	00030	SW  	2001	8	7	HEEA073734       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700031	20010807	00031	SW  	2001	8	7	HEEA073735       	1	20010620	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										M/R PITCH CHANGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999	436  				53323				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700032	20010807	00032	SW  	2001	8	7	HEEA073736       	1	20010620	G	6300	407010206103	BEARING         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BEARING WORN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700035	20010807	00035	SW  	2001	8	7	HEEA073737       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH				53311	53209				WORN. TO BE RETURNED TO VENDOR.  (J0169320)						1	G	7	1 	3U			O	H2SW    					 
2001080700036	20010807	00036	SW  	2001	8	7	HEEA073738       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				53393	53400				WORN. TO BE RETURNED TO VENDOR.  (J0159304)						1	G	7	1 	3U			O	H2SW    					 
2001080700037	20010807	00037	SW  	2001	8	7	HEEA073739       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH				53397	53397				WORN. TO BE RETURNED TO VENDOR.  (J0154475)						1	G	7	1 	3U			O	H2SW    					 
2001080700038	20010807	00038	SW  	2001	8	7	HEEA073740       	1	20010620	G	3210	407030112103	STRAP           			BELL  	407   	407         	       	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				SURFACE DAMAGE. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700039	20010807	00039	SW  	2001	8	7	HEEA073741       	1	20010620	G	5210	407070620138	PANEL           			BELL  	407   	407         	       	SW  										PAX DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				CRACKED AND WORN. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700040	20010807	00040	SW  	2001	8	7	HEEA073742       	1	20010620	G	5210	407070620157	PANEL           			BELL  	407   	407         	       	SW  										PAX/CREW DOOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				DOOR PANEL DAMAGED. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700041	20010807	00041	SW  	2001	8	7	HEEA073743       	1	20010620	G	5210	407070620157	PANEL           			BELL  	407   	407         	       	SW  										PAX/CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				CRACKED AND BROKEN. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700042	20010807	00042	SW  	2001	8	7	HEEA073744       	1	20010620	G	5210	407070620158	PANEL           			BELL  	407   	407         	       	SW  										PAX/CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				CRACKED AND BROKEN. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700043	20010807	00043	SW  	2001	8	7	HEEA073745       	1	20010620	G	5210	407070620158	PANEL           			BELL  	407   	407         	       	SW  										PAX/CREW DOOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				DAMAGED. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700044	20010807	00044	SW  	2001	8	7	HEEA073746       	1	20010620	G	5210	407070620218	PANEL           			BELL  	407   	407         	       	SW  										PAX/CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				CRACKED AND STAINED. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700046	20010807	00046	SW  	2001	8	7	HEEA073747       	1	20010620	G	5260	407301109	STEP            			BELL  	407   	407         	       	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				HEAVY CORROSION AROUND MOUNTING HOLES. SCRAPPED LOCALLY.						1	G	7	1 	3U			O	H2SW    					 
2001080700049	20010807	00049		2001	8	7	HEEA073748       	4	20010620	G	2350	PA1120NVPHI	HEADSET         			BELL  	407   	407         	       	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407XM					53464				WILL NOT TRANSMIT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001080700052	20010807	00052	SW  	2001	8	7	HEEA073749       	1	20010620	G	6520	PHI407111	HOUSING         			BELL  	407   	407         	       	SW  										INPUT SEAL	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001080700053	20010807	00053		2001	8	7	HEEA073750       	4	20010620	G	3400	CI196	ANTENNA         			BELL  	407   	407         	       	SW  										NAVIGATION	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				CORROSION AT BASE. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001080700054	20010807	00054	GL  	2001	8	7	HEEA073751       	2	20010620	G	7421	CH34187A	IGNITER         			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	ERODED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				ELECTRODE ERODED CAUSING DELAYED LIGHT OFF. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080700056	20010807	00056	SW  	2001	8	7	HEEA073752       	1	20010620	G	3110	407375038101	PANEL           			BELL  	407   	407         	       	SW  										COCKPIT	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				SWITCH GUARD BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001080700057	20010807	00057	GL  	2001	8	7	HEEA073753       	2	20010620	G	7313	6899001	NOZZLE          			BELL  	407   	407         	       	SW  	ALLSN 	250C  	250C47B     	 	GL  					FUEL SYSTEM	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	740PH	291  				53435	CAE847473			THREADS RUSTED AND DAMAGED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001080700058	20010807	00058	SW  	2001	8	7	HEEA073754       	1	20010620	G	7921	407062021101	DUCT            			BELL  	407   	407         	       	SW  										OIL COOLER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				OIL COOLER TRANSITION DUCT IS CRACKED. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700059	20010807	00059	SW  	2001	8	7	HEEA073755       	1	20010620	G	6330	407310203101	MOUNT           			BELL  	407   	407         	       	SW  										TRANSMISSION	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				RUBBER IN MOUNT BAD.  SERIAL NUMBERS REMOVED ARE LP1891 AND LP1902. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700060	20010807	00060	SW  	2001	8	7	HEEA073756       	1	20010620	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										T/R DRIVE	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				BROKEN. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700061	20010807	00061	SW  	2001	8	7	HEEA073757       	1	20010620	G	2840	407362005103	SWITCH          			BELL  	407   	407         	       	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				FALSE INDICATION, LIGHT ON WITH 400 LBS OF FUEL. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700062	20010807	00062	SW  	2001	8	7	HEEA073758       	1	20010620	G	2840	407362005103	SWITCH          			BELL  	407   	407         	       	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				LOW LEVEL LIGHT COMES ON INTERMITTENTLY. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700063	20010807	00063	SW  	2001	8	7	HEEA073759       	1	20010620	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										ENGINE	MALFUNCTIONED   	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				RT PUMP LIGHT DOES NOT ILLUMINATE WITH A/C POWER ON AND PUMP OFF. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700064	20010807	00064	SW  	2001	8	7	HEEA073760       	1	20010620	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				LT TRANSFER PUMP LIGHT DOES NOT ILLUMINATE WITH A/C POWER ON AND PUMP OFF. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700066	20010807	00066	SW  	2001	8	7	HEEA073761       	1	20010620	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH					53142				RT BOOST PUMP LIGHT DOES NOT ILLUMINATE WITH CIRCUIT BREAKER PULLED. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700067	20010807	00067	SW  	2001	8	7	HEEA073762       	1	20010620	G	7930	407375004101	INDICATOR       			BELL  	407   	407         	       	SW  										ENGINE OIL	INACCURATE      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				ENGINE OIL PRESSURE READS 70 PSI WITH NO ENGINE POWER. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700068	20010807	00068	SW  	2001	8	7	HEEA073763       	1	20010620	G	2910	70061V000V444A	TUBE            			BELL  	407   	407         	       	SW  										HYD SYSTEM	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				CHAFED. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700072	20010807	00072	SW  	2001	8	7	HEEA073764       	1	20010620	G	8000	SM20ACD300A21	RELAY           			BELL  	407   	407         	       	SW  										STARTER	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407XM					53464				STARTER RELAY STUCK IN CLOSED POSITION ON ENGINE WASH. TO BE RETURNED TO VENDOR.						1	G	7	1 	3U			O	H2SW    					 
2001080700073	20010807	00073	SW  	2001	8	7	HEEA073765       	1	20010620	G	2841	70077P140B370	HOSE            			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	DAMAGED         	E			HEEA	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	03	108X					33115				SHORTLY AFTER TAKEOFF, BOTH FUEL TRANSFER CAUTION LIGHTS ILLUMINATED.  THE FUEL QUANTITY INDICATOR SHOWED BOTH FORWARD F	UEL CELLS EMPTY AND MID TANKS SHOWING 50 LBS. WITH 1500 LBS ON BOARD. REPLACED 3 EACH HOSES. (P/N 70-077P140B370, P/N 70	-077P288W294, P/N 412-061-610-103)				1	G	7	2 	4U			 	H4SW    					 
2001080700074	20010807	00074	SW  	2001	8	7	HEEA073766       	1	20010620	G	2931	222375019105	TRANSMITTER     			BELL  	214   	214ST       	1182106	SW  										HYD SYSTEM	MALFUNCTIONED   	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	03	59806					28140				SHORTLY AFTER TAKEOFF, THE NR 1 HYDRAULIC PRESSURE GAUGE PEGGED OUT. REPLACED PRESSURE TRANSMITTER.						2	G	7	2 	4U			 	H10SW   					 
2001080700075	20010807	00075	SW  	2001	8	7	HEEA073767       	1	20010620	G	6420	407312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA				53038	53016				ELASTOMERIC BEARING DEBONDED. TO BE RETURNED TO VENDOR.  (J0165342-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700076	20010807	00076	SW  	2001	8	7	HEEA073768       	1	20010620	G	6510	406040339105	BEARING         		407040302101	BELL  	407   	407         	       	SW  										TAIL ROTOR	VIBRATES        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				A164	53142				ROUGH VIBRATION ON TAILBOOM. TO BE RETURNED TO VENDOR.  (J0162310-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700077	20010807	00077	SW  	2001	8	7	HEEA073769       	1	20010620	G	6510	407340339103	BEARING         		407040302101	BELL  	407   	407         	       	SW  										TAIL ROTOR	OVERHEATED      	E			HEEA	O				OTHER                   				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	467PH				A15	53142				OVERHEATED. TO BE RETURNED TO VENDOR.  (J0164213-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700235	20010807	00235	SW  	2001	8	7	HEEA073770       	1	20010620	G	6510	407340339103	BEARING         		407040302107	BELL  	407   	407         	       	SW  										TAIL ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				A1964	53400				METAL. TO BE RETURNED TO VENDOR.  (J0167780-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700236	20010807	00236	SW  	2001	8	7	HEEA073771       	1	20010620	G	6510	407340339103	BEARING         		407040302107	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH				A1949	53266				WORN. TO BE RETURNED TO VENDOR.  (J0168105-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700237	20010807	00237	SW  	2001	8	7	HEEA073772       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH				53277	53327				WORN. TO BE RETURNED TO VENDOR.  (J0166791-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700238	20010807	00238	SW  	2001	8	7	HEEA073773       	1	20010620	G	6310	406340102101	CARBON SEAL     		406040500123	BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH				A4361	53059				WORN. TO BE RETURNED TO VENDOR.  (J0165492-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700239	20010807	00239	SW  	2001	8	7	HEEA073774       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH				53396	53159				WORN. TO BE RETURNED TO VENDOR.  (J0165250-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700240	20010807	00240	SW  	2001	8	7	HEEA073775       	1	20010620	G	6310	406340102101	CARBON SEAL     		PHI407109   	BELL  	407   	407         	       	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	490PH					53378				FREEWHEELING UNIT FORWARD SEAL LEAKING OIL. TO BE RETURNED TO VENDOR.  (J0160511-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700241	20010807	00241	SW  	2001	8	7	HEEA073776       	1	20010620	G	6300	406040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH				PHI0015	53378				WORN SPLINES. TO BE RETURNED TO VENDOR.  (J0167662-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700242	20010807	00242	SW  	2001	8	7	HEEA073777       	1	20010620	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH				PHI0015	53378				ROUGH.  SERIAL NUMBERS REMOVED ARE B00-2007 AND B00-2035. TO BE RETURNED TO VENDOR.  (J0167662-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700243	20010807	00243	SW  	2001	8	7	HEEA073779       	1	20010620	G	6300	406040320101	SHAFT           		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				PHI0004	53400				WORN SPLINES. TO BE RETURNED TO VENDOR  (J0166773-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700244	20010807	00244	SW  	2001	8	7	HEEA073780       	1	20010620	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	       	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				PHI0004	53400				WORN.  SERIAL NUMBERS REMOVED ARE F99-2018 AND F99-1690. TO BE RETURNED TO VENDOR  (J0166773-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700245	20010807	00245	SW  	2001	8	7	HEEA073781       	1	20010620	G	6420	407312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	1733 			53393	53016				ELASTOMER SHEETING AND CHAFING. TO BE RETURNED TO VENDOR  (J0169927-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700246	20010807	00246	SW  	2001	8	7	HEEA073782       	1	20010620	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	       	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	613  			53393	53016				WORN. TO BE RETURNED TO VENDOR  (J0169927-WA)						1	G	7	1 	3U			O	H2SW    					 
2001080700282	20010807	00282	EU  	2001	8	7	HEEA073783       	1	20010619	G	6210	10515141	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	81982	6167 				S818				THE OUTBOARD LEADING EDGE STRIP SEPARATED ON THE OUTBOARD TIP. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2001080700283	20010807	00283	EU  	2001	8	7	HEEA073784       	1	20010619	G	6210	10515150	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	81982	5832 				S818				THE OUTBOARD LEADING EDGE STRIP SEPARATED IN SEVERAL AREAS. SENDING TO VENDOR FOR REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2001080700285	20010807	00285	EU  	2001	8	7	HEEA073785       	1	20010619	G	5320	350A21010108	DRAIN LINE      			SNIAS 	350   	AS350B2     	8680813	EU  										FUSELAGE	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	40466					3004				PIPE LEAKS AT CONNECTION. REPLACED WITH SERVICEABLE PIPE.						1	G	7	1 	3U			 	H9EU    					 
2001080700287	20010807	00287	EU  	2001	8	7	HEEA073786       	1	20010619	G	7921	1184961	OIL COOLER      			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE OIL	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466					3004				OIL COOLER CORRODED. REPLACED WITH SERVICEABLE ENG OIL COOLER.						1	G	7	1 	3U			 	H9EU    					 
2001080700288	20010807	00288	EU  	2001	8	7	HEEA073787       	1	20010619	G	6322	1184964	OIL COOLER      			SNIAS 	350   	AS350B2     	8680813	EU  										TRANSMISSION	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466					3004				OIL COOLER CORRODED. REPLACED WITH SERVICEABLE TRANS OIL COOLER.						1	G	7	1 	3U			 	H9EU    					 
2001080700325	20010807	00325	EU  	2001	8	7	HEEA073788       	1	20010619	G	6520		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										PITCH LINK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				INBOARD BEARING WORN. REPLACED WITH SERVICEABLE T/R PITCH LINK.						1	G	7	1 	3U			 	H9EU    					 
2001080700327	20010807	00327	EU  	2001	8	7	HEEA073789       	1	20010619	G	6300	350A57117720	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466					3004				WORN AT STOP. REPLACED WITH SERVICEABLE STOP PLATE.						1	G	7	1 	3U			 	H9EU    					 
2001080700331	20010807	00331	EU  	2001	8	7	HEEA073791       	1	20010619	G	3040	350A89103701	ARM             			SNIAS 	350   	AS350B2     	8680813	EU  										WINDSHIELD WIPER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466					3004				CRACKED AT MOUNT. REPLACED WITH SERVICEABLE WIPER ARM.						1	G	7	1 	3U			 	H9EU    					 
2001080700332	20010807	00332	EU  	2001	8	7	HEEA073792       	1	20010619	G	2560	504305401	INERTIA REEL    			SNIAS 	350   	AS350B2     	8680813	EU  										SEAT BELT	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4000L					2873				RECEIVED NEW INERTIAL REEL AND FOUND RELEASE CABLE AT ATTACHMENT BROKEN AT REEL. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H9EU    					 
2001080700333	20010807	00333	EU  	2001	8	7	HEEA073793       	1	20010619	G	6220	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466					3004				ELASTOMERIC RUBBER SEPARATED BEYOND LIMITS. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H9EU    					 
2001080700336	20010807	00336	EU  	2001	8	7	HEEA073794       	1	20010619	G	2931	MA12401	PRESSURE SWITCH 			SNIAS 	350   	AS350B      	8680801	EU  										HYD SYSTEM	DEFECTIVE       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				HYD. CAUTION LIGHT ILLUMINATED INTERMITTENTLY. SENDING TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H9EU    					 
2001080700337	20010807	00337		2001	8	7	HEEA073795       	4	20010619	G	3452	066106200	TRANSCEIVER     			BOLKMS	117   	BK117A1     	5626010	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911LK					7068				ATC REPORTED NOT GETTING THE RIGHT NUMBER. PERFORMED PRELIMINARY INSPECTION AND FOUND INTERMITTENT DIAL, ALSO MTL OUT OF	 SPECIFICATIONS, SIGNAL CUTS OUT AT -64DB WHEN DYNAMIC RANGE IS SET TO -9DB, ADJUSTED IF SECTION AND PRESELECTOR, NO HEL	P.  PROBLEM ON MAIN BOARD.  SENDING TO VENDOR FOR REPAIR.				1	G	7	2 	3U			 	H13EU   					 
2001091100012	20010911	00012	GL  	2001	9	11	HEEA075478       	2	20010821	G	7250	23033861	COVER           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					SUMP	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U				CAT34156F	S678				TURBINE REMOVED DUE TO NR 1 & 2 WHEEL CYCLES.  UPON INSPECTION OF TURBINE NOTED NR 8 SUMP NUT BRAZEMENT ERODED AND CRACK	ED. SCRAPPED COVER AND REPLACED WITH SERVICEABLE PART.					1	G	7	2 	3U	3	U	 	H3EU    	E4CE				 
2001091100013	20010911	00013	GL  	2001	9	11	HEEA075479       	2	20010821	G	7250	23053299	TURBINE WHEEL   			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X	1904 				51552	CAE895491			ENGINE REMOVED DUE TO 2000 HOUR INSPECTION.  UPON INSPECTION OF TURIBNE PARTS NOTED SULFIDATION ON LEADING EDGE OF NR 1 	WHEEL BLADES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091100014	20010911	00014	GL  	2001	9	11	HEEA075480       	2	20010821	G	7230	23066675	LINER           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				TORQUE OSCILLATIONS ABOVE 80%.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091100015	20010911	00015	SW  	2001	9	11	HEEA075481       	1	20010821	G	7120	23069751	MOUNT           			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091100016	20010911	00016		2001	9	11	HEEA075482       	4	20010827	G	3434	066301201	SENSOR          			SKRSKY	S76   	S76A        	8143006	NE  										MARKER BEACON	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				LIGHT SENSOR BROKEN. PERFORMED PRELIMINARY INSPECTION.  FOUND V101 PHOTOCELL BROKEN OFF.  REPLACED.  REPAIRED.  ALSO INS	TALLED 3 LIGHT HOODS.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H1NE    					 
2001091100017	20010911	00017		2001	9	11	HEEA075483       	4	20010828	G	2350	100005430	HEADSET         			SKRSKY	S76   	S76A        	8143006	NE  										RADIO	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				BROKEN WIRES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001091100018	20010911	00018	GL  	2001	9	11	HEEA075484       	2	20010828	G	7412	106149501	IGNITER BOX     			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				IGNITER BOX INOPERATIVE.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001091200001	20010912	00001		2001	9	12	HEEA075485       	4	20010828	G	3425	1113025	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										HSI	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G					760076				HSI COURSE KNOB COMES OFF.						1	G	7	2 	3U			 	H1NE    					 
2001091200002	20010912	00002	SW  	2001	9	12	HEEA075486       	1	20010821	G	6320	204040379003	QUILL           			BELL  	412   	412         	1182202	SW  											LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				QUILL ASSY SEEPING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091200003	20010912	00003	SW  	2001	9	12	HEEA075487       	1	20010821	G	3246	205050400101	SADDLE          		412050015110	BELL  	412   	412         	1182202	SW  										SKID TUBE	MISDRILLED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R				DRK100692	36007				MISDRILLED HOLES.  THE HOLES FOR THE BOLTS (99-13-1), THAT ATTACHES THE FWD. CROSSTUBE TO THE SKID TUBE SADDLE ARE DRILL	ED FOR AN4 BOLTS.					1	G	7	2 	4U			 	H4SW    					 
2001091200004	20010912	00004	SW  	2001	9	12	HEEA075488       	1	20010821	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL BOOST	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				PUMP PRODUCES NO PRESSURE.						1	G	7	2 	4U			 	H4SW    					 
2001091200018	20010912	00018	SW  	2001	9	12	HEEA075489       	1	20010821	G	6320	205076034007	FILTER ELEMENT  			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				FILTER BYPASS EXTENDED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091200019	20010912	00019	SW  	2001	9	12	HEEA075490       	1	20010821	G	6420	206001725001	PAD             			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				GREASE SEALS MISSING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200020	20010912	00020	SW  	2001	9	12	HEEA075491       	1	20010821	G	6720	206001763001	BELLCRANK       			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				TAIL ROTOR BELLCRANK ASSY HAS CORROSION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200021	20010912	00021	SW  	2001	9	12	HEEA075492       	1	20010821	G	6210	206010200133	BLADE           			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2277A	2336 				3630				EXTREME TRAILING EDGE SPAR CORRODED AT THE TIP OF THE BLADE.						1	G	7	1 	3U			 	H2SW    					 
2001091200022	20010912	00022	SW  	2001	9	12	HEEA075493       	1	20010821	G	6230	206010360005	LINK            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				MAIN ROTOR HEAD LINK ASSY IS CORRODED. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200023	20010912	00023	SW  	2001	9	12	HEEA075494       	1	20010821	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				STICKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200024	20010912	00024	SW  	2001	9	12	HEEA075495       	1	20010821	G	6220	206011117003	RESTRAINT       			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				STICKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200025	20010912	00025	SW  	2001	9	12	HEEA075496       	1	20010821	G	6420	206011725001	ROD             			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				ROD BEARING WORN. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200026	20010912	00026	SW  	2001	9	12	HEEA075497       	1	20010821	G	6300	206033553001	STOP            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				RUBBER DEBONDED. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200027	20010912	00027	SW  	2001	9	12	HEEA075498       	1	20010821	G	6300	206033554101	LINK            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARING BAD.						1	G	7	1 	3U			 	H2SW    					 
2001091200028	20010912	00028	SW  	2001	9	12	HEEA075499       	1	20010821	G	6310	206040015015	DISK            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497	8748 				51518				DISC WORN CAUSING NOISE WHEN ROTOR BRAKES APPLIED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200029	20010912	00029	SW  	2001	9	12	HEEA075500       	1	20010821	G	6310	206040270101	SUPPORT         			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200030	20010912	00030	SW  	2001	9	12	HEEA075501       	1	20010821	G	6310	206040270101	SUPPORT         			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	22751					3627				LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200031	20010912	00031	SW  	2001	9	12	HEEA075502       	1	20010821	G	6520	206040402105	GEARBOX         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497	8684 				51518				PLAY IN OUTPUT SHAFT, UNABLE TO BALANCE TAIL ROTOR. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200032	20010912	00032	SW  	2001	9	12	HEEA075503       	1	20010821	G	6520	206040402105	GEARBOX         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				MAKING METAL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200033	20010912	00033	SW  	2001	9	12	HEEA075504       	1	20010821	G	3246	206050128001	SHOE            			BELL  	206   	206L3       	1182108	SW  										MLG SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				SKID SHOE WORN. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200034	20010912	00034	SW  	2001	9	12	HEEA075505       	1	20010821	G	3246	206050129001	SHOE            			BELL  	206   	206L3       	1182108	SW  										MLG SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				SKID SHOE WORN. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200035	20010912	00035	SW  	2001	9	12	HEEA075506       	1	20010821	G	3213	206053109007	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH					51403				CORRODED BEYOND LIMITS. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200036	20010912	00036	SW  	2001	9	12	HEEA075507       	1	20010821	G	3213	206053109008	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH					51403				CROSSTUBE CORRODED BEYOND LIMITS. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200037	20010912	00037	SW  	2001	9	12	HEEA075508       	1	20010821	G	3213	206053203101	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108PH					51334				CROSSTUBE CORRODED BEYOND LIMITS. SCRAPPED.						1	G	7	1 	3U			 	H2SW    					 
2001091200038	20010912	00038	SW  	2001	9	12	HEEA075509       	1	20010821	G	2820	206061613003	FITTING         			BELL  	206   	206L3       	1182108	SW  										FUEL SUMP	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E					51498				FWD. FUEL SUMP FITTINGS CORRODED. REPLACED WITH SERVICEABLE FITTINGS.						1	G	7	1 	3U			 	H2SW    					 
2001091200039	20010912	00039	SW  	2001	9	12	HEEA075510       	1	20010821	G	2820	206061634003	VALVE           			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	42EA					51542				LEAKING FROM FUEL COCK. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200042	20010912	00042	SW  	2001	9	12	HEEA075511       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				ACTUATOR INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200044	20010912	00044	SW  	2001	9	12	HEEA075512       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR WILL NOT EXTEND OR RETRACT.						1	G	7	1 	3U			 	H2SW    					 
2001091200045	20010912	00045	SW  	2001	9	12	HEEA075513       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81SP					51029				WOULD NOT BEEP.  BEEP WAS INTERMITTENT THROUGHOUT ADJUSTMENT ATTEMPTS.						1	G	7	1 	3U			 	H2SW    					 
2001091200047	20010912	00047	SW  	2001	9	12	HEEA075514       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				N2 CHANGES IN FLIGHT.						1	G	7	1 	3U			 	H2SW    					 
2001091200048	20010912	00048	SW  	2001	9	12	HEEA075515       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001091200049	20010912	00049	SW  	2001	9	12	HEEA075516       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L4       	1182110	SW  										ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				ACTUATOR INTERMITTENT OPERATION.						1	G	7	1 	3U			NC	H2SW    					 
2001091200062	20010912	00062	SW  	2001	9	12	HEEA075517       	1	20010821	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				ACTUATOR MOTOR WORKED SEVERAL TIMES ON AIRCRAFT AND QUIT.  BENCH TEST WAS ABLE TO RETRACT BUT NOT EXTEND.						1	G	7	1 	3U			 	H2SW    					 
2001091200064	20010912	00064	SW  	2001	9	12	HEEA075518       	1	20010821	G	6710	206062721113	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR WILL NOT RETRACT.						1	G	7	1 	3U			 	H2SW    					 
2001091200066	20010912	00066	SW  	2001	9	12	HEEA075519       	1	20010821	G	2841	206063633103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										FUEL QTY	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				FLUCTUATING; OCCASIONALLY PEGGING OUT ON THE HIGH SIDE.						1	G	7	1 	3U			 	H2SW    					 
2001091200088	20010912	00088	SW  	2001	9	12	HEEA075520       	1	20010821	G	7120	206064105101	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				CORROSION ON INSIDE OF TUBE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200093	20010912	00093	SW  	2001	9	12	HEEA075521       	1	20010821	G	7120	206064105101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				PITTING ON INSIDE OF TUBE. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200094	20010912	00094	SW  	2001	9	12	HEEA075522       	1	20010821	G	7120	206064105102	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				ELONGATED HI-LOC HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200096	20010912	00096	SW  	2001	9	12	HEEA075523       	1	20010821	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				CORROSION ON INSIDE OF TUBE. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200099	20010912	00099	SW  	2001	9	12	HEEA075524       	1	20010821	G	6220	206011100159	HUB             			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				YELLOW GRIP SLINGING GREASE. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001091200100	20010912	00100	SW  	2001	9	12	HEEA075525       	1	20010821	G	6320	206040004107	TRANSMISSION    			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				MAKING METAL. REPLACED WITH SERVICEABLE ASSY.						1	G	7	1 	3U			 	H2SW    					 
2001091200101	20010912	00101	SW  	2001	9	12	HEEA075526       	1	20010821	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200102	20010912	00102	SW  	2001	9	12	HEEA075527       	1	20010821	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200103	20010912	00103	SW  	2001	9	12	HEEA075528       	1	20010821	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH					51403				END FITTING RIVET HOLES ARE ELONGATED AND WORN BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200147	20010912	00147	SW  	2001	9	12	HEEA075529       	1	20010821	G	7120	206064107101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				RIVET HOLES ARE ELONGATED. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200148	20010912	00148	SW  	2001	9	12	HEEA075530       	1	20010821	G	7120	206064107109	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				ELONGATED HI-LOC HOLES. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200149	20010912	00149	SW  	2001	9	12	HEEA075531       	1	20010821	G	7120	206064107111	LEG ASSY        			BELL  	206   	206L4       	1182110	SW  										ENGINE MOUNT	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091200150	20010912	00150	SW  	2001	9	12	HEEA075532       	1	20010821	G	6730	206076062003	CYLINDER        			BELL  	206   	206L3       	1182108	SW  										SERVO SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8594X					51531				LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200151	20010912	00151	SW  	2001	9	12	HEEA075533       	1	20010821	G	6730	206076062003	CYLINDER        			BELL  	206   	206L3       	1182108	SW  										SERVO SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8591X					51495				LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200152	20010912	00152	SW  	2001	9	12	HEEA075534       	1	20010821	G	3246	206323002M	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108PH					51334				CORRODED BEYOND LIMITS IN SADDLE AREA. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200153	20010912	00153	SW  	2001	9	12	HEEA075535       	1	20010821	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				CORROSION PITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200154	20010912	00154	SW  	2001	9	12	HEEA075536       	1	20010821	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				CORRODED BEYOND LIMITS IN AREA AROUND SADDLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200156	20010912	00156	SW  	2001	9	12	HEEA075537       	1	20010821	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200157	20010912	00157	SW  	2001	9	12	HEEA075538       	1	20010821	G	3246	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				CORROSION PITS UNDER BOTH SADDLE MOUNT AREAS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200158	20010912	00158	SW  	2001	9	12	HEEA075539       	1	20010821	G	3246	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG SKID	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200159	20010912	00159	SW  	2001	9	12	HEEA075540       	1	20010821	G	3246	206324007	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH					51403				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200160	20010912	00160	SW  	2001	9	12	HEEA075541       	1	20010821	G	3246	206324008	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH					51403				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200161	20010912	00161	SW  	2001	9	12	HEEA075542       	1	20010821	G	3246	206324459	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				RIVET POPPED. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200162	20010912	00162	SW  	2001	9	12	HEEA075543       	1	20010821	G	3246	206324459	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200174	20010912	00174	SW  	2001	9	12	HEEA075544       	1	20010821	G	3246	206324460	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200175	20010912	00175	SW  	2001	9	12	HEEA075545       	1	20010821	G	6520	212040004009	GEARBOX         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				INPUT QUILL SEAL LEAKING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001091200177	20010912	00177	SW  	2001	9	12	HEEA075546       	1	20010821	G	6300	212040005103	DRIVE SHAFT     			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				GREASE SEALS LEAKING. REPLACED WITH SERVICEABLE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001091200179	20010912	00179	SW  	2001	9	12	HEEA075548       	1	20010821	G	6510	212040600005	BEARING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	OVERHEATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				OVERTEMP INDICATION. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091200180	20010912	00180	GL  	2001	9	12	HEEA075549       	2	20010821	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				ENGINE T.O.T. RUNNING HIGHER THAN NORMAL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200182	20010912	00182	GL  	2001	9	12	HEEA075550       	2	20010821	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				ENGINE T.O.T. RUNNING HIGHER THAN NORMAL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200185	20010912	00185	GL  	2001	9	12	HEEA075551       	2	20010821	G	7200	23008727	SOLENOID        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4835					51131				STUCK OPEN CAUSING HIGH T.O.T. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200190	20010912	00190	SW  	2001	9	12	HEEA075552       	1	20010821	G	7160	23033400	FILTER          			BELL  	206   	206L3       	1182108	SW  										ENGINE INTAKE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				N1 HANGS UP DURING STARTS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200192	20010912	00192	SW  	2001	9	12	HEEA075553       	1	20010821	G	2435	23081018	STARTER GEN     			BELL  	206   	206L3       	1182108	SW  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				GENERATOR WILL NOT RESET. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091200194	20010912	00194	GL  	2001	9	12	HEEA075554       	2	20010821	G	7321	252464430	FUEL CONTROL    			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22743					3624				UNABLE TO ADJUST START TEMP. LOW ENOUGH TO GET ENG. STARTED.  START MODE FUEL FLOW APPROX. 3 TIMES ALLISON LIMITS. FOUND	 FLOWS 12PPH HIGH.  (METERING VALVE SHIFTED), RECALIBRATED AND TESTED OK.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200197	20010912	00197	GL  	2001	9	12	HEEA075555       	2	20010821	G	7323	252469211	GOVERNOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				UNABLE TO CORRECT OVERSPEED. FOUND GOVERNOR BREAK RESPONDED 100 RPM EARLY.  TESTED SATISFACTORY.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200203	20010912	00203	GL  	2001	9	12	HEEA075556       	2	20010821	G	7321	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31073	2534 				51519				ENGINE WOULD NOT ACCELERATE ON START, ADJUSTING START DERICHMENT AND START ACCELERATION TO MAXIMUM HAD NO EFFECT. FOUND 	PRESSURIZING VALVE TO BE STICKING.  REMOVED VALVE AND POLISHED.  VALVE WOULD STILL HANG UP.  REPLACED VALVE AND UNIT TES	TED SATISFACTORY.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200204	20010912	00204	GL  	2001	9	12	HEEA075557       	2	20010821	G	7321	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4282Z	9935 				51499				START ACCEL ADJUSTMENT FROZEN. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001091200208	20010912	00208	SW  	2001	9	12	HEEA075558       	1	20010821	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN BATTERY	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8587X					51464				LOW STARTING CAPACITY AND WILL NOT TAKE A FULL CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001091200209	20010912	00209	SW  	2001	9	12	HEEA075559       	1	20010821	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN BATTERY	OVERHEATED      	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	4835					51131				BATTERY HOT LIGHT CAME ON. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001091200212	20010912	00212	SW  	2001	9	12	HEEA075560       	1	20010821	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R	11837				36007				BLADE DIVES UNABLE TO TRACK.						1	G	7	2 	4U			 	H4SW    					 
2001091200213	20010912	00213	SW  	2001	9	12	HEEA075561       	1	20010821	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R	11544				36007				BLADE EXCESSIVELY HEAVY AND CANNOT GET TO 80 PERCENT ROTOR RPM.						1	G	7	2 	4U			 	H4SW    					 
2001091200214	20010912	00214	SW  	2001	9	12	HEEA075562       	1	20010821	G	3213	412050010111A	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z	3621 				36019				CROSSTUBE CORRODED. SCRAPPED.						1	G	7	2 	4U			 	H4SW    					 
2001091300001	20010913	00001	SW  	2001	9	13	HEEA075563       	1	20010821	G	3212	412050013113	FLOAT           			BELL  	412   	412         	1182202	SW  										RT MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				RT MID FLOAT BAG LEAKING AROUND RELIEF VALVE. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001091300002	20010913	00002	SW  	2001	9	13	HEEA075564       	1	20010821	G	3212	412050013113	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				FLOAT BAG LEAKING.						1	G	7	2 	4U			 	H4SW    					 
2001091300003	20010913	00003	SW  	2001	9	13	HEEA075565       	1	20010821	G	3246	412050015110	SKID            			BELL  	412   	412         	1182202	SW  										MLG	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				FWD SADDLE RIVETS LOOSE. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001091300004	20010913	00004	SW  	2001	9	13	HEEA075566       	1	20010821	G	3212	412050017133	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT BAG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				FLOAT BAG COVER VELCRO TORN.						1	G	7	2 	4U			 	H4SW    					 
2001091300005	20010913	00005	SW  	2001	9	13	HEEA075567       	1	20010821	G	3212	412050017133	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT BAG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				FLOAT BAG COVER VELCRO WORN.						1	G	7	2 	4U			 	H4SW    					 
2001091300006	20010913	00006	SW  	2001	9	13	HEEA075568       	1	20010821	G	3212	412050017135	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT BAG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				FLOAT BAG VELCRO TORN.						1	G	7	2 	4U			 	H4SW    					 
2001091300007	20010913	00007	SW  	2001	9	13	HEEA075569       	1	20010821	G	3213	412050045107	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R	1290 				36007				FOUND CORROSION UNDER CENTER PIVOT MOUNT. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE.						1	G	7	2 	4U			 	H4SW    					 
2001091300008	20010913	00008	SW  	2001	9	13	HEEA075570       	1	20010821	G	5210	412060804101	HINGE           			BELL  	412   	412         	1182202	SW  										PAX DOOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				RIVET LOOSE. REPLACED WITH SERVICEABLE HINGE.						1	G	7	2 	4U			 	H4SW    					 
2001091300009	20010913	00009	SW  	2001	9	13	HEEA075571       	1	20010821	G	2810	412061668101	CAP             			BELL  	412   	412         	1182202	SW  										FUEL CELL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				CAP CAN TURN BEYOND OPEN POSITION OR OFTEN MISPOSITIONS CLOSURE CLAWS CAUSING CAP TO BE DIFFICULT TO REMOVE. REPLACED WI	TH SERVICEABLE ASSY.					1	G	7	2 	4U			 	H4SW    					 
2001091300010	20010913	00010		2001	9	13	HEEA075572       	4	20010821	G	2330	002000002	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										PA SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				PA INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND FUSE F1 AND TRANSISTOR Q8 BAD.  REPLACED.  BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001091300011	20010913	00011		2001	9	13	HEEA075573       	4	20010821	G	2312	064101900	RADIO           			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3107N					51512				GARBLED AND WEAK. PERFORMED PRELIMINARY INSPECTION.  FOUND UNIT HAD TOO MUCH POWER OUT BUT GOOD MODULATION.  THEN MODULA	TORS BECAME VERY WEAK AND DISTORTED.  FOUND Q121, Q122 TRANSISTORS BAD.  REPLACED Q121 AND Q122 TRANSISTORS.  ADJUSTED M	IC GAIN AND SIDETONE. REPAIRED.  FOUND MEMORY NOT WORKING DUE TO BROKEN FOIL ON SW102 SWITCH.  REPAIRED BROKEN FOIL.  RE	PAIRED.  BENCH CHECK GOOD.			1	G	7	1 	3U			 	H2SW    					 
2001091300012	20010913	00012		2001	9	13	HEEA075574       	4	20010821	G	2312	064101900	RADIO           			BELL  	206   	206L1       	1182107	SW  										VHF COMMS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1076Y					45380				WOULD NOT CHANGE FREQUENCY. REPLACED BAD KHZ KNOB/SHAFT AND RESOLDERED COLD SOLDER ON SW102 SWITCH.  REPAIRED.  ALIGNED 	RECEIVER AND ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE.  REPLACED BAD DISPLAY LENS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300013	20010913	00013		2001	9	13	HEEA075575       	4	20010824	G	2312	064101902	RADIO           			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8593X					51509				INTERMITTENTLY UNABLE TO CHANGE FREQUENCY. PERFORMED PRELIMINARY INSPECTION.  FOUND SELECTOR KNOBS INTERMITTENTLY DO NOT	 CHANGE FREQUENCY.  CLEANED WAFER SWITCHES.  REPAIRED.  FOUND POWER OUT LOW AT 135 MHZ.  REPLACED C623 AND C624 CAPACITO	RS.  REPAIRED.  ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE.  BENCH CHECK GOOD.				1	G	7	1 	3U			 	H2SW    					 
2001091300014	20010913	00014		2001	9	13	HEEA075576       	4	20010824	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										VHF COMMS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				SQUELCH STAYS ON ALL THE TIME AND THE RF CONNECTOR IS DAMAGED. PERFORMED PRELIMINARY INSPECTION. REPLACED BAD RF CONNECT	OR.  REPAIRED.  ADJUSTED CARRIER SQUELCH, FREQUENCY AND POWER OUT.  BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001091300015	20010913	00015		2001	9	13	HEEA075577       	4	20010824	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										VHF COMMS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30YM					36032				NO SIDETONE. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT MODULATING AND TRANSMIT POWER OUT EXCESSIVE AND COULD NOT 	ADJUST EITHER.  REPLACED BAD Q109 AND Q110 TRANSISTORS.  REPAIRED.  ADJUSTED POWER OUT AND SIDETONE.  FOUND L505 COIL BR	OKEN.  REPLACED COIL. REMOVED LIGHT CORROSION FROM CHASSIS.  BENCH CHECK GOOD.				1	G	7	2 	4U			 	H4SW    					 
2001091300016	20010913	00016		2001	9	13	HEEA075578       	4	20010824	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				TRANSMISSION GARBLED. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE COMPLAINT BUT FOUND DISPLAY LENS BAD.  REPLA	CED LENS  AND REPAIRED.  ADJUSTED FREQUENCY AND SIDETONE.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300017	20010913	00017		2001	9	13	HEEA075579       	4	20010824	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	205FC					51130				FIRST AND LAST DIGITS DISAPPEAR INTERMITTENTLY. PERFORMED PRELIMINARY INSPECTION.  FOUND DISPLAY NOT DIMMING PROPERLY.  	REPLACED V901 PHOTOCELL.  REPAIRED.  FOUND FREQUENCY SELECTORS INTERMITTENT AND MHZ CHANGED BY ITSELF A COUPLE OF TIMES.	  FOUND FREQUENCY SELECTOR CONTACTS VERY DIRTY.  CLEANED. REPAIRED.  REGLUED DISPLAY LENS WHICH WAS LOOSE.  ADJUSTED FRE	QUENCY.  BENCH CHECK GOOD.			1	G	7	1 	3U			 	H2SW    					 
2001091300018	20010913	00018		2001	9	13	HEEA075580       	4	20010824	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				SQUELCH WILL NOT RESET AFTER RECEPTION OR TEST. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001091300019	20010913	00019		2001	9	13	HEEA075581       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206B3       	1181506	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22743					3624				WILL NOT TRANSMIT AT THE RIGHT FREQUENCY. PERFORMED PRELIMINARY INSPECTION.  ADJUSTED FREQUENCY, PULSE WIDTH AND POWER. 	 ALIGNED PRESELECTOR AND IF.  REPAIRED.  ALSO REPLACED BAD V301 PHOTOCELL.  UNIT BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300020	20010913	00020		2001	9	13	HEEA075582       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										VHF COMMS	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3905B					45598				SELECTOR KNOB BROKEN INTERNALLY. PERFORMED PRELIMINARY INSPECTION.  FOUND FACEPLATE BAD.  REPLACED FACEPLATE.  REPAIRED.	  CLEANED CODE SELECTOR WAFER SWITCHES.  ALIGNED IF SECTION.  UNIT BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300021	20010913	00021		2001	9	13	HEEA075583       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										VHF COMMS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	62127					52023				NO REPLY. PERFORMED PRELIMINARY INSPECTION.  FOUND REPLY LIGHT VERY DIM DUE TO BAD PHOTOCELL.  REPLACED V301 PHOTOCELL. 	 REPAIRED PROBLEM.  ALSO REPLACED BAD R477 RESISTOR AND ADJUSTED FREQUENCY AND PULSE WIDTH.  BENCH CHECK GOOD.					1	G	7	1 	3U			NC	H2SW    					 
2001091300022	20010913	00022		2001	9	13	HEEA075584       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				NO TRANSMIT. PERFORMED PRELIMINARY INSPECTION.  FOUND FOUND V101 CAVITY OSCILLATOR BAD.  REPLACED V101, REPAIRED.  ADJUS	TED TO SPECS.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300023	20010913	00023		2001	9	13	HEEA075585       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128					51134				UNIT FAILED ALTITUDE CERTIFICATION.  UNIT TRANSMITS IMPROPER CODES BETWEEN 700 AND 900 PA. PERFORMED PRELIMINARY INSPECT	ION.  ADJUSTED TUBE FOR PROPER FREQUENCY BAND WIDTH.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300024	20010913	00024		2001	9	13	HEEA075586       	4	20010824	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6161A					51611				NOT TRANSMITTING. PERFORMED PRELIMINARY INSPECTION.  FOUND DRAWING EXCESSIVE CURRENT.  FOUND Q1 AND Q3 SHORTED.  SENT TO	 AVCOM AVIONICS & INSTRUMENTS FOR INSPECTION AND REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001091300025	20010913	00025		2001	9	13	HEEA075587       	4	20010824	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										ATC	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				WENT DEAD. PERFORMED PRELIMINARY INSPECTION.  FOUND CR106 DIODE BURNT AND C111 CAPACITOR SHORTED.  ALSO FOUND C115 CAPAC	ITOR BAD.  REPLACED CR106 DIOD AND C111 AND C115 CAPACITORS.  ADJUSTED MTL.  UNIT BENCH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001091300026	20010913	00026		2001	9	13	HEEA075589       	4	20010827	G	2312	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										NAVIGATION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				BAD FROM STOCK. FOUND AT 60 DEGREES TO.  NEEDLE DOES NOT FOLLOW WHEN TURNING COMPASS.  SENT TO GREATLAKES AVIONICS FOR W	ARRANTY REPAIR.					1	G	7	2 	4U			 	H4SW    					 
2001091300027	20010913	00027		2001	9	13	HEEA075590       	4	20010827	G	3416	066304400	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				DH LIGHT IS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND DH SWITCH BROKEN AND LENS CLAMP BROKEN.  INSTALLED DH 	SWITCH AND LENS CLAMP.  ALSO REPLACED THE PHOTOCELL.  THE DH LIGHT STAYS ON AT ALL TIMES AND NO SELF TEST.  SENT TO GREA	TLAKES AVIONICS FOR INSPECTION AND REPAIR.				1	G	7	2 	4U			 	H4SW    					 
2001091300082	20010913	00082		2001	9	13	HEEA075591       	4	20010827	G	2312	0691024155	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										VHF COMMS	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				DIGITAL SEGMENTS ARE INTERMITTENT. PERFORMED PRELIMINARY INSPECTION.  REPLACED DISPLAY.  REPAIRED.  BENCH CHECK GOOD.						1	G	7	1 	3U			 	H2SW    					 
2001091300083	20010913	00083		2001	9	13	HEEA075592       	4	20010827	G	3452	071119218	CONTROL PANEL   			BELL  	214   	214ST       	1182106	SW  										ATC	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				DIGITS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND HEADER BAD.  DIGITS INTERMITTENTLY FLICKERS.  DRIVER BOARD 	CAUSING SOME BRIGHT SEGMENTS ON DISPLAY.  INSTALLED HEADER P305, J304, CAPACITOR NETWORK U301.  DIGITS WILL NOT CHANGE W	HEN DIAL IS TURNED.  SENT TO HONEYWELL, KANSAS FOR INSPECTION AND REPAIR.				2	G	7	2 	4U			 	H10SW   					 
2001091300084	20010913	00084		2001	9	13	HEEA075593       	4	20010827	G	2312	071121525	CONTROL UNIT    			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				DISPLAY HAS ONE DIGIT INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND IC 201 BAD.  REPLACED.  BENCH CHECK GOOD.						2	G	7	2 	4U			 	H10SW   					 
2001091300085	20010913	00085		2001	9	13	HEEA075594       	4	20010827	G	2312	071121540	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				UNIT DOES NOT KEEP LAST TWO DIGITS WHEN TURNED ON. PERFORMED PRELIMINARY INSPECTION.  FOUND IC 1205 BAD.  REPLACED.  BEN	CH CHECK GOOD.					1	G	7	2 	4U			 	H4SW    					 
2001091300086	20010913	00086		2001	9	13	HEEA075595       	4	20010827	G	3455	066107700	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ADF RECEIVER INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001091300087	20010913	00087	SW  	2001	9	13	HEEA075596       	1	20010827	G	2824	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL TRANSFER	INOPERATIVE     	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	2149S					36002				WHILE IN CRUISE FLIGHT, NR 2 FUEL TRANSFER LIGHT ILLUMINATED. REPLACED INOPERATIVE NR 2 TRANSFER PUMP.						1	G	7	2 	4U			 	H4SW    					 
2001091300088	20010913	00088	SW  	2001	9	13	HEEA075598       	1	20010827	G	6320	406340100101	PUMP            			BELL  	407   	407         	       	SW  										OIL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407PH					53003				INTERNAL SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001091300089	20010913	00089	SW  	2001	9	13	HEEA075605       	1	20010827	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	       	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				NO LIGHT WHEN PUMP IS OFF.						1	G	7	1 	3U			O	H2SW    					 
2001091300090	20010913	00090	SW  	2001	9	13	HEEA075607       	1	20010827	G	3340	407076502103S	CONNECTOR       			BELL  	407   	407         	       	SW  										CABIN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				CANNON PLUG CORRODED.  REPEATED PROBLEM WITH CANNON PLUG, SENDING IN FOR EVALUATION FOR POSSIBLE MFG DEFECT.						1	G	7	1 	3U			O	H2SW    					 
2001091300091	20010913	00091		2001	9	13	HEEA075609       	4	20010828	G	2350	100005430	HEADSET         			BELL  	206   	206L3       	1182108	SW  										AUDIO SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				INOPERATIVE. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300093	20010913	00093		2001	9	13	HEEA075610       	4	20010828	G	3410	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				CAUSED THE FLIGHT DIRECTOR TO OSCILLATE IN HEADING MODE.						1	G	7	2 	4U			 	H4SW    					 
2001091300096	20010913	00096		2001	9	13	HEEA075611       	4	20010828	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				COURSE NEEDLE WILL NOT FOLLOW COPILOT'S COURSE NEEDLE.						1	G	7	2 	4U			 	H4SW    					 
2001091300097	20010913	00097		2001	9	13	HEEA075612       	4	20010828	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30YM					36032				RATCHETY IN FLIGHT AND CAUSES AFCS TO KICK.						1	G	7	2 	4U			 	H4SW    					 
2001091300099	20010913	00099		2001	9	13	HEEA075613       	4	20010828	G	3420	1258103	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				COURSE SET 10 DEGREES OFF.						1	G	7	2 	4U			 	H4SW    					 
2001091300100	20010913	00100		2001	9	13	HEEA075614       	4	20010828	G	3457	13824120234	RECEIVER        			BELL  	206   	206B3       	1181506	SW  										GPS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2268V					3605				LOSES ITSELF. PERFORMED PRELIMINARY INSPECTION.  COULD NOT DUPLICATE PROBLEM.  FOUND NAV, AUX AND ENT BUTTONS VERY INTER	MITTENT.  REPLACED.  FOUND D12 BACKLIGHTING BULB INOPERATIVE.  REPLACED.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300102	20010913	00102		2001	9	13	HEEA075615       	4	20010828	G	3457	13824120234	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										GPS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	129MR					51129				CLEARS ITSELF WHEN TURNED OFF, HAS TO HAVE MGUA CODE ENTERED AND UNABLE TO DISABLE SAFEGUARD. PERFORMED PRELIMINARY INSP	ECTION.  CLEANED MEMORY AND REPROGRAMMED.  ALSO DISABLED SAFEGUARD CODE.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	1 	3U			 	H2SW    					 
2001091300103	20010913	00103	SW  	2001	9	13	HEEA075616       	1	20010828	G	5302	206031329103S	ATTACH FITTING  			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				UPPER LT TAIL BOOM FITTING CRACKED AT MOST FWD OUTBOARD RIVET HOLE. REPLACED WITH SERVICEABLE FITTING.						1	G	7	1 	3U			 	H2SW    					 
2001091300104	20010913	00104	SW  	2001	9	13	HEEA075617       	1	20010828	G	5340	206033109001	FITTING         			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				WORN. SCRAPPED AND REPLACED WITH SERVICEABLE FITTING.						1	G	7	1 	3U			 	H2SW    					 
2001091300105	20010913	00105	SW  	2001	9	13	HEEA075618       	1	20010828	G	3213	206053203115	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				CORROSION PITS. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001091300107	20010913	00107	SW  	2001	9	13	HEEA075619       	1	20010828	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				ACTUATOR INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001091300109	20010913	00109	SW  	2001	9	13	HEEA075620       	1	20010828	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300110	20010913	00110	SW  	2001	9	13	HEEA075621       	1	20010828	G	7810	206064300005	EXHAUST STACK   			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300113	20010913	00113	SW  	2001	9	13	HEEA075622       	1	20010828	G	7910	206064522101	TUBE            			BELL  	206   	206L3       	1182108	SW  										OIL SYSTEM	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				APPROXIMATELY 3/8 INCH TOO SHORT SPANWISE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300114	20010913	00114	SW  	2001	9	13	HEEA075623       	1	20010828	G	2120	206070936001	FLAPPER VALVE   			BELL  	206   	206L3       	1182108	SW  										AIR DISTRIBUTION	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251Y					51556				LEVER ON FLAPPER BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300125	20010913	00125	SW  	2001	9	13	HEEA075624       	1	20010828	G	2510	206072841111	SEAT BELT       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30KH					51527				FRAYED BELT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300127	20010913	00127	SW  	2001	9	13	HEEA075625       	1	20010828	G	7930	206075187003	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										OIL TEMP	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR READS 8 PSI HIGH.						1	G	7	1 	3U			 	H2SW    					 
2001091300131	20010913	00131	SW  	2001	9	13	HEEA075626       	1	20010828	G	2420	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										AC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				GENERATOR FAIL CAUTION LIGHT CAME ON.						1	G	7	1 	3U			 	H2SW    					 
2001091300133	20010913	00133	SW  	2001	9	13	HEEA075627       	1	20010828	G	2420	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6161A					51611				GEN FAILED LIGHT ILLUMINATED, GEN WENT OFF LINE WHEN THROTTLE ROLLED DOWN TO IDLE.						1	G	7	1 	3U			 	H2SW    					 
2001091300134	20010913	00134	SW  	2001	9	13	HEEA075628       	1	20010828	G	2420	206075447007	VOLT REGULATOR  			BELL  	206   	206L3       	1182108	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				GENERATOR WILL NOT STAY ON LINE.						1	G	7	1 	3U			 	H2SW    					 
2001091300136	20010913	00136	SW  	2001	9	13	HEEA075629       	1	20010828	G	6420	206075545005	SENSOR          			BELL  	206   	206L3       	1182108	SW  										ROTOR RPM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				NO SIGNAL SENT TO INDICATOR. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300139	20010913	00139		2001	9	13	HEEA075630       	4	20010828	G	3421	206075606103	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PRECESSING 10 DEGREES PER MINUTE.						1	G	7	1 	3U			 	H2SW    					 
2001091300140	20010913	00140	SW  	2001	9	13	HEEA075631       	1	20010828	G	7714	206075681101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				TURBINE NEEDLE STICKS DURING START.						1	G	7	1 	3U			 	H2SW    					 
2001091300142	20010913	00142	SW  	2001	9	13	HEEA075632       	1	20010828	G	7714	206075681105	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				FLUCTUATE IN FLIGHT OR GOES TO ZERO.						1	G	7	1 	3U			 	H2SW    					 
2001091300143	20010913	00143	SW  	2001	9	13	HEEA075633       	1	20010828	G	7714	206075681117	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				TURBINE NEEDLE NOT WORKING.						1	G	7	1 	3U			 	H2SW    					 
2001091300144	20010913	00144	SW  	2001	9	13	HEEA075634       	1	20010828	G	7714	206075681123	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NEEDLES OFF ZERO.						1	G	7	1 	3U			 	H2SW    					 
2001091300146	20010913	00146	SW  	2001	9	13	HEEA075635       	1	20010828	G	7714	206075682107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										GAS PRODUCER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				INDICATOR VERY ERRATIC AND UNRELIABLE IN THE LOW RANGE DURING STARTS.						1	G	7	1 	3U			 	H2SW    					 
2001091300161	20010913	00161	SW  	2001	9	13	HEEA075636       	1	20010828	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				INDICATOR HAS A CONSTANT FLUCTUATION IN CRUISE FLIGHT. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	1 	3U			 	H2SW    					 
2001091300178	20010913	00178	SW  	2001	9	13	HEEA075637       	1	20010828	G	6321	206076047003	CYLINDER        			BELL  	206   	206L1       	1182107	SW  										ROTOR BRAKE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				ROTOR BRAKE WILL NOT ENGAGE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300179	20010913	00179	SW  	2001	9	13	HEEA075638       	1	20010828	G	5260	206301109	STEP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION ON STEP BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300181	20010913	00181	SW  	2001	9	13	HEEA075639       	1	20010828	G	7933	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	30KH					51527				TOT LIGHT WILL NOT TEST. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300182	20010913	00182	SW  	2001	9	13	HEEA075640       	1	20010828	G	5260	206301110	STEP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				CORROSION ON STEP BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300183	20010913	00183	SW  	2001	9	13	HEEA075641       	1	20010828	G	7933	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	92MT					51175				TOT INDICATOR NEEDLE INTERMITTENTLY STICKS AT ZERO DURING START. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300187	20010913	00187	SW  	2001	9	13	HEEA075642       	1	20010828	G	2844	209062003001	SWITCH          			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	6559Z					36019				FLICKERING LIGHT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091300192	20010913	00192	SW  	2001	9	13	HEEA075643       	1	20010828	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										AIR INTAKE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				ACTUATOR INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001091300193	20010913	00193	SW  	2001	9	13	HEEA075644       	1	20010828	G	7922	209070262101	REGULATOR       			BELL  	412   	412         	1182202	SW  										OIL TEMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NOT MARKING PROPERLY.						1	G	7	2 	4U			 	H4SW    					 
2001091300194	20010913	00194	SW  	2001	9	13	HEEA075645       	1	20010828	G	7933	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				READS 30 PSI HIGH. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091300195	20010913	00195	SW  	2001	9	13	HEEA075646       	1	20010828	G	7931	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				READS 5 PSI LOW. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091300196	20010913	00196	SW  	2001	9	13	HEEA075647       	1	20010828	G	2912	2111328	FILTER ELEMENT  			BELL  	206   	206L1       	1182107	SW  										HYD SYSTEM	BYPASSING       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				BYPASS INDICATOR EXTENDED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001091300197	20010913	00197	SW  	2001	9	13	HEEA075648       	1	20010828	G	2912	2111328	FILTER ELEMENT  			BELL  	206   	206L4       	1182110	SW  										HYD SYSTEM	BYPASSING       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				BYPASS BUTTON POPPED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001091300198	20010913	00198	SW  	2001	9	13	HEEA075649       	1	20010828	G	7120	212060718001	BEARING         			BELL  	412   	412         	1182202	SW  										ENGINE MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001091300199	20010913	00199	SW  	2001	9	13	HEEA075650       	1	20010828	G	8011	214060056705	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										CLUTCH SLIPPAGE, OUT OF LIMITS AND STICKING						2	G	7	2 	4U			 	H10SW   					 
2001091300200	20010913	00200	SW  	2001	9	13	HEEA075651       	1	20010829	G	3212	206050247135	COVER           			BELL  	407   	407         	       	SW  										FLOAT BAG	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				DETERIORATED. SCRAPPED IN HOUSE.  PHI REQUESTS FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#68645101.						1	G	7	1 	3U			O	H2SW    					 
2001091300218	20010913	00218	SW  	2001	9	13	HEEA075653       	1	20010831	G	6220	206011149105	YOKE            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR HEAD	SPALLED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										SPAULDING ON OUTBOARD JOURNAL, SCUFFING ON INBOARD JOURNAL AND CORROSION ON RETAINER BORE. SENT TO BELL HELICOPTER TEXTR	ON FOR WARRANTY REPAIR.  REFERENCE:  DMR#727503.					1	G	7	1 	3U			 	H2SW    					 
2001091300220	20010913	00220	SW  	2001	9	13	HEEA075654       	1	20010831	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										BURNED AND WON'T CROSS START.						2	G	7	2 	4U			 	H10SW   					 
2001091300221	20010913	00221	EU  	2001	9	13	HEEA075655       	1	20010821	G	6320	4638302002	PINION GEAR     		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	SPALLED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911HM				226	S683				GEAR TEETH SPALLING AT TOOTH TIP. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2001091300223	20010913	00223	EU  	2001	9	13	HEEA075656       	1	20010821	G	6320	4638303001	BEVEL GEAR      		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	SPALLED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911HM				226	S683				GEAR TEETH SPALLING AT TOOTH ROOT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2001091300224	20010913	00224		2001	9	13	HEEA075657       	4	20010824	G	2350	066105571	AUDIO PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				ICS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  FOUND SWITCH S211 BAD AND SWITCHES S201 THROUGH 210 NOISY.  REPLACED	 SWITCH S211 AND CLEANED SWITCHES S201 THROUGH 210 WITH MISTY CONTACT CLEANER.  REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U			 	H3EU    					 
2001091300244	20010913	00244	EU  	2001	9	13	HEEA075658       	1	20010824	G	2435	150SG122Q	STARTER GEN     			SNIAS 	350   	AS350B2     	8680813	EU  										ELECTRICAL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	40466	345  				3004				WOULD NOT START OR GENERATE POWER.						1	G	7	1 	3U			 	H9EU    					 
2001091300245	20010913	00245	EU  	2001	9	13	HEEA075659       	1	20010824	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4000L	3850 				2873				TAIL ROTOR BLADE HAS A CRACKED SPAR.						1	G	7	1 	3U			 	H9EU    					 
2001091300248	20010913	00248		2001	9	13	HEEA075660       	4	20010827	G	2312	071121540	CONTROL PANEL   			BOLKMS	105   	BO105S      	5626006	EU  										VHF COMMS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				DISPLAY UNREADABLE. PERFORMED PRELIMINARY INSPECTION.  FOUND DISPLAY SEGMENTS UNREADABLE.  FOUND CORROSION UNDER J203 HE	ADER CAUSING PROBLEM.  REMOVED HEADER AND REMOVED CORROSION.  REPLACED J203 HEADER AND APPLIED HUMISEAL AROUND HEADER FO	R CORROSION CONTROL.  REPAIRED DISPLAY PROBLEM.  FOUND TRANSFER SWITCH INTERMITTENT.  CLEANED S102 TRANSFER SWITCH.  REP	AIRED AND BENCH CHECK GOOD.			1	G	7	2 	3U			 	H3EU    					 
2001091300249	20010913	00249	EU  	2001	9	13	HEEA075661       	1	20010828	G	7933	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	INCORRECT       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COULD NOT REMOVE ERRORS.  OFF AT EACH END OF SCALE.						1	G	7	2 	3U			 	H3EU    					 
2001091300251	20010913	00251	EU  	2001	9	13	HEEA075662       	1	20010828	G	5510	11730550	STRUCTURE       			BOLKMS	117   	BK117A1     	5626010	EU  										HORIZONTAL STAB	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL					7198				PAINT PEELED AND TRAILING EDGE DEBONDED.						1	G	7	2 	3U			 	H13EU   					 
2001091300252	20010913	00252	EU  	2001	9	13	HEEA075663       	1	20010828	G	5510	11730550	STRUCTURE       			BOLKMS	117   	BK117A1     	5626010	EU  										HORIZONTAL STAB	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				PAINT DETERIORATED, STRIP.  METAL TRAILING EDGE ALODINED AND PRIMED.  RIGHT DEVORE FLOODLIGHT INSERT LOOSE.						1	G	7	2 	3U			 	H13EU   					 
2001100100093	20011001	00093		2001	10	1	HEEA075926       	4	20010910	G	3416	066303102	ALTIMETER       																	COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PARTS LOOSE INSIDE. SENT TO FIELDTECH AVIONICS, INC. FOR WARRANTY REPAIR.																			 
2001100200063	20011002	00063	GL  	2001	10	2	HEEA075927       	2	20010910	G	7323	252469211	GOVERNOR        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	5435V					760158	CAE890469S			ENGINE N2, T5, FUEL FLOW AND N1 ALL BLEED OFF PRIOR TO REACHING ENGINE LIMITING CHECK PARAMETERS. REPLACED WITH SERVICEA	BLE PART.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001100200066	20011002	00066	GL  	2001	10	2	HEEA075928       	2	20010918	G	7250	23062753	NOZZLE          			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE VANE	BURNED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G					3610	CAE835824			BOLT BROKEN OFF IN NR 6 & 7 JET MOUNT.  NR 1 NOZZLE VANES BURNED BEYOND REPAIRABLE LIMITS.  OVERTEMP INSPECTION CW 2-23-	00 FOR A 930 DEGREE EXCEEDANCE AND FOUND ACCEPTABLE. PART SCRAPPED.  REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001100200068	20011002	00068	GL  	2001	10	2	HEEA075929       	2	20010918	G	7250	6886407	TURBINE WHEEL   			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE SECTION	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G	808  				3610	CAE835824			BOLT BROKEN OFF IN #6&7 JET MOUNT.  WHEEL BLADES SULPHIDATED DUE TO OVERTEMP OF 930 DEGREES ON 2-23-00.  PARTS WERE FOUN	D TO BE ACCEPTABLE WHEN INSPECTED FOR OVERTEMP. PART SCRAPPED.  REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001100200069	20011002	00069	GL  	2001	10	2	HEEA075930       	2	20010918	G	7250	6898782	TURBINE WHEEL   			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G	808  				3610	CAE835824			BOLT BROKEN OFF IN 6&7 JET MOUNT.  WHEEL BLADES SULPHIDATED DUE TO OVERTEMP OF 930 DEGREES ON 2-23-00.  PARTS WERE FOUND	 TO BE ACCEPTABLE WHEN INSPECTED FOR OVERTEMP. PART SCRAPPED.  REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001100200071	20011002	00071	NE  	2001	10	2	HEEA075931       	1	20010924	G	7500	650852201	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										NR 1 ENGINE	MALFUNCTIONED   	E			HEEA	A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		HO	HOVERING       	1			SW	03	760PH					760078				WHEN ATTEMPTING TO DEPART, A LARGE TORQUE SPLIT OCCURRED WHEN ATTEMPTING TO PICK UP INTO A HOVER.  INSPECTION OF NR 1 EN	GINE BY PILOT REVEALED THE PC SAFETY VALVE PARTIALLY CLOSED. PILOT OPENED VALVE AND COMPLIED WITH POWER CHECK AND FOUND 	NORMAL.  MAINTENANCE INSPECTED VALVE AND ENGINE.  RELEASED AIRCRAFT FOR SERVICE.				1	G	7	2 	3U			 	H1NE    					 
2001100200072	20011002	00072	SW  	2001	10	2	HEEA075933       	1	20010910	G	2824	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL TRANFER	INOPERATIVE     	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	03	2149S					36002				WHILE IN CRUISE FLIGHT, NR 2 TRANSFER LIGHT ILLUMINATED. REPLACED INOPERATIVE NR 2 TRANSFER PUMP.						1	G	7	2 	4U			 	H4SW    					 
2001100200075	20011002	00075		2001	10	2	HEEA075934       	4	20010910	G	2312	064101902	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007N					45184				FIRST START OF THE DAY UNIT WOULD NOT TRANSMIT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001100200076	20011002	00076		2001	10	2	HEEA075935       	4	20010910	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				NO INDICATED OUTPUT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001100200077	20011002	00077	GL  	2001	10	2	HEEA075936       	2	20010910	G	7412	103815504	EXCITER         			BELL  	412   	412         	1182202	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				CAUSING THE CIRCUIT BREAKER TO POP.						1	G	7	2 	4U	3	T	 	H4SW    	E10CE				 
2001100200089	20011002	00089	SW  	2001	10	2	HEEA075938       	1	20010910	G	6330	206033554101	LINK            			BELL  	206   	206L4       	1182110	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				ELASTOMERIC PURGING OUT OF MOUNT.						1	G	7	1 	3U			NC	H2SW    					 
2001100200090	20011002	00090	SW  	2001	10	2	HEEA075939       	1	20010910	G	7714	206075682107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										GAS PRODUCER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				ERRATIC BETWEEN 0-15 DEGREES.						1	G	7	1 	3U			 	H2SW    					 
2001100200091	20011002	00091	SW  	2001	10	2	HEEA075941       	1	20010910	G	6510	212040600005	HANGER ASSY     			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				COUPLING LEAKING GREASE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200093	20011002	00093	SW  	2001	10	2	HEEA075942       	1	20010910	G	7722	212075067105	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				FLUCTUATING AT HIGH TEMPERATURES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200094	20011002	00094	SW  	2001	10	2	HEEA075943       	1	20010910	G	6730	212076005111	SERVO           			BELL  	412   	412         	1182202	SW  										ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				TOP PILOT VALVES LEAK WHEN THE AIRCRAFT IS STATIC, NOT RUNNING.  NO LEAKS WHEN AIRCRAFT RUNS IS A STATIC LEAK ONLY. REPL	ACED WITH SERVICEABLE PART.					1	G	7	2 	4U			 	H4SW    					 
2001100200095	20011002	00095	SW  	2001	10	2	HEEA075944       	1	20010910	G	2820	214066226103	CHECK VALVE     			BELL  	412   	412         	1182202	SW  											INTERMITTENT    	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	2148K					36001				INTERMITTENT LIGHT. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200097	20011002	00097		2001	10	2	HEEA075945       	4	20010910	G	2200	2593996333	TARSYN          			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D					31135				PILOTS ADI BEGAN TUMBLING IN LEVEL FLIGHT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	4U			 	H4SW    					 
2001100200098	20011002	00098	SW  	2001	10	2	HEEA075946       	1	20010910	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	31077					51520				WEAK BATTERY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001100200099	20011002	00099	GL  	2001	10	2	HEEA075947       	2	20010910	G	7320	324473513	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	OUT OF ADJ      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				NO TOPPING ADJUSTMENT LEFT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	3	T	 	H4SW    	E10CE				 
2001100200100	20011002	00100	SW  	2001	10	2	HEEA075948       	1	20010910	G	6220	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200102	20011002	00102	SW  	2001	10	2	HEEA075949       	1	20010910	G	6230	412010405109	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200103	20011002	00103	SW  	2001	10	2	HEEA075950       	1	20010910	G	6230	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200104	20011002	00104	SW  	2001	10	2	HEEA075951       	1	20010910	G	6230	412010406115	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200105	20011002	00105	SW  	2001	10	2	HEEA075952       	1	20010910	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				LARGE CRACK BY MID TRIM TAB. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200106	20011002	00106	SW  	2001	10	2	HEEA075953       	1	20010910	G	3213	412050016102	SHOE            			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200107	20011002	00107	SW  	2001	10	2	HEEA075954       	1	20010910	G	6710	412310400101	ROD END         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200110	20011002	00110		2001	10	2	HEEA075955       	4	20010910	G	3421	50400179015	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				WILL NOT CAGE AND PRECESSES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001100200111	20011002	00111		2001	10	2	HEEA075956       	4	20010910	G	3457	8143902240B	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				RAIM UNAVAILABLE.						1	G	7	2 	4U			 	H4SW    					 
2001100200112	20011002	00112		2001	10	2	HEEA075957       	4	20010910	G	3416	8800T	ENCODER         			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				GPS DISPLAYS EXTERNAL ALTIMETER LOST COMMUNICATIONS MESSAGE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001100200114	20011002	00114	SW  	2001	10	2	HEEA075958       	1	20010910	G	7740	DPUA0101	COMPUTER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				INTELLISTART LIGHT STAYS ON, COULDN'T ACCESS WITH MLP. SENT TO ALTAIR AVIONICS CORP. FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001100200115	20011002	00115	SW  	2001	10	2	HEEA075959       	1	20010910	G	6520	PHI2062003	SEAL            			BELL  	206   	206L3       	1182108	SW  										T/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	30KH					51527				SEAL LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001100200117	20011002	00117		2001	10	2	HEEA075960       	4	20010910	G	3400	212075399101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WILL NOT REFLECT AN INDICATION. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.						1	G	7	1 	4U			 	H4SW    					 
2001100200118	20011002	00118	SW  	2001	10	2	HEEA075961       	1	20010910	G	5302	206031329103S	ATTACH FITTING  			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FITTING WILL NOT SIT FLAT AGAINST TAILBOOM RING.  FITTING IS NOT MACHINED FLAT AND HAS A SLIGHTLY ROUNDED CONTOUR SO THE	RE IS A GAP AROUND THE PERIMETER OF THE FACE OF THE FITTING.  ALSO FOUND FITTING TO BE APPROXIMATELY .30 THICKER AT THE 	TAILBOOM ATTACH BOLT HOLE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT.				1	G	7	1 	3U			 	H2SW    					 
2001100300009	20011003	00009	SW  	2001	10	3	HEEA075971       	1	20010913	G	5302	407030801105	SKIN            			BELL  	407   	407         	       	SW  										TAILBOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999	2516 				53323				CRACK IN SKIN ON LEFT HAND SIDE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFEREN	CE:   DMR#720464.					1	G	7	1 	3U			O	H2SW    					 
2001100300010	20011003	00010	SW  	2001	10	3	HEEA075972       	1	20010913	G	6210	407015001117	BLADE           			BELL  	407   	407         	       	SW  										MAIN ROTOR	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	3683 				53207				DELAMINATION NEAR BLADE TIP.						1	G	7	1 	3U			O	H2SW    					 
2001100300011	20011003	00011	SW  	2001	10	3	HEEA075974       	1	20010913	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	       	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH	1368 				53327				GREASE DISCOLORED AND LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001100300012	20011003	00012	SW  	2001	10	3	HEEA075975       	1	20010913	G	3246	407050202101	CROSSTUBE       			BELL  	407   	407         	       	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				CORROSION AT CHAFE PADS.  SENT IN FOR EVALUATION DUE TO PREVIOUS MANUFACTURE DEFECTS.						1	G	7	1 	3U			O	H2SW    					 
2001100300016	20011003	00016	SW  	2001	10	3	HEEA075977       	1	20010913	G	2700	412301300101	ACTUATOR        			BELL  	412   	412EP       	1182205	SW  										FLIGHT CONTROLS	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6106C					36257				STICKING INTERMITTENTLY IN FLIGHT.						1	G	7	2 	4U			 	H4SW    					 
2001100300017	20011003	00017	SW  	2001	10	3	HEEA075978       	1	20010914	G	6710	406310404101	ROD END         			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH	3352 				53188				ROD END WORN.						1	G	7	1 	3U			O	H2SW    					 
2001100300018	20011003	00018	SW  	2001	10	3	HEEA075980       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	923  				53283				UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001100300019	20011003	00019	SW  	2001	10	3	HEEA075981       	1	20010914	G	6310	214040814105	SLEEVE          			BELL  	407   	407         	       	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#720445.						1	G	7	1 	3U			O	H2SW    					 
2001100300022	20011003	00022	SW  	2001	10	3	HEEA075987       	1	20010914	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	       	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001100300023	20011003	00023	SW  	2001	10	3	HEEA075988       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	720PH	1442 				53277				WORN BEYOND LIMITS. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#7190	8903.					1	G	7	1 	3U			O	H2SW    					 
2001100300025	20011003	00025	SW  	2001	10	3	HEEA075989       	1	20010914	G	2840	407362005103	SWITCH          			BELL  	407   	407         	       	SW  										FUEL INDICATOR	FAILED          	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	498PH					53399				LOW LEVEL ANNUNCIATOR LIGHT WOULD NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2001100300042	20011003	00042	SW  	2001	10	3	HEEA075990       	1	20010914	G	6510	406001704101	BELLCRANK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				CHAFED FROM CONTROL TUBE.						1	G	7	1 	3U			O	H2SW    					 
2001100300053	20011003	00053	SW  	2001	10	3	HEEA075993       	1	20010914	G	2910		FITTING         			BELL  	407   	407         	       	SW  										HYD HOSE	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				FITTING BROKE OFF IN HOSE END, CANNOT REMOVE.						1	G	7	1 	3U			O	H2SW    					 
2001100300054	20011003	00054	SW  	2001	10	3	HEEA075994       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH	767  				53198				WEAR BEYOND ALLOWABLE LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2001100300055	20011003	00055	SW  	2001	10	3	HEEA075995       	1	20010914	G	2910		B-NUT           			BELL  	407   	407         	       	SW  										HYD SYSTEM	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	740PH	729  				53435				B NUT THREADS ARE UNDERCUT AND WILL NOT TIGHTEN.						1	G	7	1 	3U			O	H2SW    					 
2001100300056	20011003	00056	SW  	2001	10	3	HEEA075996       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH	2509 				53147				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001100300057	20011003	00057	SW  	2001	10	3	HEEA075997       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001100300059	20011003	00059	SW  	2001	10	3	HEEA075998       	1	20010914	G	6710	406010425107	LEVER           			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH	1848 				53396				WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001100300060	20011003	00060	SW  	2001	10	3	HEEA075999       	1	20010914	G	6710	406010425107	LEVER           			BELL  	407   	407         	       	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH	1848 				53396				WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001100300061	20011003	00061	SW  	2001	10	3	HEEA076000       	1	20010914	G	5320	407070620125	PANEL           			BELL  	407   	407         	       	SW  										COLLECTIVE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				PANEL CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001100300062	20011003	00062	SW  	2001	10	3	HEEA076001       	1	20010914	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	       	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH	1139 				53397				BEARING UNSTAKED.						1	G	7	1 	3U			O	H2SW    					 
2001100300063	20011003	00063	SW  	2001	10	3	HEEA076006       	1	20010914	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				CRACKED. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001100300070	20011003	00070	SW  	2001	10	3	HEEA076007       	1	20010914	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				CRACKED. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001100300073	20011003	00073	SW  	2001	10	3	HEEA076008       	1	20010914	G	6510	407340340101	DISC PACK       			BELL  	407   	407         	       	SW  										TAIL ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	722PH					53288				CRACKED. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001100300074	20011003	00074	SW  	2001	10	3	HEEA076009       	1	20010914	G	6310	204040760109	FILTER ELEMENT  			BELL  	407   	407         	       	SW  										TRANSMISSION	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				RUN IN AFTER TRANS CHANGE. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001100300076	20011003	00076	SW  	2001	10	3	HEEA076012       	1	20010914	G	7170	70031A202000	LINE            			BELL  	407   	407         	       	SW  										EXH DRAIN	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				DRAIN LINE WAS WORN THROUGH STEEL BRAIDING. SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001100300078	20011003	00078	SW  	2001	10	3	HEEA076016       	1	20010917	G	6710	214001347005	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT SYS	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ROTARY ACTUATOR STICKING.						2	G	7	2 	4U			 	H10SW   					 
2001100300079	20011003	00079	SW  	2001	10	3	HEEA076017       	1	20010917	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR MOTOR FROZEN.						1	G	7	2 	4U			 	H4SW    					 
2001100300081	20011003	00081	SW  	2001	10	3	HEEA076018       	1	20010917	G	2840	473203003	SIGNAL COND UNIT			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	OUT OF ADJ      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COULD NOT ADJUST E TO -.03PF WHEN CALIBRATING NR 1 FUEL SYSTEM.						1	G	7	2 	4U			 	H4SW    					 
2001100300083	20011003	00083	SW  	2001	10	3	HEEA076019       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T	233  				28101				WEAK. WOULD NOT TAKE A CHARGE.						2	G	7	2 	4U			 	H10SW   					 
2001100300084	20011003	00084	SW  	2001	10	3	HEEA076020       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T	233  				28101				WEAK. WOULD NOT TAKE A CHARGE.						2	G	7	2 	4U			 	H10SW   					 
2001100300085	20011003	00085	SW  	2001	10	3	HEEA076021       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806	487  				28140				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300086	20011003	00086	SW  	2001	10	3	HEEA076022       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806	473  				28140				WON'T START AIRCRAFT.						2	G	7	2 	4U			 	H10SW   					 
2001100300087	20011003	00087	SW  	2001	10	3	HEEA076023       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5748M	465  				28102				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300089	20011003	00089	SW  	2001	10	3	HEEA076024       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5748M	465  				28102				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300090	20011003	00090	SW  	2001	10	3	HEEA076025       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N	902  				28106				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300092	20011003	00092	SW  	2001	10	3	HEEA076026       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806	911  				28140				WON'T START AIRCRAFT.						2	G	7	2 	4U			 	H10SW   					 
2001100300094	20011003	00094	SW  	2001	10	3	HEEA076027       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N	380  				28106				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300095	20011003	00095	SW  	2001	10	3	HEEA076028       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	SHORTED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N	380  				28106				WEAK. FOUND UNIT INTERNALLY SHORTED.						2	G	7	2 	4U			 	H10SW   					 
2001100300097	20011003	00097	SW  	2001	10	3	HEEA076029       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y	89   				28139				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300098	20011003	00098	SW  	2001	10	3	HEEA076030       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y	89   				28139				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300099	20011003	00099	SW  	2001	10	3	HEEA076031       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T					28101				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300100	20011003	00100	SW  	2001	10	3	HEEA076032       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T					28101				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100300101	20011003	00101	SW  	2001	10	3	HEEA076033       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y	253  				28139				WON'T HOLD A CHARGE.						2	G	7	2 	4U			 	H10SW   					 
2001100300102	20011003	00102	SW  	2001	10	3	HEEA076034       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806	742  				28140				WON'T START AIRCRAFT. SCRAPPED.						2	G	7	2 	4U			 	H10SW   					 
2001100400005	20011004	00005	SW  	2001	10	4	HEEA076035       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N	226  				28106				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100400006	20011004	00006	SW  	2001	10	4	HEEA076036       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806	372  				28140				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100400007	20011004	00007	SW  	2001	10	4	HEEA076037       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	OVERHEATED      	E			HEEA	K				NONE                    				M	L		OVER TEMP                 	NO TEST                   		IN	INSP/MAINT     	1			SW	03	5748M					28102				OVERHEAT AND ACID SMELL. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400008	20011004	00008	SW  	2001	10	4	HEEA076038       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	5748M					28102				OVERHEAT AND ACID SMELL. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400009	20011004	00009	SW  	2001	10	4	HEEA076039       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59805					28141				WON'T START AIRCRAFT. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400010	20011004	00010	SW  	2001	10	4	HEEA076040       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59805					28141				WON'T START AIRCRAFT. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400011	20011004	00011	SW  	2001	10	4	HEEA076041       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				WEAK. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400012	20011004	00012	SW  	2001	10	4	HEEA076042       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				WEAK. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400013	20011004	00013	SW  	2001	10	4	HEEA076043       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y					28139				WON'T HOLD A CHARGE. REPLACED WITH SERVICEABE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400014	20011004	00014	SW  	2001	10	4	HEEA076044       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T					28101				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100400015	20011004	00015	SW  	2001	10	4	HEEA076045       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				WEAK.						2	G	7	2 	4U			 	H10SW   					 
2001100400016	20011004	00016	SW  	2001	10	4	HEEA076046       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				WEAK. REPLACED WITH SERVICEABLE BATTERY.						2	G	7	2 	4U			 	H10SW   					 
2001100400022	20011004	00022	SW  	2001	10	4	HEEA076047       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59805	461  				28141				WON'T START AIRCRAFT.						2	G	7	2 	4U			 	H10SW   					 
2001100400029	20011004	00029	SW  	2001	10	4	HEEA076048       	1	20010919	G	2432	RG214	BATTERY         			BELL  	214   	214ST       	1182106	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										BATTERY DEAD.						2	G	7	2 	4U			 	H10SW   					 
2001100400030	20011004	00030	SW  	2001	10	4	HEEA076049       	1	20010924	G	3212	214031792102	COVER           			BELL  	214   	214ST       	1182106	SW  										MLG FLOAT	MISSING         	E			HEEA	O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	03	8045T					28101				AFTER SHUTDOWN AT HELIPORT, FOUND AFT PORTION OF RIGHT HAND FLOAT COVER MISSING. REPLACED FLOAT COVER.						2	G	7	2 	4U			 	H10SW   					 
2001100400031	20011004	00031		2001	10	4	HEEA076050       	4	20010924	G	2397	M39012160004	CONNECTOR       			BELL  	212   	212         	1181420	SW  										NR 1 VHF RADIO	SHORTED         	E			HEEA	C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			SW	03	102PH					30899				PRIOR TO TAKEOFF, SMELLED ELECTRICAL "BURNING" ODOR. MAINTENANCE FOUND WIRING HARNESS FROM NR 1 VHF RADIO TO BULKHEAD FI	TTING SHORTED AT CANNON PLUG.					1	G	7	1 	4U			 	H4SW    					 
2001100400038	20011004	00038	SW  	2001	10	4	HEEA076051       	1	20010924	G	6322	6038T59P02	BLOWER          			BELL  	214   	214ST       	1182106	SW  										SHAFT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T					28101				THE #1 PARTICLE SEPARATOR CAUTION LIGHT CAME ON. MAINTENANCE FOUND PARTICLE SEPARATOR BLOWER SHAFT SHEARED.						2	G	7	2 	4U			 	H10SW   					 
2001100400051	20011004	00051	SW  	2001	10	4	HEEA076054       	1	20010924	G	6220	407310101101	BEARING         		407010100115	BELL  	407   	407         	       	SW  										MAIN ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH				A222	53003				SEPARATION.						1	G	7	1 	3U			O	H2SW    					 
2001100400054	20011004	00054	SW  	2001	10	4	HEEA076056       	1	20010924	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	       	SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	723PH					53283				ENGINE PRESSURE DROPPED TO ZERO.						1	G	7	1 	3U			O	H2SW    					 
2001100400056	20011004	00056	SW  	2001	10	4	HEEA076058       	1	20010928	G	7120	206064107103	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ROD END BEARING ON NEW LEG ASSEMBLY IS NEAR WEAR LIMITS.						1	G	7	1 	3U			 	H2SW    					 
2001100400083	20011004	00083	SW  	2001	10	4	HEEA076060       	1	20010928	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										PART DOES NOT FIT PHI INSPECTION FIXTURE WHICH WAS MANUFACTURED TO MATCH SEVERAL OF THESE PART NUMBERED LEG ASSEMBLIES.						1	G	7	1 	3U			 	H2SW    					 
2001100400084	20011004	00084	EU  	2001	10	4	HEEA076062       	1	20010910	G	6230	126891P	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				WORN ROD END BEARINGS ON MAIN ROTOR PC LINKS. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001100400085	20011004	00085	EU  	2001	10	4	HEEA076063       	1	20010910	G	2432	30248001	BATTERY         			BOLKMS	105   	BO105S      	5626006	EU  										MAIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6607K					S841				"BATT 60" LIGHT CAME ON WHEN ATTEMPTING ENGINE START. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2001100400086	20011004	00086	EU  	2001	10	4	HEEA076064       	1	20010910	G	6321	350A32050002	BRAKE ASSY      			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	972AE	502  				3234				WORN BRAKE LINING. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001100400087	20011004	00087	EU  	2001	10	4	HEEA076066       	1	20010910	G	6410	355A09103601	BEARING         		355A12005004	SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE				7458	3230				LAMINANT SEPARATION AT THE END OF THE BEARINGS. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001100400088	20011004	00088	GL  	2001	10	4	HEEA076067       	2	20010910	G	7421	9550168770	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	ALLSN 	250C  	250C*       	 	GL  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH	612  				3352				LT IGNITER PLUG WORN. SCRAPPED AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H9EU    	E4CE				 
2001100400089	20011004	00089	EU  	2001	10	4	HEEA076068       	1	20010910	G	6230		BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				WORN ROD END BEARINGS ON MAIN ROTOR PC LINKS. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001102200110	20011022	00110	GL  	2001	10	22	HEEA076247       	2	20011002	G	7230	23064570	LINER           			BELL  	407   	407         	1182206	SW  	ALLSN 	250B  	250B*       	 	GL  					COMPRESSOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				RUMBLING NOISE AROUND 30 PERCENT N1 DURING START. SENT TO STANDARD AERO FOR EXCHANGE.						1	G	7	1 	3U	3	T	O	H2SW    	E10CE				 
2001102200112	20011022	00112	GL  	2001	10	22	HEEA076248       	2	20011002	G	7412	23064130	IGNITER         			BELL  	407   	407         	1182206	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH					53457				IGNITOR BOX INOPERATIVE.						1	G	7	1 	3U	3	T	O	H2SW    	E10CE				 
2001102200115	20011022	00115	NE  	2001	10	22	HEEA076249       	2	20011003	G	7320	0292928650	VALVE           			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					FUEL METERING	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	936  				3230	22072			NG AND TORQUE FLUCTUATIONS. PENDING VENDOR RETURN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001102300003	20011023	00003	EU  	2001	10	23	HEEA076250       	1	20011003	G	7197	0301037070	HARNESS         			SNIAS 	350   	AS350B      	8680801	EU  										ENGINE	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH	703  				3352				T-4 ERRATIC. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001102300004	20011023	00004		2001	10	23	HEEA076251       	4	20011004	G	8300	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  										RGB	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				RGB SECTION MAKING METAL CHIPS IN FILTER AND CHIP PLUG. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102300005	20011023	00005	NE  	2001	10	23	HEEA076252       	1	20011004	G	7714		BUTTON          			SKRSKY	S76   	S76A        	8143006	NE  										N1 INDICATOR	MISSING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	760PH					760078				TACHO CHECK BUTTON MISSING. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001102300006	20011023	00006	NE  	2001	10	23	HEEA076253       	1	20011004	G	3212	7625101102101	FLOAT           			SKRSKY	S76   	S76A        	8143006	NE  										MLG	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911MJ					760231				FAILED INFLATION TEST. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001102300007	20011023	00007		2001	10	23	HEEA076254       	4	20011004	G	2215	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERING      	E			HEEA	O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	760PH					760078				CHATTERING INDUCING PORPOISE IN AIRCRAFT. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001102300008	20011023	00008	EA  	2001	10	23	HEEA076255       	2	20011009	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NACELLE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	102PH					30899				HIGH OIL CONSUMPTION. SENT TO PRATT AND WHITNEY FOR WARRANTY REPAIR.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300009	20011023	00009	EA  	2001	10	23	HEEA076256       	2	20011009	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NACELLE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1079U	16590				31122				CORROSION AT 12 OCLOCK. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300010	20011023	00010	EA  	2001	10	23	HEEA076257       	2	20011009	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NACELLE	STALLED         	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	5736D	9772 				31135				COMPRESSOR STALLS AND HIGH ITT. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300011	20011023	00011	NE  	2001	10	23	HEEA076258       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NACELLE	STALLED         	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	3893N	20429				33010				COMPRESSOR STALLS ABOVE 85 PERCENT N1 AND OVERTEMP (PEGGED OUT GAUGE). SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPA	IR.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300012	20011023	00012	EA  	2001	10	23	HEEA076259       	2	20011009	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NACELLE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	5009N	6539 				30936				LOW POWER. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300013	20011023	00013	NE  	2001	10	23	HEEA076260       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NACELLE	OSCILLATES      	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	22347	1620 				36005				TORQUE OSCILLATIONS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300014	20011023	00014	EA  	2001	10	23	HEEA076261       	2	20011009	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NACELLE	HOT START       	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	5736D	7809 				31135				HOT STARTS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300015	20011023	00015	NE  	2001	10	23	HEEA076262       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NACELLE	STALLED         	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	22347	5034 				36005				COMPRESSOR STALLS AND ITT OVER 1000 DEGREES. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300016	20011023	00016	NE  	2001	10	23	HEEA076263       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NACELLE	STALLED         	E			HEEA	O				OTHER                   				C	J		F.O.D.                    	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	7128R	11662				36007				COMPRESSOR STALLS - FOD TO COMPRESSOR BLADES. SENT TO PRATT AND WHITNEY FOR OVERHAUL.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300017	20011023	00017	SW  	2001	10	23	HEEA076264       	1	20011009	G	5412		FIREWALL        			BELL  	412   	412         	1182202	SW  										ENGINE BAY	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N	15595				33002				AFT ENGINE FIRE WALL ATTACHMENT FLANGE RIVETS LOOSE.						1	G	7	2 	4U			 	H4SW    					 
2001102300018	20011023	00018	NE  	2001	10	23	HEEA076265       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	OVERHEATED      	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	2149S	1691 				36002				ITT WENT ABOVE 900 DEGREES DURING MANUAL GOVERNOR CHECK..						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300019	20011023	00019	NE  	2001	10	23	HEEA076266       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	OVERHEATED      	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	3893P	15285				33012				HIGH N1 ON POWER CHECK.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300020	20011023	00020	NE  	2001	10	23	HEEA076267       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	OVERHEATED      	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	2298Z	12293				33077				HIGH ITT AND WEAR ON GEARBOX CASE AND COVER.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300021	20011023	00021	NE  	2001	10	23	HEEA076268       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	OVERSPEED       	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	22347	8022 				36005				N1 OVERSPEED AT 116 PERCENT.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300022	20011023	00022	EA  	2001	10	23	HEEA076269       	2	20011009	G	7200		BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENG COMPRESSOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1082G	16728				31109				COMPRESSOR BLADE CORRODED.						1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102300023	20011023	00023	NE  	2001	10	23	HEEA076270       	2	20011009	G	7200		COMPRESSOR      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	SEIZED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L	6819 				33006				COMPRESSOR SEIZED.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300024	20011023	00024	NE  	2001	10	23	HEEA076271       	2	20011009	G	7297		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	MALFUNCTIONED   	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	800Y	7681 				33134				ENGINE HAS HIGH T-5 HARNESS OHMS OUT LESS THAN 100 OHMS.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300025	20011023	00025	NE  	2001	10	23	HEEA076272       	2	20011009	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE BAY	OVERSPEED       	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	22347	17028				36005				N1 OVERSPEED AT 116 PERCENT. REPLACED WITH SERVICEABLE ENGINE.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102300026	20011023	00026	GL  	2001	10	23	HEEA076273       	2	20011011	G	7323	252469211	GOVERNOR        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	OSCILLATES      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5435V	10875				760158	CAE890432S			ENGINE N1, T5, TORQUE AND FUEL FLOW OSCILLATES AT HIGH POWER SETTINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001102300027	20011023	00027	NE  	2001	10	23	HEEA076274       	1	20011011	G	6321	40004769R	CALIPER         			SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	911MJ					760231				CALIPER LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001102300028	20011023	00028	NE  	2001	10	23	HEEA076275       	1	20011011	G	6321	40004769R	CALIPER         			SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	911MJ					760231				CALIPER LEAKING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001102300029	20011023	00029	NE  	2001	10	23	HEEA076276       	1	20011011	G	2121	7650007901102	BLOWER          			SKRSKY	S76   	S76A        	8143006	NE  										VENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				VENT BLOWER POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001102300030	20011023	00030		2001	10	23	HEEA076277       	4	20011012	G	3450	258719342	COMPASS         			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	760PH					760078				HIS OFF FLAG WILL NOT PULL. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001102300031	20011023	00031	NE  	2001	10	23	HEEA076278       	1	20011012	G	6321	7665009803105	MODULE          		350A33200406	SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE ASSY	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH				MA1154	760078				ROTOR BRAKE WARNING LIGHT INTERMITTENTLY DOES NOT ILLUMINATE WITH ROTOR BRAKE ENGAGED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001102300032	20011023	00032	NE  	2001	10	23	HEEA076279       	2	20011012	G	7421	9550166670	IGNITER         			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	760PH					760078				INOPERATIVE NO SPARK. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E19EU				 
2001102300033	20011023	00033	SW  	2001	10	23	HEEA076280       	1	20011001	G	3212	407073848101	BOTTLE          			BELL  	407   	407         	1182206	SW  										FLOAT BAG	DISCHARGED      	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	491PH					53386				VALVE VENTING.  COULD NOT SERVICE WITH NITROGEN.						1	G	7	1 	3U			O	H2SW    					 
2001102300034	20011023	00034	SW  	2001	10	23	HEEA076281       	1	20011001	G	3212	407073848101	BOTTLE          			BELL  	407   	407         	1182206	SW  										FLOAT BAG	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				VALVE VENTING.  COULD NOT SERVICE WITH NITROGEN.						1	G	7	1 	3U			O	H2SW    					 
2001102300035	20011023	00035	SW  	2001	10	23	HEEA076283       	1	20011001	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	495PH	2628 				53397				STARTING PROBLEMS.  DEAD SPOT.						1	G	7	1 	3U			O	H2SW    					 
2001102300036	20011023	00036	SW  	2001	10	23	HEEA076284       	1	20011001	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	622  			Y0099	53207				WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001102300037	20011023	00037	SW  	2001	10	23	HEEA076285       	1	20011001	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH	248  				53461				PAINT PEELING FROM BLADE.						1	G	7	1 	3U			O	H2SW    					 
2001102300038	20011023	00038	SW  	2001	10	23	HEEA076286       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				METAL IN OIL.						1	G	7	2 	4U			 	H4SW    					 
2001102300039	20011023	00039	SW  	2001	10	23	HEEA076287       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	1202T					33112				LEAKING FROM CENTER SECTION. REPLACED WITH SERVICEABLE COOLER.						1	G	7	2 	4U			 	H4SW    					 
2001102300040	20011023	00040	SW  	2001	10	23	HEEA076288       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	1202T					33112				HIGH TEMPERATURE READINGS ABOUT 100 DEGREES IN RED LINE.  ALSO C-BOX CAUTION LIGHT CAME ON. REPLACED WITH SERVICEABLE CO	OLER.					1	G	7	2 	4U			 	H4SW    					 
2001102300041	20011023	00041	SW  	2001	10	23	HEEA076289       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	212   	212         	1181420	SW  										OIL SYSTEM	CONTAMINATED    	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	3131S					30953				CONTAMINATED FROM MAST, ALSO LEAKS.						1	G	7	1 	4U			 	H4SW    					 
2001102300042	20011023	00042	SW  	2001	10	23	HEEA076290       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	CONTAMINATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				METAL CONTAMINATED.						1	G	7	2 	4U			 	H4SW    					 
2001102300043	20011023	00043	SW  	2001	10	23	HEEA076291       	1	20011001	G	6320		TRANSMISSION    			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	800Y					33134				TRANSMISSION MAKING METAL. SENT TO DRAKE AIR FOR INSPECTION AND REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102300044	20011023	00044	SW  	2001	10	23	HEEA076292       	1	20011001	G	6310		COMBINING BOX   			BELL  	412   	412         	1182202	SW  										TRANSMISSION	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	800Y					33134				C-BOX MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2001102300045	20011023	00045	SW  	2001	10	23	HEEA076293       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										OIL SYSTEM	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	2258F					33073				OIL COOLER LEAKS.						1	G	7	2 	4U			 	H4SW    					 
2001102300046	20011023	00046	SW  	2001	10	23	HEEA076294       	1	20011001	G	7921	8538100	OIL COOLER      			BELL  	212   	212         	1181420	SW  										OIL SYSTEM	CONTAMINATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736J					31140				METAL CONTAMINATION.						1	G	7	1 	4U			 	H4SW    					 
2001102300052	20011023	00052	SW  	2001	10	23	HEEA076295       	1	20011001	G	6310		COMBINING BOX   			BELL  	412   	412         	1182202	SW  										TRANSMISSION	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				C-BOX MAKING METAL.						1	G	7	2 	4U			 	H4SW    					 
2001102300064	20011023	00064	SW  	2001	10	23	HEEA076296       	1	20011001	G	6300	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	1202T					33112				OIL COOLER LEAKING FROM CENTER CORE.						1	G	7	2 	4U			 	H4SW    					 
2001102300071	20011023	00071	SW  	2001	10	23	HEEA076298       	1	20011001	G	6300	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CONTAMINATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	33008					36004				METAL CONTAMINATION.						1	G	7	2 	4U			 	H4SW    					 
2001102300131	20011023	00131	SW  	2001	10	23	HEEA076299       	1	20011001	G	6300	8538100	OIL COOLER      			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	CONTAMINATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736D					31135				OIL COOLER HAS METAL CONTAMINATION.						1	G	7	1 	4U			 	H4SW    					 
2001102300132	20011023	00132	SW  	2001	10	23	HEEA076300       	1	20011001	G	6300	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03										OIL COOER LEAKING OIL.						1	G	7	2 	4U			 	H4SW    					 
2001102300133	20011023	00133	SW  	2001	10	23	HEEA076301       	1	20011001	G	6300	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	22347					36005				OIL COOLER SEEPING.						1	G	7	2 	4U			 	H4SW    					 
2001102300134	20011023	00134	SW  	2001	10	23	HEEA076302       	1	20011001	G	6320		TRANSMISSION    			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736D					31135				TRANSMISSION MAKING METAL.						1	G	7	1 	4U			 	H4SW    					 
2001102300135	20011023	00135	SW  	2001	10	23	HEEA076303       	1	20011002	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH	1566 			2109	53277				BRUSHES WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300136	20011023	00136	SW  	2001	10	23	HEEA076307       	1	20011002	G	6500	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102300139	20011023	00139	SW  	2001	10	23	HEEA076308       	1	20011002	G	6500	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102300140	20011023	00140	SW  	2001	10	23	HEEA076309       	1	20011002	G	6500	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				TAIL ROTOR COOLER BLOWER HOUSING HAS WORKING RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2001102300142	20011023	00142	SW  	2001	10	23	HEEA076310       	1	20011002	G	2821	206061634003	VALVE           			BELL  	407   	407         	1182206	SW  										FUEL FILTER	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	406PH					53198				EXTERNAL FUEL FILTER DRAIN VALVE LEAKING AROUND HANDLE WHEN DRAINING FUEL.						1	G	7	1 	3U			O	H2SW    					 
2001102300146	20011023	00146	SW  	2001	10	23	HEEA076311       	1	20011002	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH				95189	53401				300 HOUR SCHEDULE CHANGE.  WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001102300148	20011023	00148	SW  	2001	10	23	HEEA076312       	1	20011002	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8595X	1808 				53267				STARTER GENERATOR WOULD NOT CRANK ENGINE ON LAST START OF THE DAY.						1	G	7	1 	3U			O	H2SW    					 
2001102300149	20011023	00149	SW  	2001	10	23	HEEA076313       	1	20011002	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	2203 			98136	53378				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001102300167	20011023	00167	SW  	2001	10	23	HEEA076314       	1	20011002	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH	1607 			99100	53398				STARTER GEN HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001102300168	20011023	00168	SW  	2001	10	23	HEEA076317       	1	20011002	G	5347	206072215102	SUPPORT         			BELL  	407   	407         	1182206	SW  										CABIN	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				FOUND SEAT SUPPORT BROKEN IN TWO.						1	G	7	1 	3U			O	H2SW    					 
2001102300169	20011023	00169	SW  	2001	10	23	HEEA076318       	1	20011002	G	6321		HOUSING         			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH	1701 				53398				REMOVED FOR MODIFICATION.  FOUND EXCESSIVE WEAR ON HOUSING, BRAKE PAD BOLT RETAINER HOLES AND PAD RETAINER BOLTS.						1	G	7	1 	3U			O	H2SW    					 
2001102300170	20011023	00170	SW  	2001	10	23	HEEA076319       	1	20011002	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				UNREADABLE DUE TO MOISTURE IN GLASS.						1	G	7	1 	3U			O	H2SW    					 
2001102300171	20011023	00171	SW  	2001	10	23	HEEA076320       	1	20011002	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				WATER IN GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2001102300175	20011023	00175	SW  	2001	10	23	HEEA076321       	1	20011002	G	2510	222320823130	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				SEAT BELT FRAYED.						1	G	7	1 	3U			O	H2SW    					 
2001102300176	20011023	00176	SW  	2001	10	23	HEEA076322       	1	20011002	G	2844	222375077115	TRANSDUCER      			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	READS LOW       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	467PH	3307 				53142				PRESSURE READS LOW.						1	G	7	1 	3U			O	H2SW    					 
2001102300177	20011023	00177	SW  	2001	10	23	HEEA076323       	1	20011002	G	7714	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										ENGINE TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH	3728 				53207				FADEC DEGRADE LIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001102300178	20011023	00178	GL  	2001	10	23	HEEA076324       	2	20011002	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	496PH					53398				HIGH MGT. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300179	20011023	00179	GL  	2001	10	23	HEEA076325       	2	20011002	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH					53207				FADEC DEGRADE LIGHT ILLUMINATED ON SHUTDOWN.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300180	20011023	00180	GL  	2001	10	23	HEEA076326       	2	20011002	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH					53207				CONSTANT FADEC DEGRADE LIGHT. TO BE SENT TO VENDOR FOR CREDIT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300181	20011023	00181	GL  	2001	10	23	HEEA076327       	2	20011002	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	496PH					53398				FADEC DEGRADE LIGHT. TO BE SENT TO VENDOR FOR CREDIT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300182	20011023	00182	GL  	2001	10	23	HEEA076328       	2	20011002	G	7297	23065805	HARNESS         			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH					53207				SHORT BETWEEN PIN D & C OF TORQUE TRANSMITTER CONNECTOR. TO BE SENT TO VENDOR FOR CREDIT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300183	20011023	00183	SW  	2001	10	23	HEEA076329       	1	20011002	G	7700	23071644	ECU             			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	490PH					53378				CONTINUES TO HAVE NPOS & OS FAULTS. TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102300184	20011023	00184	SW  	2001	10	23	HEEA076330       	1	20011002	G	2432	31908001	BATTERY         			BELL  	407   	407         	1182206	SW  										MAIN	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	501PH					53401				BATTERY WEAK.						1	G	7	1 	3U			O	H2SW    					 
2001102300185	20011023	00185	SW  	2001	10	23	HEEA076331       	1	20011002	G	3201	400052007109	BEAM            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				BEAM ASSY CORRODED AND BOLT HOLE WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300186	20011023	00186	SW  	2001	10	23	HEEA076332       	1	20011002	G	3201	400052007115	BEAM            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				BEAM CORRODED AROUND BUSHINGS. IN SHEETMETAL SHOP FOR REPAIR.						1	G	7	1 	3U			O	H2SW    					 
2001102300187	20011023	00187	SW  	2001	10	23	HEEA076333       	1	20011002	G	3201	400052009101	BOLT            			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH					53059				PITTED THROUGH COATING. SCRAPPED AND REPLACED WITH SERVICEABLE BOLT.						1	G	7	1 	3U			O	H2SW    					 
2001102300188	20011023	00188	SW  	2001	10	23	HEEA076334       	1	20011002	G	6720	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				ROD END BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300189	20011023	00189	SW  	2001	10	23	HEEA076335       	1	20011002	G	6310		BEARING         		406040500119	BELL  	407   	407         	1182206	SW  										SUPPORT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X				A1505	53267				ROLLER FELL OUT OF BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102300190	20011023	00190	SW  	2001	10	23	HEEA076336       	1	20011002	G	6310		SEAL            		406040500123	BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH				A4015	53199				FRONT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102300191	20011023	00191	SW  	2001	10	23	HEEA076337       	1	20011002	G	6310		SEAL            		406040500127	BELL  	407   	407         	1182206	SW  										FREEWHEEL UNIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407PH				A3753	53003				FRONT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102300193	20011023	00193	SW  	2001	10	23	HEEA076338       	1	20011002	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	404PH	3368 				53188				ROD END ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300200	20011023	00200	SW  	2001	10	23	HEEA076339       	1	20011002	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	1498 				53199				MAIN ROTOR UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300202	20011023	00202	SW  	2001	10	23	HEEA076340       	1	20011002	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	1817 				53228				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300203	20011023	00203	SW  	2001	10	23	HEEA076341       	1	20011002	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300204	20011023	00204	SW  	2001	10	23	HEEA076342       	1	20011002	G	6710	406310405101	UNIVERSAL JOINT 			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102300206	20011023	00206	SW  	2001	10	23	HEEA076343       	1	20011002	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102300209	20011023	00209	SW  	2001	10	23	HEEA076344       	1	20011002	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102300211	20011023	00211	SW  	2001	10	23	HEEA076345       	1	20011002	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				MAIN ROTOR CONTROL IDLER ASSY HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102300214	20011023	00214	SW  	2001	10	23	HEEA076348       	1	20011002	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	4756 				53278				CLICKING NOISE.						1	G	7	1 	3U			O	H2SW    					 
2001102300216	20011023	00216	SW  	2001	10	23	HEEA076349       	1	20011002	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										T/R TRUNNION	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	2540 				53199				CLICKING NOISE COMING FROM TRUNNION BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102300217	20011023	00217	SW  	2001	10	23	HEEA076350       	1	20011002	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	1468 				53288				CLICKING NOISE WHEN PUSHED TO STOPS.						1	G	7	1 	3U			O	H2SW    					 
2001102300219	20011023	00219	SW  	2001	10	23	HEEA076351       	1	20011002	G	6300	407340339103	BEARING         		407040302101	BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH				A926	53142				WORN ON INNER DIAMETER.						1	G	7	1 	3U			O	H2SW    					 
2001102300221	20011023	00221	SW  	2001	10	23	HEEA076352       	1	20011002	G	7810	407062021101	DUCT            			BELL  	407   	407         	1182206	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				EXHAUST DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400001	20011024	00001	SW  	2001	10	24	HEEA076353       	1	20011003	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										T/R TRUNNION	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	2803 				53199				T/R TRUNNION BEARING CLICKS WHEN FLAPPED.						1	G	7	1 	3U			O	H2SW    					 
2001102400002	20011024	00002	SW  	2001	10	24	HEEA076354       	1	20011003	G	6410		BLADE           			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	251  				53288				PAINT FLAKING OFF BLADES.						1	G	7	1 	3U			O	H2SW    					 
2001102400003	20011024	00003	SW  	2001	10	24	HEEA076355       	1	20011003	G	3212	212073905001	GAUGE           		407073848101	BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH				242	53397				NEEDLE STICKING AND FACE CRACKED. TO BE RETURNED TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASE	D.					1	G	7	1 	3U			O	H2SW    					 
2001102400004	20011024	00004	SW  	2001	10	24	HEEA076356       	1	20011003	G	6500	407340340101	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				NR 3 SHORT SHAFT FWD COUPLING DISK PACK FOUND CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400005	20011024	00005	SW  	2001	10	24	HEEA076357       	1	20011003	G	6500	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				FWD COUPLING DISC ON NR 4 T/R SEGMENTED DRIVE SHAFT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400006	20011024	00006	SW  	2001	10	24	HEEA076358       	1	20011003	G	6500	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				CRACKED. TO BE RETURNED TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW    					 
2001102400007	20011024	00007	SW  	2001	10	24	HEEA076359       	1	20011003	G	3212	407350300101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				FLOAT BAG TORN.						1	G	7	1 	3U			O	H2SW    					 
2001102400008	20011024	00008	SW  	2001	10	24	HEEA076360       	1	20011003	G	3212	407350302101	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102400009	20011024	00009	SW  	2001	10	24	HEEA076361       	1	20011003	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL CELL	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	417PH	4129 				53038				TRANSFER LIGHT WILL NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2001102400010	20011024	00010	SW  	2001	10	24	HEEA076362       	1	20011003	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL CELL	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	495PH					53397				PRESSURE SWITCH STUCK IN OFF POSITION.						1	G	7	1 	3U			O	H2SW    					 
2001102400011	20011024	00011	SW  	2001	10	24	HEEA076363       	1	20011003	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999	2556 				53323				TORQUE INDICATOR LIGHT INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001102400012	20011024	00012	SW  	2001	10	24	HEEA076364       	1	20011003	G	7714	407375008101	TACHOMETER      			BELL  	407   	407         	1182206	SW  										COCKPIT	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH	3728 				53207				ROTOR NEEDLE FAILS BIT TEST.						1	G	7	1 	3U			O	H2SW    					 
2001102400013	20011024	00013	SW  	2001	10	24	HEEA076365       	1	20011003	G	3210	70079H000Y150	HOSE            			BELL  	407   	407         	1182206	SW  										MLG	KINKED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				HOSE ASSY KINKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400014	20011024	00014	SW  	2001	10	24	HEEA076366       	1	20011003	G	3212	8226003	FUSEABLE PLUG   			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LT FLOAT BOTTLE LEAKING AT CENTER OF FUSIBLE PLUG.						1	G	7	1 	3U			O	H2SW    					 
2001102400015	20011024	00015	SW  	2001	10	24	HEEA076367       	1	20011003	G	3212	8226003	FUSEABLE PLUG   			BELL  	407   	407         	1182206	SW  										FLOAT BOTTLE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				FUSIBLE PLUG FAILED RELEASING ALL PRESSURE FROM FLOAT BOTTLE.						1	G	7	1 	3U			O	H2SW    					 
2001102400016	20011024	00016	SW  	2001	10	24	HEEA076371       	1	20011003	G	6300		SPLINE ADAPTER  		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH				PHI0010	53198				WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001102400017	20011024	00017	SW  	2001	10	24	HEEA076372       	1	20011003	G	6300	407340339101	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	407PH				PHI0013	53003				OIL COOLER BLOWER BEARING OVERHEATED.						1	G	7	1 	3U			O	H2SW    					 
2001102400018	20011024	00018	SW  	2001	10	24	HEEA076375       	1	20011003	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	409PH				PHI0019	53059				BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001102400019	20011024	00019	SW  	2001	10	24	HEEA076376       	1	20011003	G	6300		BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416				PHI0022	53070				WORN AND ROUGH BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102400020	20011024	00020	SW  	2001	10	24	HEEA076378       	1	20011003	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH				PHI0031	53114				COOLER BLOWER BEARING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102400021	20011024	00021	SW  	2001	10	24	HEEA076383       	1	20011003	G	6520	PHI407112	BOOT            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	405PH					53207				BOOT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102400022	20011024	00022	SW  	2001	10	24	HEEA076384       	1	20011003	G	6520	PHI407112	BOOT            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	409PH					53059				BOOT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102400023	20011024	00023	SW  	2001	10	24	HEEA076385       	1	20011003	G	6720		BUSHING         		PHI407112   	BELL  	407   	407         	1182206	SW  										IDLER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				WEAR ON BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102400024	20011024	00024	SW  	2001	10	24	HEEA076386       	1	20011003	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				INOPERATIVE. REPLACED WITH SERVICEABLE BOOST PUMP CARTRIDGE.						1	G	7	1 	3U			O	H2SW    					 
2001102400025	20011024	00025	SW  	2001	10	24	HEEA076387       	1	20011003	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH				2239	53378				STARTER GEN BRUSHES FAILED INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2001102400026	20011024	00026	GL  	2001	10	24	HEEA076388       	2	20011003	G	7320	23007827	VALVE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				VALVE STICKING. REPLACED WITH SERVICEABLE VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102400027	20011024	00027	SW  	2001	10	24	HEEA076389       	1	20011003	G	6300	406310405101	BEARING         			BELL  	407   	407         	1182206	SW  										UNIVERSAL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102400028	20011024	00028	SW  	2001	10	24	HEEA076390       	1	20011003	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102400029	20011024	00029	SW  	2001	10	24	HEEA076391       	1	20011003	G	6230	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BOOT TORN.						1	G	7	1 	3U			O	H2SW    					 
2001102400030	20011024	00030	SW  	2001	10	24	HEEA076392       	1	20011003	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102400031	20011024	00031	SW  	2001	10	24	HEEA076394       	1	20011003	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	3924 				53198				MAIN ROTOR BLADE IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400032	20011024	00032	SW  	2001	10	24	HEEA076395       	1	20011003	G	6510	407340339101	BEARING         		407040302107	BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH				A1937	53386				TAIL ROTOR DRIVESHAFT BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001102400034	20011024	00034	SW  	2001	10	24	HEEA076396       	1	20011003	G	7120		BEARING         			BELL  	407   	407         	1182206	SW  										BIPOD MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				BIPOD MOUNT HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102400035	20011024	00035	SW  	2001	10	24	HEEA076397       	1	20011003	G	7120		BEARING         			BELL  	407   	407         	1182206	SW  										BIPOD MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102400036	20011024	00036	SW  	2001	10	24	HEEA076398       	1	20011003	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 IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102400037	20011024	00037	SW  	2001	10	24	HEEA076399       	1	20011003	G	7933	407375005101	INDICATOR       			BELL  	407   	407         	1182206	SW  										XMSN OIL TEMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				TRANSMISSION OIL TEMP INDICATOR SHOWED ONLY 2 BAR SEGMENTS.						1	G	7	1 	3U			O	H2SW    					 
2001102400038	20011024	00038		2001	10	24	HEEA076400       	4	20011003	G	3421	50400179015	ADI             			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				FLAG DOES NOT PULL AND GAUGE DOES NOT CORRESPOND TO ATTITUDE. REPLACED WITH SERVICEABLE ATTITUDE IND.						1	G	7	1 	3U			O	H2SW    					 
2001102400039	20011024	00039		2001	10	24	HEEA076401       	4	20011003	G	3421	50400179015	ADI             			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				ATTITUDE INDICATOR STAYS IN LEFT TURN. REPLACED WITH SERVICEABLE ATTITUDE IND.						1	G	7	1 	3U			O	H2SW    					 
2001102400040	20011024	00040	SW  	2001	10	24	HEEA076403       	1	20011003	G	6300		BEARING         		PHIPBH40701F	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH				PHI0015	53386				OIL COOLER BLOWER HAS ROUGH BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102400041	20011024	00041	SW  	2001	10	24	HEEA076404       	1	20011003	G	3213	407050201101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				FORWARD CROSSTUBE HAS CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			O	H2SW    					 
2001102400042	20011024	00042	SW  	2001	10	24	HEEA076405       	1	20011003	G	3213	407050202101	CROSSTUBE       			BELL  	407   	407         	1182206	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				AFT CROSSTUBE HAS CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			O	H2SW    					 
2001102400043	20011024	00043	SW  	2001	10	24	HEEA076406       	1	20011003	G	2510	407070720117	SEAT BACK       			BELL  	407   	407         	1182206	SW  										COCKPIT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				TORN. SCRAPPED AND REPLACED WITH SERVICEABLE SEAT BACK.						1	G	7	1 	3U			O	H2SW    					 
2001102400044	20011024	00044	SW  	2001	10	24	HEEA076407       	1	20011003	G	5210	407070620137	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400045	20011024	00045	SW  	2001	10	24	HEEA076408       	1	20011003	G	5210	407070620138	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				CRACKED AND BROKEN IN SEVERAL PLACES. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400046	20011024	00046	SW  	2001	10	24	HEEA076409       	1	20011003	G	5210	407070620138	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				SEVERAL CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400047	20011024	00047	SW  	2001	10	24	HEEA076410       	1	20011003	G	5230	407070620143	PANEL           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LITTER DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400048	20011024	00048	SW  	2001	10	24	HEEA076411       	1	20011003	G	5230	407070620157	PANEL           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				LT REAR DOOR PANEL HAS NUMEROUS CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400049	20011024	00049	SW  	2001	10	24	HEEA076412       	1	20011003	G	5210	407070620157	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				DOOR TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400050	20011024	00050	SW  	2001	10	24	HEEA076413       	1	20011003	G	5210	407070620157	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LT PASSENGER DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400051	20011024	00051	SW  	2001	10	24	HEEA076414       	1	20011003	G	5210	407070620158	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				CRACKED PANEL. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400052	20011024	00052	SW  	2001	10	24	HEEA076415       	1	20011003	G	5230	407070620158	PANEL           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				RT REAR DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400053	20011024	00053	SW  	2001	10	24	HEEA076416       	1	20011003	G	5210	407070620179	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400054	20011024	00054	SW  	2001	10	24	HEEA076417       	1	20011003	G	5310	407070620180	PANEL           			BELL  	407   	407         	1182206	SW  										DOOR FRAME	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				PILOT DOOR POST TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400055	20011024	00055	SW  	2001	10	24	HEEA076418       	1	20011003	G	5230	407070620205	COVER           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				LITTER DOOR LATCH COVER CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE COVER.						1	G	7	1 	3U			O	H2SW    					 
2001102400056	20011024	00056	SW  	2001	10	24	HEEA076419       	1	20011003	G	5210	407070620217	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400057	20011024	00057	SW  	2001	10	24	HEEA076420       	1	20011003	G	5210	407070620218	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400058	20011024	00058	SW  	2001	10	24	HEEA076421       	1	20011003	G	5230	407070620205	COVER           			BELL  	407   	407         	1182206	SW  										CARGO DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LITTER DOOR LATCH COVER CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE COVER.						1	G	7	1 	3U			O	H2SW    					 
2001102400059	20011024	00059	SW  	2001	10	24	HEEA076422       	1	20011003	G	5210	407070620218	PANEL           			BELL  	407   	407         	1182206	SW  										CREW DOOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL.						1	G	7	1 	3U			O	H2SW    					 
2001102400060	20011024	00060	SW  	2001	10	24	HEEA076423       	1	20011003	G	2510	407070622115	SEAT            			BELL  	407   	407         	1182206	SW  										ARM REST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LT AFT FACING SEAT ARM REST FABRIC TORN. SCRAPPED AND REPLACED WITH SERVICEABLE ARM REST.						1	G	7	1 	3U			O	H2SW    					 
2001102400061	20011024	00061		2001	10	24	HEEA076424       	4	20011003	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										RADIO SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5759N					33002				WEAK AND GARBLED. IN SHOP REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400062	20011024	00062		2001	10	24	HEEA076425       	4	20011003	G	2312	064101900	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										RADIO SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3116P					51530				DOES NOT RECEIVE. IN SHOP REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001102400063	20011024	00063		2001	10	24	HEEA076426       	4	20011003	G	3452	066106200	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										ATC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21497					51518				WOULD NOT TRANSMIT POWER MODE C SIGNALS. IN SHOP REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001102400064	20011024	00064		2001	10	24	HEEA076427       	4	20011003	G	3451	066106600	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										DME SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				DME SYSTEM TRANSCEIVER INOPERATIVE; WILL NOT COME ON. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102400065	20011024	00065		2001	10	24	HEEA076428       	4	20011003	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										ATC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				TRANSMIT OFF FREQUENCY AND REPLY RATE IS LOW AND ERRATIC. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102400066	20011024	00066		2001	10	24	HEEA076429       	4	20011003	G	3416	066304400	ALTIMETER       			BELL  	412   	412         	1182202	SW  										RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2149S					36002				KEEPS CYCLING AFTER PUSHING TEST BUTTON. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400067	20011024	00067		2001	10	24	HEEA076430       	4	20011003	G	3453	066402600	TRANSCEIVER     																	LORAN SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DISPLAY REMAINED BLANK AFTER BEING ON FOR 10 MINUTES AND REMAINED BLANK AFTERWARDS. PENDING VENDOR REPAIR.																			 
2001102400068	20011024	00068		2001	10	24	HEEA076431       	4	20011003	G	3452	071119218	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TRANSPONDER	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				WON'T TEST PROPERLY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102400069	20011024	00069	SW  	2001	10	24	HEEA076432       	1	20011003	G	5520	205030856131	STRUCTURE       			BELL  	412   	412         	1182202	SW  										ELEVATOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				SHEETMETAL CRACK WHERE SPAR IS MOUNTED TO ELEVATOR. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102400070	20011024	00070	SW  	2001	10	24	HEEA076433       	1	20011003	G	6700		BEARING         			BELL  	206   	206L3       	1182108	SW  										BELLCRANK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				BEARINGS WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102400071	20011024	00071	SW  	2001	10	24	HEEA076434       	1	20011003	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	4180F									STICKS IN THE DOWN POSITION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102400079	20011024	00079	SW  	2001	10	24	HEEA076435       	1	20011003	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	4835					51131				STICKING IN RETRACT POSITION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102400086	20011024	00086	SW  	2001	10	24	HEEA076436       	1	20011003	G	6320	206040088005	VALVE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										IMPROPERLY MANUFACTURED THREADS, CANNOT BE INSTALLED INTO TRANSMISSION CASE WITHOUT CAUSING DAMAGE TO CASE THREADS.  TRI	ED TO INSTALL VALVE INTO TWO DIFFERENT CASES AND COULD NOT.					1	G	7	1 	3U			 	H2SW    					 
2001102400087	20011024	00087	SW  	2001	10	24	HEEA076437       	1	20011003	G	6320	206040190005	PUMP            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				LEAKS PAST SEAL. REPLACED WITH SERVICEABLE PUMP.						1	G	7	1 	3U			 	H2SW    					 
2001102400127	20011024	00127	SW  	2001	10	24	HEEA076438       	1	20011003	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										M/R CONTROL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014Y					45219				INOPERATIVE NO EXTENSION OR RETRACTION OF CONTROL SHAFT. REPLACED WITH SERVICEABLE ACTUATOR.						1	G	7	1 	3U			 	H2SW    					 
2001102400130	20011024	00130	SW  	2001	10	24	HEEA076439       	1	20011003	G	3212	206073926109	VALVE           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				LEAKS ABOVE 2900 PSI. REPLACED WITH SERVICEABLE VALVE.						1	G	7	2 	4U			 	H4SW    					 
2001102400132	20011024	00132	SW  	2001	10	24	HEEA076440       	1	20011003	G	3213	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				CORRODED BEYOND LIMITS AT SUPPORT MOUNT AREA, MEASURED .010 INCHES IN ZONE 1. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001102400133	20011024	00133	SW  	2001	10	24	HEEA076441       	1	20011003	G	3213	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				CORRODED BEYOND LIMITS AT SUPPORT MOUNT AREA, MEASURED .010 INCHES IN ZONE 1. REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U			 	H2SW    					 
2001102400134	20011024	00134	SW  	2001	10	24	HEEA076442       	1	20011004	G	3246	206324008	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31821					51076				18 INCH CRACK AT LOWER SIDE SKID TUBE. REPLACED WITH SERVICEABLE SKID TUBE.						1	G	7	1 	3U			 	H2SW    					 
2001102400135	20011024	00135	SW  	2001	10	24	HEEA076443       	1	20011004	G	5260	206331119	STEP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				INTERGRANULAR CORROSION BEYOND LIMITS AT MOUNT AREA. REPLACED WITH SERVICEABLE STEP.						1	G	7	1 	3U			 	H2SW    					 
2001102400136	20011024	00136	SW  	2001	10	24	HEEA076444       	1	20011004	G	5260	206331120	STEP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	53119					51575				INTERGRANULAR CORROSION BEYOND LIMITS AT MOUNT AREA. REPLACED WITH SERVICEABLE STEP.						1	G	7	1 	3U			 	H2SW    					 
2001102400137	20011024	00137	SW  	2001	10	24	HEEA076445       	1	20011004	G	7933	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										OVERTEMP	WILL NOT TEST   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3116P					51530				OVERTEMP LIGHT WILL NOT TEST. PENDING VENDOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001102400138	20011024	00138	SW  	2001	10	24	HEEA076446       	1	20011004	G	7921	209062501005	OIL COOLER      			BELL  	412   	412         	1182202	SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2149S					36002				LEAKING. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400145	20011024	00145	SW  	2001	10	24	HEEA076447       	1	20011004	G	7600	212061101001	BEARING         			BELL  	412   	412         	1182202	SW  										ENGINE CONTROLS	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN BEARING. REPLACED WITH SERVICEABLE BEARING.						1	G	7	2 	4U			 	H4SW    					 
2001102400146	20011024	00146		2001	10	24	HEEA076448       	4	20011004	G	3100	212070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				PRESSURE NEEDLE STICKS AFTER START UP ONLY SHOWS PRESSURE IF GAUGE IS TAPPED. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001102400147	20011024	00147	SW  	2001	10	24	HEEA076449       	1	20011004	G	5260	212075418105	STEP            			BELL  	412   	412         	1182202	SW  										FUSELAGE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				WILL NOT EXTEND. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400148	20011024	00148	SW  	2001	10	24	HEEA076450       	1	20011004	G	6730	212076004101	SERVO           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	107X					33113				LEAKING. REPLACED WITH SERVICEABLE SERVO.						1	G	7	2 	4U			 	H4SW    					 
2001102400149	20011024	00149	SW  	2001	10	24	HEEA076451       	1	20011004	G	6730	212076005111	SERVO           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	STIFF           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				MOVEMENTS ARE STIFFENED AND VERY HARD TO MOVE. REPLACED WITH SERVICEABLE SERVO.						1	G	7	2 	4U			 	H4SW    					 
2001102400151	20011024	00151	SW  	2001	10	24	HEEA076452       	1	20011004	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				STICKING. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400153	20011024	00153	GL  	2001	10	24	HEEA076453       	2	20011004	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X	7023 				51552				HIGH TOT, DIDN'T CLOSE SMOOTHLY WHEN PRESSURE WAS APPLIED. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001102400154	20011024	00154	GL  	2001	10	24	HEEA076454       	2	20011004	G	7310	23005667	LINE            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL SYSTEM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				LINE IS CRACKED AT FLARE. REPLACED WITH SERVICEABLE LINE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001102400157	20011024	00157	GL  	2001	10	24	HEEA076455       	2	20011004	G	7310	23007827	SOLENOID VALVE  			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					FUEL SYSTEM	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E					51498				STICKS INTERMITTENTLY. REPLACED WITH SOLENOID VALVE.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001102400158	20011024	00158	SW  	2001	10	24	HEEA076456       	1	20011004	G	7120	23069751	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				BEARING CAME UNSTAKED. REPLACED WITH SERVICEABLE MOUNT.						1	G	7	1 	3U			 	H2SW    					 
2001102400159	20011024	00159	GL  	2001	10	24	HEEA076457       	2	20011004	G	7323	252469211	GOVERNOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V	13616				45217				N2 DROOP TO 97 PERCENT.  COMPLETED DROOP COMPENSATION ADJUSTMENTS AND COMPLETED OPERATIONAL CHECK.  FOUND ACCEPTABLE.  A	FTER 2:45 ADDITIONAL FLIGHT HOURS REPORTED N2 DROOP TO 97 PERCENT WITH N2 OVERSPEED TO 102 PERCENT. REPLACED WITH SERVIC	EABLE GOVERNOR.				1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001102400164	20011024	00164	NE  	2001	10	24	HEEA076458       	2	20011004	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FREE TURBINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				NR 2 ENGINE SURGES. REPLACED WITH SERVICEABLE GOVERNOR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102400168	20011024	00168	NE  	2001	10	24	HEEA076459       	2	20011004	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FREE TURBINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ENGINE OSCILLATES CONSTANTLY 1 TO 3 PERCENT N1 WITH ITT FLUCTUATIONS. REPLACED WITH SERVICEABLE GOVERNOR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102400170	20011024	00170	NE  	2001	10	24	HEEA076460       	2	20011004	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FREE TURBINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	800Y					33134				SURGING. REPLACED WITH SERVICEABLE GOVERNOR.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102400171	20011024	00171	SW  	2001	10	24	HEEA076461       	1	20011004	G	7603		THROTTLE        			BELL  	206   	206L3       	1182108	SW  										ENGINE CONTROLS	STIFF           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				THROTTLE STIFF. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	1 	3U			 	H2SW    					 
2001102400173	20011024	00173	SW  	2001	10	24	HEEA076462       	1	20011004	G	7603		THROTTLE        			BELL  	206   	206L3       	1182108	SW  										FUEL CONTROL	STIFF           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077					51520				THROTTLE STIFF. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	1 	3U			 	H2SW    					 
2001102400179	20011024	00179		2001	10	24	HEEA076463       	4	20011004	G	2200	2593996333	TARSYN          			BELL  	412   	412         	1182202	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				COMPASS CONTROL PANEL NEEDLE FLIPPING CONSTANTLY. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400183	20011024	00183	EA  	2001	10	24	HEEA076464       	2	20011004	G	7532		DIAPHRAGM       		3033063     	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					BLEED VALVE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	102PH				2A599	30899				INCREASE OF 40 DEGREES ITT AND 4 PERCENT N1 AT POWER CHECK SETTINGS.  FOUND HOLE IN DIAPHRAGM. REPLACED WITH SERVICEABLE	 DIAPHRAGM.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA				 
2001102400184	20011024	00184	SW  	2001	10	24	HEEA076465       	1	20011004	G	7100	32447066	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TORQUE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				CAUSING TORQUE SPLITS. REPLACED WITH SERVICEABLE TORQUE CONTROL UNIT.						1	G	7	2 	4U			 	H4SW    					 
2001102400195	20011024	00195	NE  	2001	10	24	HEEA076466       	2	20011004	G	7320	324473514	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				ENGINE SURGING DURING POWER CHANGES CAUSING AIRCRAFT TO YAW. REPLACED WITH SERVICEABLE FUEL CONTROL.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102400198	20011024	00198		2001	10	24	HEEA076467       	4	20011004	G	3442	4000023010	RADAR           			BELL  	206   	206L3       	1182108	SW  										WX RADAR SYS	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				NO MODULATION OUT. REPLACED WITH SERVICEABLE RT-15.						1	G	7	1 	3U			 	H2SW    					 
2001102400200	20011024	00200		2001	10	24	HEEA076468       	4	20011004	G	3442	4000038	CONTROL HEAD    			BELL  	206   	206L3       	1182108	SW  										WX RADAR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	42EA					51542				HAS DEAD SPOT ON VOLUME CONTROL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102400202	20011024	00202	SW  	2001	10	24	HEEA076469       	1	20011004	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				UNABLE TO TRACK. REPLACED WITH SERVICEABLE BLADE.						1	G	7	2 	4U			 	H4SW    					 
2001102400203	20011024	00203	SW  	2001	10	24	HEEA076470       	1	20011004	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				LEADING EDGE EROSION. REPLACED WITH SERVICEABLE BLADE.						1	G	7	2 	4U			 	H4SW    					 
2001102400204	20011024	00204	SW  	2001	10	24	HEEA076471       	1	20011004	G	3212	412050013109	FLOAT           			BELL  	412   	412         	1182202	SW  										MLG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				LEAKING. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102400205	20011024	00205	SW  	2001	10	24	HEEA076472       	1	20011004	G	3212	412050017135	COVER           			BELL  	412   	412         	1182202	SW  										FLOAT BAG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				WORN AND TORN. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102500001	20011025	00001	SW  	2001	10	25	HEEA076473       	1	20011004	G	3213	412050045107	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	800Y	3378 				33134				CORRODED IN SEVERAL AREAS BEYOND LIMITS.  THE CORRODED AREAS ARE NEAR THE SKID MOUNTS TO 18" TOWARD THE CENTER. RETURNIN	G FOR CREDIT.					1	G	7	2 	4U			 	H4SW    					 
2001102500002	20011025	00002	SW  	2001	10	25	HEEA076475       	1	20011004	G	6220	412310400101	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				WORN LOWER BEARING. REPLACED WITH SERVICEABLE BEARING.						1	G	7	2 	4U			 	H4SW    					 
2001102500003	20011025	00003	SW  	2001	10	25	HEEA076476       	1	20011004	G	6320	41800044	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	3893N					33010				PRESSURE INDICATOR NEEDLE PEGGED OUT ON HIGH SIDE. REPLACED WITH SERVICEABLE TRANSMITTER.						1	G	7	2 	4U			 	H4SW    					 
2001102500004	20011025	00004		2001	10	25	HEEA076477       	4	20011004	G	3421	5040017928	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				INDICATOR PRECESSES 5-8 DEGREES. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001102500005	20011025	00005		2001	10	25	HEEA076478       	4	20011004	G	3130	6895D4655	SWITCH          			BELL  	412   	412         	1182202	SW  										CVR	MALFUNCTIONED   	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	107X					33113				CVR INTERMITTENTLY WON'T TEST. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001102500006	20011025	00006	SW  	2001	10	25	HEEA076479       	1	20011004	G	2844	7G547	SWITCH          			BELL  	206   	206B3       	1181506	SW  										FUEL PRESSURE	FAILED          	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	22751					3627				FUEL PRESSURE SWITCH OPERATED CORRECTLY ON INSTALLATION - NEXT MORNING FUEL PUMP LIGHT CAME ON AND WOULD NOT GO OUT. REP	LACED WITH SERVICEABLE SWITCH.					1	G	7	1 	3U			 	H2SW    					 
2001102500007	20011025	00007		2001	10	25	HEEA076480       	4	20011004	G	3442	7021450601	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M					28102				WEATHER RADAR SYSTEM DROPS OFF IN FLIGHT. PENDING VENDOR REPAIR.						2	G	7	2 	4U			 	H10SW   					 
2001102500008	20011025	00008		2001	10	25	HEEA076481       	4	20011004	G	2350	AA38300	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										ICS	NOISY           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				LOUD STATIC NOISE WHEN AIRCRAFT IS RUNNING. PENDING VENDOR RETURN.						1	G	7	2 	4U			 	H4SW    					 
2001102500009	20011025	00009		2001	10	25	HEEA076482       	4	20011004	G	2350	AA38300	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										ICS	NOISY           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				LOUD STATIC NOISE WHEN AIRCRAFT IS RUNNING. PENDING VENDOR RETURN.						1	G	7	2 	4U			 	H4SW    					 
2001102500010	20011025	00010	SW  	2001	10	25	HEEA076483       	1	20011004	G	3213	AB412050016101	SKID SHOE       			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WORN. REPLACED WITH SERVICEABLE SKID SHOE.						1	G	7	2 	4U			 	H4SW    					 
2001102500011	20011025	00011	SW  	2001	10	25	HEEA076484       	1	20011004	G	3213	AB412050016102	SKID SHOE       			BELL  	412   	412         	1182202	SW  										MLG	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				WORN. REPLACED WITH SERVICEABLE SKID SHOE.						1	G	7	2 	4U			 	H4SW    					 
2001102500012	20011025	00012		2001	10	25	HEEA076485       	4	20011004	G	3442	MI5851345	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				WON'T PAINT TARGETS ON 10 MILE SCALE. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001102500013	20011025	00013		2001	10	25	HEEA076486       	4	20011004	G	3442	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				SCREEN GOES BLANK AND SHOWS YELLOW VERTICAL LINES. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001102500014	20011025	00014		2001	10	25	HEEA076487       	4	20011004	G	3442	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR SYSTEM	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				SCREEN SHRINKS. REPLACED WITH SERVICEABLE INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001102500015	20011025	00015	SW  	2001	10	25	HEEA076488       	1	20011004	G	2497	MS915872	SHUNT           			BELL  	206   	206L3       	1182108	SW  										GENERATOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				GENERATOR LIGHT ILLUMINATED IN FLIGHT AND GEN. WOULD RESET. REPLACED WITH SERVICEABLE SHUNT.						1	G	7	1 	3U			 	H2SW    					 
2001102500016	20011025	00016		2001	10	25	HEEA076489       	4	20011004	G	3421	PHI4121017601	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893L					33006				PRECESSES EXCESSIVELY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500017	20011025	00017	SW  	2001	10	25	HEEA076490       	1	20011004	G	5260	407301107	STEP            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	409PH					53059				CORROSION BEYOND LIMITS. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2001102500018	20011025	00018	SW  	2001	10	25	HEEA076491       	1	20011004	G	5260	407301108	STEP            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	409PH					53059				CORROSION BEYOND LIMITS. SCRAPPED.						1	G	7	1 	3U			O	H2SW    					 
2001102500019	20011025	00019	SW  	2001	10	25	HEEA076492       	1	20011004	G	6320	407375005101	INDICATOR       			BELL  	407   	407         	1182206	SW  										XMSN OIL TEMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	740PH					53435				NO TRANSMISSION TEMPERATURE INDICATION.  INDICATOR READ ZERO.						1	G	7	1 	3U			O	H2SW    					 
2001102500020	20011025	00020	SW  	2001	10	25	HEEA076495       	1	20011005	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				FLOAT COVER HAS WORN END CAPS.						1	G	7	1 	3U			O	H2SW    					 
2001102500021	20011025	00021	SW  	2001	10	25	HEEA076496       	1	20011005	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				BLOWER HOUSING HAS A CRACKED AT CORNER.						1	G	7	1 	3U			O	H2SW    					 
2001102500022	20011025	00022	SW  	2001	10	25	HEEA076497       	1	20011005	G	6710	406310404101	ROD END         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH	1749 				53399				MAIN ROTOR ROD END HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102500023	20011025	00023	SW  	2001	10	25	HEEA076498       	1	20011005	G	6220	412010219101	BEARING         			BELL  	412   	412EP       	1182205	SW  										PENDULUM DAMPER	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6106C	388  				36257				SEAL ON PENDULUM DAMPER TORN CAUSING LOSS OF GREASE AND WEAR ON INNER RACE.						1	G	7	2 	4U			 	H4SW    					 
2001102500024	20011025	00024	SW  	2001	10	25	HEEA076499       	1	20011005	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH	451  				53278				UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500025	20011025	00025	SW  	2001	10	25	HEEA076500       	1	20011005	G	6720		BEARING         			BELL  	407   	407         	1182206	SW  										LINK ASSY	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				STICKING BEARING. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#720438	.					1	G	7	1 	3U			O	H2SW    					 
2001102500026	20011025	00026	SW  	2001	10	25	HEEA076501       	1	20011005	G	6300	206362002103	CAP             			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				WORN AND HARD TO OPEN.						1	G	7	1 	3U			O	H2SW    					 
2001102500027	20011025	00027	SW  	2001	10	25	HEEA076502       	1	20011005	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH	1246 				53198				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500028	20011025	00028	SW  	2001	10	25	HEEA076503       	1	20011005	G	2432	28SP100	CELL            			BELL  	407   	407         	1182206	SW  										BATTERY	BURNED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH					53401				CELL BURNT.						1	G	7	1 	3U			O	H2SW    					 
2001102500029	20011025	00029	SW  	2001	10	25	HEEA076504       	1	20011005	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				ONE BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500030	20011025	00030	SW  	2001	10	25	HEEA076505       	1	20011005	G	3212	206050247131	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				TATTERED AND TORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500034	20011025	00034	SW  	2001	10	25	HEEA076506       	1	20011005	G	6310	406040316101	ADAPTER         			BELL  	407   	407         	1182206	SW  										ENG XMSN COUP	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				WORN SPLINES. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#720545.						1	G	7	1 	3U			O	H2SW    					 
2001102500035	20011025	00035	SW  	2001	10	25	HEEA076507       	1	20011005	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	409PH					53059				COOLER BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102500036	20011025	00036	SW  	2001	10	25	HEEA076508       	1	20011005	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	57416					53070				COOLER BLOWER HOUSING CRACKED AND RIVETS WORKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500037	20011025	00037	SW  	2001	10	25	HEEA076509       	1	20011005	G	3212	206050247131	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				TORN END COVER.						1	G	7	1 	3U			O	H2SW    					 
2001102500038	20011025	00038	SW  	2001	10	25	HEEA076510       	1	20011005	G	2510	407370720101	RESTRAINT       			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				INERTIA REEL LOCKS UP AND STRAPS FRAYED.						1	G	7	1 	3U			O	H2SW    					 
2001102500039	20011025	00039	SW  	2001	10	25	HEEA076511       	1	20011005	G	2822	2C273	CARTRIDGE       			BELL  	412   	412EP       	1182205	SW  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6106C					36257				FUEL CARTRIDGE INOPERATIVE.						1	G	7	2 	4U			 	H4SW    					 
2001102500040	20011025	00040	SW  	2001	10	25	HEEA076513       	1	20011005	G	2820	206061634003	VALVE           			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				FUEL VALVE STICKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500041	20011025	00041	SW  	2001	10	25	HEEA076520       	1	20011008	G	6510	407340339103	BEARING         		407040302101	BELL  	407   	407         	1182206	SW  										T/R DRIVESHAFT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH				A15	53400				WORN BEARING.  SCRAPPED IN HOUSE.						1	G	7	1 	3U			O	H2SW    					 
2001102500042	20011025	00042	SW  	2001	10	25	HEEA076521       	1	20011008	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	BURNED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M	161  				28102				BURNT.  WILL NOT OPERATE.						2	G	7	2 	4U			 	H10SW   					 
2001102500043	20011025	00043	SW  	2001	10	25	HEEA076522       	1	20011008	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M	210  				28102				WILL NOT DISENGAGE.						2	G	7	2 	4U			 	H10SW   					 
2001102500044	20011025	00044	SW  	2001	10	25	HEEA076523       	1	20011008	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806	42   				28140				WILL NOT ENGAGE.  CLUTCH IN PIECES.						2	G	7	2 	4U			 	H10SW   					 
2001102500045	20011025	00045	SW  	2001	10	25	HEEA076524       	1	20011008	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5748M	51   				28102				DOES NOT DISENGAGE.						2	G	7	2 	4U			 	H10SW   					 
2001102500046	20011025	00046	SW  	2001	10	25	HEEA076525       	1	20011009	G	5320	206020113173S	CAP             			BELL  	206   	206A        	1181508	SW  										FUSELAGE	CRACKED         	E			HEEA	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03										RECEIVED DENTED AND CRACK AT LEADING EDGE.						1	G	7	1 	3U			 	H2SW    					 
2001102500050	20011025	00050	SW  	2001	10	25	HEEA076527       	1	20011010	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH	1228 				53396				LOW TORQUE INDICATION.						1	G	7	1 	3U			O	H2SW    					 
2001102500061	20011025	00061	SW  	2001	10	25	HEEA076528       	1	20011010	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										MLG	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				DISCHARGED ON ITS OWN.  INSTALLED 11-9-99 AT A/C TOTAL TIME 2102:15 AND REMOVED AT A/C TOTAL TIME 3683:40.						1	G	7	1 	3U			O	H2SW    					 
2001102500062	20011025	00062	SW  	2001	10	25	HEEA076529       	1	20011010	G	2400	A490ATSCF1428	POWER SUPPLY    			BELL  	407   	407         	1182206	SW  											WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH	2297 				53393				POWER SUPPLY HAS WEAK OUTPUT.						1	G	7	1 	3U			O	H2SW    					 
2001102500063	20011025	00063	SW  	2001	10	25	HEEA076530       	1	20011010	G	7700	222375077113	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										OIL PRESSURE	FLUCTUATES      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH	6597 				53003				FLUCTUATING APPROX. 10 PSI.						1	G	7	1 	3U			O	H2SW    					 
2001102500068	20011025	00068	SW  	2001	10	25	HEEA076531       	1	20011010	G	7714	212075037109	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										ENGINE	FLUCTUATES      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6106C					36257				FLUCTUATES ON START CYCLE UNTIL 30 PERCENT N1 SPEED ATTAINED.						1	G	7	2 	4U			 	H4SW    					 
2001102500069	20011025	00069	SW  	2001	10	25	HEEA076532       	1	20011010	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N	477  				28106				FAILED CLUTCH INSPECTION AND BEARING EXTENDING FROM HOUSING.						2	G	7	2 	4U			 	H10SW   					 
2001102500104	20011025	00104	SW  	2001	10	25	HEEA076534       	1	20011010	G	3110	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH					53142				START LIGHT WILL NOT ILLUMINATE.						1	G	7	1 	3U			O	H2SW    					 
2001102500106	20011025	00106	SW  	2001	10	25	HEEA076535       	1	20011010	G	7933	407375004101	INDICATOR       			BELL  	407   	407         	1182206	SW  										ENG OIL TEMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				WILL GO TO ZERO INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW    					 
2001102500107	20011025	00107	SW  	2001	10	25	HEEA076536       	1	20011010	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	720PH					53277				NO INDICATION ON GAUGE.  IT WILL NOT TEST.						1	G	7	1 	3U			O	H2SW    					 
2001102500108	20011025	00108	SW  	2001	10	25	HEEA076537       	1	20011010	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										ENGINE OIL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				ENGINE PRESSURE DROPPED TO ZERO. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFEREN	CE:  DMR#720488.					1	G	7	1 	3U			O	H2SW    					 
2001102500109	20011025	00109	SW  	2001	10	25	HEEA076538       	1	20011010	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										MLG	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				UNABLE TO SEAT FILLER VALVE.						1	G	7	1 	3U			O	H2SW    					 
2001102500110	20011025	00110	SW  	2001	10	25	HEEA076539       	1	20011010	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										BOOST PUMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	30   				53283				LEFT BOOST PUMP LIGHT DOESN'T ILLUMINATE WHEN SWITCH IS IN OFF POSITION.						1	G	7	1 	3U			O	H2SW    					 
2001102500111	20011025	00111	SW  	2001	10	25	HEEA076540       	1	20011010	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										MLG FLOAT	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				FLOAT BAG SOLENOID VALVE LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500112	20011025	00112	SW  	2001	10	25	HEEA076541       	1	20011010	G	2913	206076030111	PUMP            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH	1452 				53386				DRIVE SPLINES WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500113	20011025	00113	SW  	2001	10	25	HEEA076542       	1	20011010	G	6320		BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH	3893 				53198				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500117	20011025	00117	SW  	2001	10	25	HEEA076543       	1	20011010	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										FLOAT BAG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				FLOAT BAG SOLENOID VALVE IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500119	20011025	00119	SW  	2001	10	25	HEEA076545       	1	20011010	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH	1163 				53396				GREASE PURGES THROUGH THE TOP.						1	G	7	1 	3U			O	H2SW    					 
2001102500120	20011025	00120	SW  	2001	10	25	HEEA076546       	1	20011010	G	3212	206373901103	SOLENOID VALVE  			BELL  	407   	407         	1182206	SW  										FLOAT BAG	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH					53142				SOLENOID VALVE FOR FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500121	20011025	00121	SW  	2001	10	25	HEEA076547       	1	20011010	G	6300	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	1974 				53400				MAIN ROTOR MOUNT DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2001102500122	20011025	00122	SW  	2001	10	25	HEEA076550       	1	20011010	G	6310	406040500123B	FREEWHEEL UNIT  			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	723PH	3100 				53283				LEAKING AT FRONT SEAL. .						1	G	7	1 	3U			O	H2SW    					 
2001102500123	20011025	00123	SW  	2001	10	25	HEEA076551       	1	20011010	G	6300	407010206103	SPRING          			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	SEPARATED       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH	2485 				53283				SPRING HAS SEPARATION.						1	G	7	1 	3U			O	H2SW    					 
2001102500125	20011025	00125	SW  	2001	10	25	HEEA076555       	1	20011010	G	6730	206076062107	SERVO           			BELL  	407   	407         	1182206	SW  										CYCLIC	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	494PH	1866 				53396				CYCLIC SERVO LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500126	20011025	00126	SW  	2001	10	25	HEEA076556       	1	20011010	G	6730	206076062107	SERVO           			BELL  	407   	407         	1182206	SW  										CYCLIC	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	494PH	1866 				53396				CYCLIC SERVO LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001102500128	20011025	00128	SW  	2001	10	25	HEEA076557       	1	20011010	G	6210	407015001117	BLADE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	409PH	4173 				53059				MAIN ROTOR BLADE CRACKED AT OUTBOUND TRIM TAB.						1	G	7	1 	3U			O	H2SW    					 
2001102500129	20011025	00129	SW  	2001	10	25	HEEA076558       	1	20011010	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH	1594 				53278				MAIN ROTOR TRANSMISSION MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2001102500130	20011025	00130	SW  	2001	10	25	HEEA076559       	1	20011010	G	6300		BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH	3728 				53207				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001102500133	20011025	00133		2001	10	25	HEEA076560       	4	20011010	G	3197		CONNECTOR       			BELL  	407   	407         	1182206	SW  										INSTRUMENT PANEL	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH	3728 				53207				BENT PIN IN PLUG.						1	G	7	1 	3U			O	H2SW    					 
2001102500134	20011025	00134	SW  	2001	10	25	HEEA076564       	1	20011010	G	7714	32005037	TACH GENERATOR  			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				ON INBOUND FLIGHT, THE NR 2 ENGINE OUT LIGHT ILLUMINATED. REPLACED NR 2 ENGINE N1 TACH GEN.						1	G	7	2 	4U			 	H4SW    					 
2001102500136	20011025	00136	SW  	2001	10	25	HEEA076565       	1	20011010	G	2910	212076433001	LINE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	CRACKED         	E			HEEA	A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			SW	03	1202T					33112				WHILE IN CRUISE FLIGHT, NR 1 HYDRAULIC SYSTEM FAILED. MAINTENANCE REPLACED HYDRAULIC TUBE ASSY DUE TO CRACK IN ONE OF TH	E CURVES.					1	G	7	2 	4U			 	H4SW    					 
2001102500140	20011025	00140	NE  	2001	10	25	HEEA076566       	2	20011011	G	7200	23063412	HOSE            			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				HOSE LEAKS UNDER PRESSURE. REPLACED WITH SERVICEABLE HOSE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001102500142	20011025	00142	SW  	2001	10	25	HEEA076567       	1	20011011	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	720PH	1861 				53277				SWASHPLATE SEAL SPINNING IN CAP.						1	G	7	1 	3U			O	H2SW    					 
2001102500143	20011025	00143	SW  	2001	10	25	HEEA076568       	1	20011011	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	8595X					53267				SUPPORT LEAKING FROM SEAL.						1	G	7	1 	3U			O	H2SW    					 
2001102500144	20011025	00144	SW  	2001	10	25	HEEA076572       	1	20011011	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH	1146 				53461				TAIL ROTOR HUB HAS A WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001102500145	20011025	00145	SW  	2001	10	25	HEEA076573       	1	20011011	G	6300	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2001102500146	20011025	00146	SW  	2001	10	25	HEEA076574       	1	20011011	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102500148	20011025	00148	SW  	2001	10	25	HEEA076575       	1	20011011	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001102500149	20011025	00149		2001	10	25	HEEA076580       	4	20011011	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										VHF SYSTEM	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				TRANSMITS WEAK. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500150	20011025	00150		2001	10	25	HEEA076581       	4	20011011	G	3420	071105200	INDICATOR       			BELL  	230   	230         	1182149	SW  										ATTITUDE	PRECESSES       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911RC					23037				INTERMITTENT PROBLEM OF PRECESSING 30 DEGREES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			NC	H9SW    					 
2001102500151	20011025	00151		2001	10	25	HEEA076582       	4	20011011	G	3442	071111401	ANTENNA         			BELL  	206   	206L3       	1182108	SW  										RADAR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6748D					51106				COAX PULLED OUT FROM ANTENNA CONNECTOR. REPLACED WITH SERVICEABLE PART.  TO BE SENT TO VENDOR FOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001102500152	20011025	00152		2001	10	25	HEEA076583       	4	20011011	G	3457	13824120234	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3905B					45598				FAILED DUMPING ALL WAYPOINTS, RECEIVER AND BATTERY BACK UP FAIL KEPT FLASHING IN MESSAGE MODE. REPLACED WITH SERVICEABLE	 PART.					1	G	7	1 	3U			 	H2SW    					 
2001102500153	20011025	00153	SW  	2001	10	25	HEEA076584       	1	20011011	G	6510	204040620011	SHAFT           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WEIGHT MISSING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500154	20011025	00154	SW  	2001	10	25	HEEA076585       	1	20011011	G	2140	205072277009	VALVE           			BELL  	412   	412         	1182202	SW  										HEATER	INTERMITTENT    	E				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				HEATER MIXING VALVE WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500163	20011025	00163	SW  	2001	10	25	HEEA076586       	1	20011011	G	6400		BEARING         			BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E					51498				BEARINGS WORN AND RUSTED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102500164	20011025	00164	SW  	2001	10	25	HEEA076587       	1	20011011	G	3212	206050248111	FLOAT           			BELL  	206   	206L3       	1182108	SW  										MLG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				FAILED ALTERNATE CHAMBER CHECK. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102500165	20011025	00165	GL  	2001	10	25	HEEA076588       	2	20011011	G	7230	206075682107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GAS PRODUCER	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6748D					51106				DID NOT FUNCTION PROPERLY.  NEEDLE SLOW TO REACT AND HANGS UP AT APPROX. 10 PERCENT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL				 
2001102500166	20011025	00166	NE  	2001	10	25	HEEA076589       	2	20011011	G	7510	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				STICKING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102500167	20011025	00167	SW  	2001	10	25	HEEA076590       	1	20011011	G	2910	212076433011	TUBE            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	CRACKED         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1202T					33112				TUBE ASSY CRACKED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500169	20011025	00169	SW  	2001	10	25	HEEA076591       	1	20011011	G	2510	222320823119	SEAT BELT       			BELL  	206   	206L4       	1182110	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				SEAT BELT FRAYED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			NC	H2SW    					 
2001102500170	20011025	00170	SW  	2001	10	25	HEEA076592       	1	20011011	G	2432	30126001	BATTERY         			BELL  	412   	412         	1182202	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				SLOW TO CHARGE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500171	20011025	00171	SW  	2001	10	25	HEEA076593       	1	20011011	G	7714	32005037	TACH GENERATOR  			BELL  	412   	412         	1182202	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				ENGINE OUT LIGHT WON'T GO OUT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500172	20011025	00172	SW  	2001	10	25	HEEA076594       	1	20011011	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4835					51131				WEAK AND AIRCRAFT SLOW TO START. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102500173	20011025	00173	NE  	2001	10	25	HEEA076595       	2	20011011	G	7320	324473511	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	2149S					36002				CAUSING TORQUE OSCILLATIONS OF 10-15 PERCENT AT A HOVER. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102500174	20011025	00174		2001	10	25	HEEA076596       	4	20011011	G	2561	3500145NL72	LIFE VEST       			BELL  	412   	412         	1182202	SW  										EMERGENCY EQUIP	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				LIFE VEST LEAKS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500175	20011025	00175	SW  	2001	10	25	HEEA076597       	1	20011011	G	2422	412075101101	INVERTER        			BELL  	412   	412         	1182202	SW  										ELECTRICAL	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				WORKS INTERMITTENTLY DUE TO WATER DAMAGE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500185	20011025	00185		2001	10	25	HEEA076598       	4	20011011	G	3421	5050010902	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5019F					45244				ADJUSTMENT KNOB WILL NOT FUNCTION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102500186	20011025	00186	SW  	2001	10	25	HEEA076599       	1	20011011	G	3340	7028521	LIGHT           			BELL  	412   	412         	1182202	SW  										STROBE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				WILL NOT COME ON. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500188	20011025	00188		2001	10	25	HEEA076600       	4	20011011	G	3457	8143902240B	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	33008					36004				WHEN UNIT IS TURNED ON, POWERS UP FOR APPROX. 15 SECONDS TO ONE MINUTE THEN GOES BLANK. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500189	20011025	00189	SW  	2001	10	25	HEEA076601       	1	20011011	G	2497	A1077V	CONTACTOR       			BELL  	206   	206L3       	1182108	SW  										ELECTRICAL	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4835					51131				A2 TERMINAL STUD LOOSE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001102500190	20011025	00190		2001	10	25	HEEA076602       	4	20011011	G	2340	A3016R	MIXER BOX       			BELL  	412   	412         	1182202	SW  										INTERPHONE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				LIGHT BLINKS ON AND OFF. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500192	20011025	00192		2001	10	25	HEEA076603       	4	20011011	G	2562	ELP362D	ELT             			BELL  	412   	412         	1182202	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				BATTERY WEAK, LOW VOLTAGE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500193	20011025	00193		2001	10	25	HEEA076604       	4	20011011	G	2562	ELT910	ELT             			BELL  	412   	412         	1182202	SW  										CABIN	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				INTERMITTENTLY COMES ON IN FLIGHT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500195	20011025	00195		2001	10	25	HEEA076605       	4	20011011	G	2300	G4434A	CONTROL HEAD    			BELL  	412   	412         	1182202	SW  										COMM SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				ON/OFF SWITCH INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500196	20011025	00196		2001	10	25	HEEA076606       	4	20011011	G	3140	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										INSTRUMENT PANEL	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				DISPLAYS ONLY GREEN IN MAP MODE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500200	20011025	00200		2001	10	25	HEEA076607       	4	20011011	G	3442	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				DISPLAYS RANDOM RANGES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500202	20011025	00202		2001	10	25	HEEA076608       	4	20011011	G	3442	MI585200	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				DISPLAYS RANDOM RANGES. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500204	20011025	00204	SW  	2001	10	25	HEEA076609       	1	20011011	G	5260	PHI101741	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1202T					33112				STEP WON'T GO DOWN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500207	20011025	00207	SW  	2001	10	25	HEEA076610       	1	20011011	G	6720	PHI41294	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				WORN BEARINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500209	20011025	00209	SW  	2001	10	25	HEEA076611       	1	20011012	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				BEARING WORN. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW    					 
2001102500211	20011025	00211	SW  	2001	10	25	HEEA076612       	1	20011012	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001102500212	20011025	00212	SW  	2001	10	25	HEEA076613       	1	20011012	G	6420	407312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										TAIL ROTOR HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH				53025	53386				WORN ELASTOMER. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  LABOR CREDIT ACCOM	PLISHED ON J0188327-WA (INVOICE AND DMR NO. 687168).					1	G	7	1 	3U			O	H2SW    					 
2001102500214	20011025	00214	NE  	2001	10	25	HEEA076614       	2	20011012	G	7314	02527730008	PUMP            			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE FUEL	FAILED          	E			HEEA	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	2149S					36002				ENGINE OSCILLATIONS AND SEAL LEAKING. REPLACED WITH SERVICEABLE FUEL PUMP.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001102500216	20011025	00216	SW  	2001	10	25	HEEA076615       	1	20011012	G	3040	204070907101	MOTOR           			BELL  	412   	412         	1182202	SW  										WINDSHIELD WIPER	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893L					33006				PILOT WIPER INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500218	20011025	00218	SW  	2001	10	25	HEEA076616       	1	20011012	G	5310		BEARING         			BELL  	412   	412         	1182202	SW  										STRUCTURE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2298Z					33077				I/D BORE BEARING TOO SMALL.  (BEARING P/N 209-031-351-001) REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500219	20011025	00219	SW  	2001	10	25	HEEA076617       	1	20011012	G	7700	B4429	CHIP DETECTOR   		350A33200406	BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2148K				MA1154	36001				CAUSES REMOTE CAT'S EYE TO TRIP. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001102500221	20011025	00221		2001	10	25	HEEA076618       	4	20011003	G	3457	0110010600	GPS             			BOLKMS	117   	BK117A1     	5626010	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	217UC					7152				GPS WENT BLANK. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H13EU   					 
2001102500222	20011025	00222	EU  	2001	10	25	HEEA076622       	1	20011004	G	6300	350A33215300	BEARING         			SNIAS 	350   	AS350B1     	8680811	EU  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				BEARING WORN.						1	G	7	1 	3U			 	H9EU    					 
2001102500223	20011025	00223	EU  	2001	10	25	HEEA076623       	1	20011004	G	7500	704A34415099	HOSE            			SNIAS 	350   	AS350B      	8680801	EU  										BLEED AIR	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	972AE	88   				3234				TORN. PENDING VENDOR RETURN FOR CREDIT.						1	G	7	1 	3U			 	H9EU    					 
2001102500224	20011025	00224	EU  	2001	10	25	HEEA076625       	1	20011004	G	6730	EMRL8RSP3C	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR SERVO	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	974AE					2653				WORN ROD END BEARINGS ON MAIN ROTOR SERVOS. PENDING VENDOR RETURN FOR CREDIT.						1	G	7	1 	3U			 	H9EU    					 
2001102500225	20011025	00225	EU  	2001	10	25	HEEA076628       	1	20011004	G	6520	350A33215001	BEARING         			SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				WORN BEARING.						1	G	7	1 	3U			 	H9EU    					 
2001102500226	20011025	00226	EU  	2001	10	25	HEEA076629       	1	20011004	G	7721	56375600010	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				ERRATIC INDICATIONS. SENT TO AMERICAN EUROCOPTER CORP. FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  RMA# 	R032847.					1	G	7	1 	3U			 	H9EU    					 
2001102500228	20011025	00228	EU  	2001	10	25	HEEA076630       	1	20011004	G	6730	704A34240015	ACCUMULATOR     			SNIAS 	350   	AS350B      	8680801	EU  										ROTO SERVO	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	974AE					2653				WILL NOT HOLD CHARGE.  LEAKING.						1	G	7	1 	3U			 	H9EU    					 
2001102500229	20011025	00229	EU  	2001	10	25	HEEA076631       	1	20011011	G	2435		BRUSHES         			SNIAS 	350   	AS350B      	8680801	EU  										STARTER GEN	ARCED           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				BRUSHES ARCING WHEN STARTER IS TURNING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001102500231	20011025	00231		2001	10	25	HEEA076632       	4	20011011	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	856PH					3352				DOES NOT KEEP CORRECT TIME. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001111400001	20011114	00001	GL  	2001	11	14	HEEA076800       	2	20011016	G	7250	6898977	COUPLING        								ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03							CAE272598			N1 COUPLING HAS EXCESSIVE RUST CAUSING PITTING.											3	U			E4CE				 
2001111400002	20011114	00002	NE  	2001	11	14	HEEA076801       	2	20011019	G	7421	9550168760	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  						WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				CONDUCTOR WORN. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001111400003	20011114	00003	NE  	2001	11	14	HEEA076802       	1	20011019	G	7700	9550176740	THERMOCOUPLE    			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH					760505				WORN PROBES.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001111400004	20011114	00004	NE  	2001	11	14	HEEA076803       	1	20011025	G	7100	0292005310	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					NACELLE	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH	1306 				760505				LOW POWER, LEAKING.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001111400005	20011114	00005	SW  	2001	11	14	HEEA076806       	1	20011016	G	6300	407340339103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400006	20011114	00006	SW  	2001	11	14	HEEA076807       	1	20011016	G	6300	407340339103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400007	20011114	00007	SW  	2001	11	14	HEEA076808       	1	20011016	G	6300	407340339103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400008	20011114	00008	SW  	2001	11	14	HEEA076809       	1	20011016	G	6300	407340339103	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400009	20011114	00009	SW  	2001	11	14	HEEA076810       	1	20011016	G	6510	407040302107	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH	1903 				53398				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400010	20011114	00010	SW  	2001	11	14	HEEA076811       	1	20011016	G	6510	407040302107	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH	1299 				53398				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400011	20011114	00011	SW  	2001	11	14	HEEA076812       	1	20011016	G	6510	407040302103	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400013	20011114	00013	SW  	2001	11	14	HEEA076813       	1	20011016	G	6510	407040302107	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH	1597 				53390				BEARING INNER RACE TURNING ON SHAFT JOURNAL.						1	G	7	1 	3U			O	H2SW    					 
2001111400015	20011114	00015	SW  	2001	11	14	HEEA076814       	1	20011016	G	6510		SHAFT           			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	FAILED          	E			HEEA	A				UNSCHED LANDING         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			SW	03	4999					53323				IN CRUISE, AIRCRAFT DEVELOPED SEVERE VERTICAL VIBRATION.  FOUND FORWARD BEARING ON NR 2 TAIL ROTOR OIL COOLER BLOWER SHA	FT FAILURE.					1	G	7	1 	3U			O	H2SW    					 
2001111400017	20011114	00017	SW  	2001	11	14	HEEA076815       	1	20011017	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	31821					51076				RECEIVED FROM PARTS.  WEAK FROM INSTALLATION AND FAILED COMPLETELY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400018	20011114	00018	SW  	2001	11	14	HEEA076816       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	3116P					51530				WILL NOT HOLD CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400020	20011114	00020	SW  	2001	11	14	HEEA076817       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	4180F									TOO WEAK TO START AIRCRAFT. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400027	20011114	00027	NE  	2001	11	14	HEEA076820       	2	20011018	G	7321	32448891	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FLUCTUATES      	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	03	22608	10321				33075				AFTER DEPARTURE, NR 1 ENGINE STARTED TO HAVE N1 FLUCTUATIONS. REPLACED FUEL CONTROL.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001111400028	20011114	00028	SW  	2001	11	14	HEEA076821       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	406EH					45183				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400029	20011114	00029	SW  	2001	11	14	HEEA076822       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	206LS					51070				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400031	20011114	00031	SW  	2001	11	14	HEEA076823       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	5745S					45491				DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400032	20011114	00032	SW  	2001	11	14	HEEA076824       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	8593X					51509				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400034	20011114	00034	SW  	2001	11	14	HEEA076825       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	54641					51184				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400035	20011114	00035	SW  	2001	11	14	HEEA076826       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	2777D					45299				DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400046	20011114	00046	SW  	2001	11	14	HEEA076827       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	8587X					51464				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400047	20011114	00047	SW  	2001	11	14	HEEA076828       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6610C					51425				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400048	20011114	00048	SW  	2001	11	14	HEEA076829       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	41791					51465				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400050	20011114	00050	SW  	2001	11	14	HEEA076830       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6161A					51611				WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400051	20011114	00051	SW  	2001	11	14	HEEA076831       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	31077					51520				WON'T TAKE A CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400052	20011114	00052	SW  	2001	11	14	HEEA076832       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	41791					51465				DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400054	20011114	00054	SW  	2001	11	14	HEEA076833       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03										WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400055	20011114	00055	SW  	2001	11	14	HEEA076834       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	FAILED          	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	141BH					51303				WON'T TAKE CHARGE. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400057	20011114	00057	SW  	2001	11	14	HEEA076835       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6160Y					51609				DEAD. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400059	20011114	00059	SW  	2001	11	14	HEEA076836       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L1       	1182107	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	1078D					45397				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400061	20011114	00061	SW  	2001	11	14	HEEA076837       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	141BH					51303				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400066	20011114	00066	SW  	2001	11	14	HEEA076838       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6161A					51611				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400067	20011114	00067	SW  	2001	11	14	HEEA076839       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	41791					51465				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400068	20011114	00068	SW  	2001	11	14	HEEA076840       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	54641					51184				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400069	20011114	00069	SW  	2001	11	14	HEEA076841       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	4835					51131				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400071	20011114	00071	SW  	2001	11	14	HEEA076842       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6251Y					51556				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400072	20011114	00072	SW  	2001	11	14	HEEA076843       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	4835					51131				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400073	20011114	00073	SW  	2001	11	14	HEEA076844       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6160Z					51610				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400075	20011114	00075	SW  	2001	11	14	HEEA076845       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	6160Z					51610				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400076	20011114	00076	SW  	2001	11	14	HEEA076846       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	8591X					51495				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400080	20011114	00080	SW  	2001	11	14	HEEA076847       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	OVERHEATED      	E			HEEA	O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	81SP					51029				BATTERY HOT LIGHT. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400093	20011114	00093	SW  	2001	11	14	HEEA076848       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	32041					51539				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400094	20011114	00094	SW  	2001	11	14	HEEA076849       	1	20011018	G	2432	32007001	BATTERY         			BELL  	206   	206L3       	1182108	SW  										MAIN	DISCHARGED      	E			HEEA	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	41791					51465				WEAK. REPLACED WITH SERVICEABLE BATTERY.						1	G	7	1 	3U			 	H2SW    					 
2001111400095	20011114	00095	SW  	2001	11	14	HEEA076850       	1	20011019	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL INDICATION	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	417PH					53038				LOW LEVEL LIGHT STAYS ON.						1	G	7	1 	3U			O	H2SW    					 
2001111400096	20011114	00096	SW  	2001	11	14	HEEA076851       	1	20011019	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111400098	20011114	00098	SW  	2001	11	14	HEEA076852       	1	20011019	G	3212	206373902103	RELIEF VALVE    			BELL  	407   	407         	1182206	SW  										MLG	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	404PH					53188				RELIEF VALVE KEPT RELEASING PRESSURE DOWN TO 2750 PSI.						1	G	7	1 	3U			O	H2SW    					 
2001111400099	20011114	00099	SW  	2001	11	14	HEEA076853       	1	20011019	G	3212	206050247135	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				END COVERS COMING UNSEWN.						1	G	7	1 	3U			O	H2SW    					 
2001111400113	20011114	00113	SW  	2001	11	14	HEEA076854       	1	20011019	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				END COVERS COMING UNSEWN.						1	G	7	1 	3U			O	H2SW    					 
2001111400114	20011114	00114	SW  	2001	11	14	HEEA076856       	1	20011019	G	2510	407370720101	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				SHOULDER STRAP FRAYED FROM WEAR.						1	G	7	1 	3U			O	H2SW    					 
2001111400115	20011114	00115	SW  	2001	11	14	HEEA076857       	1	20011019	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				DETERIORATED.						1	G	7	1 	3U			O	H2SW    					 
2001111400117	20011114	00117	SW  	2001	11	14	HEEA076858       	1	20011019	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				PRESSURE GAUGE HAS MOISTURE AND RUST.						1	G	7	1 	3U			O	H2SW    					 
2001111400121	20011114	00121	SW  	2001	11	14	HEEA076859       	1	20011019	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         	1182206	SW  										ENGINE	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001111400122	20011114	00122	SW  	2001	11	14	HEEA076860       	1	20011019	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAI ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400125	20011114	00125	SW  	2001	11	14	HEEA076862       	1	20011019	G	2822	206076030111	PUMP            			BELL  	407   	407         	1182206	SW  										FUEL BOOST	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH	864  				53401				PUMP SHAFT SPLINE WEAR.						1	G	7	1 	3U			O	H2SW    					 
2001111400126	20011114	00126	SW  	2001	11	14	HEEA076863       	1	20011019	G	6300	407010206103	SPRING          			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH	2952 				53278				WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400127	20011114	00127	SW  	2001	11	14	HEEA076864       	1	20011019	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	2025 				53400				LINK HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400140	20011114	00140	SW  	2001	11	14	HEEA076865       	1	20011019	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	2025 				53400				LINK HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400142	20011114	00142	SW  	2001	11	14	HEEA076866       	1	20011019	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				LINK HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400143	20011114	00143	SW  	2001	11	14	HEEA076867       	1	20011019	G	6710	406010426101	LINK            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	2025 				53400				LINK HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111400145	20011114	00145	SW  	2001	11	14	HEEA076869       	1	20011019	G	2840	407375016103	SIGNAL COND UNIT			BELL  	407   	407         	1182206	SW  										FUEL INDICTION	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	495PH					53397				LOW LEVEL LIGHT WILL NOT GO OUT.						1	G	7	1 	3U			O	H2SW    					 
2001111400146	20011114	00146	SW  	2001	11	14	HEEA076870       	1	20011019	G	3110	407375005101	INDICATOR       			BELL  	407   	407         	1182206	SW  										XMSN OIL TEMP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	457PH					53147				TRANSMISSION OIL TEMP INDICATOR INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001111400147	20011114	00147	SW  	2001	11	14	HEEA076871       	1	20011019	G	2840	407375016103	SIGNAL COND UNIT			BELL  	407   	407         	1182206	SW  										FUEL INDICATION	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	495PH					53397				LEVEL LIGHT STAYING ON WITH 550 POUNDS OF FUEL.						1	G	7	1 	3U			O	H2SW    					 
2001111400148	20011114	00148	SW  	2001	11	14	HEEA076872       	1	20011022	G	3210	206323006	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MLG CROSSTUBE CORRODED.						1	G	7	1 	3U			 	H2SW    					 
2001111400152	20011114	00152	SW  	2001	11	14	HEEA076873       	1	20011023	G	6710	406010429101	PIN             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				PIN WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111400158	20011114	00158	SW  	2001	11	14	HEEA076874       	1	20011023	G	6300	406040316101	ADAPTER         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				ADAPTER HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW    					 
2001111400159	20011114	00159	SW  	2001	11	14	HEEA076875       	1	20011023	G	6710	406010429101	PIN             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH					53038				PIN WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111400160	20011114	00160	SW  	2001	11	14	HEEA076878       	1	20011023	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	467PH	3152 				53142				ROTOR BRAKE IS DAMAGED AND LEAKS.						1	G	7	1 	3U			O	H2SW    					 
2001111400161	20011114	00161	SW  	2001	11	14	HEEA076879       	1	20011023	G	6321		HOUSING         			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH	1638 				53378				EXCESSIVE HOUSING WEAR.						1	G	7	1 	3U			O	H2SW    					 
2001111400162	20011114	00162	SW  	2001	11	14	HEEA076880       	1	20011023	G	6230	406010401115	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH					53114				DUPLEX BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500001	20011115	00001	SW  	2001	11	15	HEEA076881       	1	20011023	G	6710	406010428109	HUB             			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH	646  				53038				HUB IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500008	20011115	00008	SW  	2001	11	15	HEEA076884       	1	20011024	G	3110	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				GOES TO TEST IN FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001111500009	20011115	00009	SW  	2001	11	15	HEEA076885       	1	20011024	G	6320	407340339101	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH	44   			PHI0039	53461				ROUGH AND NOISY.						1	G	7	1 	3U			O	H2SW    					 
2001111500010	20011115	00010	SW  	2001	11	15	HEEA076886       	1	20011024	G	6320	206040156001	SEAL            			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				SEAL HAS OIL LEAK.						1	G	7	1 	3U			O	H2SW    					 
2001111500016	20011115	00016	SW  	2001	11	15	HEEA076887       	1	20011024	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				TORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500017	20011115	00017	SW  	2001	11	15	HEEA076888       	1	20011024	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				WORN. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW    					 
2001111500018	20011115	00018	SW  	2001	11	15	HEEA076889       	1	20011024	G	3212	206050247138	FLOAT           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500019	20011115	00019	SW  	2001	11	15	HEEA076890       	1	20011024	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001111500020	20011115	00020	SW  	2001	11	15	HEEA076891       	1	20011024	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH					53283				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001111500022	20011115	00022	SW  	2001	11	15	HEEA076892       	1	20011024	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH				96240	53283				STARTER GENERATOR HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001111500025	20011115	00025	SW  	2001	11	15	HEEA076893       	1	20011024	G	6730	206076062107	SERVO           			BELL  	407   	407         	1182206	SW  										CYCLIC	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				PISTON ROD END BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500026	20011115	00026	SW  	2001	11	15	HEEA076894       	1	20011024	G	6321	206340301103	BRAKE           			BELL  	407   	407         	1182206	SW  										ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	2496 				53276				FOUND EXCESSIVE WEAR ON HOUSING, BRAKE PAD BOLT RETAINER HOLES AND PAD RETAINER BOLTS. OVERHAULED, MODIFIED, TESTED AND 	RETURNED TO AIRCRAFT.					1	G	7	1 	3U			O	H2SW    					 
2001111500028	20011115	00028	SW  	2001	11	15	HEEA076895       	1	20011024	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FOGGED OVER.  CANNOT READ AMOUNT OF PRESSURE IN FLOAT BOTTLE.						1	G	7	1 	3U			O	H2SW    					 
2001111500029	20011115	00029	SW  	2001	11	15	HEEA076896       	1	20011024	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				NUMBERED DIAL MOVES.  UNABLE TO VERIFY EXACT AMOUNT OF PRESSURE IN FLOAT BOTTLE. T						1	G	7	1 	3U			O	H2SW    					 
2001111500032	20011115	00032	GL  	2001	11	15	HEEA076897       	2	20011024	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	03	4999					53323				LOW POWER ENGINE. IN SHOP REPAIR.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001111500036	20011115	00036	SW  	2001	11	15	HEEA076898       	1	20011024	G	6230	406010401117	SWASHPLATE      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				GREASE LEAKING FROM TOP SEAL.						1	G	7	1 	3U			O	H2SW    					 
2001111500037	20011115	00037	SW  	2001	11	15	HEEA076899       	1	20011024	G	6520	406040400117	GEARBOX         			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH					53378				OUTPUT SHAFT SPLINE WORN. REPLACED WITH SERVICEABLE T/R GEARBOX ASSEMBLY.						1	G	7	1 	3U			O	H2SW    					 
2001111500049	20011115	00049	SW  	2001	11	15	HEEA076900       	1	20011024	G	6310	406040500123B	FREEWHEEL UNIT  			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	8595X					53267				LEAKING FROM SEAL. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001111500050	20011115	00050	SW  	2001	11	15	HEEA076901       	1	20011024	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				RED MAIN ROTOR P/C LINK BEARING WORN WITH PLAY.						1	G	7	1 	3U			O	H2SW    					 
2001111500051	20011115	00051	SW  	2001	11	15	HEEA076902       	1	20011024	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				BEARING HAD RADIAL PLAY.						1	G	7	1 	3U			O	H2SW    					 
2001111500055	20011115	00055	SW  	2001	11	15	HEEA076903       	1	20011024	G	6710	406310407101	SEAL            		406010401115	BELL  	407   	407         	1182206	SW  										SWASHPLATE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH				A707	53198				UPPER BEARING GREASE SEAL LEAKING ON UNIBALL.						1	G	7	1 	3U			O	H2SW    					 
2001111500056	20011115	00056	SW  	2001	11	15	HEEA076904       	1	20011024	G	6230	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										M/R MAST	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				MAST BOOT TORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500058	20011115	00058	SW  	2001	11	15	HEEA076905       	1	20011024	G	6710	407001523101	IDLER ASSY      			BELL  	407   	407         	1182206	SW  										M/R CONTROL	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724PH					53327				TAIL ROTOR CONTROL IDLER ASSY HAS BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500059	20011115	00059	SW  	2001	11	15	HEEA076906       	1	20011024	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	1765 				53378				WORN ELASTOMERIC BEARING. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW    					 
2001111500061	20011115	00061	SW  	2001	11	15	HEEA076907       	1	20011024	G	6797	407076508103	HARNESS         			BELL  	407   	407         	1182206	SW  										INSTRUMENT PANEL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				PEDAL STOP SWITCH DAMAGED BY INTERFERENCE WITH INSTRUMENT PANEL FRAME.						1	G	7	1 	3U			O	H2SW    					 
2001111500063	20011115	00063	SW  	2001	11	15	HEEA076908       	1	20011024	G	5260	407301110	STEP            			BELL  	407   	407         	1182206	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				CORRODED AT BRACKET MOUNT BOLT HOLES. REPLACED WITH SERVICEABLE STEP.						1	G	7	1 	3U			O	H2SW    					 
2001111500064	20011115	00064	SW  	2001	11	15	HEEA076909       	1	20011024	G	6220	407310101101	BEARING         		407010100115	BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH				A436	53401				SHEAR BEARINGS WORN AND SEPARATING. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW    					 
2001111500067	20011115	00067	SW  	2001	11	15	HEEA076910       	1	20011024	G	6220	407310104103	SPRING          		407010150105	BELL  	407   	407         	1182206	SW  										FRAHM ASSY	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH				A560	53401				SPRINGS FOUND BROKEN.						1	G	7	1 	3U			O	H2SW    					 
2001111500068	20011115	00068	SW  	2001	11	15	HEEA076911       	1	20011024	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	OVERHEATED      	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	404PH					53188				BEARING OVERHEATED.						1	G	7	1 	3U			O	H2SW    					 
2001111500069	20011115	00069	SW  	2001	11	15	HEEA076912       	1	20011024	G	6510	407340340103	DISC PACK       			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4999					53323				FORWARD BLOWER SHAFT BEARING FAILED.						1	G	7	1 	3U			O	H2SW    					 
2001111500070	20011115	00070		2001	11	15	HEEA076913       	4	20011024	G	3120	M803B205VBATT	LIGHT           			BELL  	407   	407         	1182206	SW  										CLOCK	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	498PH					53399				HALF OF INDICATOR BACKLIGHT INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001111500071	20011115	00071	SW  	2001	11	15	HEEA076914       	1	20011024	G	2400	MS24509A10	SWITCH          			BELL  	407   	407         	1182206	SW  										ELECTRICAL DIST	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				BROKEN INTERNALLY. REPLACED WITH SERVICEABLE SWITCH.						1	G	7	1 	3U			O	H2SW    					 
2001111500093	20011115	00093	SW  	2001	11	15	HEEA076918       	1	20011024	G	6200	206011135105	BOLT            			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NICKS IN THREADED AREA.						1	G	7	1 	3U			 	H2SW    					 
2001111500094	20011115	00094	SW  	2001	11	15	HEEA076919       	1	20011026	G	6700	206011732103	SLEEVE          			BELL  	407   	407         	1182206	SW  										CONTROL TUBE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			O	H2SW    					 
2001111500095	20011115	00095	SW  	2001	11	15	HEEA076920       	1	20011026	G	6220		BEARING         		407010100115	BELL  	407   	407         	1182206	SW  										M/R HUB	SHEARED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH				A436	53401				SHEARING BEARINGS SEPARATION.						1	G	7	1 	3U			O	H2SW    					 
2001111500096	20011115	00096	SW  	2001	11	15	HEEA076921       	1	20011026	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	741PH	1022 				53457				WORN BEARING, CLICKING NOISE. PARTS AND LABOR CREDIT ACCOMPLISHED ON J0189948-WA.						1	G	7	1 	3U			O	H2SW    					 
2001111500097	20011115	00097	SW  	2001	11	15	HEEA076922       	1	20011026	G	6510	407340339103	BEARING         		407040302107	BELL  	407   	407         	1182206	SW  										TAIL ROTOR	ROUGH           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH				A1871	53386				BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001111500098	20011115	00098	SW  	2001	11	15	HEEA076923       	1	20011026	G	6510	407340339103	BEARING         		407040302107	BELL  	407   	407         	1182206	SW  										TAIL ROTOR	ROUGH           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH				A1875	53386				ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001111500099	20011115	00099	SW  	2001	11	15	HEEA076924       	1	20011026	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111500108	20011115	00108	SW  	2001	11	15	HEEA076926       	1	20011026	G	7931	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										OIL PRESSURE	READS HIGH      	E			HEEA	O				OTHER                   				N			FALSE WARNING             			CL	CLIMB          	1			SW	03	33008					36004				AFTER TAKEOFF, PILOT NOTED NR 2 ENGINE OIL PRESSURE WAS INDICATING HIGH. REPLACED OIL TEMP/PRESS INDICATOR.						1	G	7	2 	4U			 	H4SW    					 
2001111500110	20011115	00110	EU  	2001	11	15	HEEA076927       	1	20011019	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	317  				3235				CRACKED SPHERICAL STOP CUT OUT AREA, LOWER AFT AS MARKED.						1	G	7	1 	3U			 	H9EU    					 
2001111500112	20011115	00112		2001	11	15	HEEA076928       	4	20011019	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				DOES NOT KEEP CORRECT TIME.						1	G	7	1 	3U			 	H9EU    					 
2001111500113	20011115	00113		2001	11	15	HEEA076936       	4	20011030	G	3416	066104800	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911MJ					760231				RT WAS CAUSING ERRATIC READING ON APPROACH. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001111500114	20011115	00114	NE  	2001	11	15	HEEA076937       	1	20011031	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G	8350 				760076				CORROSION ON BOX BEAM AND TRAILING IS SPLIT OPEN ON PADDLE "B". PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001111500115	20011115	00115	NE  	2001	11	15	HEEA076938       	1	20011031	G	6220	7610208500046	SPINDLE         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	BINDING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1545K					760047				DROOP STOP BINDS UP WHEN INSTALLED.  FOUND WHEN TORQUEING UP SPINDLE.  A BIND PREVENTS THE DROOP STOP FROM RETURNING TO 	STATIC POSITION AT SHUTDOWN.  IT IS FREE TO MOVE WHEN NOT INSTALLED. PENDING VENDOR REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001111500116	20011115	00116	NE  	2001	11	15	HEEA076939       	1	20011031	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	760PH					760078				OUTER DOUBLER ON LOWER SIDE CRACKED AND HAS "C" CHANNEL DEBONDED. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001111500118	20011115	00118	NE  	2001	11	15	HEEA076940       	1	20011031	G	6210	7615009043054	TIP CAP         			SKRSKY	S76   	S76C        	8143008	NE  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	505PH					760505				FIBERGLASS SKIN NEAR THE TRAILING EDGE IS CRACKED AND HAS SOME SEPARATION NEXT TO THE ABRASION STRIP. PENDING VENDOR REP	AIR.					1	G	7	2 	3U			NC	H1NE    					 
2001111500119	20011115	00119	NE  	2001	11	15	HEEA076941       	1	20011031	G	6210	7615009100041A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1545K	12595				760047				LEADING EDGE TITANIUM STRIP HAS A COMPLETE CHORDWISE CRACK WITH MULTIPLE BRANCH WHICH EXTENDS BEYOND LIMITS. PENDING VEN	DOR REPAIR.					1	G	7	2 	3U			 	H1NE    					 
2001111500120	20011115	00120	NE  	2001	11	15	HEEA076942       	1	20011031	G	6210	7615009100042A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911MJ	14090				760231				TRAILING EDGE CRACKED JUST INBOARD OF TRIM TAB. REPLACED WITH SERVICEABLE BLADE.						1	G	7	2 	3U			 	H1NE    					 
2001111500121	20011115	00121	NE  	2001	11	15	HEEA076943       	1	20011031	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911MJ	5266 				760231				TRAILING EDGE DAMAGE AT AREA OF P/N - S/N STENCIL. REPLACED WITH SERVICEABLE BLADE.						1	G	7	2 	3U			 	H1NE    					 
2001111500122	20011115	00122	NE  	2001	11	15	HEEA076944       	1	20011031	G	6320	7635109045102	GEAR            			SKRSKY	S76   	S76A        	8143006	NE  										M/R GEARBOX	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RIVET NOT INSTALLED IN GEAR.  RIVET REQUIRED TO PREVENT OIL FROM LEAKING. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001111500123	20011115	00123	NE  	2001	11	15	HEEA076945       	1	20011031	G	6320	7635109500043	TRANSMISSION    			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ	10333				760231				CHIP LIGHT ON LANDING.  INSPECTED AND FOUND A 1/2" BY 3/16" PIECE OF A GEAR TOOTH ON THE LEFT CHIP PLUG. REPLACED WITH S	ERVICEABLE ASSEMBLY.					1	G	7	2 	3U			 	H1NE    					 
2001111500125	20011115	00125	NE  	2001	11	15	HEEA076946       	1	20011031	G	3340	7655002005101	LIGHT           			SKRSKY	S76   	S76A        	8143006	NE  										SEARCH LIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	792CH					760193				WILL NOT MOVE UP OR DOWN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001111500127	20011115	00127	NE  	2001	11	15	HEEA076947       	1	20011031	G	6730	7665009803106	POWERPACK       			SKRSKY	S76   	S76A        	8143006	NE  										SERVO SYSTEM	CRACKED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911MJ					760231				POWER PACK HOUSING CRACKED AT DRAIN FITTING. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001111500130	20011115	00130	GL  	2001	11	15	HEEA076948       	2	20011031	G	7421	9550166530	LEAD            			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					IGNITER	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				FRAYED AND WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001111500132	20011115	00132	GL  	2001	11	15	HEEA076949       	2	20011031	G	7421	9550166670	IGNITER         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				FRAYED AND WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001111500133	20011115	00133	GL  	2001	11	15	HEEA076950       	2	20011031	G	7421	9550168770	IGNITER         			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				INOPERATIVE - WILL NOT FIRE.  CENTER ELETRODE CAME OUT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001111500134	20011115	00134	NE  	2001	11	15	HEEA076951       	1	20011031	G	7410	9550176020	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					IGNITER	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	760PH					760078				CORROSION. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2001111500135	20011115	00135		2001	11	15	HEEA076952       	4	20011031	G	2340	A3016W	INTERPHONE      			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				COMM NR 1 TRANSMITS GARBLED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H1NE    					 
2001111500136	20011115	00136		2001	11	15	HEEA076953       	4	20011031	G	3442	7007700613	INDICATOR       			SKRSKY	S76   	S76C        	8143008	NE  										RADAR SYSTEM	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	505PH					760505				INTERMITTENTLY DISPLAYS FAIL. PENDING VENDOR REPAIR.						1	G	7	2 	3U			NC	H1NE    					 
2001111500137	20011115	00137		2001	11	15	HEEA076954       	4	20011031	G	2350	AA34300	CONNECTOR       			SKRSKY	S76   	S76A        	8143006	NE  										RADIO	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	913UK					760276				CANNOT PROGRAM MOTOROLA MCS 2000 RADIO. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H1NE    					 
2001111500139	20011115	00139		2001	11	15	HEEA076955       	4	20011031	G	3457	N0002000	GPS             																	COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										NEW UNIT DOES NOT GIVE GPS POSITION AND TRANSMITS INTERMITTENTLY WITH CDU. TO BE SENT TO VENDOR FOR WARRANTY REPAIR.																			 
2001111600047	20011116	00047	EU  	2001	11	16	HEEA076956       	1	20011101	G	7100	0292005220	ENGINE          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					NACELLE	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466	5392 				3004				ENGINE MAKING METAL.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001111600050	20011116	00050		2001	11	16	HEEA076957       	4	20011030	G	3457	0110005400	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				TAKES AN EXTENDED PERIOD OF TIME TO ACQUIRE SATTELITES. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600051	20011116	00051		2001	11	16	HEEA076958       	4	20011030	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	2261D					33076				TRANSMITS WEAK AND GARBLED. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600053	20011116	00053		2001	11	16	HEEA076959       	4	20011030	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	107X					33113				UNIT CUTS OUT IN FLIGHT INTERMTTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600054	20011116	00054		2001	11	16	HEEA076960       	4	20011030	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				RECEIVES VERY WEAK/ TRANSMITS GOOD. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600055	20011116	00055		2001	11	16	HEEA076961       	4	20011030	G	2312	064105430	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	30KH					51527				INOPERATIVE. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600056	20011116	00056		2001	11	16	HEEA076962       	4	20011030	G	3455	066104701	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										ADF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				WILL NOT PAINT AND NO AUDIO. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600058	20011116	00058		2001	11	16	HEEA076963       	4	20011030	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INTERFERENCE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31821					51076				TRANSPONDER SQUAWKING 24000 FEET. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600060	20011116	00060		2001	11	16	HEEA076964       	4	20011030	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	7128R					36007				INOPERATIVE, WILL NOT TRANSMIT. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001111600061	20011116	00061		2001	11	16	HEEA076965       	4	20011030	G	3452	066107100	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				INOPERATIVE. PENDING VENDOR REPAIR.						2	G	7	2 	4U			 	H10SW   					 
2001111600066	20011116	00066		2001	11	16	HEEA076966       	4	20011030	G	3100	071119208	CONTROL SWITCH  			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				STATION KNOB WHEN TURN TO RIGHT IT SPRINGS BACK TO LEFT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600067	20011116	00067		2001	11	16	HEEA076967       	4	20011030	G	3400	071121525	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				SEVERAL SEGMENTS INOPERATIVE. REPLACED WITH SERVICEABLE PART.  COULD NOT VERIFY COMPLAINT.   BENCH CHECK GOOD.						1	G	7	2 	4U			 	H4SW    					 
2001111600073	20011116	00073		2001	11	16	HEEA076968       	4	20011030	G	2312	071121525	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				DIGITS INTERMITTENTLY LOSE PART OF NUMBERS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600082	20011116	00082		2001	11	16	HEEA076969       	4	20011030	G	3454	071121627	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										NAVIGATION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				WHEN SUN HITS KFS, IT DOES NOT GET BRIGHT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600083	20011116	00083	SW  	2001	11	16	HEEA076970       	1	20011030	G	2422		INVERTER        			BELL  	412   	412         	1182202	SW  										ELECTRIAL	FAILED          	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	03	142PH					33150				NR 1 INVERTER DROPPED OFF LINE AND ELECTRICAL FUMES WERE NOTED BY PILOT. FOUND BURNED WIRE IN WINDSHIELD POST COVER AT T	OP OF POST.					1	G	7	2 	4U			 	H4SW    					 
2001111600084	20011116	00084	SW  	2001	11	16	HEEA076971       	1	20011030	G	2820	AE89411M	VENT            			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	O				OTHER                   				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	03	22608					33075				HAD STRONG FUEL ODOR IN COCKPIT. FOUND A SMALL AMOUNT OF FUEL HAD SEEPED THROUGH THE RT EXTERNAL TANK VENT DUE TO HIGH F	UEL LEVEL AND THE ATTITUDE OF THE AIRCRAFT.					1	G	7	2 	4U			 	H4SW    					 
2001111600085	20011116	00085	SW  	2001	11	16	HEEA076972       	1	20011031	G	3212	206030104023	FITTING         			BELL  	206   	206L3       	1182108	SW  										MLG FLOAT	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				PART IS CHAFED. REPLACED WITH SERVICEABLE FITTING.						1	G	7	1 	3U			 	H2SW    					 
2001111600086	20011116	00086	SW  	2001	11	16	HEEA076973       	1	20011031	G	6300	206033501004	FITTING         			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	54641					51184				FITTING IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600088	20011116	00088	SW  	2001	11	16	HEEA076974       	1	20011031	G	6320	206033518007	STOP            			BELL  	206   	206L3       	1182108	SW  										M/R GEARBOX	DETERIORATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31077					51520				DETERIORATION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600089	20011116	00089	SW  	2001	11	16	HEEA076975       	1	20011031	G	3210	206052105013	STRAP           			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6251X					51552				CORROSION. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600090	20011116	00090	SW  	2001	11	16	HEEA076976       	1	20011031	G	6710	206076062003	CYLINDER        			BELL  	206   	206L3       	1182108	SW  										CYCLIC	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	3116L					51529				LEAKING BEYOND LIMITS ON END CAP SIDE OF SERVO. PENDING VENDOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001111600091	20011116	00091	SW  	2001	11	16	HEEA076977       	1	20011031	G	7800	212061117001	TUBE            			BELL  	412   	412         	1182202	SW  										EXHAUST	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WORN BEARINGS. REPLACED WITH SERVICEABLE TUBE ASSY.						1	G	7	2 	4U			 	H4SW    					 
2001111600093	20011116	00093	SW  	2001	11	16	HEEA076978       	1	20011031	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										AUTO FLIGHT	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				STICKS INTERMITTENTLY. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001111600096	20011116	00096		2001	11	16	HEEA076979       	4	20011031	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				CO-PILOT RATE OF TURN NEEDLE DOES NOT MOVE. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001111600098	20011116	00098	SW  	2001	11	16	HEEA076980       	1	20011031	G	6220	222310504101	BEARING         			BELL  	230   	230         	1182149	SW  										MAIN ROTOR	DELAMINATED     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911RC					23037				DELAMINATION. PENDING VENDOR REPAIR.						1	G	7	2 	3U			NC	H9SW    					 
2001111600102	20011116	00102	SW  	2001	11	16	HEEA076981       	1	20011031	G	2435	23032048	STARTER GEN     			BELL  	212   	212         	1181420	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	03	102PH					30899				RED GLOW WAS OBSERVED IN THE STARTER GENERATOR FOLLOWED BY SMOKE, STARTER NEVER ENGAGED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	4U			 	H4SW    					 
2001111600103	20011116	00103	NE  	2001	11	16	HEEA076982       	2	20011031	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	OSCILLATES      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				ENGINE OSCILLATES AT 100 PERCENT ON GROUND. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001111600104	20011116	00104	SW  	2001	11	16	HEEA076983       	1	20011031	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										BOOST PUMP	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5007N					45184				LT BOOST PUMP FUEL PRESSURE DROPPED TO ZERO, LT BOOST PUMP LIGHT ILLUMINATED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600109	20011116	00109	NE  	2001	11	16	HEEA076984       	2	20011031	G	7320	324473514	FUEL CONTROL    			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	SURGES          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				ENGINE SURGING AT 100 PERCENT NR. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001111600111	20011116	00111	SW  	2001	11	16	HEEA076985       	1	20011031	G	2841	393008047	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736J					31140				UNIT READ ZERO. PENDING VENDOR REPAIR.						1	G	7	1 	4U			 	H4SW    					 
2001111600112	20011116	00112	SW  	2001	11	16	HEEA076986       	1	20011031	G	6710	412001300105	BELLCRANK       			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				BEARING WILL NOT ROTATE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600113	20011116	00113	SW  	2001	11	16	HEEA076987       	1	20011031	G	6220	412001900101	SUPPORT         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600115	20011116	00115	SW  	2001	11	16	HEEA076988       	1	20011031	G	6230	412010405109	LINK            			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T					33112				SPUN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600116	20011116	00116	SW  	2001	11	16	HEEA076989       	1	20011031	G	5260	412076620101	UNIVERSAL       			BELL  	412   	412         	1182202	SW  										STEPS	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5759N					33002				WORN BEARING. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600117	20011116	00117	SW  	2001	11	16	HEEA076990       	1	20011031	G	2400	51539002N	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										ELELCTRICAL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				WON'T HOLD PARALLEL VOLTAGE. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001111600119	20011116	00119	SW  	2001	11	16	HEEA076991       	1	20011031	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										GENERATOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				CAUSES GENERATOR TO KICK OFF LINE. PENDING VENDOR REPAIR.						1	G	7	2 	4U			 	H4SW    					 
2001111600120	20011116	00120		2001	11	16	HEEA076992       	4	20011031	G	3416	8503S20LW	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS LOW       	E			HEEA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				READS 125 FEET LOW. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600121	20011116	00121	SW  	2001	11	16	HEEA076993       	1	20011031	G	6321	94501031	BRAKE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				PUCKS WORN AND BROKEN MICRO SWITCH. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600123	20011116	00123		2001	11	16	HEEA076994       	4	20011031	G	2340	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				VOLUME KNOB SHAFT LOOSE. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600124	20011116	00124		2001	11	16	HEEA076995       	4	20011031	G	3442	MI5851352	RADAR           			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ANTENNA WOULD NOT SWEEP. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600125	20011116	00125		2001	11	16	HEEA076996       	4	20011031	G	3140	MI5852013	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				PICTURE PULSES AND TEST PATTERN IS BROKEN AND OFF COLOR. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600126	20011116	00126		2001	11	16	HEEA076997       	4	20011031	G	3140	MI585200	RADAR           			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				PILOT HSI CIRCUIT BREAKER POPS IN FLIGHT. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	4U			 	H4SW    					 
2001111600127	20011116	00127		2001	11	16	HEEA076998       	4	20011031	G	3140	MI5852013	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				SCREEN FLASHES ON THEN OFF WITH DISTORTED IMAGING. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	4U			 	H4SW    					 
2001111600130	20011116	00130		2001	11	16	HEEA076999       	4	20011031	G	3442	MI585202	RADAR           			BELL  	412   	412         	1182202	SW  										WX SYSTEM	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WEATHER RADAR HAS GAPS IN DISPLAY, FLUTTER WHILE SWEEPING.  FOUND WATER IN UNIT. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600132	20011116	00132	SW  	2001	11	16	HEEA077000       	1	20011031	G	6720		BUSHING         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				WORN BUSHINGS AND BEARINGS. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600133	20011116	00133	SW  	2001	11	16	HEEA077001       	1	20011031	G	2840	MS3108R14S5S	CONNECTOR       			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	SHORTED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22347					36005				FUEL VALVE LIGHT CAME ON. MAINTENANCE FOUND SHORTED CANNON PLUG AT NR 2 ENGINE LORI VALVE CAUSING FUEL VALVE TO CYCLE.						1	G	7	2 	4U			 	H4SW    					 
2001111600134	20011116	00134		2001	11	16	HEEA077002       	4	20011031	G	2200	212001139001	PIN             			BELL  	412   	412         	1182202	SW  										NR 2 ENGINE	LOOSE           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				COPILOT THROTTLE WOULD NOT CONTROL THE NR 2 ENGINE. MAINTENANCE FOUND PIN CONNECTING COPILOT THROTTLE GRIP TO SHAFT IN C	OLLECTIVE STICK TO HAD BACKED OUT.  REINSTALLED PIN.					1	G	7	2 	4U			 	H4SW    					 
2001111600137	20011116	00137		2001	11	16	HEEA077003       	4	20011031	G	3453	066402600	COMPUTER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				WILL NOT POWER UP. PENDING VENDOR REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001111600139	20011116	00139	SW  	2001	11	16	HEEA077004       	1	20011031	G	3246	206324007	SKID            			BELL  	206   	206L3       	1182108	SW  										MLG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31801					51074				BOTTOM OF SKID TUBE HAS A 20 INCH CRACK EXTENDING FROM BELOW WHEEL LUG AFT.  THERE ARE TWO ADDITIONAL CRACKS IN THE SAME	 AREA. PENDING VENDOR REPAIR.					1	G	7	1 	3U			 	H2SW    					 
2001111600140	20011116	00140	SW  	2001	11	16	HEEA077005       	1	20011031	G	2810	222366652003	FITTING         			BELL  	206   	206L3       	1182108	SW  										FUEL CELL	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81SP					51029				THREADS ON FITTING CORRODED. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H2SW    					 
2001111600162	20011116	00162		2001	11	16	HEEA077006       	4	20011031	G	2561	5018362071028	HARNESS         			BELL  	412   	412         	1182202	SW  										SAFETY EQUIP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				WORN. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	4U			 	H4SW    					 
2001111600163	20011116	00163	SW  	2001	11	16	HEEA077007       	1	20011031	G	2823	206063640109	VALVE           			BELL  	407   	407         	1182206	SW  										FUEL SHUT OFF	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				FUEL SHUT OFF VALVE MAKING GRINDING NOISE. REPLACED WITH SERVICEABLE VALVE.						1	G	7	1 	3U			O	H2SW    					 
2001111900001	20011119	00001	SW  	2001	11	19	HEEA077008       	1	20011031	G	2820	206063640109	VALVE           			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				INOPERATIVE - STUCK IN THE MID TRAVEL POSITION. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PAR	T PURCHASED.					1	G	7	1 	3U			O	H2SW    					 
2001111900002	20011119	00002	GL  	2001	11	19	HEEA077009       	2	20011031	G	7532	23005366	BLEED VALVE     			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				HIGH MGT. REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001111900004	20011119	00004	SW  	2001	11	19	HEEA077010       	1	20011031	G	7100	23069706	TUBE            			BELL  	407   	407         	1182206	SW  										ENGINE	WRONG PART      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				INCORRECT LINE. REPLACED WITH SERVICEABLE TUBE.						1	G	7	1 	3U			O	H2SW    					 
2001111900005	20011119	00005	SW  	2001	11	19	HEEA077011       	1	20011031	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				RED BLADE PITCH ROD UNIVERSAL BEARING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111900006	20011119	00006	SW  	2001	11	19	HEEA077012       	1	20011031	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					53390				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001111900007	20011119	00007	SW  	2001	11	19	HEEA077013       	1	20011031	G	6710	406310411101	BOOT            			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	TORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				BOOT TORN.						1	G	7	1 	3U			O	H2SW    					 
2001111900008	20011119	00008	SW  	2001	11	19	HEEA077014       	1	20011031	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				T/R P/C LINK WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001111900009	20011119	00009	SW  	2001	11	19	HEEA077015       	1	20011031	G	6720	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				T/R P/C LINK WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001111900010	20011119	00010	SW  	2001	11	19	HEEA077016       	1	20011031	G	6420	407012101111	HUB             			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				WORN FEATHERING BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2001111900012	20011119	00012	SW  	2001	11	19	HEEA077019       	1	20011031	G	2840	407375016103	SIGNAL COND UNIT			BELL  	407   	407         	1182206	SW  										FUEL INDICATION	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	495PH					53397				LOW LEVEL LIGHT ON WITH PLENTY OF FUEL ON BOARD.						1	G	7	1 	3U			O	H2SW    					 
2001111900013	20011119	00013	SW  	2001	11	19	HEEA077020       	1	20011031	G	6240	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				DUAL TACH INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001111900038	20011119	00038	SW  	2001	11	19	HEEA077022       	1	20011031	G	3340	4596	LAMP            			BELL  	407   	407         	1182206	SW  										EXTERIOR	BURNED OUT      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X					53267				BURNED OUT. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			O	H2SW    					 
2001111900040	20011119	00040	GL  	2001	11	19	HEEA077023       	2	20011031	G	7510	6899080B	VALVE           			BELL  	407   	407         	1182206	SW  	ALLSN 	250C  	250C47B     	 	GL  					ANTI ICE SYSTEM	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				ANTI ICE VALVE STICKS IN ON POSITION INTERMITTENTLY. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL				 
2001111900041	20011119	00041	SW  	2001	11	19	HEEA077024       	1	20011031	G	3210	70079H000Y150	HOSE            			BELL  	407   	407         	1182206	SW  										MLG	KINKED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	493PH					53393				HOSE ASSY KINKED.						1	G	7	1 	3U			O	H2SW    					 
2001111900042	20011119	00042	SW  	2001	11	19	HEEA077025       	1	20011031	G	6321	D01631	PAD             			BELL  	407   	407         	1182206	SW  										M/R BRAKE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				WORN PAD.						1	G	7	1 	3U			O	H2SW    					 
2001111900043	20011119	00043	SW  	2001	11	19	HEEA077026       	1	20011031	G	5320	D01661	BOLT            			BELL  	407   	407         	1182206	SW  										FUSELAGE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				GROOVED.						1	G	7	1 	3U			O	H2SW    					 
2001111900045	20011119	00045		2001	11	19	HEEA077027       	4	20011031	G	3120		LIGHT           			BELL  	407   	407         	1182206	SW  										COCKPIT CLOCK	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8595X	3053 				53267				INTERNAL LIGHT QUIT WORKING.						1	G	7	1 	3U			O	H2SW    					 
2001111900047	20011119	00047	SW  	2001	11	19	HEEA077028       	1	20011031	G	2800	P49389	RELEASE SYSTEM  			BELL  	407   	407         	1182206	SW  										VALVE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				FAILED INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2001111900053	20011119	00053	SW  	2001	11	19	HEEA077032       	1	20011101	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  											WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001111900055	20011119	00055	NE  	2001	11	19	HEEA077035       	2	20011101	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2	FAILED          	E			HEEA	O				OTHER                   				R	X	J	PARTIAL RPM/PWR LOSS      	ENGINE FLAMEOUT           	WARNING INDICATION        	CR	CRUISE         	1			SW	03	22347					36005				SHORTLY AFTER DEPARTURE, IN CRUISE, PILOT HEARD SQUEAL, BANG AND LOW RPM AUDIO.  NOTED NR 2 ENGINE FAILED. SECURED ENGIN	E AND COMPLETED FLIGHT WITH RUN ON LANDING.					1	G	7	2 	4U	4	U	 	H4SW    	E22EA				 
2001111900056	20011119	00056	SW  	2001	11	19	HEEA077036       	1	20011102	G	5302	214040617105	HANGER ASSY     			BELL  	214   	214ST       	1182106	SW  											MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	825H					28137				WILL NOT FIT IN SUPPORT ON AIRCRAFT.  HOLES MILLED IN WRONG AREA.						2	G	7	2 	4U			 	H10SW   					 
2001111900058	20011119	00058	SW  	2001	11	19	HEEA077037       	1	20011102	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DISENGAGES DURING STARTING WITH GOOD BATTERIES.						2	G	7	2 	4U			 	H10SW   					 
2001111900060	20011119	00060	SW  	2001	11	19	HEEA077038       	1	20011102	G	7120	206064107103	MOUNT           			BELL  	206   	206L3       	1182108	SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	623Q	292  								ENGINE MOUNT LEG WORN BEARING BEYOND LIMITS. SENT TO BELL HELICOPTER TEXTRON FOR WARRANTY CREDIT ON BEHALF OF CUSTOMER U	.S. WEST.  REFERENCE:  INVOICE AND DMR NO. 687181.					1	G	7	1 	3U			 	H2SW    					 
2001111900077	20011119	00077		2001	11	19	HEEA077039       	4	20011030	G	2350	066105571	AUDIO PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				COIL LOOSE MOUNT AND NOT CONNECTED TO BOARD. PENDING VENDOR REPAIR.						1	G	7	2 	3U			 	H3EU    					 
2001111900078	20011119	00078		2001	11	19	HEEA077040       	4	20011030	G	3454	071121612	CONTROL UNIT    			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				LED READ OUT ARE UNREADABLE ON DISPLAY. REPLACED WITH SERVICEABLE PART.						1	G	7	2 	3U			 	H3EU    					 
2001111900079	20011119	00079	EU  	2001	11	19	HEEA077041       	1	20011031	G	6321	350A32501000	LINER           		350A32050002	SNIAS 	350   	AS350B      	8680801	EU  										M/R BRAKE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	971AE				M918	3230				WORN LINING.						1	G	7	1 	3U			 	H9EU    					 
2001111900080	20011119	00080	EU  	2001	11	19	HEEA077042       	1	20011031	G	6720	350A33215001	BALL            		350A33200406	SNIAS 	350   	AS350B      	8680801	EU  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	972AE				MA1154	3234				WORN BALL. PENDING VENDOR RETURN FOR CREDIT.						1	G	7	1 	3U			 	H9EU    					 
2001111900081	20011119	00081		2001	11	19	HEEA077043       	4	20011031	G	3420	5050010902	GYRO            			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	856PH					3352				COMPASS CARD SPINS. REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U			 	H9EU    					 
2001111900082	20011119	00082	EU  	2001	11	19	HEEA077044       	1	20011031	G	6730	SC5083	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  										SERVO SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE	958  				3230				LEAKING PAST SHAFT SEAL. PENDING VENDOR RETURN.						1	G	7	1 	3U			 	H9EU    					 
2001111900083	20011119	00083	EU  	2001	11	19	HEEA077045       	1	20011031	G	2432	RG390E	BATTERY         			BOLKMS	117   	BK117A1     	5626010	EU  										MAIN	WEAK            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911RS					S670				WEAK. REPLACED BATTERY.						1	G	7	2 	3U			 	H13EU   					 
2001111900084	20011119	00084	EU  	2001	11	19	HEEA077046       	1	20011031	G	6730	1564T1005	ACTUATOR        			BOLKMS	117   	BK117A1     	5626010	EU  										NR 2 RPM	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911RS					S670				AFTER STARTING BOTH ENGINES, NR 2 RPM COULD NOT BE INCREASED OR DECREASED WITH BEEP SWITCH. REPLACED ACTUATOR.						1	G	7	2 	3U			 	H13EU   					 
2001120400169	20011204	00169	NE  	2001	12	4	HEEA077200       	1	20011106	G	6210		TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										M/R BLADE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342	16268				760096				UNABLE TO INSTALL TIP CAP, SCREW HOLES DO NOT LINE UP.						1	G	7	2 	3U			 	H1NE    					 
2001120400170	20011204	00170	NE  	2001	12	4	HEEA077201       	1	20011106	G	3297	PHIS761178002	HARNESS         			SKRSKY	S76   	S76A        	8143006	NE  										MLG	OUT OF ADJ      	E			HEEA	O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	03	911UK					760275				ON TAKE OFF UPON RETRACTING LANDING GEAR GOT AN UNSAFE FLIGHT. MAINTENANCE ADJUSTED THE NOSE CENTERING PROXIMITY SENSOR.						1	G	7	2 	3U			 	H1NE    					 
2001120400172	20011204	00172	SW  	2001	12	4	HEEA077204       	1	20011106	G	6322	PHIPBH40701	BLOWER          			BELL  	407   	407         	1182206	SW  										OIL COOLER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				FORWARD BEARING LOUD AND ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001120400174	20011204	00174	SW  	2001	12	4	HEEA077205       	1	20011106	G	7120	214031252141	SUPPORT         			BELL  	214   	214ST       	1182106	SW  										ENG MOUNT	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISIDENTIFIED.  SUPPORT RECEIVED WAS A RT SUPPORT; YET WAS MARKED FOR THE LT SUPPORT P/N.						2	G	7	2 	4U			 	H10SW   					 
2001120400177	20011204	00177	SW  	2001	12	4	HEEA077206       	1	20011106	G	7120	206064107103	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENG MOUNT	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISIDENTIFIED AND MISMANUFACTURED.						1	G	7	1 	3U			 	H2SW    					 
2001120400178	20011204	00178	SW  	2001	12	4	HEEA077207       	1	20011106	G	5302	206020113173S	CAP             			BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DENTED AND CRACKED AT LEADING EDGE.						1	G	7	1 	3U			 	H2SW    					 
2001120400179	20011204	00179	SW  	2001	12	4	HEEA077208       	1	20011107	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										WON'T STAY ENGAGED AT CROSS START.						2	G	7	2 	4U			 	H10SW   					 
2001120400180	20011204	00180	SW  	2001	12	4	HEEA077209       	1	20011107	G	6300	214040104001	ROLLER          			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PITTING ON ROLLERS.						2	G	7	2 	4U			 	H10SW   					 
2001120400183	20011204	00183	SW  	2001	12	4	HEEA077210       	1	20011109	G	3300	214175140103	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										LIGHTS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										POWER SUPPLY INOPERATIVE.						2	G	7	2 	4U			 	H10SW   					 
2001120400184	20011204	00184	SW  	2001	12	4	HEEA077211       	1	20011109	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	402PH	1157 				53159				FAILED 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW    					 
2001120400186	20011204	00186	SW  	2001	12	4	HEEA077212       	1	20011113	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENG MOUNT	MISMARKED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PARTS MISIDENTIFIED.						1	G	7	1 	3U			 	H2SW    					 
2001120400188	20011204	00188	SW  	2001	12	4	HEEA077213       	1	20011113	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	1790 			95171	53400				WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2001120400192	20011204	00192	SW  	2001	12	4	HEEA077214       	1	20011115	G	3300	214175140103	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										LIGHTS	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										POWER SUPPLY DEAD.						2	G	7	2 	4U			 	H10SW   					 
2001120400194	20011204	00194	SW  	2001	12	4	HEEA077215       	1	20011115	G	6520	214040404101	SHAFT           		214540001101	BELL  	214   	214ST       	1182106	SW  										T/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806	1711 			A26	28140				EXCESSIVE CORROSION AT TAIL ROTOR OUTPUT SHAFT DRIVE SPLINES.						2	G	7	2 	4U			 	H10SW   					 
2001120400200	20011204	00200	SW  	2001	12	4	HEEA077216       	1	20011115	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENG MOUNT	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISIDENTIFIED.  IT SHOULD BE 206-064-106-001.						1	G	7	1 	3U			 	H2SW    					 
2001120400220	20011204	00220	SW  	2001	12	4	HEEA077217       	1	20011115	G	6300	206010003007	CONE SET        			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MISMARKED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CONE SET MISIDENTIFIED.						1	G	7	1 	3U			 	H2SW    					 
2001120400221	20011204	00221	SW  	2001	12	4	HEEA077218       	1	20011116	G	6300	212010103007	FITTING         			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	GOUGED          	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										PART IS GOUGED ON TOP AND WAS NOT ACCEPTABLE PER OUR INSPECTORS.						1	G	7	1 	4U			 	H4SW    					 
2001120400223	20011204	00223	SW  	2001	12	4	HEEA077222       	1	20011120	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				WON'T INDICATE TORQUE.						1	G	7	1 	3U			O	H2SW    					 
2001120500001	20011205	00001	SW  	2001	12	5	HEEA077223       	1	20011120	G	6730	206076062105	SERVO           			BELL  	407   	407         	1182206	SW  										ROTOR SERVO	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	4730 				53159				SERVO IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001120500002	20011205	00002	SW  	2001	12	5	HEEA077228       	1	20011120	G	6220	407010150105A	FRAHM           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				FRAHM HAS A BROKEN SPRING.						1	G	7	1 	3U			O	H2SW    					 
2001120500003	20011205	00003	SW  	2001	12	5	HEEA077232       	1	20011120	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				BACK LIGHT INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001120500004	20011205	00004	SW  	2001	12	5	HEEA077233       	1	20011120	G	6510	407040302103	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				SPLINES WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW    					 
2001120500005	20011205	00005	SW  	2001	12	5	HEEA077235       	1	20011120	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				NR NEEDLE INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001120500006	20011205	00006	SW  	2001	12	5	HEEA077238       	1	20011120	G	7714	407375008101	INDICATOR       			BELL  	407   	407         	1182206	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TURBINE NEEDLE PEGGED TO THE HIGH.						1	G	7	1 	3U			O	H2SW    					 
2001120500011	20011205	00011	SW  	2001	12	5	HEEA077241       	1	20011121	G	6310	214040841101	SEAL            			BELL  	407   	407         	1182206	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				SEAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500012	20011205	00012	SW  	2001	12	5	HEEA077242       	1	20011121	G	6310	214040814105	SLEEVE          			BELL  	407   	407         	1182206	SW  										TRANSMISSION	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH					53390				SLEEVE WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500014	20011205	00014	SW  	2001	12	5	HEEA077243       	1	20011121	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH	1588 				53327				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500015	20011205	00015	SW  	2001	12	5	HEEA077244       	1	20011121	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH	908  				53401				WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500016	20011205	00016	SW  	2001	12	5	HEEA077245       	1	20011121	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH	908  				53401				UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500018	20011205	00018	SW  	2001	12	5	HEEA077246       	1	20011121	G	6710	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	501PH	908  				53401				WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500020	20011205	00020	SW  	2001	12	5	HEEA077247       	1	20011121	G	2910	70061J180W164A	HOSE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				CHAFED.						1	G	7	1 	3U			O	H2SW    					 
2001120500021	20011205	00021	SW  	2001	12	5	HEEA077248       	1	20011121	G	2910	70061J285W210A	HOSE            			BELL  	407   	407         	1182206	SW  										HYD SYSTEM	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				CHAFED.						1	G	7	1 	3U			O	H2SW    					 
2001120500033	20011205	00033	SW  	2001	12	5	HEEA077249       	1	20011121	G	2840	206362002103	ADAPTER         			BELL  	407   	407         	1182206	SW  										FUEL INDICATOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				FUEL INDICATOR ADAPTER IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500035	20011205	00035	SW  	2001	12	5	HEEA077250       	1	20011121	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				COOLER BLOWER HOUSING IS CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2001120500040	20011205	00040	SW  	2001	12	5	HEEA077251       	1	20011121	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	407   	407         	1182206	SW  										EXTERIOR LIGHTS	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	141MA					53016				FAULTY GROUND WIRE AT PLUG CAUSED UNIT TO FAIL.						1	G	7	1 	3U			O	H2SW    					 
2001120500041	20011205	00041	SW  	2001	12	5	HEEA077252       	1	20011121	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  											INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				INTERMITTENT.						1	G	7	1 	3U			O	H2SW    					 
2001120500043	20011205	00043	SW  	2001	12	5	HEEA077253       	1	20011121	G	2497	407375012103	WIRE            			BELL  	407   	407         	1182206	SW  										FADEC	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				CAUSING FADEC DEGRADE LIGHT.						1	G	7	1 	3U			O	H2SW    					 
2001120500044	20011205	00044	SW  	2001	12	5	HEEA077254       	1	20011121	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         	1182206	SW  										COCKPIT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				CAUSES IGNITION FAULT TO APPEAR SEVERAL TIMES.						1	G	7	1 	3U			O	H2SW    					 
2001120500046	20011205	00046	SW  	2001	12	5	HEEA077255       	1	20011121	G	2820	70079H000Y150	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	KINKED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH					53378				HOSE ASSY KINKED.						1	G	7	1 	3U			O	H2SW    					 
2001120500048	20011205	00048	SW  	2001	12	5	HEEA077256       	1	20011121	G	6340	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										TRANSMISSION OIL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				TRANSMISSION OIL PRESSURE LIGHT DOESN'T COME ON DURING SHUT DOWN.						1	G	7	1 	3U			O	H2SW    					 
2001120500049	20011205	00049	SW  	2001	12	5	HEEA077257       	1	20011121	G	7120	407060111101	MOUNT           			BELL  	407   	407         	1182206	SW  										ENGINE	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	417PH	4197 				53038				INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2001120500050	20011205	00050	SW  	2001	12	5	HEEA077258       	1	20011121	G	6320	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	OVERHEATED      	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				BEARING OVERHEATED						1	G	7	1 	3U			O	H2SW    					 
2001120500052	20011205	00052	SW  	2001	12	5	HEEA077259       	1	20011121	G	6710		BEARING         			BELL  	407   	407         	1182206	SW  										IDLER ASSY	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH				CT1279	53386				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2001120500053	20011205	00053	SW  	2001	12	5	HEEA077260       	1	20011121	G	2844	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										FUEL PRESSURE	STUCK           	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH					53114				STICKS IN CLOSED POSITION.						1	G	7	1 	3U			O	H2SW    					 
2001120500054	20011205	00054	SW  	2001	12	5	HEEA077261       	1	20011121	G	5210	206064819006S	DOOR            			BELL  	407   	407         	1182206	SW  										PAX/CREW	CORRODED        	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	723PH					53283				CORRODED AROUND BOTH LATCHES.						1	G	7	1 	3U			O	H2SW    					 
2001120500055	20011205	00055	SW  	2001	12	5	HEEA077262       	1	20011121	G	2820	70079H100F210	HOSE            			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				INSULATION CHAFED THROUGH.						1	G	7	1 	3U			O	H2SW    					 
2001120500056	20011205	00056	SW  	2001	12	5	HEEA077263       	1	20011121	G	3210	407040624101	TUBE            			BELL  	407   	407         	1182206	SW  										MLG	CHAFED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				TUBE ON MLG CHAFED.						1	G	7	1 	3U			O	H2SW    					 
2001120500057	20011205	00057		2001	12	5	HEEA077264       	4	20011121	G	2340	PM212302	SWITCH          			BELL  	407   	407         	1182206	SW  										COCKPIT	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				MIC SPRING TABS WORN.  REPORTED STICKING ICS.						1	G	7	1 	3U			O	H2SW    					 
2001120500058	20011205	00058	SW  	2001	12	5	HEEA077267       	1	20011121	G	6340	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										TRANSMISSION OIL	INTERMITTENT    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				INTERMITTENTLY STICKING.  LIGHT WILL NOT COME ON AFTER SHUTDOWN.						1	G	7	1 	3U			O	H2SW    					 
2001120500069	20011205	00069	SW  	2001	12	5	HEEA077269       	1	20011121	G	6321		PAD             			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	612PH					53199				WORN PADS,						1	G	7	1 	3U			O	H2SW    					 
2001120500070	20011205	00070	SW  	2001	12	5	HEEA077270       	1	20011121	G	3212	206050247131	COVER           			BELL  	407   	407         	1182206	SW  										MLG FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724PH					53327				COVER WORN.						1	G	7	1 	3U			O	H2SW    					 
2001120500071	20011205	00071	SW  	2001	12	5	HEEA077271       	1	20011121	G	6310	214040841101	SEAL            			BELL  	407   	407         	1182206	SW  										TRANSMISSION	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	722PH					53288				LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2001120500072	20011205	00072	SW  	2001	12	5	HEEA077272       	1	20011121	G	6400		BEARING         			BELL  	407   	407         	1182206	SW  										OIL COOLER SHAFT	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH					53400				OIL COOLER SHAFT BEARING FAILED.						1	G	7	1 	3U			O	H2SW    					 
2002011800081	20020118	00081	NE  	2002	1	18	HEEA077387       	2	20011203	G	7200		ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	505PH	2030 				760505	20529TEC			ENGINE WOULD NOT START.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2002011800082	20020118	00082	NE  	2002	1	18	HEEA077388       	1	20011204	G	6210	7615009100048A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	911MJ	12101				760231				UNABLE TO INSTALL TIP CAPS - TWO DIFFERENT TIP CAPS.  TIP CAP BLOCK HOLES APPEAR TO BE DRILLED 1/8 INCH TOO FAR FORWARD 	WHEN AFT SCREWS INSERTED.					1	G	7	2 	3U			 	H1NE    					 
2002011800083	20020118	00083	NE  	2002	1	18	HEEA077389       	1	20011204	G	6210	7615009100051A	RIB             			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR BLADE	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U	11828				760167				MAIN ROTOR BLADE TIP RIB UNBONDED.						1	G	7	2 	3U			 	H1NE    					 
2002011800084	20020118	00084	NE  	2002	1	18	HEEA077390       	1	20011204	G	6210		TAB             			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR BLADE	SPLIT           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S	7247 				760035				MAIN ROTOR BLADE TRIM TAB IS SPLIT OPEN NEAR THE TIP OF THE BLADE.						1	G	7	2 	3U			 	H1NE    					 
2002011800088	20020118	00088	NE  	2002	1	18	HEEA077391       	1	20011204	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S	7056 				760035				LAMINATE AT STA 44 ON THE LOWER SIDE IS SEPARATED. .						1	G	7	2 	3U			 	H1NE    					 
2002011800090	20020118	00090		2002	1	18	HEEA077392       	4	20011204	G	3420	501145301	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5435V					760158				VERTICAL GYRO PRECESSES.						1	G	7	2 	3U			 	H1NE    					 
2002011800091	20020118	00091		2002	1	18	HEEA077393       	4	20011204	G	3420	125780	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ADI	PRECESSES       	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5426U					760167				ADI PRECESSES HORIZONTALLY IN FLIGHT.						1	G	7	2 	3U			 	H1NE    					 
2002011800092	20020118	00092	NE  	2002	1	18	HEEA077394       	2	20011211	G	7261	9560134100	MAGNETIC SEAL   			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	974AE					2653				ENGINE MAGNETIC SEAL IS LEAKING.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011800093	20020118	00093	NE  	2002	1	18	HEEA077395       	2	20011211	G	7421	9550168760	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE					3230				ENGINE IGNITER WORN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011800094	20020118	00094	NE  	2002	1	18	HEEA077396       	2	20011211	G	7421	9550168760	IGNITER         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	971AE					3230				ENGINE IGNITER WORN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011800095	20020118	00095	EU  	2002	1	18	HEEA077397       	1	20011211	G	7170	0174078010	DRAIN VALVE     			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	4031L	3078 				2907				ENGINE DRAIN VALVE LEAKING FUEL AT PLUG.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002011800096	20020118	00096	SW  	2002	1	18	HEEA077401       	1	20011126	G	2435		BRUSHES         			BELL  	407   	407         	1182206	SW  										STARTER GEN	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH	2533 			98221	53003				STARTER GENERATOR HAS WORN BRUSHES.						1	G	7	1 	3U			O	H2SW    					 
2002011800099	20020118	00099		2002	1	18	HEEA077402       	4	20011127	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRIPS OFF WHEN CONTROL IS MOVED.						2	G	7	2 	4U			 	H10SW   					 
2002011800105	20020118	00105		2002	1	18	HEEA077403       	4	20011127	G	2210	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PITCH TRIPS AFTER 30 TO 45 MINUTES OF FLIGHT.  RESETS BUT ONLY FOR SHORT PERIOD OF TIME.						2	G	7	2 	4U			 	H10SW   					 
2002011800109	20020118	00109	SW  	2002	1	18	HEEA077404       	1	20011127	G	2730	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										ELEVATORS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR TRIPS OFF BOTH ELEVATOR SYSTEMS.						2	G	7	2 	4U			 	H10SW   					 
2002011800115	20020118	00115	SW  	2002	1	18	HEEA077428       	1	20011203	G	7120		BEARING         			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARING WORN PREMATURELY.						1	G	7	1 	3U			 	H2SW    					 
2002012200001	20020122	00001	SW  	2002	1	22	HEEA077429       	1	20011203	G	6300	206040320103	SHAFT           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										UNABLE TO BALANCE SHAFT.						1	G	7	1 	3U			 	H2SW    					 
2002012200002	20020122	00002	SW  	2002	1	22	HEEA077430       	1	20011203	G	6320	206040146103	GEAR            			BELL  	206   	206L3       	1182108	SW  										M/R GEARBOX	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										GEAR SERIAL NUMBER A-FS9423 AND A-FS9409 ARE IMPROPERLY MARKED WITH PART NUMBER 204-040-146-103.						1	G	7	1 	3U			 	H2SW    					 
2002012200003	20020122	00003	SW  	2002	1	22	HEEA077431       	1	20011203	G	3213	206323017	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CROSSTUBE HAS CORROSION.						1	G	7	1 	3U			 	H2SW    					 
2002012200004	20020122	00004	SW  	2002	1	22	HEEA077432       	1	20011203	G	3213	206323018	CROSSTUBE       			BELL  	206   	206L3       	1182108	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CROSSTUBE HAS CORROSION.						1	G	7	1 	3U			 	H2SW    					 
2002012200005	20020122	00005	SW  	2002	1	22	HEEA077433       	1	20011203	G	6320	214001373101	IDLER GEAR      			BELL  	214   	214ST       	1182106	SW  										NEW	MISSING         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BEARING MISSING WHEN PACKAGED PART WAS OPENED.						2	G	7	2 	4U			 	H10SW   					 
2002012200006	20020122	00006	SW  	2002	1	22	HEEA077434       	1	20011203	G	2913	222380009105	PUMP            			BELL  	430   	430         	1182150	SW  										NR 1 HYD SYSTEM	FAILED          	E			HEEA	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	03	430X	1638 				49058				DURING CLIMB OUT AFTER TAKEOFF, THE NR 1 HYDRAULIC SYSTEM FAILED. MAINTENANCE FOUND DRIVE SHAFT DISENGAGED FROM THE NR 1	 HYDRAULIC PUMP.  REPLACED PUMP.					1	G	7	2 	3U			RT	H9SW    					 
2002012200007	20020122	00007	SW  	2002	1	22	HEEA077435       	1	20011203	G	2497		WIRE            			BELL  	412   	412         	1182202	SW  										NR 1 GENERATOR	BROKEN          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	33008					36004				NR 1 GENERATOR FAILED. MAINTENANCE FOUND WIRE BROKEN AT TERMINAL "A" ON NR 1 GENERATOR.						1	G	7	2 	4U			 	H4SW    					 
2002012200008	20020122	00008	SW  	2002	1	22	HEEA077436       	1	20011206	G	7120	206064106101	LEG ASSY        			BELL  	206   	206L3       	1182108	SW  										ENGINE MOUNT	MISMARKED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PART NUMBER INCORRECT, PART MADE OF STEEL (MISIDENTIFIED) SHOULD BE 206064106001.						1	G	7	1 	3U			 	H2SW    					 
2002012200009	20020122	00009	SW  	2002	1	22	HEEA077437       	1	20011206	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STEP ACTUATOR WOULD NOT MOVE AT ALL.						1	G	7	2 	4U			 	H4SW    					 
2002012200010	20020122	00010	SW  	2002	1	22	HEEA077438       	1	20011206	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	378  				28102				STARTER WILL NOT STAY ENGAGED.						2	G	7	2 	4U			 	H10SW   					 
2002012200011	20020122	00011	SW  	2002	1	22	HEEA077439       	1	20011206	G	8011	214060056705	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806	241  				28140				STARTER STAYS STUCK IN THE ON POSITION.						2	G	7	2 	4U			 	H10SW   					 
2002012200012	20020122	00012	SW  	2002	1	22	HEEA077440       	1	20011206	G	6220	222310503101	BEARING         			BELL  	230   	230         	1182149	SW  										MAIN ROTOR HEAD	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARING HAS DELAMINATED ELASTOMER.						1	G	7	2 	3U			NC	H9SW    					 
2002012200013	20020122	00013	SW  	2002	1	22	HEEA077441       	1	20011206	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	457PH	2446 				53147				STARTER GENERATOR WILL NOT MOTOR OVER.						1	G	7	1 	3U			O	H2SW    					 
2002012200014	20020122	00014	SW  	2002	1	22	HEEA077442       	1	20011206	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	1182206	SW  										ENGINE	ARCED           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741PH	2258 				53457				STARTER GENERATOR IS ARCING.						1	G	7	1 	3U			O	H2SW    					 
2002012200015	20020122	00015	SW  	2002	1	22	HEEA077445       	1	20011210	G	2910		HYDRAULIC SYSTEM			BELL  	430   	430         	1182150	SW  										NR 1	MALFUNCTIONED   	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	430X					49058				ONE HOUR AND 10 MINUTES INTO THE FLIGHT THE SCAS KICKED OFF.  THE NR 1 HYDRAULIC SYSTEM PRESSURE FLUCTUATED BETWEEN 0 AN	D 130 PSI WITH RESITANCE IN THE TAIL ROTOR PEDALS.  DURING ENGINE COOL DOWN, TURNED NR 1 HYDRAULIC SYSTEM ON AND PRESSUR	E WAS STEADY AT 1430 PSI WITH NO RESISTANCE IN THE TAIL ROTOR PEDALS.  CLEANED ALL CONNECTORS IN HYDRAULIC SYSTEM AT BYP	ASS SOLENOID, PRESSURE SWITCHES, PRESSURE TRANSDUCERS AND SERVICED RESERVOIR.			1	G	7	2 	3U			RT	H9SW    					 
2002012200016	20020122	00016	SW  	2002	1	22	HEEA077446       	1	20011214	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	SLOW            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N	270  				28106				STARTER IS SLOW TO START.						2	G	7	2 	4U			 	H10SW   					 
2002012200017	20020122	00017	SW  	2002	1	22	HEEA077447       	1	20011214	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	WEAK            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3897N	36   				28106				STARTER IS WEAK.						2	G	7	2 	4U			 	H10SW   					 
2002012200018	20020122	00018	SW  	2002	1	22	HEEA077448       	1	20011214	G	8011	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T	431  				28101				STARTER WON'T STAY ENGAGED.						2	G	7	2 	4U			 	H10SW   					 
2002012200019	20020122	00019	EU  	2002	1	22	HEEA077449       	1	20011203	G	7931	ZRA25500	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  										ENG OIL PRESS	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	973AE					3229				ENGINE OIL PRESSURE HADN`T ANY INDICATION ON START FOR 3 SECONDS.						1	G	7	1 	3U			 	H9EU    					 
2002012200020	20020122	00020	EU  	2002	1	22	HEEA077450       	1	20011203	G	6310	350A35110500	GIMBAL JOINT    			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	855PH					3351				GIMBAL JOINT IS BROKEN.						1	G	7	1 	3U			 	H9EU    					 
2002012200021	20020122	00021	EU  	2002	1	22	HEEA077451       	1	20011203	G	7721	56375600010	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	856PH					3352				T4 INDICATOR WAS RECEIVED WITH RATTLE NOISE INSIDE.  DID NOT INSTALL ON AIRCRAFT.  WAS ISSUED AND RETIRED UNSERVICEABLE.	  SOUNDS LIKE LOOSE SCREW INSIDE.					1	G	7	1 	3U			 	H9EU    					 
2002012200022	20020122	00022		2002	1	22	HEEA077452       	4	20011203	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				CLOCK WILL NOT WIND UP.						1	G	7	1 	3U			 	H9EU    					 
2002012200023	20020122	00023	EU  	2002	1	22	HEEA077453       	1	20011203	G	6320	350A32310121	FRICTION RING   			SNIAS 	350   	AS350B      	8680801	EU  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	855PH					3351				FRICTION RING LEAKS.						1	G	7	1 	3U			 	H9EU    					 
2002012200024	20020122	00024	EU  	2002	1	22	HEEA077454       	1	20011203	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	855PH					3351				SERVO LEAKS.						1	G	7	1 	3U			 	H9EU    					 
2002012200025	20020122	00025	EU  	2002	1	22	HEEA077455       	1	20011203	G	7721	56375600010	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	856PH					3352				T4 INDICATOR NEEDLE STICKS INTERMITTENTLY AT 700 DURING START.						1	G	7	1 	3U			 	H9EU    					 
2002012200026	20020122	00026	EU  	2002	1	22	HEEA077456       	1	20011203	G	6710	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				SERVO LEAKING.						1	G	7	1 	3U			 	H9EU    					 
2002012200027	20020122	00027		2002	1	22	HEEA077458       	4	20011203	G	3160	350A67622202	INDICATOR       			SNIAS 	350   	AS350B      	8680801	EU  										PITOT HEAT	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	856PH					3352				PITOT HEAT LIGHT WOULD NOT GO OUT.						1	G	7	1 	3U			 	H9EU    					 
2002012200028	20020122	00028	EU  	2002	1	22	HEEA077459       	1	20011203	G	6230		PAINT           			SNIAS 	350   	AS350B      	8680801	EU  										M/R SHAFT	MISSING         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	974AE					2653				THE MAIN ROTOR SHAFT`S SPECIAL PAINT COAT MISSING.						1	G	7	1 	3U			 	H9EU    					 
2002012200029	20020122	00029	EU  	2002	1	22	HEEA077460       	1	20011203	G	6220	350A37112601	LINK            			SNIAS 	350   	AS350B      	8680801	EU  										MAIN ROTOR HEAD	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				SCISSOR LINKS HAS CORROSION.						1	G	7	1 	3U			 	H9EU    					 
2002012200030	20020122	00030	EU  	2002	1	22	HEEA077461       	1	20011203	G	6230	350A37100206	STAR            			SNIAS 	350   	AS350B      	8680801	EU  										SWASHPLATE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	974AE					2653				NON ROTATING STAR HAS CORROSION.						1	G	7	1 	3U			 	H9EU    					 
2002012200031	20020122	00031		2002	1	22	HEEA077462       	4	20011206	G	3416	150201182	ALTIMETER       			SNIAS 	350   	AS350B2     	8680813	EU  										NEW	DAMAGED         	E			HEEA	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	03										PART WAS RECEIVED AT PHI CLAIMING TO BE SERVICEABLE, MECHANIC CLAIMS GUAGE OFF.						1	G	7	1 	3U			 	H9EU    					 
2002012200032	20020122	00032		2002	1	22	HEEA077463       	4	20011206	G	3416	150201182	ALTIMETER       			SNIAS 	350   	AS350B      	8680801	EU  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	972AE					3234				ALTIMETER STICKS WHEN GOING UP AS MUCH AS 300 FEET.						1	G	7	1 	3U			 	H9EU    					 
2002012200033	20020122	00033	EU  	2002	1	22	HEEA077464       	1	20011211	G	6520	350A33214501	ROD END BEARING 			SNIAS 	350   	AS350B      	8680801	EU  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	855PH					3351				PITCH CONTROL ROD SPHERICAL BEARING WORN.						1	G	7	1 	3U			 	H9EU    					 
2002012200034	20020122	00034	GL  	2002	1	22	HEEA077550       	2	20011217	G	7260	23007248	GEARSHAFT       		23035179    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	SPALLED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1545X	339  			CAG95129	760050	CAE890508S			GEARSHAFT IN GEARBOX HAS SPALLING ON GEARTEETH.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002012200035	20020122	00035	GL  	2002	1	22	HEEA077551       	2	20011217	G	7260	23007151	BEARING         		23035179    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	SPALLED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1545X	339  			CAG95129	760050	CAE890508S			GEAR HAS SPALLING ON BALL BEARING.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL				 
2002012200036	20020122	00036	NE  	2002	1	22	HEEA077552       	2	20011220	G	7320	0164248690	FUEL CONTROL    			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    	 	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4034Q	1806 				2918				ENGINE SLOW START DURING COLD WEATHER.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2002012200042	20020122	00042	SW  	2002	1	22	HEEA077559       	1	20011217	G	3110	407375015103	WARN PANEL      			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	4999					53323				HYD. SYSTEM LIGHT FLASHING IN FLIGHT.						1	G	7	1 	3U			O	H2SW    					 
2002012200043	20020122	00043	SW  	2002	1	22	HEEA077560       	1	20011217	G	6240	412075010111	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										TRIPLE TACH	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6106C					36257				TRIPLE TACH NEEDLES FLUCTUATE.						1	G	7	2 	4U			 	H4SW    					 
2002012200044	20020122	00044	SW  	2002	1	22	HEEA077561       	1	20011217	G	6240	412075010111	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										TRIPLE TACH	FLUCTUATES      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6106C					36257				TRIPLE TACH NEEDLES FLUCTUATE.						1	G	7	2 	4U			 	H4SW    					 
2002012200045	20020122	00045	SW  	2002	1	22	HEEA077562       	1	20011217	G	2821	222366621103	FUEL FILTER     			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	DEFECTIVE       	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	493PH					53393				FUEL FILTER LIGHT ILLUMINATED.						1	G	7	1 	3U			O	H2SW    					 
2002012200056	20020122	00056	SW  	2002	1	22	HEEA077563       	1	20011217	G	7700	407375016103	SIGNAL COND UNIT			BELL  	407   	407         	1182206	SW  										ENGINE	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				SIGNAL CONDITIONING UNIT LOW LEVEL ON FULL FUEL.						1	G	7	1 	3U			O	H2SW    					 
2002012200071	20020122	00071	SW  	2002	1	22	HEEA077568       	1	20011217	G	6220		SPRING          			BELL  	407   	407         	1182206	SW  										FRAHM ASSY	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	742PH					53461				FRAHM ASSEMBLY HAS A BROKEN SPRING.						1	G	7	1 	3U			O	H2SW    					 
2002012200072	20020122	00072	SW  	2002	1	22	HEEA077569       	1	20011217	G	6320	407040006107	GEARBOX         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	3052 				53397				MAIN ROTOR GEARBOX MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2002012200073	20020122	00073	SW  	2002	1	22	HEEA077570       	1	20011217	G	6310	406040500131	FREEWHEEL UNIT  			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	741PH	1173 				53457				FREEWHEEL UNIT IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002012200075	20020122	00075	SW  	2002	1	22	HEEA077572       	1	20011217	G	6310	406040500127	FREEWHEEL UNIT  			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH	1405 				53397				FREEWHEEL UNIT IS MAKING METAL.						1	G	7	1 	3U			O	H2SW    					 
2002012200077	20020122	00077	SW  	2002	1	22	HEEA077575       	1	20011217	G	6510	407040302107	DRIVE SHAFT     			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	PEELING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH	967  				53401				PAINT PEELING OFF TAIL ROTOR DRIVE SHAFT.						1	G	7	1 	3U			O	H2SW    					 
2002012200078	20020122	00078	SW  	2002	1	22	HEEA077576       	1	20011217	G	7714	407375002103	INDICATOR       			BELL  	407   	407         	1182206	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	491PH					53386				NG INDICATOR SHOWS EXCEEDANCE, CANNOT CLEAR.						1	G	7	1 	3U			O	H2SW    					 
2002012200080	20020122	00080	SW  	2002	1	22	HEEA077577       	1	20011217	G	6220		SPRING          			BELL  	407   	407         	1182206	SW  										FRAHM ASSY	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH				A630	53393				FRAHM ASSY HAS BROKEN SPRING.						1	G	7	1 	3U			O	H2SW    					 
2002012200081	20020122	00081	SW  	2002	1	22	HEEA077578       	1	20011217	G	7712	407375003107	INDICATOR       			BELL  	407   	407         	1182206	SW  										TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	406PH					53198				TORQUE INDICATOR HAS DIM LIGHTING.						1	G	7	1 	3U			O	H2SW    					 
2002012200084	20020122	00084		2002	1	22	HEEA077580       	4	20011217	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										CAUSES ELEVATOR TO TRIP OFF LINE.						2	G	7	2 	4U			 	H10SW   					 
2002012200087	20020122	00087	SW  	2002	1	22	HEEA077583       	1	20011218	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										BOOST PUMP	FAILED          	E			HEEA	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	402PH					53159				BOOST PUMP LIGHT WILL NOT COME ON WHEN PUMP OFF.						1	G	7	1 	3U			O	H2SW    					 
2002012200091	20020122	00091	SW  	2002	1	22	HEEA077584       	1	20011218	G	6322	407062021101	DUCT            			BELL  	407   	407         	1182206	SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				OIL COOLER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002012200124	20020122	00124	SW  	2002	1	22	HEEA077585       	1	20011218	G	6300	407340339103	BEARING         		PHIPBH40701 	BELL  	407   	407         	1182206	SW  										COOLER BLOWER	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH				PHI0025	53209				WORN BEARING.						1	G	7	1 	3U			O	H2SW    					 
2002012200127	20020122	00127	SW  	2002	1	22	HEEA077586       	1	20011218	G	3212	212073905001	GAUGE           			BELL  	407   	407         	1182206	SW  										FLOAT PRESSURE	CONTAMINATED    	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4999					53323				PRESSURE GAUGE IS FULL OF MOISTURE.						1	G	7	1 	3U			O	H2SW    					 
2002012200128	20020122	00128	SW  	2002	1	22	HEEA077587       	1	20011218	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH					53114				FLOAT COVER IS BADLY WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012200130	20020122	00130	SW  	2002	1	22	HEEA077589       	1	20011218	G	3212	8226003	FUSEABLE PLUG   			BELL  	407   	407         	1182206	SW  										FLOAT	LEAKING         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				FLOAT BOTTLE FUSABLE PLUG IS LEAKING.						1	G	7	1 	3U			O	H2SW    					 
2002012200131	20020122	00131	SW  	2002	1	22	HEEA077590       	1	20011218	G	6321	206076047101	CYLINDER        			BELL  	407   	407         	1182206	SW  										ROTOR BRAKE	LEAKING         	E			HEEA	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	490PH					53378				CYLINDER LEAKING FROM PISTON SEAL.						1	G	7	1 	3U			O	H2SW    					 
2002012200132	20020122	00132	SW  	2002	1	22	HEEA077592       	1	20011218	G	6320	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH					53378				RIVETS WORKING.						1	G	7	1 	3U			O	H2SW    					 
2002012200133	20020122	00133	SW  	2002	1	22	HEEA077593       	1	20011218	G	6340	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										XMSN OIL	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	491PH					53386				TRANSMISSION OIL PRESSURE CAUTION LIGHT CAME ON.						1	G	7	1 	3U			O	H2SW    					 
2002012200134	20020122	00134	SW  	2002	1	22	HEEA077594       	1	20011218	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	447PH					53114				FAILED OPERATIONAL TEST (RAN HOT ABOVE 270 F.)						1	G	7	1 	3U			O	H2SW    					 
2002012200135	20020122	00135	SW  	2002	1	22	HEEA077595       	1	20011218	G	6420	406312103101	LINK            			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	721PH					53278				TAIL ROTOR LINK WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012200136	20020122	00136	SW  	2002	1	22	HEEA077596       	1	20011218	G	6330	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										TRANSMISSION	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				TRANSMISSION MOUNT RUBBER BAD.						1	G	7	1 	3U			O	H2SW    					 
2002012200137	20020122	00137	SW  	2002	1	22	HEEA077598       	1	20011218	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	499PH	1198 				53400				MAIN ROTOR DRIVE UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012200139	20020122	00139	SW  	2002	1	22	HEEA077600       	1	20011218	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										ENGINE	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH					53398				PRESSURE SWITCH FAILED.						1	G	7	1 	3U			O	H2SW    					 
2002012200147	20020122	00147	SW  	2002	1	22	HEEA077601       	1	20011218	G	6720	406312103101	PITCH LINK      			BELL  	407   	407         	1182206	SW  										TAIL ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	510PH					53209				PITCH LINK WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012200148	20020122	00148	SW  	2002	1	22	HEEA077602       	1	20011218	G	6320	407310203101	MOUNT           			BELL  	407   	407         	1182206	SW  										TRANSMISSION	CRACKED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	494PH					53396				TRANSMISSION MOUNT CRACKED RUBBER.						1	G	7	1 	3U			O	H2SW    					 
2002012200149	20020122	00149	SW  	2002	1	22	HEEA077603       	1	20011218	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE METER	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				TORQUE SPIKE TO 134.1 PERCENT FOR ONE SECOND.						1	G	7	1 	3U			O	H2SW    					 
2002012200150	20020122	00150	SW  	2002	1	22	HEEA077604       	1	20011218	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										T/R HUB	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	496PH				53006	53398				WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.  REFERENCE:  DMR#73147302.  LABOR C	REDIT ACCOMPLISHED ON J0194971-WA (INVOICE AND DMR NO. 687199).					1	G	7	1 	3U			O	H2SW    					 
2002012200151	20020122	00151	SW  	2002	1	22	HEEA077607       	1	20011218	G	6710	406010425107	LEVER           			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	498PH	2031 				53399				LEVER ASSY HAS WORN BUSHINGS.						1	G	7	1 	3U			O	H2SW    					 
2002012300001	20020123	00001	SW  	2002	1	23	HEEA077608       	1	20011218	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										TAIL ROTOR HUB	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	492PH				53246	53390				TAIL ROTOR HUB BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300092	20020123	00092	SW  	2002	1	23	HEEA077609       	1	20011218	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										BELLCRANK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				TAIL ROTOR BELLCRANK BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300002	20020123	00002	SW  	2002	1	23	HEEA077610       	1	20011218	G	6510		BEARING         			BELL  	407   	407         	1182206	SW  										BELLCRANK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH					53159				TAIL ROTOR BELLCRANK BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300003	20020123	00003	SW  	2002	1	23	HEEA077611       	1	20011218	G	6300		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH LINK	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	402PH				AF6463	53159				BEARING WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300004	20020123	00004	SW  	2002	1	23	HEEA077612       	1	20011218	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	490PH					53378				MAIN ROTOR DRIVE UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300005	20020123	00005	SW  	2002	1	23	HEEA077613       	1	20011218	G	6321	206076047101	CYLINDER        			BELL  	407   	407         	1182206	SW  										MAIN ROTOR BRAKE	DAMAGED         	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	495PH					53397				MAIN ROTOR BRAKE CYLINDER HANDLE HARD TO OPERATE.						1	G	7	1 	3U			O	H2SW    					 
2002012300006	20020123	00006	SW  	2002	1	23	HEEA077614       	1	20011218	G	2822	1C2710	CARTRIDGE       			BELL  	407   	407         	1182206	SW  										FUEL PUMP	INOPERATIVE     	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH					53266				FUEL PUMP CARTRIDGE INOPERATIVE.						1	G	7	1 	3U			O	H2SW    					 
2002012300007	20020123	00007	SW  	2002	1	23	HEEA077615       	1	20011219	G	6320	214040806003	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	499PH					53400				WOULD NOT TURN ON TRANSMISSION LIGHT AFTER SHUTDOWN.						1	G	7	1 	3U			O	H2SW    					 
2002012300008	20020123	00008	SW  	2002	1	23	HEEA077616       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	2367 				53396				MAIN ROTOR DRIVE UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300009	20020123	00009	SW  	2002	1	23	HEEA077617       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	671  				53396				MAIN ROTOR DRIVE UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300010	20020123	00010	SW  	2002	1	23	HEEA077618       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	1150 				53396				MAIN ROTOR DRIVE UNIVERAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300011	20020123	00011	SW  	2002	1	23	HEEA077619       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	494PH	2201 				53396				MAIN ROTOR DRIVE UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300012	20020123	00012	SW  	2002	1	23	HEEA077620       	1	20011219	G	6322	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH					53393				COOLER BLOWER HOUSING HAS WORKING RIVETS.						1	G	7	1 	3U			O	H2SW    					 
2002012300013	20020123	00013	SW  	2002	1	23	HEEA077621       	1	20011219	G	2840	407362005103	SWITCH          			BELL  	407   	407         	1182206	SW  										FUEL SYSTEM	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				SWITCH STICKING, INACCURATE READINGS TO GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2002012300014	20020123	00014	SW  	2002	1	23	HEEA077622       	1	20011219	G	6420	406312100101	BEARING         		407012101111	BELL  	407   	407         	1182206	SW  										TAIL ROTOR HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	493PH				53400	53393				TAIL ROTOR HUB BEARING IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300015	20020123	00015	SW  	2002	1	23	HEEA077623       	1	20011219	G	7712	222375077119	TRANSMITTER     			BELL  	407   	407         	1182206	SW  										TORQUE INDICATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				CEASED SENDING PRESSURE SIGNAL TO TORQUE GAUGE.						1	G	7	1 	3U			O	H2SW    					 
2002012300016	20020123	00016	SW  	2002	1	23	HEEA077624       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	916  				53435				MAIN ROTOR DRIVE UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300017	20020123	00017	SW  	2002	1	23	HEEA077625       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	740PH	916  				53435				MAIN ROTOR DRIVE UNIVERSAL IS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300018	20020123	00018	SW  	2002	1	23	HEEA077626       	1	20011219	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	491PH					53386				RIGHT FUEL BOOST PUMP LIGHT DOES NOT COME ON WHEN CIRCUIT BREAKER SWITCH IS TURNED OFF.						1	G	7	1 	3U			O	H2SW    					 
2002012300019	20020123	00019	SW  	2002	1	23	HEEA077627       	1	20011219	G	2510	407370720101	SEAT BELT       			BELL  	407   	407         	1182206	SW  										COCKPIT	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				SEAT BELT HAS FRAYED ENDS.						1	G	7	1 	3U			O	H2SW    					 
2002012300095	20020123	00095	SW  	2002	1	23	HEEA077628       	1	20011219	G	6300	406012129101	PITCH LINK      			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				PITCH LINK BEARING WORN ON RIVET SIDE.						1	G	7	1 	3U			O	H2SW    					 
2002012300097	20020123	00097	SW  	2002	1	23	HEEA077629       	1	20011219	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	492PH					53390				GREASE TURNING DARK GREY.  BEARING ROUGH.						1	G	7	1 	3U			O	H2SW    					 
2002012300099	20020123	00099	SW  	2002	1	23	HEEA077630       	1	20011219	G	6300	407340339101	BEARING         			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	OVERHEATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				MAIN ROTOR BEARING RUNNING HOT.  LABEL TURNED BLACK.						1	G	7	1 	3U			O	H2SW    					 
2002012300100	20020123	00100	SW  	2002	1	23	HEEA077631       	1	20011219	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501PH					53401				BLOWER HOUSING CRACKED AT LEFT HAND CORNER.						1	G	7	1 	3U			O	H2SW    					 
2002012300101	20020123	00101	SW  	2002	1	23	HEEA077632       	1	20011219	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         	1182206	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	495PH					53397				LIGHT WILL NOT COME ON.						1	G	7	1 	3U			O	H2SW    					 
2002012300102	20020123	00102	SW  	2002	1	23	HEEA077634       	1	20011219	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         	1182206	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	490PH	1910 				53378				MAIN ROTOR UNIVERSAL WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300103	20020123	00103	SW  	2002	1	23	HEEA077635       	1	20011219	G	6510	206061432121	HOUSING         			BELL  	407   	407         	1182206	SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				COOLER BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW    					 
2002012300104	20020123	00104	SW  	2002	1	23	HEEA077638       	1	20011219	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	499PH					53400				BEARINGS WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300105	20020123	00105	SW  	2002	1	23	HEEA077640       	1	20011219	G	6420		BEARING         			BELL  	407   	407         	1182206	SW  										PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	496PH					53398				PITCH LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW    					 
2002012300106	20020123	00106	SW  	2002	1	23	HEEA077641       	1	20011219	G	3212	206050247138	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300107	20020123	00107	SW  	2002	1	23	HEEA077642       	1	20011219	G	3212	206050247137	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				FLOAT COVER END CAP WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300108	20020123	00108	SW  	2002	1	23	HEEA077643       	1	20011219	G	3212	206050247132	COVER           			BELL  	407   	407         	1182206	SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	491PH					53386				FLOAT COVER ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2002012300109	20020123	00109	SW  	2002	1	23	HEEA077644       	1	20011219	G	6420	406012129101	LINK            			BELL  	407   	407         	1182206	SW  										PITCH LINK ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PITCH LINK ASSY WORN.						1	G	7	1 	3U			O	H2SW    					 
2002060600082	20020606	00082	SW  	2002	6	6	HEEA079393       	1	20010910	G	7740	DPUA0101	COMPUTER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				INTELLISTART LIGHT STAYS ON, COULDN'T ACCESS WITH MLP. SENT TO ALTAIR AVIONICS CORP. FOR INSPECTION AND REPAIR.						1	G	7	1 	3U			 	H2SW    					 
2001041900195	20010419	00195		2001	4	19	HEED072193       	4	20010314	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	ERRATIC         	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	278X					760440				ERRATIC OPERATION WHEN CYCLIC ISMOVED TO THE RIGHT OF CENTER. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900218	20010419	00218	SW  	2001	4	19	HEED072195       	1	20010314	G	2435	206062200113	STARTER GEN     			BELL  	407   	407         	       	SW  										ENGINE	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3193E					53276				PILOT INFLIGHT HEARD BANG IN HEADSET FOLLOWED BY SERVERE STATIC IN HEADSET. GENERATOR VOLTAGE METER STARTED DROPPING FRO	M 28 VOLTS UP ON LANDING. REPLACED UNIT.					1	G	7	1 	3U			O	H2SW    					 
2001041900219	20010419	00219		2001	4	19	HEED072198       	4	20010314	G	3416	06603640005	ENCODER         			BELL  	407   	407         	       	SW  										ALTIMETER	MALFUNCTIONED   	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3193E					53276				UNRELIABLE SIGNAL RYAN TCAD DISPLAYS STARS CODE. PART WAS BAD FROM STOCK.  MODE C SIGNAL WAS 22,000 FT (SHOULD HAVE BEEN	 1,000 FT) REPLACED UNIT.					1	G	7	1 	3U			O	H2SW    					 
2001041900196	20010419	00196		2001	4	19	HEED072200       	4	20010314	G	3454	066107810	RECEIVER        			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INOPERATIVE     	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				DOES NOT DRIVE NR 1 POINTER ON HSI PILOTS OR COPILOTS. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900197	20010419	00197		2001	4	19	HEED072201       	4	20010314	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				INTERMITTANT LOSS OF HEADSET SIDETONE. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900198	20010419	00198	NE  	2001	4	19	HEED072202       	1	20010314	G	7920	0292105230	PUMP            			SKRSKY	S76   	S76C        	8143008	NE  										OIL SYSTEM	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				OIL DRAINS BACK INTO ACCESSORY GEARBOX AFTER SHUTDOWN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900199	20010419	00199	NE  	2001	4	19	HEED072203       	2	20010314	G	7421	9550166670	IGNITER         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	WEAK            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				WEAK- WILL NOT START AIRCRAFT. FOUND BAD ON 150 HOURS INSPECTION. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001041900200	20010419	00200	NE  	2001	4	19	HEED072204       	2	20010314	G	7210	9560134100	MAGNETIC SEAL   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	LEAKING         	E			HEED	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	476X					760436				THIS SEAL LEAKED SINCE THE ENGINE 15529 WAS INSTALLED ON 9/7/2000 AT ATT: 4867.15 REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001041900201	20010419	00201		2001	4	19	HEED072205       	4	20010314	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	478X					760493				BOX CUTS OUT IN ICS. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900202	20010419	00202		2001	4	19	HEED072206       	4	20010314	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	478X					760493				INTERMITTLY INOPERATIVE COMPLETELY IN ALL SWITCH POSITIONS. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900203	20010419	00203		2001	4	19	HEED072207       	4	20010314	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	MALFUNCTIONED   	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	278X					760440				THIDS ICS BOX WAS JUST RETURNED FROM REPAIR FOR THE SAME THING-BLEED OVER ON VHF''''S AND NAV''''S. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900204	20010419	00204	NE  	2001	4	19	HEED072208       	1	20010314	G	2910	7665009801104	MODULE          			SKRSKY	S76   	S76C        	8143008	NE  										HYD SYSTEM	MALFUNCTIONED   	E			HEED	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03	478X					760493				HYD MODULE CAUSES INTERMITT 32 SYSTEM SERVO LITE. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900205	20010419	00205	NE  	2001	4	19	HEED072211       	1	20010314	G	6210	7615009100053	BLADE           			SKRSKY	S76   	S76C        	8143008	NE  										MAIN ROTOR	CRACKED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X					760436				SUSPECT CRACKING OF MAIN ROTOR SPAR. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900206	20010419	00206	NE  	2001	4	19	HEED072212       	2	20010314	G	7421	9550166670	IGNITER         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	ERODED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				ERODED CENTER ELECTRODE. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001041900207	20010419	00207	NE  	2001	4	19	HEED072213       	2	20010314	G	7261	0292105230	PUMP            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					OIL SYSTEM	FLUCTUATES      	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436	15529TEC			FLUCTUATING OIL PRESSURE . REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001041900208	20010419	00208	NE  	2001	4	19	HEED072214       	1	20010314	G	2437	50284003	PANEL           			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	WILL NOT TEST   	E			HEED	O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			SW	03	476X					760436				BATTERY FEED FAULT WILL NOT TEST PROPERLY. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900209	20010419	00209		2001	4	19	HEED072215       	4	20010314	G	3457	8144002241D	GPS             			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	MALFUNCTIONED   	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	476X					760436				COPILOT HSI NEEDLE WILL NOT POINT TO LRN HEADING, SYSTEM WENT OFFLINE AND LOST. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900210	20010419	00210	NE  	2001	4	19	HEED072216       	2	20010314	G	7200	1S1	ENGINE          			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE BAY	MAKING METAL    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				GENERATING METAL AT THE ACCESSORY MAG PLUG. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001041900211	20010419	00211	NE  	2001	4	19	HEED072218       	1	20010315	G	6220	SB5080102	ROD END BEARING 			SKRSKY	S76   	S76C        	8143008	NE  										MAIN ROTOR	WORN            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				BEARING WORN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900212	20010419	00212		2001	4	19	HEED072220       	4	20010315	G	2300	A30161ACYR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	278X					760440				ICS BOX INTERMITTENT OPERATION IN ALL CHANNELS. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900213	20010419	00213	NE  	2001	4	19	HEED072221       	1	20010315	G	7922	8A308203	THERMOSTAT      			SKRSKY	S76   	S76C        	8143008	NE  										OIL TEMP	MALFUNCTIONED   	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				CAUSING HIGH OIL TEMPERATURE.  LOCALLY SCRAPPED. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001042000079	20010420	00079	NE  	2001	4	20	HEED072223       	1	20010315	G	3246	50075551	WHEEL           			SKRSKY	S76   	S76C        	8143008	NE  										NLG	WORN            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				LININGS P/N 50007665, WORN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900214	20010419	00214		2001	4	19	HEED072224       	4	20010315	G	2300	A30161ACR	MIXER BOX       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				CUTS OUT ALL STATIONS DURING TRANSMITTION AND RECEPTION. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900215	20010419	00215	NE  	2001	4	19	HEED072225       	1	20010315	G	3246	50075551	WHEEL           			SKRSKY	S76   	S76C        	8143008	NE  										NLG	WORN            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				LININGS ARE WORN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900220	20010419	00220	SW  	2001	4	19	HEED072226       	1	20010315	G	2841	407375006101	INDICATOR       			BELL  	407   	407         	       	SW  										FUEL QUANITY	INOPERATIVE     	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3193E					53276				DISPLAY, BLANK, NO NUMBER ON BARS SHOWING. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001041900221	20010419	00221	SW  	2001	4	19	HEED072233       	1	20010315	G	3244	028630	TIRE            			BELL  	430   	430         	1182150	SW  										MLG	WORN            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	430X	857  				49058				EXCESSIVE WEAR. REPLACED UNIT.						1	G	7	2 	3U			RT	H9SW    					 
2001041900216	20010419	00216	NE  	2001	4	19	HEED072251       	1	20010316	G	3610	7650007903102	SHUTOFF VALVE   			SKRSKY	S76   	S76C        	8143008	NE  										BLEED AIR	LEAKING         	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				LEAKING WILL NOT SHUT OFF. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001041900217	20010419	00217	NE  	2001	4	19	HEED072254       	2	20010316	G	7210	9560115450	MAGNETIC SEAL   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	LEAKING         	E			HEED	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	476X					760436				THIS SEAL LEAKED SINCE THE ENGINE S/N 15529 WAS INSTALLED ON 9/7/2000. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080700338	20010807	00338		2001	8	7	HEED073491       	4	20010614	G	2350	A30161ACVR	ICS BOX         			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	478X	61   				760493				INTERMITTENTLY TRANSMISSION ON ALL CHANNELS. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700339	20010807	00339	NE  	2001	8	7	HEED073492       	1	20010614	G	3340	3012543	LIGHT           			SKRSKY	S76   	S76C        	8143008	NE  										STROBE	BURNED OUT      	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X					760493				FLASH TUBE BURNED OUT.  SCRAPPED REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700340	20010807	00340	NE  	2001	8	7	HEED073493       	1	20010614	G	7714	H190110	INDICATOR       			SKRSKY	S76   	S76C        	8143008	NE  										ENGINE N1	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X					760493				PIECES OF LED SECTIONS MISSING IN NUMBER DISPLAY. BURNED OUT. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700341	20010807	00341	NE  	2001	8	7	HEED073494       	1	20010614	G	2432	RG380E44	BATTERY         			SKRSKY	S76   	S76C        	8143008	NE  										MAIN	DISCHARGED      	E			HEED	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	478X					760493				WOULD CRANK AIRCRAFT ENGINES TO START BATTERY DEAD. VERY WEAK ON FIRST START OFTHE DAY. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700344	20010807	00344	NE  	2001	8	7	HEED073495       	1	20010614	G	3110		SCREW           			SKRSKY	S76   	S76C        	8143008	NE  										AHRS	BROKEN          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X	3507 			1005	760436				J2 PLUG ATTACHMENT SCREW IS BROKEN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700346	20010807	00346	NE  	2001	8	7	HEED073496       	1	20010614	G	5320	9550147560	FITTING         			SKRSKY	S76   	S76C        	8143008	NE  										THREADS	CORRODED        	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X					760436				INTERNAL THREADS FOR BANJO FITTING ARE CORRODED. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700347	20010807	00347	NE  	2001	8	7	HEED073497       	2	20010614	G	7321	0164348810	FUEL CONTROL    			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	MALFUNCTIONED   	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X					760436				N2 LAGS CREATING A 20 PERCENT TORQUE SPLIT. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080700351	20010807	00351	NE  	2001	8	7	HEED073498       	2	20010614	G	7261		CHECK VALVE     			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					OIL PUMP	STUCK           	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X				722SO	760436				CHECK VALVE STICKING. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080700353	20010807	00353	NE  	2001	8	7	HEED073499       	1	20010614	G	2560	110175601	SEAT BELT       			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	476X	5687 				760436				WORN SEAT BELT. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700355	20010807	00355		2001	8	7	HEED073500       	4	20010614	G	2210		BEARING         			SKRSKY	S76   	S76C        	8143008	NE  										AFCS ACTUATOR	WORN            	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				PIVOT BEARINGS WORN. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700357	20010807	00357		2001	8	7	HEED073501       	4	20010614	G	2312	071128265	CONTROL HEAD    			SKRSKY	S76   	S76C        	8143008	NE  										VHF SYSTEM	MALFUNCTIONED   	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				TURNS ITSELF OFF AFTER 2 OR 3 MINUTES. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700359	20010807	00359		2001	8	7	HEED073502       	4	20010614	G	2350	A30161ACVR	ICS BOX         			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	NOISY           	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				LOUD NOISE IN MIC. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700361	20010807	00361		2001	8	7	HEED073503       	4	20010614	G	2350	A30161ACVR	ICS BOX         			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				COPILOT HEADSET FREQUENTLY CUTS OUT.  BAD FROM STOCK. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700363	20010807	00363		2001	8	7	HEED073504       	4	20010614	G	2350	A30161ACVR	ICS BOX         			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	89H					760406				COPILOT HEADSET FREQUENTLY CUTS OUT.  BAD FROM STOCK. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700365	20010807	00365		2001	8	7	HEED073505       	4	20010614	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	CHATTERING      	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	478X					760493				CHATTERING. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700366	20010807	00366	NE  	2001	8	7	HEED073506       	2	20010614	G	7200	70BMA01040	CONTROL UNIT    			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S1   	60030	NE  					ENGINE	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	478X	2968 				760493	20063			NR 1 ENGINE RUN UP FAULT. REPLACED UNIT.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU				 
2001080700367	20010807	00367		2001	8	7	HEED073507       	4	20010614	G	2370	D5152010112	CVR             			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT	WILL NOT TEST   	E			HEED	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	478X					760493				FDR WILL NOT TEST. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700368	20010807	00368		2001	8	7	HEED073508       	4	20010614	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	INTERMITTENT    	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	478X					760493				KICKING INTERMITTLY. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700396	20010807	00396		2001	8	7	HEED073511       	4	20010614	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	CHATTERING      	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	278X					760440				CHATTERING, ROUGH IN TRAVEL, STICKING. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700398	20010807	00398	NE  	2001	8	7	HEED073512       	1	20010614	G	3240		BRAKE           			SKRSKY	S76   	S76C        	8143008	NE  										NLG	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	278X					760440				WORN BRAKES. S/NOS: DEC-82-217, AND NOV-3-467. REPLACED UNIT. S/NOS: JAN 80-286, AND MAR 84-677.						1	G	7	2 	3U			NC	H1NE    					 
2001080700399	20010807	00399		2001	8	7	HEED073513       	4	20010614	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76C        	8143008	NE  										AFCS	CHATTERING      	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	278X					760440				JUMPING, CHATTERING. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700401	20010807	00401	NE  	2001	8	7	HEED073514       	1	20010614	G	3230	4608	PRIORITY VALVE  			SKRSKY	S76   	S76C        	8143008	NE  										MLG	FAULTY          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	278X	5007 				760440				IRREGULAR PRESSURE CAUSES RANGING GEAR TO RETRACT UNEVENLY. REPLACED UNIT.						1	G	7	2 	3U			NC	H1NE    					 
2001080700403	20010807	00403	SW  	2001	8	7	HEED073543       	1	20010614	G	3260	222336001105	ACTUATOR        			BELL  	430   	430         	1182150	SW  										DOWNLOCK	LEAKING         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430X	1081 				49058				LEAKS. REPLACED UNIT.						1	G	7	2 	3U			RT	H9SW    					 
2001080700428	20010807	00428	SW  	2001	8	7	HEED073545       	1	20010614	G	7400	FCB205AT9	RELAY           			BELL  	407   	407         	       	SW  	ALLSN 	250B  	250B*       	 	GL  					IGNITER	FAILED          	E			HEED	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3193E	1986 				53276				AUTO RELIGHT ON CAUTION PANEL FAILED TO COME ON AT ENGINE START ATTEMPLT AND NO ENGINE IGNITION OR LIGHT OFF. SCRAPPED. 	REPLACED UNIT.					1	G	7	1 	3U	3	T	O	H2SW    	E10CE				 
2001080700429	20010807	00429	GL  	2001	8	7	HEED073546       	2	20010614	G	7421	CH34187A	IGNITER         			BELL  	407   	407         	       	SW  	ALLSN 	250B  	250B*       	 	GL  					ENGINE	CRACKED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	1986 				53276				CRACKED CERAMIC AND ERROIDED TIP. REPLACED UNIT.						1	G	7	1 	3U	3	T	O	H2SW    	E10CE				 
2001080700430	20010807	00430	SW  	2001	8	7	HEED073548       	1	20010614	G	6500	ES731861	BLOWER          			BELL  	407   	407         	       	SW  										TAIL ROTOR	SHORTED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E					53276				POPS CIRCUIT BREAKER. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001080700431	20010807	00431	SW  	2001	8	7	HEED073549       	1	20010614	G	2841	407375006101	INDICATOR       			BELL  	407   	407         	       	SW  										FUEL QUANITY	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E					53276				DISPLAY BLANK REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001080700432	20010807	00432		2001	8	7	HEED073550       	4	20010614	G	3120	775330200	CLOCK           			BELL  	407   	407         	       	SW  										COCKPIT	STOPPED         	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E					53276				CLOCK STOPPED. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001080700433	20010807	00433	SW  	2001	8	7	HEED073552       	1	20010614	G	6322	407040303101	SHAFT           			BELL  	407   	407         	       	SW  										FAN	VIBRATION       	E			HEED	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	3193E	1178 				53276				HIGH RDA VIBRATION LEVEL. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001080700434	20010807	00434	SW  	2001	8	7	HEED073553       	1	20010614	G	6510	ES731861	MOTOR           			BELL  	407   	407         	       	SW  										BLOWER	FAILED          	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E					53276				POP CIRCUIT BREAKER. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001092400101	20010924	00101	SW  	2001	9	24	HEED073554       	1	20010614	G	6300	406310405101	BEARING         			BELL  	407   	407         	       	SW  										P/C LINK	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	2164 				53276				WORN BEARINGS, SCRAPPED. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001092400103	20010924	00103	SW  	2001	9	24	HEED073555       	1	20010614	G	6300	406010417101	BEARING         			BELL  	407   	407         	       	SW  										P/C LINK	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	2189 				53276				WORN BEARINGS, SCRAPPED. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001092400104	20010924	00104	SW  	2001	9	24	HEED073556       	1	20010614	G	6300	406010417101	BEARING         			BELL  	407   	407         	       	SW  										P/C LINK	WORN            	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	2189 				53276				WORN BEARINGS, SCRAPPED. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001092400105	20010924	00105	SW  	2001	9	24	HEED073557       	1	20010614	G	7931	222375077113	TRANSMITTER     			BELL  	407   	407         	       	SW  										OIL PRESSURE	FLUCTUATES      	E			HEED	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3193E	2065 				53276				FLUCTUATING OIL PRESSURE. REPLACED UNIT.						1	G	7	1 	3U			O	H2SW    					 
2001071300079	20010713	00079	NM  	2001	7	13	HN6R0000218      	1	20010618	G	5311		FRAME           			BOEING	737   	737400      	       	NM  										FUSELAGE	CRACKED         	B			HN6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	932NU					25248				BS 827 FRAME IS CRACKED AT PSU RAIL ATTACHMENT BRACKET INBOARD FASTENER (LEFT HAND SIDE).  CAUSE  UNKNOWN .  REMOVED DAM	AGE, FABRICATED REPAIR PARTS AND INSTALLED.					2	L	7	2 	4F			RT	A16WE   					 
2002012300133	20020123	00133	EU  	2002	1	23	ISHA077178       	1	20011119	G	6520	350A3310021	PINION GEAR     		350A33020005	SNIAS 	350   	AS350D      	8680803	EU  										T/R GEARBOX	DEFECTIVE       	H			ISHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	67GE	3243 			M1280	1604				GEAR REJECTED AT INTERMOUNTAIN TURBINE FOR PITTING AND UNABLE TO ESTABLISH PROPER STATIC GEAR PATTERN REPLACED ASSY. WIT	H EXCHANGE					1	G	7	1 	3U			 	H9EU    					 
2002012300134	20020123	00134	EU  	2002	1	23	ISHA077179       	1	20011119	G	6520	350A33100121	BEVEL GEAR      		350A33020005	SNIAS 	350   	AS350D      	8680803	EU  										T/R GEARBOX	DEFECTIVE       	H			ISHA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	67GE	3243 			M1280	1604				REJECTED BY NAMPA VALLEY HELICOPTERS DUE TO PITTING AND UNABLE TO ESTABLISH STATIC GEAR PATTERN REPLACED WITH EXCHANGE A	SSY.					1	G	7	1 	3U			 	H9EU    					 
2001092400107	20010924	00107	EU  	2001	9	24	IVSA074819       	1	20010806	G	3340	122394R5123	MODULE          			UROCOP	EC120 	EC120B      	8680987	EU  										LIGHT	BURNED OUT      	H			IVSA	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			FS	01	166DL	227  				1066				PILOT REPORTED ANTI COLLISION LIGHT INOP.  FLASH TUBE FOUND BURNED AND CRACKED. REPLACEMENT TUBE ORDERED AND INSTALLED. 	 OPS CHECKED OK.					1	G	7	2 	3U			NC	R0001RD 					 
2001092400108	20010924	00108	WP  	2001	9	24	IVSA075461       	1	20010831	G	6310	D2761	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  										CLUTCH	DEFECTIVE       	H			IVSA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	UNK	76   				1031				MOTOR FAILED TO OPERATE WHEN CALLED ON TO ENGAGE M/R DRIVE BELTS.  WOULD NOT OPERATE IN EITHER DIRECTION. MOTOR REPLACED	, DEFECTIVE MOTOR RETURNED TOROBINSON FOR WARRANTY CREDIT.					1	G	7	1 	3O			 	H11NM   					 
2001100400091	20011004	00091	WP  	2001	10	4	IVSA075920       	1	20010924	G	6320	D2761	ACTUATOR        			ROBSIN	R44   	R44         	7640120	WP  										CLUTCH	FAILED          	H			IVSA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	7189C	176  				1031				CLUTCH ACTUATOR MOTOR FAILED FOR THE 2ND TIME.  REPLACEMENT MOTOR INSTALLED.  FURTHER TOUBLESHOOTING REVEALED SHEAVE ALI	GNMENT OUT OF LIMITS CAUSING INFLIGHT ILLUMINATION OF CLUTCH LIGHT.  ALIGNMENT CORRECTED AND FLIGHTS CONTINUED NORMALLY.	 BAD MOTOR RETURNED FOR WARRANTY CREDIT. 					1	G	7	1 	3O			 	H11NM   					 
2002011000162	20020110	00162	EU  	2002	1	10	IVSA076105       	1	20011003	G	6210	355A11002009	BLADE           			AEROSP	AS355 	AS355*      	       	EU  										MAIN ROTOR	CRACKED         	H			IVSA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	335FP	4892 				5456				BLADE REMOVED FOR REPAIR OF LEADING EDGE ABRASION STRIP CRACKS.  CUSTOMER REQUESTED EXCHANGE BLADE IN ORDER TO RESUME FL	IGHTS.  EXCHANGE BLADE INSTALLED, REPAIRABLE BLADE RETURNED TO AEC					1	G	7	2 	3U			 	H11EU   					 
2002012300136	20020123	00136	WP  	2002	1	23	IVSA077371       	1	20011212	G	6300	D1742	WHEEL           			ROBSIN	R44   	R44         	7640120	WP  										CENTER HUB	CORRODED        	H			IVSA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	7186Z	190  				737C				PAINT ON FAN WHEEL LOOSE AND FLAKING OFF DUE TO POOR ADHESION, PROBABLY CAUSED BY IMPROPER PREPARATION, ALLOWING PREMATU	RE CORROSION.					1	G	7	1 	3O			 	H11NM   					 
2001092400111	20010924	00111	SW  	2001	9	24	JJWA073276       	1	20010612	G	6320	206040236017	HOUSING         			BELL  	206   	206B        	1181511	SW  										GEARBOX	STRIPPED        	H			JJWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	5005N	8864 				1931				STUD PULLED OUT WITH LESS THAN 50 INCH POUND ON TORQUE WRENCH WHEN INSTALLING FW UNIT IN ENGINE -  HIDDEN DAMAGE NOT FOU	ND BY BELL CSF OVERHAUL FACILITY. NEW HOUSING SENT BY CSF.					1	G	7	1 	3U			 	H2SW    					 
2002012400001	20020124	00001	SW  	2002	1	24	JJWA077061       	1	20011105	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	CORRODED        	H			JJWA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	281CB					3303				ACTUATOR FAILED AFTER FEBRUARY 2001 OVERHAUL. NO ALODINE OR OTHER CORROSION PROTECTION ON INSIDE OF CASE.INTERNAL CORROS	ION CAUSED FAILURE.					1	G	7	1 	3U			 	H2SW    					 
2001121100136	20011211	00136	NE  	2001	12	11	JV652J           	2	20010828	G	7250	UL36199	CASE            								RROYCE	RB211 	RB211535E4  	54555	NE  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07		21825					ESN31340			CASE ASSEMBLY EXHIBITED 2 AXIAL CRACKS APPROXIMATELY 2.0 INCHES IN LENGTH AND 3.5 TO 4 INCHES APART.  CRACKS PROPAGATED 	THROUGH THE CASE WALL. CASE HAD 7277 TOTAL CYCLE.										4	F			E12EU				 
2001040500110	20010405	00110	EU  	2001	4	5	KBMA88583        	1	20010205	G	6520	350A33215300	LAMINATED HINGE 			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	DELAMINATED     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	1188P	9755 				2347				HINGE DELAMINATED						1	G	7	1 	3U			NC	H9EU    					 
2001030700630	20010307	00630	EU  	2001	3	7	KBMA88585        	1	20010127	G	6720	350A33214501	BUSHING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					T/R ROD BEARING	CRACKED         	I			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	115SH	2136 				3141				BUSHING CRACKED						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001030700633	20010307	00633	EU  	2001	3	7	KBMA88634        	1	20010127	G	5320	350A54112420	BRACKET         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					STARTER GEN	CRACKED         	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	115SH	2136 				3141				STARTER GENTERATOR AIR VENT DUCT BRACKET IS CRACKED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001030700631	20010307	00631	EU  	2001	3	7	KBMA88637        	1	20010201	G	7714	0177555170	CONTROL BOX     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TACH GEN	MALFUNCTIONED   	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	350SH	4435 				2957				TACH BOX CLOSES BLEED VALVE AT 96% AND OPENS AT 95%						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001030700629	20010307	00629	EU  	2001	3	7	KBMA88638        	1	20010127	G	5320	TL100AXE12L50DK	LATCH           			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					FUSELAGE	STUCK           	I			KBMA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	180EH	3439 				2337				LATCH WAS STICKING.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001030700621	20010307	00621	EU  	2001	3	7	KBMA88639        	1	20010130	G	2915	12TW13	SWITCH          			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					HYDRAULIC SYSTEM	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	37SH	9207 				2300				HYDRAULIC SWITCH WAS FAULTY.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040500100	20010405	00100	EU  	2001	4	5	KBMA88643        	1	20010215	G	7110	350A58154322	HINGE PIN       			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENG COWLING	BROKEN          	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	115SH	2169 				3141				COWLING HINGE PIN BROKEN.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040500124	20010405	00124	EU  	2001	4	5	KBMA88645        	1	20010217	G	7712	9580113720	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  										TORQUE INDICATOR	INOPERATIVE     	E			KBMA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	19	37SH	9250 				2300				TORQUE GUAGE NOT WORKING PROPERLY.						1	G	7	1 	3U			 	H9EU    					 
2001040500105	20010405	00105		2001	4	5	KBMA88646        	4	20010218	G	2312	064105430	VHF COMM        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	INOPERATIVE     	E			KBMA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	19	350SH	4474 				2957				VHF INOPERATIVE, COMES ON ONLY WHEN VOLUME IS ALL THE WAY DOWN.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001040500106	20010405	00106		2001	4	5	KBMA88649        	4	20010220	G	2312	064010540030	VHF COMM        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	MALFUNCTIONED   	E			KBMA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	19	1188P	9792 				2347				VHF HAS CONSTANT SQUELCH ON AFTER APPROX 30 MINUTES OF OPERATION.  WILL NOT RESET.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001040500109	20010405	00109	GL  	2001	4	5	KBMA88679        	2	20010227	G	7310	7G547	PRESSURE SWITCH 			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL SYSTEM	MALFUNCTIONED   	E			KBMA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			WP	19	667JM	9830 				3444				FUEL PRESSURE SWITCHES NOT OPERATING PROPERLY. CAUTION LITE REMAINS ON WITH CIRCUIT BREAKER IN.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001050300002	20010503	00002	NE  	2001	5	3	KBMA88694        	2	20010320	G	7210	9560134100	MAGNETIC SEAL   			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	LEAKING         	B			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	230SH	3523 				2337				ENGINE FRONT MAG SEAL LEAKING.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001050300004	20010503	00004	EU  	2001	5	3	KBMA88695        	1	20010320	G	6420	350A33215300	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL ROTOR	WORN            	B			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	230SH	3523 				2337				TAIL ROTOR TETTER BEARINGS WORN.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001050300020	20010503	00020	EU  	2001	5	3	KBMA88698        	1	20010320	G	6220		BUSHING         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					MAIN ROTOR	DEBONDED        	B			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	230SH	3523 				2337				REBONDED BUSHING.  DUE TO STATIONARY SCISSORS BUSHING DEBONDED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001041700018	20010417	00018	NE  	2001	4	17	KBMA88699        	2	20010320	G	7414	9560137520	MAGNETO         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					RIGHT	LEAKING         	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	230SH	3523 				2337				REAR ENGINE MAGNETO SEAL LEAKING.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001050300022	20010503	00022	EU  	2001	5	3	KBMA88700        	1	20010320	G	2435	9560134100	MAGNETIC SEAL   			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	LEAKING         	B			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	230SH	3523 				2337				STARTER GENERATOR MAGNETIC SEAL LEAKING.  REMOVED AND REPLACED SEAL.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001041700020	20010417	00020		2001	4	17	KBMA88706        	4	20010317	G	3422	5050031904	GYRO            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	PRECESSES       	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	345SH	69   				3345				DIRECTIONAL GYRO RAPIDLY PRESSESSING.  GYRO HAD APPROX. 10 HOURS ON UNIT.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001041700017	20010417	00017	EU  	2001	4	17	KBMA88707        	1	20010318	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					MAIN ROTOR	LEAKING         	C			KBMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	19	115SH	2268 				3141				LEAKING FROM WEEPHOLE.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001041700023	20010417	00023	EU  	2001	4	17	KBMA88709        	1	20010318	G	7712	9580113720	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE TORQUE	MALFUNCTIONED   	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH	7577 				1864				NEEDLE MOVES TO UPPER LIMIT OF SCALE AND STOPS THERE FOR A COUPLE OF MINUTES.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001041700021	20010417	00021	NE  	2001	4	17	KBMA88711        	2	20010323	G	7412	955016870	IGNITER         			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					RIGHT	INTERMITTENT    	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH	7599 				1864				RIGHT IGNITER INTERMITTENT.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001041700019	20010417	00019	EU  	2001	4	17	KBMA88712        	1	20010311	G	7410	HE402F	IGNITER BOX     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					RIGHT	INOPERATIVE     	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	1188P	9846 				2347				RIGHT IGNITOR IS INOPERATIVE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001041700022	20010417	00022	NE  	2001	4	17	KBMA88713        	2	20010312	G	7230	420800003	FAN             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	CHAFED          	C			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	53SH	4998 				2009				FAN BLADES HITTING HOUSING.  ADJUSTED BLADES.  OPS CHECKED GOOD.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001052900040	20010529	00040	EU  	2001	5	29	KBMA88728        	1	20010418	G	5553	22201BC060016L	BOLT            			SNIAS 	350   	AS350BA     	8680817	EU  										VERTICAL STAB	SHEARED         	E			KBMA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	19	270SH	7704 				1864				BOLTS SHEARED, INSTALLED NEW BOLTS AS REQUIRED.						1	G	7	1 	3U			NC	H9EU    					 
2001040500108	20010405	00108		2001	4	5	KBMA88818        	4	20010208	G	3421	5040017901	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	INOPERATIVE     	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH	7475 				1864				PRECESSING AND FLAG INDICATOR INOPERATIVE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001040500107	20010405	00107		2001	4	5	KBMA88819        	4	20010208	G	3422	200DCL	GYRO            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	MALFUNCTIONED   	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	270SH	7475 				1864				DIRECTIONAL GYRO MAKES EXCESSIVE NOISE.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU				 
2001040500125	20010405	00125	EU  	2001	4	5	KBMA99419        	1	20010109	G	6520	350A33215001	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	WORN            	E			KBMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	350SH	4396 				2957				BEARING WORN.						1	G	7	1 	3U			NC	H9EU    					 
2001100400138	20011004	00138	EU  	2001	10	4	KUVA075921       	1	20010928	G	6420	109013105111	PIVOT           			AGUSTA	A109  	A109A2      	0260120	EU  										TAIL ROTOR	WORN            	H			KUVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	584RH	2361 				7356				T/R TURNNION P/N 109-0131-05-111 TT: 2360.8. THE TRUNNION SHOWED SIGNIFIGANT WEAR AT DISSASSEMBLY AFTER THE PILOT NOTED 	A HIGH FREQUENCY VIBRATION. THE AGUSTA T/R ASSY IS SUBJECT TO BECOMING STIFF, WHEN THIS OCCURS THE T/R HUB SHOULD BE COM	PLETELY DISSASSEMBLED AND INSPECTED FOR WEAR. I WOULD SUGGEST AGUSTA INSTITUTE A SCHEDULED INSPECTION PRIOR TO THE 2400 	HR. INSPECTION THAT IS NOW IN PLACE.			1	G	7	2 	3U			 	H7EU    					 
2001100400140	20011004	00140	EU  	2001	10	4	KUVA075922       	1	20010928	G	6420	109013105111	PIVOT           			AGUSTA	A109  	A109        	0260109	EU  										TAIL ROTOR	WORN            	H			KUVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	584RH	2361 				7356				T/R TURNNION P/N 109-0131-05-111 TT: 2360.8. THE TRUNNION SHOWED SIGNIFIGANT WEAR AT DISSASSEMBLY AFTER THE PILOT NOTED 	A HIGH FREQUENCY VIBRATION. THE AGUSTA T/R ASSY IS SUBJECT TO BECOMING STIFF, WHEN THIS OCCURS THE T/R HUB SHOULD BE COM	PLETELY DISSASSEMBLED AND INSPECTED FOR WEAR. I WOULD SUGGEST AGUSTA INSTITUTE A SCHEDULED INSPECTION PRIOR TO THE 2400 	HR. INSPECTION THAT IS NOW IN PLACE.			1	G	7	2 	3U			 	H7EU    					 
2002012400002	20020124	00002	GL  	2002	1	24	KUVA076138       	2	20011010	G	7230	6890483	BEARING RACE    		6890550     	AGUSTA	A109  	A109A2      	0260120	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	CHAFED          	H			KUVA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	168BH				CAC6026	7256	CAC6026			BEARING P/N 23034787 S/N MP78657 CHAFFED RACE P/N 6890483 S/N MP119218 CAUSING BOTH PARTS TO SCRAP.						1	G	7	2 	3U	3	U	 	H7EU    	E4CE				 
2001041900222	20010419	00222	SW  	2001	4	19	LS1R071905       	1	20010404	G	7921	8538312	COOLER          			BELL  	206   	206B3       	1181506	SW  										TRANSMISSION	CONTAMINATED    	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY					2871				PART HAS TRANSMISSION CHIPS.						1	G	7	1 	3U			 	H2SW    					 
2001041900223	20010419	00223	WP  	2001	4	19	LS1R071906       	1	20010404	G	3340	6014313	POWER SUPPLY    			HUGHES	369   	369D        	4470706	WP  										STROBE	FAILED          	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART WILL NOT FLASH.						1	G	7	1 	3U			 	H3WE    					 
2001041900224	20010419	00224	WP  	2001	4	19	LS1R071907       	1	20010404	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J					900801D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001041900225	20010419	00225	WP  	2001	4	19	LS1R071908       	1	20010404	G	3211	369H6006	BRACE           			HUGHES	369   	369D        	4470706	WP  										MLG	WORN            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2001041900226	20010419	00226	WP  	2001	4	19	LS1R071909       	1	20010404	G	3211	369H6006	BRACE           			HUGHES	369   	369D        	4470706	WP  										MLG	WORN            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2001041900227	20010419	00227	WP  	2001	4	19	LS1R071910       	1	20010404	G	3211	369H6006	BRACE           			HUGHES	369   	369D        	4470706	WP  										MLG	CRACKED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001041900228	20010419	00228	WP  	2001	4	19	LS1R071911       	1	20010404	G	2821	369A8116	FUEL FILTER     			HUGHES	369   	369D        	4470706	WP  										ENGINE	BROKEN          	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART IS BROKEN.						1	G	7	1 	3U			 	H3WE    					 
2001041900229	20010419	00229	GL  	2001	4	19	LS1R071914       	2	20010404	G	7210	810151	MAGNETIC SEAL   			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	E			LS1R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	206BX					2872				PART IS LEAKING.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2001041900230	20010419	00230	GL  	2001	4	19	LS1R071915       	2	20010404	G	7210	6894171	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LEAKING         	E			LS1R	O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	5211R					1161D				PART IS LEAKING.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041900231	20010419	00231	SW  	2001	4	19	LS1R071916       	1	20010406	G	6510	204040602005	SHAFT           			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	WORN            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	53AG					7221588				PART IS WORN EXCESSIVELY.						1	G	7	1 	4U			 	EXPA1G71					 
2001041900232	20010419	00232	SW  	2001	4	19	LS1R071917       	1	20010406	G	6510	204040602005	SHAFT           			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	WORN            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	53AG					7221588				PART IS WORN EXCESSIVELY.						1	G	7	1 	4U			 	EXPA1G71					 
2001041900233	20010419	00233	SW  	2001	4	19	LS1R071918       	1	20010406	G	7930	206011721009	BEARING         			BELL  	206   	206B3       	1181506	SW  										INDICATOR	LOOSE           	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	90322					1736				PART IS LOOSE BEARINGS.						1	G	7	1 	3U			 	H2SW    					 
2001041900234	20010419	00234	GL  	2001	4	19	LS1R071919       	2	20010406	G	7314	369A81433	PUMP            			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	NOISY           	E			LS1R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			EA	13	765KV					0082E				PART IS NOISY.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001041900235	20010419	00235	SW  	2001	4	19	LS1R071920       	1	20010406	G	6320	206031509001	DRAG PIN        			BELL  	206   	206B3       	1181506	SW  										M/R GEARBOX	WORN            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	90322					1736				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H2SW    					 
2001041900236	20010419	00236	SW  	2001	4	19	LS1R071921       	1	20010406	G	5522	206070178012	SKIN            			BELL  	206   	206B3       	1181506	SW  										ELEVATOR	DAMAGED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K					2040				PART HAS A HOLE.						1	G	7	1 	3U			 	H2SW    					 
2001041900194	20010419	00194	WP  	2001	4	19	LS1R072189       	1	20010410	G	7714	369A45167	TACHOMETER      			HUGHES	369   	369E        	4470707	WP  										COCKPIT	INACCURATE      	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	8330P	105  				0330E				TACHOMETER IS INACCURATE.						1	G	7	1 	3U			 	H3WE    					 
2003080700113	20030807	00113	SW  	2003	8	7	LS1R072190       	1	20010410	G	2700	205001706009	CABLE DRUM      			BELL  	204   	UH1H        	1181407	SW  										FLT CONTROLS	STRETCHED       	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	51AG					7120178				CABLE DRUM STRETCHED.						1	G	7	1 	4U			 	EXPA1G71					 
2001050700552	20010507	00552	SW  	2001	5	7	LS1R072589       	1	20010416	G	6300	206030539101	MOUNT           			BELL  	206   	206B3       	1181506	SW  										INPUT DRIVE	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322	8439 				1736				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H2SW    					 
2001050700553	20010507	00553	SW  	2001	5	7	LS1R072590       	1	20010416	G	3310	20407570545	CONTROL PANEL   			BELL  	204   	UH1H        	1181407	SW  										COCKPIT LIGHTS	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	53AG	4790 				7221588				LIGHTS WILL NOT COME ON. CONTROL PANEL INOPERATIVE.						1	G	7	1 	4U			 	EXPA1G71					 
2001050700554	20010507	00554		2001	5	7	LS1R072591       	4	20010416	G	3457	66000201	GPS             			BELL  	206   	OH58A       	1181579	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	54AG	221  				7120721				GPS WILL NOT RECIEVE.						1	G	7	1 	3U			 	H2SW    					 
2001050700555	20010507	00555	SW  	2001	5	7	LS1R072592       	1	20010416	G	2424	07639CSV1152	REGULATOR       			BELL  	204   	UH1H        	1181407	SW  										ELECTRICAL	OUT OF ADJ      	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	53AG					7221588				REGULATOR UNABLE TO HOLD ADJUSTMENT.						1	G	7	1 	4U			 	EXPA1G71					 
2001050700563	20010507	00563	SW  	2001	5	7	LS1R072735       	1	20010419	G	7714	32005023	TACH GENERATOR  			BELL  	206   	206B3       	1181506	SW  										ENGINE	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BX					2872				PART IS BROKEN.						1	G	7	1 	3U			 	H2SW    					 
2001050800201	20010508	00201	SW  	2001	5	8	LS1R072736       	1	20010419	G	2740	205001505001	BEARING         			BELL  	212   	212         	1181420	SW  										BELLCRANK	LOOSE           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				BELLCRANK HAS LOOSE BEARINGS.						1	G	7	1 	4U			 	H4SW    					 
2001050700564	20010507	00564	SW  	2001	5	7	LS1R072737       	1	20010419	G	7714	212070108007	INDICATOR       			BELL  	212   	212         	1181420	SW  										TRIPLE TACH	INTERMITTENT    	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F	1241 				30920				PART IS INTERMITTENT.						1	G	7	1 	4U			 	H4SW    					 
2001050700565	20010507	00565	WP  	2001	5	7	LS1R072738       	1	20010419	G	2740	369A717011	MOTOR           			HUGHES	369   	369D        	4470706	WP  										LATERAL TRIM	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	4014 				290456D				PART IS SLOW.						1	G	7	1 	3U			 	H3WE    					 
2001050700566	20010507	00566	SW  	2001	5	7	LS1R072739       	1	20010425	G	7603	206062721113	BEARING         			BELL  	206   	206B3       	1181506	SW  										ACTUATOR	LOOSE           	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY	318  				2871				PART HAS LOOSE BEARINGS.						1	G	7	1 	3U			 	H2SW    					 
2001050700567	20010507	00567	SW  	2001	5	7	LS1R072740       	1	20010426	G	2822	1C381	PUMP            			BELL  	206   	206B3       	1181506	SW  										FUEL BOOST	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K	563  				2040				PART IS INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2001050700568	20010507	00568	WP  	2001	5	7	LS1R072741       	1	20010427	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R	529  				1161D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001050700569	20010507	00569	WP  	2001	5	7	LS1R072742       	1	20010427	G	2740	369A7010	LOCK            			HUGHES	369   	369E        	4470707	WP  										STAB	DAMAGED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	765KV					0082E				PART HAS FEED BACK.						1	G	7	1 	3U			 	H3WE    					 
2001051500435	20010515	00435		2001	5	15	LS1R072915       	4	20010509	G	2300	069102100	RADIO           			HUGHES	369   	369D        	4470706	WP  										COCKPIT	WEAK            	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J					900801D				RADIO IS WEAK.						1	G	7	1 	3U			 	H3WE    					 
2001051500436	20010515	00436	WP  	2001	5	15	LS1R072916       	1	20010509	G	7714	369H4551	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE	SHEARED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J					900801D				TACH GEN IS SHEARED.						1	G	7	1 	3U			 	H3WE    					 
2001051500437	20010515	00437		2001	5	15	LS1R072917       	4	20010509	G	2300	TFM1380	CONTROL UNIT    			HUGHES	369   	369D        	4470706	WP  										RADIO	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5211R					1161D				RADIO CONTROL INOP.						1	G	7	1 	3U			 	H3WE    					 
2001051500438	20010515	00438	WP  	2001	5	15	LS1R072918       	1	20010509	G	3300	369H64255	CONTROL UNIT    			HUGHES	369   	369D        	4470706	WP  										DIMMER SWITCH	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	1461 				900801D				DIMMER SWITCH CIRCUIT-SHORTED.						1	G	7	1 	3U			 	H3WE    					 
2001051500439	20010515	00439	GL  	2001	5	15	LS1R072919       	2	20010509	G	7412	10614950	EXCITER         			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	UNSERVICEABLE   	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	765KV	952  				0082E				EXCITER IS UNSERVICEABLE.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001051500440	20010515	00440	WP  	2001	5	15	LS1R072920       	1	20010509	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369E        	4470707	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	129GA					0052E				HAS SOLID TONE.						1	G	7	1 	3U			 	H3WE    					 
2001051500441	20010515	00441		2001	5	15	LS1R072921       	4	20010509	G	2350	066105570	AUDIO PANEL     			HUGHES	369   	369E        	4470707	WP  										COCKPIT	INTERMITTENT    	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	129GA					0052E				AUDIO PANEL IS INTERMITTENT.						1	G	7	1 	3U			 	H3WE    					 
2001072700136	20010727	00136	WP  	2001	7	27	LS1R073005       	1	20010522	G	2110	6890550	COMPRESSOR      			HUGHES	369   	369E        	4470707	WP  										AIR CONDITIONER	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	129GA	1647 				0052E				COMPRESSOR IS DAMAGED.						1	G	7	1 	3U			 	H3WE    					 
2001072700137	20010727	00137	WP  	2001	7	27	LS1R073117       	1	20010524	G	6420	369D27609501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	LOOSE           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	1006 				290456D				SWASHPLATE HAS EXCESIVE AXIAL PLAY.						1	G	7	1 	3U			 	H3WE    					 
2001072700147	20010727	00147	WP  	2001	7	27	LS1R073118       	1	20010524	G	6520	369D25400	GEARBOX         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	MAKING METAL    	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW	3154 				470117D				TAIL ROTOR GEARBOX IS MAKING METAL.						1	G	7	1 	3U			 	H3WE    					 
2001072700148	20010727	00148	WP  	2001	7	27	LS1R073263       	1	20010604	G	7714	369A45167	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										TACHOMETER	SHORTED         	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5211R	1479 				1161D				TACHOMETER IS SHORTED OUT.						1	G	7	1 	3U			 	H3WE    					 
2001072700149	20010727	00149	WP  	2001	7	27	LS1R073264       	1	20010604	G	6700	369A717011	MOTOR           			HUGHES	369   	369D        	4470706	WP  										LATERAL TRIM	INTERMITTENT    	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	1683 				900801D				LATERAL TRIM MOTER IS INTERMITTENT.						1	G	7	1 	3U			 	H3WE    					 
2001072700150	20010727	00150		2001	7	27	LS1R073265       	4	20010604	G	2312	KY195B	RADIO           			HUGHES	369   	369D        	4470706	WP  										VHF	DISTORTED       	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P	2220 				611002D				VHF RADIO IS DISTORTED.						1	G	7	1 	3U			 	H3WE    					 
2001072700154	20010727	00154	WP  	2001	7	27	LS1R073266       	1	20010604	G	3300	369H6425	SWITCH          			HUGHES	369   	369E        	4470707	WP  										DIMMER CONTROL	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P	1215 				0330E				DIMMER CONTROL INOPERATIVE.						1	G	7	1 	3U			 	H3WE    					 
2001072700156	20010727	00156	WP  	2001	7	27	LS1R073267       	1	20010604	G	2436	369A4652	VOLT REGULATOR  			HUGHES	369   	369E        	4470707	WP  										ELECTRICAL	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	8330P	1791 				0330E				VOLTAGE REGULATOR  WILL NOT COME ON LINE.						1	G	7	1 	3U			 	H3WE    					 
2001072700159	20010727	00159	SW  	2001	7	27	LS1R073268       	1	20010604	G	7714		SHAFT           			BELL  	206   	OH58A       	1181579	SW  										TACH GENERATOR	SHEARED         	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	58AG	809  			13702	7221131				TACH GENERATOR SHAFT IS SHEARED.						1	G	7	1 	3U			 	H2SW    					 
2001092400115	20010924	00115	WP  	2001	9	24	LS1R073476       	1	20010618	G	2822	164A81343	PUMP            			HUGHES	369   	369E        	4470707	WP  										FUEL SYSTEM	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	765KV	18   				0082E				PART IS WILL NOT RUN WHEN POWER A.						1	G	7	1 	3U			 	H3WE    					 
2001092400116	20010924	00116	WP  	2001	9	24	LS1R073477       	1	20010618	G	6720	369D21800501	SEAL            			HUGHES	369   	369D        	4470706	WP  										T/R PITCH CONTRO	ROTATED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R	1151 				1161D				PART IS SEAL ROTATES.						1	G	7	1 	3U			 	H3WE    					 
2001092400117	20010924	00117	WP  	2001	9	24	LS1R073478       	1	20010618	G	6300	204031920003	DAMPER          			HUGHES	369   	369E        	4470707	WP  										MAIN ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2001092400118	20010924	00118	SW  	2001	9	24	LS1R073479       	1	20010619	G	6700	0710105200	VALVE           			BELL  	212   	212         	1181420	SW  										FLIGHT CONTROL	BROKEN          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				PART IS BROKEN.						1	G	7	1 	4U			 	H4SW    					 
2001092400119	20010924	00119	WP  	2001	9	24	LS1R073480       	1	20010619	G	2510	369H6525503	SEAT            			HUGHES	369   	369D        	4470706	WP  										COCKPIT	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001092400120	20010924	00120	WP  	2001	9	24	LS1R073481       	1	20010619	G	2810	369H81013	FUEL CELL       			HUGHES	369   	369D        	4470706	WP  										FUSELAGE	LEAKING         	E			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	369AW					470117D				PART IS LEAKING.						1	G	7	1 	3U			 	H3WE    					 
2001092400121	20010924	00121	WP  	2001	9	24	LS1R073482       	1	20010619	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001092400122	20010924	00122	SW  	2001	9	24	LS1R073483       	1	20010619	G	6320	206032309536	BEARING         			BELL  	206   	OH58A       	1181579	SW  										MAIN ROTOR	DAMAGED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	58AG					7221131				PART IS OUT OF RACE.						1	G	7	1 	3U			 	H2SW    					 
2001092400123	20010924	00123	SW  	2001	9	24	LS1R073484       	1	20010619	G	2432	201A	GAUGE           			BELL  	206   	OH58A       	1181579	SW  										BATTERY	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	58AG					7221131				GAGE PEGS OUT.						1	G	7	1 	3U			 	H2SW    					 
2001092400124	20010924	00124	WP  	2001	9	24	LS1R073485       	1	20010619	G	6300	369D21400503	DAMPER          			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	STRETCHED       	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				PART IS STRETCHED.						1	G	7	1 	3U			 	H3WE    					 
2001092400126	20010924	00126	WP  	2001	9	24	LS1R073486       	1	20010619	G	6230	369D27609501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	LOOSE           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				PART HAS EXCESIVE AXIAL PLAY.						1	G	7	1 	3U			 	H3WE    					 
2001092400127	20010924	00127	WP  	2001	9	24	LS1R073487       	1	20010619	G	6720	369D21800501	BEARING         			HUGHES	369   	369E        	4470707	WP  										T/R ROTOR	LOOSE           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	129GA					0052E				BEARINGS FALL OUT.						1	G	7	1 	3U			 	H3WE    					 
2001092400128	20010924	00128		2001	9	24	LS1R073488       	4	20010619	G	2300	TFM138B	RADIO           			HUGHES	369   	369D        	4470706	WP  										COCKPIT	STUCK           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				PART IS STICKING.						1	G	7	1 	3U			 	H3WE    					 
2001092400130	20010924	00130	SW  	2001	9	24	LS1R074916       	1	20010720	G	2432	AG380E4440	BATTERY         			BELL  	204   	UH1H        	1181407	SW  										MAIN BATTERY	WEAK            	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	51AG					7120178				PART IS WEAK.						1	G	7	1 	4U			 	EXPA1G71					 
2001092400131	20010924	00131	SW  	2001	9	24	LS1R074917       	1	20010720	G	2432	G641E	BATTERY         			BELL  	206   	206B3       	1181506	SW  										MAIN BATTERY	DISCHARGED      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				PART IS BAD CELLS.						1	G	7	1 	3U			 	H2SW    					 
2001092400132	20010924	00132	WP  	2001	9	24	LS1R074918       	1	20010720	G	6510	369D2172121	BEARING         			HUGHES	369   	369E        	4470707	WP  										T/R LINK	LOOSE           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	765KV					0082E				BEARINGS FALL OUT.						1	G	7	1 	3U			 	H3WE    					 
2001092400134	20010924	00134	WP  	2001	9	24	LS1R074919       	1	20010720	G	6400	369D2172313	LINK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2001092400136	20010924	00136	WP  	2001	9	24	LS1R074920       	1	20010720	G	6400	369D2172313	LINK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				PART IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2001092400138	20010924	00138	WP  	2001	9	24	LS1R074921       	1	20010720	G	7332	369H81443	PRESSURE SWITCH 			HUGHES	369   	369E        	4470707	WP  										FUEL SYSTEM	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				COMES IN TO LOW.						1	G	7	1 	3U			 	H3WE    					 
2001092400140	20010924	00140	WP  	2001	9	24	LS1R074922       	1	20010720	G	7714	8DJ150FEA	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										COCKPIT	UNSERVICEABLE   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS UNREADABLE AND UNSERVICEABLE.						1	G	7	1 	3U			 	H3WE    					 
2001092400141	20010924	00141	WP  	2001	9	24	LS1R074923       	1	20010720	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369E        	4470707	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	765KV	457  				0082E				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001092400142	20010924	00142	WP  	2001	9	24	LS1R074924       	1	20010720	G	7810	369A8230503	EXHAUST PIPE    			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001092400143	20010924	00143	WP  	2001	9	24	LS1R074925       	1	20010720	G	2432	G641E	BATTERY         			HUGHES	369   	369E        	4470707	WP  										MAIN BATTERY	OVERHEATED      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART OVERHEATED.						1	G	7	1 	3U			 	H3WE    					 
2001092400144	20010924	00144	SW  	2001	9	24	LS1R074926       	1	20010720	G	5320	206031302269	SUPPORT         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				PART IS CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001092400145	20010924	00145	SW  	2001	9	24	LS1R074927       	1	20010720	G	5320	206031301129	SUPPORT         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				PART IS CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001092400147	20010924	00147	SW  	2001	9	24	LS1R074928       	1	20010720	G	2730	205001905001	BELLCRANK       			BELL  	212   	212         	1181420	SW  										ELEVATOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530B					30702				PART IS WORN EXCESSIVELY.						1	G	7	1 	4U			 	H4SW    					 
2001092400148	20010924	00148	WP  	2001	9	24	LS1R074929       	1	20010720	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				PART IS CRACKED.						1	G	7	1 	3U			 	H3WE    					 
2001092400150	20010924	00150	GL  	2001	9	24	LS1R074930       	2	20010720	G	7320	369A717011	MOTOR           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					LATERAL TRIM	NOISY           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5211R					1161D				PART IS NOISY.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001092400151	20010924	00151	SW  	2001	9	24	LS1R074931       	1	20010720	G	2810	20601675001	FUEL CELL       			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	LEAKING         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718					1917				PART IS LEAKING.						1	G	7	1 	3U			 	H2SW    					 
2001092400153	20010924	00153	SW  	2001	9	24	LS1R074932       	1	20010720	G	2910	205076099007	CYLINDER        			BELL  	204   	UH1H        	1181407	SW  										HYD SYSTEM	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				PART IS WORN EXCESSIVELY.						1	G	7	1 	4U			 	EXPA1G71					 
2001092400155	20010924	00155	SW  	2001	9	24	LS1R074934       	1	20010803	G	5320	2060313291	FITTING         			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	CRACKED         	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				PART IS CRACKED.						1	G	7	1 	3U			 	H2SW    					 
2001092400157	20010924	00157	SW  	2001	9	24	LS1R074935       	1	20010813	G	6321	204001376003	BRAKE           			BELL  	206   	OH58A       	1181579	SW  										MAIN ROTOR	STUCK           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	58AG	1360 				7221131				PART MOVEMENT RESTRICTED.						1	G	7	1 	3U			 	H2SW    					 
2001092400159	20010924	00159	WP  	2001	9	24	LS1R074936       	1	20010813	G	8000	IC34	BRUSHES         			HUGHES	369   	369E        	4470707	WP  										STARTER	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART IS BAD BRUSHES.						1	G	7	1 	3U			 	H3WE    					 
2001092400160	20010924	00160	WP  	2001	9	24	LS1R074937       	1	20010813	G	2810	164A134	FUEL CELL       			HUGHES	369   	369D        	4470706	WP  										FUSELAGE	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				NO POWER.						1	G	7	1 	3U			 	H3WE    					 
2001092400162	20010924	00162	WP  	2001	9	24	LS1R074938       	1	20010813	G	2821	369H8102	HOSE            			HUGHES	369   	369E        	4470707	WP  										FUEL SYSTEM	DIRTY           	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				DIRT IN FUEL FILTER.						1	G	7	1 	3U			 	H3WE    					 
2001092400163	20010924	00163	WP  	2001	9	24	LS1R074939       	1	20010813	G	2822	IC34	PUMP            			HUGHES	369   	369E        	4470707	WP  										FUEL SYSTEM	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART WILL NOT OPERATE.						1	G	7	1 	3U			 	H3WE    					 
2001092400168	20010924	00168	WP  	2001	9	24	LS1R074940       	1	20010813	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369E        	4470707	WP  										ENGINE	MALFUNCTIONED   	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	8330P					0330E				PART WON'T TURN OFF.						1	G	7	1 	3U			 	H3WE    					 
2001092400169	20010924	00169	SW  	2001	9	24	LS1R074941       	1	20010813	G	2432	G641	BATTERY         			BELL  	206   	206B3       	1181506	SW  										MAIN BATTERY	BURNED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				PART IS BURNED.						1	G	7	1 	3U			 	H2SW    					 
2001092400171	20010924	00171	SW  	2001	9	24	LS1R074942       	1	20010817	G	7921	8537651	OIL COOLER      			BELL  	212   	212         	1181420	SW  										ENGINE	MAKING METAL    	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F					30920				PART MAKING METAL.						1	G	7	1 	4U			 	H4SW    					 
2001092400172	20010924	00172		2001	9	24	LS1R074943       	4	20010817	G	2300	FM138	RADIO           			HUGHES	369   	369E        	4470707	WP  										COCKPIT	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART WILL NOT TRANSMITT.						1	G	7	1 	3U			 	H3WE    					 
2001092400173	20010924	00173	WP  	2001	9	24	LS1R075709       	1	20010905	G	7400	369A45133	EPO ASSY        			HUGHES	369   	369E        	4470707	WP  										ENGINE	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				PART WARNING SIGNAL ACTIVATES.						1	G	7	1 	3U			 	H3WE    					 
2001092400174	20010924	00174	WP  	2001	9	24	LS1R075710       	1	20010905	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369D        	4470706	WP  											MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P	14   				611002D				PART WARNING SIGNAL ACTIVATES.						1	G	7	1 	3U			 	H3WE    					 
2001092400175	20010924	00175	WP  	2001	9	24	LS1R075711       	1	20010905	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369E        	4470707	WP  										ENGINE	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P	51   				0330E				PART WARNING SIGNAL ACTIVATES.						1	G	7	1 	3U			 	H3WE    					 
2001100400143	20011004	00143	WP  	2001	10	4	LS1R075923       	1	20010928	G	7400	369A45143	EPO ASSY        		369D        	HUGHES	369   	369D        	4470706	WP  										COCKPIT	OUT OF ADJ      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW	673  			470117D	470117D				PART IS OUT OF CALIBRATION.						1	G	7	1 	3U			 	H3WE    					 
2001100400144	20011004	00144	SW  	2001	10	4	LS1R075924       	1	20010928	G	7720	SEL019BC	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INACCURATE      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K	1000 				2040				PART IS INACCURATE.						1	G	7	1 	3U			 	H2SW    					 
2001100400145	20011004	00145	WP  	2001	10	4	LS1R075925       	1	20010928	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			EA	13	369AW					470117D				PART IS ACTUATES WARNING HORN.						1	G	7	1 	3U			 	H3WE    					 
2002012400003	20020124	00003	GL  	2002	1	24	LS1R076721       	2	20011022	G	7321	23065104	FUEL CONTROL    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				MAKES ENGINE RUMBLE AT IDLE; ENGINE N1 DECREASES 1/2 TO 1 PERCENT WITH START PUMP ON AND RETURNS TO NORMAL WHEN OFF.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2002012400004	20020124	00004	WP  	2002	1	24	LS1R076722       	1	20011022	G	3150	369H64255	CONTROL UNIT    		369D        	HUGHES	369   	369D        	4470706	WP  										INSTRUMENT PANEL	FAILED          	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	369AW				470117D	470117D				INSTRUMENT PANEL LIGHT DIMMER CONTROL FAILED.						1	G	7	1 	3U			 	H3WE    					 
2002012400005	20020124	00005		2002	1	24	LS1R076723       	4	20011022	G	3420	206070274005	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY					2871				ATTITUDE INDICATOR NEEDLE WILL NOT MOVE.						1	G	7	1 	3U			 	H2SW    					 
2002012400006	20020124	00006	WP  	2002	1	24	LS1R076724       	1	20011022	G	2822	1C34	PUMP            			HUGHES	369   	369D        	4470706	WP  										FUEL BOOST	FAILED          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				BOOST PUMP WILL NOT TURN ON.						1	G	7	1 	3U			 	H3WE    					 
2002012400007	20020124	00007		2002	1	24	LS1R076725       	4	20011022	G	3424	206070274005	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K					2040				TURN AND BANK INDICATOR NEEDLE WILL NOT MOVE.						1	G	7	1 	3U			 	H2SW    					 
2002012400008	20020124	00008	SW  	2002	1	24	LS1R076726       	1	20011022	G	2822	206062681101	PUMP            			BELL  	206   	206B3       	1181506	SW  										FUEL BOOST	MALFUNCTIONED   	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY					2871				BOOST PUMP PRODUCING LOW PRESSURE AND LOUD NOISE.						1	G	7	1 	3U			 	H2SW    					 
2002012400009	20020124	00009	WP  	2002	1	24	LS1R076727       	1	20011022	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P					611002D				LOW ROTOR RPM ACTUATES WHEN EPO IS ACTIVATED.						1	G	7	1 	3U			 	H3WE    					 
2002012400010	20020124	00010	WP  	2002	1	24	LS1R076728       	1	20011022	G	6400	369D27514	BELLCRANK       			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				TAIL ROTOR BELLCRANK EARS WORN AND SPRUNG.						1	G	7	1 	3U			 	H3WE    					 
2002012400011	20020124	00011	WP  	2002	1	24	LS1R076729       	1	20011022	G	6720	369D21800501	PITCH CONTROL   			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				TAIL ROTOR PITCH CONTROL IS WORN EXCESSIVELY.						1	G	7	1 	3U			 	H3WE    					 
2002012400012	20020124	00012	SW  	2002	1	24	LS1R076730       	1	20011022	G	7603	1606470001	THROTTLE CABLE  			BELL  	206   	206B3       	1181506	SW  										ENGINE	BROKEN          	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322					1736				THROTTLE CABLE IS BROKEN.						1	G	7	1 	3U			 	H2SW    					 
2002012400013	20020124	00013	GL  	2002	1	24	LS1R076731       	2	20011022	G	7261	1740996	FILTER          			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE OIL	LEAKING         	E			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	206BX					2872				ENGINE OIL FILTER IS LEAKING.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE				 
2002012400014	20020124	00014	WP  	2002	1	24	LS1R076732       	1	20011022	G	2820	369D281081	VENT LINE       			HUGHES	369   	369D        	4470706	WP  										ENGINE FUEL	BENT            	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				FUEL VENT LINE IS BENT.						1	G	7	1 	3U			 	H3WE    					 
2002012400015	20020124	00015		2002	1	24	LS1R076733       	4	20011022	G	3422	103002201	GYRO            			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				DIRECTIONAL GYRO IS INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2002012400016	20020124	00016		2002	1	24	LS1R076734       	4	20011022	G	3421	500DC	GYRO            			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				ATTITUDE GYRO CONTROL INOPERATIVE.						1	G	7	1 	3U			 	H2SW    					 
2002012400017	20020124	00017	WP  	2002	1	24	LS1R076929       	1	20011031	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				EPO UNIT FEEDS BACK.						1	G	7	1 	3U			 	H3WE    					 
2002012400018	20020124	00018	WP  	2002	1	24	LS1R076930       	1	20011031	G	7400	369A45143	EPO ASSY        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				EPO ASSY FEEDS BACK.						1	G	7	1 	3U			 	H3WE    					 
2002012400019	20020124	00019	SW  	2002	1	24	LS1R076931       	1	20011031	G	7931	209070262009	INDICATOR       			BELL  	212   	212         	1181420	SW  										ENGINE OIL	INTERMITTENT    	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530B					30702				INTERMITTENT.						1	G	7	1 	4U			 	H4SW    					 
2002012400020	20020124	00020	WP  	2002	1	24	LS1R076932       	1	20011031	G	2430	A700ZG	RCCB            			HUGHES	369   	369D        	4470706	WP  										ELECTRICAL	FAILED          	E			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW					470117D				RCCB HAS NO OUTPUT.						1	G	7	1 	3U			 	H3WE    					 
2002012400021	20020124	00021	WP  	2002	1	24	LS1R076933       	1	20011031	G	2424	369A4652	VOLT REGULATOR  			HUGHES	369   	369D        	4470706	WP  										ELELCTRICAL	OUT OF ADJ      	E			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				PART IS OUT OF CALIBRATION.						1	G	7	1 	3U			 	H3WE    					 
2002012400022	20020124	00022		2002	1	24	LS1R076934       	4	20011031	G	3420	5040017901	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	8530B					30702				ARTIFICIAL HORIZON WILL NOT COME ON LINE.						1	G	7	1 	4U			 	H4SW    					 
2002012400023	20020124	00023		2002	1	24	LS1R076935       	4	20011031	G	3420	5040017901	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	8530F					30920				ARTIFICIAL HORIZON WILL NOT COME ON LINE.						1	G	7	1 	4U			 	H4SW    					 
2001032600396	20010326	00396	EU  	2001	3	26	MALA010220       	1	20010220	G	5320		FLOOR SUPPORT   			SAAB  	SF340 	340B        	7860101	EU  										FUSELAGE	CORRODED        	A			MALA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	424XJ					424				FOUND DURING C-CHECK, CORROSION ON LT FLOOR SUPPORT FLANGE ON SEAT TRACK AT BL-0 STA 294 THRU STA 413.  REFER TO CELSIUS	 W/O 19347, TASK 1526.  MAINTENANCE REMOVED CORROSION AND CHECK LIMIT.  REMOVED CORROSION IAW 51-70-40 MATERIAL REMOVED 	IS OUT OF LIMITS IAW SRM 53-70-60.  REMOVED FWD CLIP IAW SRM 51-40-21, FABRICATED NEW ANGLE IAW SRM 51-20-20/30, ALODINE	D, PRIMED AND PAINTED IAW SRM 51-20-42/43.  INSTALLED IAW SRM 51-40-21/23.  REMAINING AREA WITHIN ALLOWABLE LIMIT REF SR	M 53-70-60.		2	L	7	2 	4T			RT	A52EU   					 
2001041700083	20010417	00083	SO  	2001	4	17	MQGR20013601     	1	20010412	G	5740	1159W307012	ATTACH FITTING  			GULSTM	G1159 	G1159B      	3953535	SO  										WINGLET	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	74A	5720 				036				DURING RECOMMENDED INSPECTION OF WINGLET ATTACH HARDWARE FOR CORROSION, FOUND CORROSION IN THE WINGLET TO WING ATTACHMEN	T FITTING.  IT APPEARS THIS CORROSION IS THE RESULT OF IMPROPER SEALING OF THE ATTACHMENT HARDWARE SINCE WATER WAS FOUND	 TRAPPED IN THE ONLY AREA OF CORRSION.  THIS CORROSION WAS VERY DEEP AND WAS IN THE VOID BETWEEN THE UPPER AND LOWER BUS	HINGS.			2	L	7	2 	4F			RT	A12EA   					 
2003091800071	20030918	00071	WP  	2003	9	18	N32B2001004      	1	20010910	G	5713		STRINGER        			DOUG  	DC6   	DC6A        	3021706	WP  	PWA   	R2800 	R2800*      	52026	NE  					STA17, LT WING	CRACKED         	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	7780B	21494				45372				STRINGER 17 CRACKED AT WING, STA 140.  REPAIRED 17 AT WING STA L40 IAW NAC 2001-05.						2	L	7	4 	4R	4	R	 	6A3     	5E8				 
2001092400178	20010924	00178	CE  	2001	9	24	N988ME           	1	20010918	G	2752	505211516	PISTON          	BEECH       		BEECH 	B300  	B300        	1159232	CE  										RT FLAP ACTUATOR	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	988ME	4611 			935A91					RIGHT OUTBOARD FLAP ACTUATOR CRACKED AT BASE OF PISTON WHERE THE END PLUG IS ATTACHED.  THE CRACK WAS 1.5 INCHES LONG AN	D RESULTED IN THE LOSS OF THE LUBRICATING OIL FROM OUT OF THE PISTON AND SCREW ASSEMBLY.  THE LOSS OF OIL WAS THE FIRST 	INDICATION OF A PROBLEM, AND IT WAS WHILE INVESTIGATING THE OIL LEAK THAT THE CRACK WAS DISCOVERED.THIS CRACK COULD RESU	LT IN A SIGNIFICANT LOSS OF STRUCTURAL STRENGTH OF THE ACTUATOR WHICH COULD RESULT IN THE STRUCTURAL FAILURE OF THE ACTU	ATOR ASSEMBLY.		2	L	7	2 	4T			RT	A24CE   					 
2001052400007	20010524	00007	NE  	2001	5	24	NE032001B2128    	2	20010330	G	7260		BEARING         	HAMSTD      		SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GEARCASE	CRACKED         	D			MHMF	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		20743			UDAG0844		GEE785555			UPON DISASSEMBLY OF GEARCASE FOUND THE RIGHT AFT BEARING AND FORWARD ROLLER BEARING CRACKED.  ALSO THE LEFT IDLER BEARIN	G WAS FOUND WITH BRINNELLING/SPALLING ON RACEWAYS.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE				 
2001092400179	20010924	00179	CE  	2001	9	24	NMO192           	1	20010912	G	3230	S217830144	HOSE            			CESSNA	210   	T210L       	2073449	CE  										NOSE GEAR	FAILED          	G				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			NM	01	6721M	3000 	34   			21061137				DURING LANDING, NOSE GEAR EXTENDED AND LOCKED, BUT MAIN GEAR DID NOT LOCK INTO PLACE. PILOT TRIED TO LOCK MAIN GEAR USIN	G HAND HYDRAULIC PUMP WITH NO SUCCESS. AIRCRAFT LANDED WITH LOCKED NOSE GEAR AND COLLAPSED MAIN GEAR. SUFFERED DAMAGE TO	 REAR OF FUSELAGE, LEFT ELEVATOR, AND LEFT HORIZONTAL STABILIZER. INVESTIGATION FOUND FAILED  NOSE GEAR HYDRAULIC FLEX L	INE. THE FAILURE OF THIS LINE ALLOWED EXHAUSTION OF LANDING GEAR HYDRAULIC FLUID AFTER THE NOSE GEAR EXTENDED AND LOCKED	, PREVENTING THE MAIN GEAR FROM LOCKING INTO PLACE.CONDITIONAL PART FAILURE. NO HISTORY NOTED IN AIRCRAFT MAINTENANCE RE	CORDS ASSOCIATED WITH NOSE GEAR HYDRAULIC HOSE REPLACEMENT SINCE 1976.	1	H	7	1 	3O			 	3A21    					 
2001040900520	20010409	00520	GL  	2001	4	9	NWOR140K         	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  					BJ567		INSPECTION FOUND CRACKS AT TRAILING EDGE SIDE OF RETENTION AREA.																5	C	P6EA	 
2001040900521	20010409	00521	GL  	2001	4	9	NWOR140K1        	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  					BJ567		INSPECTION FOUND CRACK ALONG LEADING EDGE SIDE OF RETENTION AREA.																5	C	P6EA	 
2001040900493	20010409	00493	GL  	2001	4	9	NWOR140K2        	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  					560		DURING INSPECTION, CRACK FOUND ALONG TRAILING EDGE OF RETENTION AREA OF BLADE.																5	C	P6EA	 
2001040900540	20010409	00540	GL  	2001	4	9	NWOR140K3        	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  					560		DURING INSPECTION CRACK WAS FOUND ALONG TRAILING EDGE OF RETENTION AREA.																5	C	P6EA	 
2001040900551	20010409	00551	GL  	2001	4	9	NWOR140K4        	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  					560		ON INSPECTION 4.5 INCH CRACK WAS FOUND ON TRAILING EDGE SIDE OF BLADE RETENTION AREA.																5	C	P6EA	 
2001040900552	20010409	00552	GL  	2001	4	9	NWOR140K5        	3	20010301	G	6111	V8433NS4	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			490  							FOUND 3.5 INCH CRACK ALONG TRAILING EDGE SIDE OF RETENTION AREA OF BLADE.																5	C	P6EA	 
2001040900163	20010409	00163	EA  	2001	4	9	NX4200315        	2	20010207	G	8550	78531	PUMP            								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE OIL	DEFECTIVE       	B			NX42	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		2177 					L2780951A			WHEN REASSEMBLING THE OIL PUMP, IT WAS NOTED THAT DESPITE ATTEMPTS TO CENTER THE OIL PUMP BODY, THE IMPELLERS WOUL BIND 	WITH TORQUE APPLIED TO THE HOUSING.  ALL DIMENTIONAL INSPECTIONS WERE WITHIN LIMITS.  THE PROBLEM DISAPPEARED AFTER REPL	ACING THE COMBINATION OF THE OIL PUMP HOUSING AND DRIVEN IMPELLER.  IT IS ASSUMED THAT THERE WAS A MACHING ALIGNMENT ERR	OR IN THE HOUSING, DRIVEN IMPELLER SHAFT, OR POSSIBLY A COMBINATION OF BOTH.								3	O			1E10				 
2001040900159	20010409	00159	EA  	2001	4	9	NX4200420        	2	20010207	G	8520	LW16711	BEARING         								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DEFECTIVE       	B			NX42	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		2179 					L2780651A			DURING ENGINE DISASSEMBLY FOR ROUTINE OVERHAUL IT WAS NOTED THAT SOME NR 3 MAIN BEARING SURFACE MATERIAL HAD RELEASED FR	OM THE BEARING SHELL.										3	O			1E10				 
2001040900160	20010409	00160	EA  	2001	4	9	NX4200440        	2	20010207	G	8520	LW13884	MAIN BEARING    								LYC   	IO360 	IO360L2A    	 	EA  					ENGINE	DEFECTIVE       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15		2169 					L2784651A			DURING ENGINE DISASSEMBLY FOR ROUTINE OVERHAUL IT WAS NOTED THAT SOME NR 2 MAIN BEARING SURFACE MATERIAL HAD RELEASED FR	OM THE BEARING SHELL.										3	O			1E10				 
2001121300020	20011213	00020		2001	12	13	O3HR111501       	4	20011115	G	2564		INLET           																	LIFE RAFT	OBSTRUCTED      	B			O3HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										DURING SCHEDULED MAINTENANCE INSPECTION ON RAFT (PN 64449101, SN 0150), IT WAS NOTED THAT ONE COMPARTMENT INFLATED AT A 	FASTER RATE THAN THE OTHER, SUBSEQUENT INSPECTION REVEALED A FOREIGN OBJECT BLOCKING THE INLET PORT.  THE DEBRIS APPEARS	 TO BE INTERNAL HOSE MATERIAL, WHICH ACCUMULATED DURING THE MANUFACTURING PROCESS.  RECOMMENDATION:  INSPECT HOSE ASSEMB	LIES INTERNALLY PRIOR TO BUILD UP OF MANIFOLD. MANIFOLD ASSY PN BREAKDOWN: HOSE 64457-101    (1 EA) , HOSE 64457-103    	(2 EA))															 
2002011800055	20020118	00055	WP  	2002	1	18	OMNIDMR01        	1	20011220	G	5302	369D23601501	STRUCTURE       			HUGHES	369   	369D        	4470706	WP  										HORIZONTAL STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	86ST					711012D				HORIZONTAL STABILIZER CRACKED ON TRAILING EDGE AND TRIM TAB CRACKED ON LEADING EDGE DUE TO EXCESS FLUTTER.  CRACKING CON	CENTRATED AROUND AREA OF DAMPER WEIGHTS. TABS WERE TOO LONG AND ARE SUPPORTED ONLY BY RIVETS LOCATED ON LEADING EDGE,THE	 DAMPER WEIGHTS ADDED TO COMPENSATE. THE WEIGHTS NOT FLUSH TO TAB CREATES EXCESSIVE DRAG AND FURTHER CONTRIBUTES TO EXCE	SSIVE VIBRATION.   THE EXCESSIVE FLUTTER COMMON IN 369 SERIES.			1	G	7	1 	3U			 	H3WE    					 
2002011800056	20020118	00056	WP  	2002	1	18	OMNIDMR02        	1	20010917	G	5302	421087505	STRUCTURE       			HUGHES	369   	369E        	4470707	WP  										HORIZONTAL STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7065C									HORIZONTAL STABILIZER CRACKED ON TRAILING AND TRIM TAB CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER. CRACKING IS CON	CENTRATED AROUND AREA FO DAMPER WEIGHTS.  TABS WERE TOO LONG AND ONLY SUPPORTED BY RIVETS LOCATED ON LEADING EDGE, THE D	AMPER WEIGHTS ADDED TO COMPENSATE. THE WEIGHTS ARE NOT FLUSH TO TAB AND CREATES EXCESSIVE DRAG AND FURTHER CONTRIBUTES T	O EXCESSIVE VIBRATION. THE EXCESSIVE FLUTTER IS COMMIN 369 SERIES.  PROBLEM HAS BEEN IDENTIFIEDIN SERVICE NOTICE EN-44 (	REWORK OF HORIZONTAL STABILIZER ASSEMBLY)		1	G	7	1 	3U			 	H3WE    					 
2002011800057	20020118	00057	WP  	2002	1	18	OMNIDMR03        	1	20010807	G	5302	421087905	STRUCTURE       			HUGHES	369   	369E        	4470707	WP  										HORIZONTAL STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	440TJ					0099990812				HORIZONTAL STABILIZER IS CRACKED ON TRAILING EDGE AND TRIM TAB IS CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER.CRACK	ING IS CONCENTRATED AROUND AREA OF DAMPER WEIGHTS.  TABS WERE TOO LONG AND ONLY SUPPORTED BY RIVETS LOCATED ON LEADING E	DGE, CAUSING EXCESSIVE FLUTTER DURING FLIGHT; THE DAMPER WEIGHTS WERE ADDED TO CONPENSATE.  THESE WEIGHTS ARE NOT FLUSH 	TO TAB, CREATING EXCESSIVE DRAG ON TABS AND FURTHER CONTRIBUTES TO EXCESSIVE VIBRATION.  THIS EXCESSIVE FLUTTER IS COMMO	N IS THE 369 SERIES.  PROBLEM HAS BEEN IDENTIFIED IN SERVICE NOTICE EN-44		1	G	7	1 	3U			 	H3WE    					 
2002011800058	20020118	00058	EU  	2002	1	18	OMNIDMR04        	1	20011214	G	5302	421087503	STRUCTURE       			HUGHES	369   	369FF       	4470709	EU  										HORIZONTAL STAB	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	30042					0099990855				HORIZONTAL STABILIZER CRACKED ON TRAILING EDGE ABD TRAIM TAB CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER.  CRACKING	 IS CONCENTRATED AROUND AREA OF DAMPER WEIGHTS.  TABS WERE TOO LONG AND ONLY SUPORTED BY RIVET ON THE LEADING EDGE, CAUS	ING EXCESSIVE FLUTTER DURING FLIGHT; THE DAMPER WEIGHTS ARE NOT FLUSH TO THE TAB CREATING EXCESSIVE DRAG ON THE TABS AND	 FURTHER CONTRIBUTES TO THE EXCESSIVE VIBRATION.  THIS EXCESSIVE FLUTTER IS COMMON IN THE 369 SERIES,  AND HAS BEEN IDEN	TIFIED IN SERVICE NOTICE FN-29.1		1	G	7	1 	3U			 	H3WE    					 
2001050200051	20010502	00051	SO  	2001	5	2	PNSA010201       	1	20010227	G	3297		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  										MLG INDICATOR	DAMAGED         	E			PNSA	A				UNSCHED LANDING         				N			FALSE WARNING             			DE	DESCENT        	1			AL	03	28KE					318152049				AFTER SELECTING GEAR DOWN, LT DOWN LIGHT DID NOT ILLUMINATE. RETURNED TO BASE. REPAIRED WIRE ON LH DOWN LIGHT SWITCH. OP	S CHECKED OK.					1	L	7	2 	3O			 	A20SO   					 
2001050200052	20010502	00052	SO  	2001	5	2	PNSA010203       	1	20010228	G	6120		CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										PROP CONTROL	FAILED          	E			PNSA	C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AL	03	3588Z					318052130				DURING TAKE-OFF ROLL RT ENGINE DID NOT DEVELOPE FULL RPM. ABORTED TAKE-OFF RETURNED FOR MAINTENANCE. REPLACED PROP CONTR	OL CABLE DUE TO INTERNAL FAILURE.					1	L	7	2 	3O			 	A20SO   					 
2001041000013	20010410	00013	SO  	2001	4	10	PNSA010205       	1	20010201	G	3297		WIRE            			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	BROKEN          	E			PNSA	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	3588Z					318052130				DURING CLIMB PILOT COULD NOT PLACE THE GEAR LEVER IN THE UP POSITION. RETURNED TO BASE FOR MAINTENANCE. REPAIRED BROKEN 	WIRE ON GEAR ANTI RETRACT SOLENOID.					1	L	7	2 	3O			 	A20SO   					 
2001091800135	20010918	00135	EA  	2001	9	18	PNSA010506       	2	20010501	G	7322	25245009	SERVO           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	FAILED          	A			PNSA	C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AL	03	3588Z					318052130	L840061A			LT ENGINE WOULD NOT DEVELOP TAKEOFF POWER.  ABORTED TAKEOFF.  RETURNED FOR MAINTENANCE.  REPLACED FUEL SERVO.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA				 
2001050200053	20010502	00053	NE  	2001	5	2	R004765          	3	20010313	G	6114	D51105	FORK            			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	HUB	BROKEN          	B			SJ3R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	05	SJ3R	2503 	2503 					HL327		THE PROPELLER WAS RECEIVED FOR COMPLAINT OF VIOLENT VIBRATION. AFTER DISASSEMBLY, INSPECTION REVEALED C7075 BLADE BEARIN	GS BROKEN, BEARINGS FRAGMENTS EMBEDDED IN BLADE SOCKETS 3, 4 & 6, COMPLOSITE WINDING DAMAGE TO BLADE NR 6, BLADE NR 6 FO	RK SLOT THIN WALL SIDE BROKEN ON FORK  CAM FOLLOWER AND RETENTION WASHER DAMAGED BEYOND LIMITS ON BLADE NR 6 PITCH CHANG	E BRACKET, BLADE NR 6 PITCH CHANGE BRACKET BOLTS FAILED INCOMMING TORQUE TEST.			2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2001050200054	20010502	00054	NE  	2001	5	2	R004808          	3	20010315	G	6114	C7075	BEARING         			DORNER	DO32  	DO328100    	2996000	NM  	PWA   	119   	PW119B      	 	NE  	HARTZL	HDE6C	HDE6C3B     	NE  	HUB	BROKEN          	B			SJ3R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	05	SJ3R	1724 						HL87		THE PROPELLER WAS RECEIVED FOR COMPLAINT OF EXCESSIVE VIBRATION. AFTER DISASSEMBLY, INSPECTION REVEALED C7075 BLADE BEAR	INGS BROKEN, BEARING FRAGMENTS FOUND IN HUB BLADE SOCKETS 2 THROUGH 6, COMPOSITE WINDING DAMAGE TO BLADES 2 THROUGH 4, B	LADE NR 4 FORK SLOT THIN WALL SIDE BRIKEN ON FORK CAM FOLLOWER AND B-475 RETENTION WASHER DAMAGED BEYOND REPAIR ON BLADE	 NR 4 PITCH CHANGE BRACKET, PITCH CHANGE BRACKET BOLTS FAILED TORQUE TEST ON BLADES 3 & 4.			2	H	7	2 	4T	4	T	RT	A45NM   	E20NE	6	C	P34NE	 
2002012900020	20020129	00020	SW  	2002	1	29	R20888           	1	20011108	G	3710		SCREW           			MOONEY	M20   	M20J        	5870219	SW  										FILTER ATTACH	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	300YB					243010				INSTRUMENT AIR FILTER ATTACHING SCREW CORRODED AND CAUSES METAL DEBRIS TO ENTER VACUUM SYSTEM UNFILTERED.						1	L	7	1 	3O			 	2A3     					 
2001092500017	20010925	00017	NE  	2001	9	25	R3R220010621     	2	20010618	G	7200	3015537	SEAL            	PWA         		CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 2 ENGINE	LEAKING         	B			R3R2	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	01	586RE				PT285	5500199	PCE70585			FOUND HYDRAULIC PUMP DRIVE PAD ON ENGINE NR 2 LEAKING.  NEWLY INSTALLED SEAL I.D. FOUND APPROX. .015 INCH TOO LARGE FOR 	SHAFT IT IS SUPPOSED TO SEAL.  SHAFT DIAMETER: 0.865 INCH, SEAL ID: 0.880 INCH.  THIS PROBLEM OCCURRED WITH AT LEAST SIX	 SEALS BEFORE ONE WAS FOUND WITH THE CORRECT "TIGHT" FIT ON THE DRIVE SHAFT.				1	L	7	2 	4F	4	F	 	A22CE   	E1NE				 
2001030700604	20010307	00604		2001	3	7	R7MR291732569    	4	20010108	G	2311	TFM403G	TRANSCEIVER     			SNIAS 	350   	AS350B2     	8680813	EU  										UHF/FM TRANS	FAILED          	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	97LG					2917				UNIT FAILED UPON INSTALLATION.  UNACCEPTABLE SIDETONE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001030700606	20010307	00606	EU  	2001	3	7	R7MR325232577    	1	20010119	G	2460	SS120	INVERTER        			SNIAS 	350   	AS350B3     	8680954	EU  										ELELCTRICAL	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	392LG	374  				3252				UNIT INOPERATIVE.  NO AC OUT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001030700605	20010307	00605	NM  	2001	3	7	R7MR32573        	1	20010110	G	3150	900A3720002111	DISPLAY         			DOUG  	MD900 	MD900       	3027375	NM  										COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	75   				90000012				UNIT INOPERATIVE.  ROW OF LIGHTS ON ALPHA DISPLAY MISSING.						1	G	7	2 	3U			NC	H19NM   					 
2001030700608	20010307	00608	NE  	2001	3	7	R7MR32581        	2	20010115	G	7230	70BM035420	COMPRESSOR      			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	SEIZED          	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	97LG	413  				2917				COMPRESSOR SEIZED.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001030700609	20010307	00609	NE  	2001	3	7	R7MR32582        	2	20010115	G	7230	70BM025020	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COMPRESSOR	FAILED          	B			R7MR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	97LG	413  				2917				COMPRESSOR BLADE WILL NOT ROTATE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001030700636	20010307	00636		2001	3	7	R7MR32592        	4	20010117	G	2312	064010540030	TRANSCEIVER     			SNIAS 	350   	AS350B3     	8680954	EU  										VHF RADIO	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	848  				3128				UNIT INOPERATIVE.  BREKS SQUELCH ON ITS OWN.  REPLACED WITH NEW UNIT,  CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001030700635	20010307	00635	EU  	2001	3	7	R7MR32595        	1	20010117	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	INOPERATIVE     	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	527RM	53   				7111				UNIT INOPERATIVE.  NO INDICATION WHILE ENGINE IS RUNNING.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U			 	H13EU   					 
2001040500116	20010405	00116	NM  	2001	4	5	R7MR32618        	1	20010126	G	6710	900C3820021105	ACTUATOR        			DOUG  	MD900 	MD900       	3027375	NM  										M/ROTOR CONTROL	LEAKING         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	1926 				90000012				HYDRAULIC UNIT, DUAL SERVO ACTUATOR, MR CONTROL LEAKING BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PR	OBLEMS.					1	G	7	2 	3U			NC	H19NM   					 
2001040500123	20010405	00123	NM  	2001	4	5	R7MR32619        	1	20010127	G	2916	900H3821502107	GAUGE           			DOUG  	MD900 	MD900       	3027375	NM  										HYD RESERVOIR	LOOSE           	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	901CF	2625 				90000012				SIGHT GAUGE RIBBON WILL NOT STAY ATTACHED AT BOTTOM OF INDICATOR TUBE, WHICH RENDERS THE QUANTITY OF HYDRAULIC FLUID IN 	THE RESERVOIR UNRELIABLE.  REPLACED WITH NEW  UNIT, CORRECTED PROBLEM.					1	G	7	2 	3U			NC	H19NM   					 
2001040500117	20010405	00117	EU  	2001	4	5	R7MR32629        	1	20010102	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	PEELING         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	97LG	73   				2917				PAINT PEELING.  REPLACED WITH NEW UNIT CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900190	20010409	00190	EU  	2001	4	9	R7MR32643        	1	20010104	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					PITCH CONTROL	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	103LN	310  				3128				PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900006	20010409	00006	EU  	2001	4	9	R7MR32651        	1	20010128	G	2460	SP461310	SWITCH          			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					DC SYSTEM	WORN            	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	117SU	1080 				7527				TOGGLE SWITCH WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU				 
2001050300230	20010503	00230	EU  	2001	5	3	R7MR32654        	1	20010111	G	8000	845UN1Q4AA5F	SWITCH          			SNIAS 	350   	AS350B3     	8680954	EU  										STARTER	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52281	541  				3249				UNIT INOPERATIVE.  REMOVED AND REPLACED WITH NEW UNIT,  CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900007	20010409	00007	EU  	2001	4	9	R7MR32656        	1	20010226	G	6320	ZARISEC135	TRANSMISSION    			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	COLLAPSED       	B			R7MA	K				NONE                    				L			NO TEST                   			NR	NOT REPORTED   	1			NM	07	135SJ	594  				EC1350054				MAIN ROTOR TRANSMISSION COLLAPSED.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900009	20010409	00009	EU  	2001	4	9	R7MR32657        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	946  				EC1350054				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  THE REPLACEMENT DAMPER HAS LES	S THAN 1 YEAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900010	20010409	00010	EU  	2001	4	9	R7MR32658        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	946  				EC1350054				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  SPLITLINE CRACK LONGER THAN 40MM.  REPLACED WITH NEW UNIT, CORRECTED PROBL	EM NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900020	20010409	00020	EU  	2001	4	9	R7MR32659        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  SPLITLINE CRACK LONGER THAN 40MM.  REPLACED WITH NEW UNIT, CORRECTED PROBL	EM.  NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900021	20010409	00021	EU  	2001	4	9	R7MR32660        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  SPLITLINE CRACK LONGER THAN 40MM.  REPLACED WITH NEW UNIT, CORRECTED PROBL	EM.  NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900023	20010409	00023	EU  	2001	4	9	R7MR32661        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				REPLACED WITH LOWER DAMPER.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 Y	EAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900024	20010409	00024	EU  	2001	4	9	R7MR32662        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				REPLACED WITH LOWER DAMPER.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 Y	EAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900025	20010409	00025	EU  	2001	4	9	R7MR32663        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				REPLACED WITH LOWER DAMPER.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  NOTE:  THE REPLACEMENT DAMPER HAS LESS THAN 1 Y	EAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900029	20010409	00029	EU  	2001	4	9	R7MR32664        	1	20010228	G	6220	L621M1003101	DAMPER          			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	135SJ	390  				EC1350054				SPLITLINE CRACK LONGER THAN 40MM.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.  NOTE: THE REPLACEMENT DAMPER HAS LESS THA	N 1 YEAR TO SERVICE LIFE.					1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001040900326	20010409	00326	SO  	2001	4	9	R7MR32667        	1	20010125	G	6410	704A33633171	HINGE           			EMB   	120   	EMB120      	3260201	SO  										TAIL ROTOR	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92GL	460  				120092				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A33-2153-00, CORREC	TED PROBLEM.  2 TEETERING BEARINGS EQUALS 1 KIT.					2	L	7	2 	4T			RT	A31SO   					 
2001040900031	20010409	00031	EU  	2001	4	9	R7MR32670        	1	20010125	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	460  				2575				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A09-1036-01 CORRECT	ED PROBLEM.  4 HALF SHELLS EQUALS 1 KIT.					1	G	7	1 	3U			 	H9EU    					 
2001040900032	20010409	00032	EU  	2001	4	9	R7MR32671        	1	20010105	G	6410	704A33633116	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					TAIL ROTOR	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	94LG	649  				2728				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A09-1036-01, CORREC	TED PROBLEM.  4 HALF SHELLS EQUALS 1 KIT.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900038	20010409	00038	EU  	2001	4	9	R7MR32675        	1	20010130	G	6220	704A3363320851	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  										M/R STARFLEX	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	1203 				2575				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900039	20010409	00039	EU  	2001	4	9	R7MR32676        	1	20010130	G	6220	704A3363320851	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  										M/R STARFLEX	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	1203 				2575				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900377	20010409	00377	EU  	2001	4	9	R7MR32677        	1	20010130	G	6220	704A3363320851	STOP            			SNIAS 	350   	AS350B2     	8680813	EU  										M/R STARFLEX	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	1203 				2575				ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900046	20010409	00046	EU  	2001	4	9	R7MR32683        	1	20010204	G	2932	MA12401	PRESSURE SWITCH 			SNIAS 	350   	AS350B2     	8680813	EU  										HYD SYSTEM	INOPERATIVE     	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	12   				2575				PRESSURE SWITCH INOPERATIVE.  HYDRAULIC LIGHT GOES OUT WHEN SWITCH IS TAPPED.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM	.					1	G	7	1 	3U			 	H9EU    					 
2001040900157	20010409	00157	EU  	2001	4	9	R7MR32697        	1	20010127	G	6230	350A37112602	SCISSORS        			SNIAS 	350   	AS350B2     	8680813	EU  										SWASHPLATE	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	460  				2575				WORN BEYOND SERVICEABLE LIMITS.  SCARRED BUSHING.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900158	20010409	00158	EU  	2001	4	9	R7MR32698        	1	20010127	G	6230	704A33640021	SPACER          			SNIAS 	350   	AS350B2     	8680813	EU  										SWASHPLATE	WORN            	C			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	92LG	460  				2575				WORN BEYOND SERVICEABLE LIMITS.  REPLACED WITH NEW UNITS, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001040900211	20010409	00211		2001	4	9	R7MR32704        	4	20010221	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	193  				3268				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900215	20010409	00215		2001	4	9	R7MR32706        	4	20010202	G	3416	150201182	ALTIMETER       			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	175  				3268				UNIT INOPERATIVE.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900238	20010409	00238	NE  	2001	4	9	R7MR32713        	2	20010222	G	7261	350A54113800	TUBE            			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					AIR OIL VENT	CRACKED         	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	91   				3268				CRACKED BEYOND SERVICABLE LIMITS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001040900240	20010409	00240		2001	4	9	R7MR32716        	4	20010103	G	3160	B19030MC02	DISPLAY         			SNIAS 	350   	AS350B3     	8680954	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					COCKPIT	INOPERATIVE     	B			R7MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	397LG	163  				3268				UNIT INOPERATIVE.  WILL NOT TRANSFER INFORMATION BETWEEN SCREENS.  REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU				 
2001112700026	20011127	00026	CE  	2001	11	27	RASFTYRK178      	1	20011113	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	708TA	3367 				RK178				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR	OX 50 PERCENT THROUGH THE LOWER HALF.					2	H	7	2 	4F			RT	A16SW   					 
2001112700028	20011127	00028	CE  	2001	11	27	RASFTYRK180      	1	20011113	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	709TA	3201 				RK180				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR	OX 75 PERCENT THROUGH THE LOWER HALF.					2	H	7	2 	4F			RT	A16SW   					 
2001112700029	20011127	00029	CE  	2001	11	27	RASFTYRK183      	1	20011113	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	710TA	3195 				RK183				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR	OX 75 PERCENT THROUGH THE LOWER HALF.					2	H	7	2 	4F			RT	A16SW   					 
2001112700030	20011127	00030	CE  	2001	11	27	RASFTYRK189      	1	20011113	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	715TA	3107 				RK189				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR	OX 80 PERCENT THROUGH THE LOWER HALF.					2	H	7	2 	4F			RT	A16SW   					 
2002011000092	20020110	00092	CE  	2002	1	10	RASFTYRK195      	1	20011231	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	718TA	2992 				RK195				CRACK FOUND IN LT FORWARD ENGINE MOUNT BRACKET WHILE PERFORMING FLUORESCENT PENETRANT INSPECTION AS PER RAYTHEON AIRCRAF	T SAFETY COMMUNIQUE NR 189.					2	H	7	2 	4F			RT	A16SW   					 
2002011000093	20020110	00093	CE  	2002	1	10	RASFTYRK198      	1	20011127	G	7120	45A34361005	MOUNT BRACKET   			BEECH 	MU300 	400A        	1155402	CE  										LT ENGINE	CRACKED         	B			ERY2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	798TA	2805 				RK198				WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR	OX 75 PERCENT THROUGH THE LOWER HALF.					2	H	7	2 	4F			RT	A16SW   					 
2001092500023	20010925	00023	CE  	2001	9	25	RFS20011         	1	20010808	G	3233	NAS464P4A29	BOLT            	CESSNA      		CESSNA	210   	210K        	2073446	CE  										MLG ACTUATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8142G	5891 			1781	21059442				WHILE REPLACING THE RT MLG ACTUATOR AS PART OF COMPIANCE WITH CESSNA SEB01-2, IT WAS DISCOVERED THAT ONE OF THE THREE NA	S ATTACH BOLTS WAS BROKEN.IT WAS ONLY BEING HELD IN PLACE BY THE SAFETY WIRE LINKING THE THREE BOLTS.  THE BOLT HAD FAIL	ED BETWEEN THE FIRST AND SECOND THREADS COUNTING FROM THE SHANK OF THE BOLT.  PROCURED AND INSTALLED 3EA NEW NAS BOLTS T	O CORRECT.			1	H	7	1 	3O			 	3A21    					 
2001092500032	20010925	00032	NE  	2001	9	25	RO               	2	20010820	G	7230	30756441	CARBON SEAL     	ALIDSG      		AMD   	FALC90	FALCON900EX 	2730009	EU  	GARRTT	TFE731	TFE73160    	 	NE  					HP CASE	BROKEN          	B				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	99		1101 			NA	N990WM	112239			THE NR 4 CARBON SEAL CERAMIC RING WAS FOUND TO BE BROKEN DURING THE ENGINE TEARDOWN. THE CARBON RING SEAL WAS ALSO FOUND	 BROKEN. THERE WAS MUCH COLLATERIAL DAMAGE. THE OPERATOR REPORTED OIL LOSS DURING FLIGHT WITH SUBSEQUENT OIL CONTAMINATI	ON UPON POST FLIGHT ENGINE EXAMINATION. THERE WILL BE AN ENGINE CONDITION REPORT GENERATED TO DETAIL THE FINDINGS POST A	NALYTICAL INSPECTION.			2	L	7	3 	4F	4	F	RT	A46EU   	E1NM				 
2001092500034	20010925	00034	WP  	2001	9	25	RO462097         	2	20010905	G	7230	30745557	STATOR          			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   	 	WP  					COMPRESSOR	SEPARATED       	B				C				ABORTED TAKEOFF         				M	Y		OVER TEMP                 	ENGINE STOPPAGE           		TO	TAKEOFF        	1			SW	99		2462 					95146			ENGINE RETURNED FOR MAINTENANCE WHEN AIRCRAFT WAS EXPERIENCING ENGINE TEMPERATURE LIMIT AT TAKE OFF AND SUBSEQUENT HUNG 	STARTS.  THE INNER HUB OF THE 4TH LOW COMPRESSOR STATOR WAS FOUND SEPARATED DURING ENGINE MAINTENANCE DISASSEMBLY.  MAJO	R ENGINE COMPONENT DOWNSTREAM DAMAGE OCCURED AS SECONDARY DAMAGE.  ENGINE MANUFACTURER NOTIFIED OF THIS UNIQUE FINDINGS.				2	L	7	3 	4F	4	F	RT	A46EU   	E6WE				 
2001042400282	20010424	00282	SO  	2001	4	24	RX8R2001001      	1	20010413	G	5280	4252931	SKIN            			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG DOOR	DEBONDED        	B			RX8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	RX8R	5203 	11   			425501038	PCE99080	BU10583		AFTER LANDING IT WAS NOTICED THAT THE RIGHT INBOARD LANDING GEAR DOOR SKIN HAD PEELED OFF FROM THE REST OF THE DOOR AT T	HE LEADING EDGE. UPON FURTHER EXAMINATION THE DOOR SKIN AND SUPPORTING STRUCTURE WHICH ARE BONDED TOGETHER WITH STRUCTUR	AL ADHESIVE SHOWED CORROSION AT THE BONDING SURFACE ON BOTH THE DOOR SKIN AND THE DOOR STRUCTURE. OPERATORS OF PA42-720 	AIRCRAFT MAY WANT TO INSPECT THE LEADING EDGE OF THE INB. LNDG. DOORS FOR CORROSION AND SEPARATION OF THE SKIN.  			1	L	7	2 	4T	4	T	 	A23SO   	E4EA	6	C	P15EA	 
2001050300041	20010503	00041	EU  	2001	5	3	RYMR32642        	1	20010106	G	6420	350A33214501	CONTROL ROD     			SNIAS 	350   	AS350B3     	8680954	EU  										PITCH CONTRL	WORN            	B			R7MA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	52285	505  				3251				WORN BEYOND SERVICEABLE LIMITS.  REMOVED AND REPLACED WITH NEW UNIT, CORRECTED PROBLEM.						1	G	7	1 	3U			 	H9EU    					 
2001072400523	20010724	00523	NM  	2001	7	24	S012730131       	1	20010403	G	7100		FCU             			BOEING	747   	747209B     	       	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  							W			SAJF	E				ENGINE SHUTDOWN         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			WP	03		24628					725343			B-18771 #2 ENG FLAME OUT AT FL330,TAT -4C,EGT 352 DEG.C,EPR 1.02 & DROPPING,ENG SHUTDOWN,WINDMILLED APPROX. 1 MIN AT OIL	 PRESS 22 PSI,ENG WAS RESTARTED & OPERATED NORMALLAY.C/A:1.I.A.W AMM 71-00-43,MAIN FUEL FILTER AND EVBC FUEL FILTER INSP	ED NML AND REPLACED. 2.CHECKED EVBC PT3 AND PS3 WATER TRAP,NO WATER EVIDENCE FOUND. 3.PFMED FUEL TANKS WATER DRAINING. 4	.REPLACED FUEL CONTROL UNIT AND FUEL PUMP ASSY. 5.REPLACED FUEL HEATER DUE MOUNT BOLTS INSERT DAMAGED. 6.PFMED WINDMILLI	NG INSP,MAIN OIL FILTER AND ALL MAGNETIC CHIP DETECTORS INSPED NML. 7.ENG RUN-UP TEST WITH TAKEOFF POWER SATISFACTORY. 8	.AFTER TEST OF REMOVED PARTS FOR FINAL INVESTIGATION,THE MAIN CAUSE OF THE IFSD APPEARS TO BE A LEAN FCU ALONG WITH PO	2	L	7	4 	4F	4	F	RT	A20WE   	E3NE				 
2001061400019	20010614	00019	NE  	2001	6	14	S01472016        	2	20010426	G	7200		ENGINE          			BOEING	747   	747400      	       	NM  	PWA   	4056  	PW4056      	 	NE  					NR 4	FAILED          	W			SAJF	C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			WP	03		40413				24311	717621			COMPLETE REGISTRATION NUMBER (B18273) AFTER T/O THRUST HAS SET ON T/O ROLLING, LOUD BANG SOUND WAS HEARD, T/O IS ABORTED	 AT 110 KNOTS. (1) IAW FIM 71-00-00, ENGINE SURGE DURING FORWARD THRUST FIG 107 PERFORM ENGINE 4 INLET FAN BLADE, FAN CA	SE DUCT SEGMENTS, TURBINE EXHAUST AREA AND 6TH TURBINE BLADE INSP NORMAL. (2) BORESCOPE INSP (HPC 5,6,10TH STAGE AND HPT	 1,2ND STAGE:  LPT 3RD STAGE BLADE), CONDITION NORMAL. (3)2.5 AND 2.9 BLEED VALVE AND VSV SYS CHECK NORMAL.  (4 )REPLACE	D NR 4 ENGINE AND RUN UP CHECK NORMAL.		2	L	7	4 	4F	4	F	RT	A20WE   	E24NE				 
2001011102735	20010111	02735	CE  	2001	1	11	SAILJ1052        	1	20010102	G	3230	508200646	TORQUE TUBE     	RAYTHN      	NA          	BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6356C	5726 			NA	LJ1052				AIRCRAFT CAME INTO MAINTENANCE FOR SCHEDULED TBO OF THE LANDING GEAR MOTOR. THE MOTOR IS ATTACHED TO THE LANDING GEAR GE	ARBOX WHICH IS ALSO ATTACHED TO THE FAILED TORQUE TUBE. INSPECTION SHOWED NO EVIDENCE OF CORROSION. FAILURE AREA IS LOCA	TED AT AND AROUND THE ATTACH HARDWARE HOLES HOWEVER,INSPECTION REVEALED NO EVIDENCE OF IMPOPER INSTALLATION, ALIGNMENT, 	BINDING OR CONDITION THAT MIGHT BE ATTRIBUTE TO THE FAILURE. A COPY OF THIS REPORT WAS PROVIDED TO LOCAL FSDO 13 WEST CO	LUMBIA, SC. ASI/BOB SWITTER/ASI BILL ROBERTS FOR THEIR REVIEW. NO INCIDENT OR INJURY WAS INVOLVED.		1	L	7	2 	3T	4	T	 	3A20    	E4EA	6	C	P15EA	 
2001011100563	20010111	00563	NM  	2001	1	11	SROM200100001    	1	20010102	G	3230	65446916	HYDROMECH UNIT  			BOEING	737   	737205      	       	NM  										NLG	MALFUNCTIONED   	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733AR	6    				23466				DEPARTING ANC NOSE GEAR WOULD NOT RETRACT - STAYED DOWN & LOCKED - TRIED TWICE WITH SAME RESULTS.  RETURNED TO ANC LANDI	NG WT 111.7 SMOOTH LANDING.ACCOMPLISHED OVERWEIGHT LANDING INSPECTION PER M/M 5-51-291.  REPLACED NOSE GEAR HYD. MODULAR	 PACKAGE REF. MM 32-33-31.  REPLACED NOSE GEAR ACT. FLOW RESTRICTOR REF. MM 32-00.  REPLACED NG GRAVEL DEFLECTOR ACTU. R	EF. MM SUP. 32-23-22NOTE:  MODULAR PACKAGE REPLACED TO CORRECT PROBLEM - RESTRICTOR AND ACTUATOR REPLACEMENT WERE PRECAU	TIONARY.		2	L	7	2 	4F			 	A16WE   					 
2001011100589	20010111	00589	NM  	2001	1	11	SROM200100002    	1	20010104	G	3233		ACTUATOR        			BOEING	737   	737205      	       	NM  										NLG	FAILED          	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733AR					23466				AIR TURNBACK DUE TO NOSE GEAR WOULD NOT RETRACT  THIS IS A REPEAT EVENT THAT LAST HAPPENED 7 LANDINGS AGO.  REPLACED NOS	E GEAR LOCK MECHANISM AND SPRINGS, CONSISTING OF INDIVIDUAL ITEMS P/N 65-46245-4, 65-46242-11, 65-46240-13 & 69-6745-1, 	ALL WITH 1327 HOURS AND 1009 LANDINGS SINCE OVERHAUL.  REPLACED HYDRAULIC TRANSFER CYCLINDER P/N 69-14106-7 WITH 10 HOUR	S AND 7 LANDINGS SINCE OVERHAUL.  REPLACED LOCK ACTUATOR P/N 65-17819-14 WITH 1327 HOURS AND 1009 LANDINGS SINCE OVERHAU	L.  RE-RIGGED NOSE GEAR DOORS.  PERFORMED NORMAL RETRACTION AND EXTENSION TESTS.  PERFORMED EMERGENCY EXTENSION TEST.  A	LL TESTS NORMAL.	2	L	7	2 	4F			 	A16WE   					 
2001040900181	20010409	00181	NM  	2001	4	9	SROM200100003    	1	20010201	G	3350	58782	LEAD            			BOEING	737   	737205      	       	NM  										CABIN	FAILED          	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733AR		6    			23466				FLOOR TRACK LIGHTING - FORWARD CABIN INOP  REPLACED FORWARD TRACE STRIP.  OPS CHECKED OK FOUND OPEN IN ELECTRICAL CIRCUI	T OF STRIP.					2	L	7	2 	4F			 	A16WE   					 
2001040900061	20010409	00061	NM  	2001	4	9	SROM200100004    	1	20010202	G	3350	1010425	LENS            			BOEING	737   	737205      	       	NM  										CABIN	BROKEN          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP		3    			23465				OVERHEAD ENERGENCY LIGHT ROW 2 IS BROKEN  NOTE:  LENS ONLY BROKEN.  REPLACED UNIT P/N 10-1042-5.  EMER LT OPS CK GOOD.						2	L	7	2 	4F			 	A16WE   					 
2001050200050	20010502	00050	NM  	2001	5	2	SROM200100005    	1	20010308	G	3222	65737625	STRUT           			BOEING	737   	737290C     	138448V	NM  										NLR	DISCHARGED      	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	740AS	58172	3    			22578				AFTER TAKEOFF NOSE GEAR DID NOT LOCK UP, RED NOSE GEAR LIGHT ON, SYS A PRESURE NORMAL BUT FLUCTUATING SLIGHTLY AND ABNOR	MAL NOISES COMING FROM NOSE WHEEL, CYCLED GEAR DOWN  3 GREEN, RETRACTED SAME PROBLEM, LANDED NORMALLY.  FOUND NOSE STRUT	 FLAT, ACCOMPLISHED NOSE GEAR STRUT SERVICE PER TASK CARD 18232017.  ACCOMPLISHED GEAR RETRACT & FREE FALL TEST, OPS CHE	CKS GOOD, REMOVED NOSE GEAR JACK AND PAR.  CHANGES  SCHRADER VALVE.			2	L	7	2 	4F			 	A16WE   					 
2001050200062	20010502	00062		2001	5	2	SROM200100006    	4	20010319	G	3422	8221088001	INDICATOR       			BOEING	737   	737205      	       	NM  										COCKPIT	FAILED          	C			SROM	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AL	03	736BP	1    	1    			23465				DURING NORMAL CRUISE FLIGHT, 45 MINUTES INTO THE FLIGHT, THE FIRST OFFICIERS 5ATI EHSI WENT BLACK, FLICKERED BACK ON MOM	ENTARILY A FEW TIMES AND THEN STAYED BLACK.  THIS WAS A NEW DISPLAY ON ITS FIRST FLIGHT.  					2	L	7	2 	4F			 	A16WE   					 
2001041800298	20010418	00298	NM  	2001	4	18	SROM200100007    	1	20010223	G	5311	65582805	FRAME           			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING C CHECK INSPECTION,  FOUND CORROSION ON FRAME.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800299	20010418	00299	NM  	2001	4	18	SROM200100008    	1	20010223	G	5310	694820416	SHEAR TIE       			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING C CHECK,  FOUND CORROSION ON SHEAR TIE.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800300	20010418	00300	NM  	2001	4	18	SROM200100009    	1	20010223	G	5320	65582806	ANGLE           			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING C CHECK INSPECTION, FOUND LEVEL 1 CORROSION ON ANGLE.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800302	20010418	00302	NM  	2001	4	18	SROM200100010    	1	20010223	G	5313	6948948501	STRINGER        			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING C CHECK INSPECTION,  FOUND CORROSION ON STRINGER.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800303	20010418	00303	NM  	2001	4	18	SROM200100011    	1	20010307	G	5743	658276415	BEAM            			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT MLG	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	29717				23465				DURING C CHECK INSPECTION,   FOUND THE LEFT MLG BEAM HAS SEVERAL AREA OF LEVEL 1 CORROSION ON LOWER SURFACE AT PANEL MOU	NTING HOLES.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800309	20010418	00309	NM  	2001	4	18	SROM200100012    	1	20010310	G	5330		SKIN            			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	29717				23465				DURING C CHECK INSPECTION,  FOUND A CRACK IN THE FORWARD GALLEY DOOR (R1) EXTERIOR SKIN AT LOWER HINGE CUTOUT CRACKED AT	 UPPER CORNER.					2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800304	20010418	00304	NM  	2001	4	18	SROM200100013    	1	20010310	G	5330		SKIN            			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	29717				23465				DURING C CHECK INSPECTION,   FOUND A CRACK IN SKIN AT UPPER HINGE CUTOUT ON THE FORWARD GALLEY DOOR.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041800305	20010418	00305	NM  	2001	4	18	SROM200100014    	1	20010312	G	5330	6546881143	SKIN            			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	29717				23465				DURING C CHECK INSPECTION,   FOUND SKIN DAMAGE/CRACK AT THE FORWARD APU DOOR HINGE CUTOUT.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001041000272	20010410	00272	NM  	2001	4	10	SROM200100015    	1	20010312	G	5330	6546881143	SKIN            			BOEING	737   	737205      	       	NM  										FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP	29717				23465				DURING C CHECK INSPECTION FOUND SKIN DAMAGE/CRACK AT APU DOOR AFT HINGE CUTOUT.						2	L	7	2 	4F			 	A16WE   					 
2001041800306	20010418	00306	NM  	2001	4	18	SROM200100016    	1	20010313	G	5330	655298873	SKIN            			BOEING	737   	737205      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CRACKED         	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	736BP					23465				DURING C CHECK INSPECTION,   FOUND A SKIN CRACK AT AFT ENTRY DOOR (L2) CUTOUT (LOWER).						2	L	7	2 	4F	4	F	 	A16WE   	E2EA				 
2001042400266	20010424	00266	NM  	2001	4	24	SROM200100017    	1	20010323	G	5343	65465431	ATTACH FITTING  			BOEING	737   	737205      	       	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	3332 			23466				DURING C CHECK INSPECTION FOUND CORROSION ON BORE AND FACES OF BS 685 LUG, LT.  REPAIRED PER EA 5310-01930.						2	L	7	2 	4F			 	A16WE   					 
2001042400267	20010424	00267	NM  	2001	4	24	SROM200100018    	1	20010323	G	5330	654576960	SKIN            			BOEING	737   	737205      	       	NM  										FUSELAGE	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	3332 			23466				DURING C CHECK INSPECTION, FOUND LEVEL 1 CORROSION ON SKIN.  REPAIRED PER EA 5330-01517.						2	L	7	2 	4F			 	A16WE   					 
2001042400268	20010424	00268	NM  	2001	4	24	SROM200100019    	1	20010403	G	5720	656717217	FITTING         			BOEING	737   	737205      	       	NM  										LT WING	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	3332 			23466				DURING C CHECK INSPECTION, FOUND CORROSION ON ATTACH FITTING.  REPLACED FITTING PER MM 57-15-50.						2	L	7	2 	4F			 	A16WE   					 
2001042400269	20010424	00269	NM  	2001	4	24	SROM200100020    	1	20010321	G	5330	654577453	SKIN            			BOEING	737   	737205      	       	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	1704 			23466				DURING C CHECK INSPECTION, FOUND FUSELAGE EXTERNAL SKIN GOUGE BS 830 STRINGER 22 LT.  REPAIRED PER SRM 53-30-03 FIGURE 6	.					2	L	7	2 	4F			 	A16WE   					 
2001042400270	20010424	00270	NM  	2001	4	24	SROM200100021    	1	20010321	G	5330	654577453	SKIN            			BOEING	737   	737205      	       	NM  										FUSELAGE	GOUGED          	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	1704 			23466				DURING C CHECK INSPECTION, FOUND FUSELAGE EXTERNAL SKIN GOUGED AT BS 890 STRINGER 21 LT.  REPAIRED PER SRM 53-30-03 FIGU	RE 6.					2	L	7	2 	4F			 	A16WE   					 
2001042400271	20010424	00271	NM  	2001	4	24	SROM200100022    	1	20010323	G	5743	656717218	FITTING         			BOEING	737   	737205      	       	NM  										LT WING	CORRODED        	C			SROM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	733AR	29449	3332 			23466				DURING C CHECK INSPECTION AND MAIN LANDING GEAR TIME CHANGE,  FOUND FACES OF RT MLG I/B STABILIZER AFT MOUNT FITTING COR	RODED.  REPLACED FITTING PER MM 57-15-0/SOPM 20-50-01 DWG 65-82770.					2	L	7	2 	4F			 	A16WE   					 
2001092500035	20010925	00035		2001	9	25	SROM200100023    	4	20010522	G	3420	8221088001	DISPLAY         			BOEING	737   	737205      	       	NM  										COCKPIT	FAILED          	C			SROM	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			AL	03	736BP	299  	299  			23465				CAPTAINS 5 ATI EHSI FAILED IN CRUISE FLIGHT.  INSTUMENT DISPLAY WAS STILL PRESENTED, BUT WAS NON-FUNCTIONAL WITH A "DU F	AILURE" ANNUNCIATOR LIT.  REPLACEMENT UNIT CORRECTED THE PROBLEM.					2	L	7	2 	4F			 	A16WE   					 
2001092500036	20010925	00036	NM  	2001	9	25	SROM200100025    	1	20010712	G	3350	58209	LIGHT           			BOEING	737   	737205      	       	NM  										CABIN	DEFECTIVE       	C			SROM	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	733PA		6    			23466				L1 EXIT LIGHT AT BOTTOM RIGHT CORNER IS VERY DIM.  REPLACED BATTERY PACK AND LIGHT/LENS, ALSO REPAIRED BROKEN WIRE AT CO	NNECTOR.  PERFORMED OPS CHECK WITH NO AMBIENT LIGHT, BRIGHTNESS EQUAL TO OTHER EXIT SIGNS.					2	L	7	2 	4F			 	A16WE   					 
2001092500037	20010925	00037	NM  	2001	9	25	SROM200100026    	1	20010821	G	2910	106056342	LINE            			BOEING	737   	737205      	       	NM  										HYD SYSTEM	CHAFED          	C			SROM	H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AL	03	736BP		1    			23465				DURING NORMAL CRUISE FLIGHT LEFT "A" SYSTEM HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED, LEFT "A" SYSTEM PUMP TURNED OFF AN	D NOTICED QUNTITY WAS LOW, THEN "A" SYSTEM RIGHT SIDE STARTED TO FLUCUATE AND SHUT DOWN WITH RETURN TO ANC.  INSPECTION 	FOUND PRESSURE LINE CHAFFED THRU AT GENERATOR BLAST TUBE SUPPORT JUST AFT OF PUMP.  REPLACE LINE. AND ADDED CLAMP STAND 	OFF.  REPLACED CASE DRAIN FILTER WHICH WAS FOUND CLEAN.  OPS AND LEAK CHECKED GOOD.  REFILLED HYD SYSTEM.  REF. 29-11-41	.		2	L	7	2 	4F			 	A16WE   					 
2001100900035	20011009	00035	NM  	2001	10	9	SROM200100027    	1	20011008	G	5210	694070310	COVER           			BOEING	737   	737205      	       	NM  										PAX DOOR	BROKEN          	C			SROM	A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			AL	03	736BP		47   			23465				"EXTREMELY LOUD AIR LEAK FROM L1 DOOR.  RETURNED TO PANC."    INSP FOUND L-1 DOOR LOWER HINGE TOP TRIM PIECE HAD BROKEN 	LOOSE AND JAMMED IN DOOR HINGE.  REPLACED HINGE FLAP ASSY.  PRESS A/C NO LEAKS.					2	L	7	2 	4F			 	A16WE   					 
2002012900152	20020129	00152	NM  	2002	1	29	SROM200100028    	1	20011101	G	3233	6544604	ACTUATOR        			BOEING	737   	737205      	1384456	NM  										MLG	DEFECTIVE       	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733PA		1084 			23466				ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT NOSE GEAR WOULD NOT LOCK UP AFTER T/O.  CYCLED GEAR WITH SAME RESULTS.  NOSE GREEN 	LIGHT GOES OUT, BUT RED LIGHT STAYS ON WITH AIR NOISE HEARD.  GEAR LOCKED DOWN OK.    REMOVED AND REPLACED NOSE GEAR GRA	VEL DEFLECTOR ACTUATOR PER MM 32-23-22.  LUBED NOSE GEAR PER TASK CARD  18212000.  OPS CK PER TASK  18132003.  EMERGENCY	 EXTENSION CK GOOD.  FOUND STRUT FLAT SERVICED PER A/C PLACARD.			2	L	7	2 	4F			RT	A16WE   					 
2002012900153	20020129	00153	NM  	2002	1	29	SROM200100029    	1	20011123	G	3222	657376210	MODULE          			BOEING	737   	737205      	1384456	NM  										NLG	INTERMITTENT    	A			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733PA		2795 			23466				ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "ON DEPARTURE FROM ANCHORAGE NOSE WHEEL WOULD NOT RETRACT CYCLED GEAR ONCE, NOSE WH	EEL WOULD NOT RETRACT, RETURNED TO AIRPORT FOR OVERWEIGHT LANDING WAS SMOOTH AND NORMAL".  AIRCRAFT PLACED ON JACKS AND 	GEAR TESTED NORMAL.  AS PRECAUTION REPLACED NLG MODULAR PACKAGE, AND LUBED GEAR.  GEAR AGAIN TESTED NORMAL.				2	L	7	2 	4F			RT	A16WE   					 
2002013000022	20020130	00022	NM  	2002	1	30	SROM200100030    	1	20011125	G	3220	657376210	LANDING GEAR    			BOEING	737   	737205      	1384456	NM  										NOSE	INOPERATIVE     	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733PA		2796 			23466				ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF - RETURNED TO AIRPORT".						2	L	7	2 	4F			RT	A16WE   					 
2002013000023	20020130	00023	NM  	2002	1	30	SROM200100031    	1	20011213	G	3220	657376210	LANDING GEAR    			BOEING	737   	737205      	1384456	NM  										NOSE	CONTAMINATED    	C			SROM	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AL	03	733PA		2869 			23466				ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE GEAR RED LIGHT STAYED ON AFTER GEAR RETRACTION (GEAR SOUNDED LIKE IT DID NOT 	RETRACT COMPLETELY)  RECYCLED GEAR SAME PROBLEM.  RETURNED TO ANC LANDING WT. WAS 109.7.   INSP. FOUND SLUSH IN GEAR ARE	A (NOSE) AND STRUT WAS A LITTLE LOW.  CLEANED GEAR OF SLUSH AND RESET NOSE STRUT PRESS.  LUBED NOSE GEAR CYCLED NOSE SEV	ERAL TIMES OPS CK GOOD.			2	L	7	2 	4F			RT	A16WE   					 
2001041900134	20010419	00134	SW  	2001	4	19	SW152001         	1	20010321	G	6510	476441809	SHAFT           			BELL  	47    	47          	1180602	SW  										TAIL ROTOR	FAILED          	G			HFZS	B	R			EMER. DESCENT           	AUTOROTATION            			D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		UK	UNKNOWN        	1			SW	15	1575		73   							TAIL ROTOR DRIVE FAILURE. TAIL ROTOR FORWARD SHAFT, AFT COUPLING FAILURE.  LOSS OF LUBRICATION DUE TO STRIPPED TREADS ON	 SCREW ILLUSTRATED PARTS BREAKDOWN.					1	G	7	1 	3O			 	H1      					 
2001051000249	20010510	00249	WP  	2001	5	10	SW15200110389    	1	20010315	G	6230	369D22014	MAST            			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FLAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	500TP	5200 	5200 			0494E	CAE836593			COATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST.  COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION.  CAUS	E OF FLAKING, UNKNOWN.  NO FACTORY REPAIR AUTHORIZED IN THE MHI.  FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR.  EFFECT	 ON MAST AND TRANSMISSION.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001051000248	20010510	00248	WP  	2001	5	10	SW15200110390    	1	20010315	G	6230	369D22014	MAST            			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FLAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	600TP	5200 	5200 			525	CAE836593			COATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST.  COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION.  CAUS	E OF FLAKING UNKNOWN.  NO FACTORY REPAIR AUTHORIZED IN THE HMI.  FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR.  EFFECT 	ON MAST AND TRANSMISSION?				1	G	7	1 	3U	3	U	 	H3WE    	E4CE				 
2001050300135	20010503	00135	CE  	2001	5	3	SW15200110531    	1	20010326	G	5330	002440000143	DOUBLER         			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470*      	17026	SO  					FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	94SS	9446 				CD1089				DURING 100 HOUR INSPECTION FOUND CRACKS IN THE DOUBLER TALL PN 002440000143.  THE DOUBLER IS CRACKED JUST FORWARD OF THE	 AFT BULKHEAD APPROX 1 INCH JUST BEFORE THE RADIUSED AREA EXTENDING OUTBOARD .2500.					1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2001050300149	20010503	00149	CE  	2001	5	3	SW15200110535    	1	20010326	G	5520	639204	BUSHING         			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470*      	17026	SO  					COUNTERWEIGHT	IMPROPER PART   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	94SS					CD1089				THE INCORRECT BUSHING WAS IDENTIFIED DURING DEMINSIONAL INSPECTION OF THE COUNTER- WEIGHT PRIOR TO INSTALLATION.						1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2001050300003	20010503	00003	CE  	2001	5	3	SW15200110536    	1	20010328	G	5312	00244002465	BULKHEAD        			BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470*      	17026	SO  					FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	1444M	7583 				CD827				DURING 100 HOUR INSPECTION FOUND CRACKS IN THE DOUBLER TAIL, A CRACK ON THE RIGHT HAND SKIN SECTION AND A CRACK ON THE A	FT BULKHEAD APPROX  1 INCH AT THE BEGINNING OF THE RADIUSED AREA RADIATING OUTBOARD .7500 ON THE RIGHT SIDE AND .5000 ON	 THE LEFT SIDE.  THE SKIN SECTION IS CRACKED  1.75 INCH FROM THE AFT EDGE OF THE SKIN,  JUST ABOVE THE CRACK IN THE DOUB	LER EXTENDING OUTBOARD .7500 INCH.  THE BULKHEAD CRACKS EXTENDS .3750 INCH DOWN THE RADIUSED AREA AT THE TOP LEFT HAND C	ORNER.		1	L	7	1 	3O	3	O	 	3A15    	E1CE				 
2001050300315	20010503	00315	EA  	2001	5	3	SW15200110851    	2	20010405	G	7314	LW15473	PUMP            			PIPER 	PA28  	PA28*       	       	SO  	LYC   	O360  	IO360A1A    	41514	EA  					FUEL SYSTEM	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15		0    					L977336A			PART INSTALLED NEW AT OVERHAUL.  TEST CESS OPERATION WITHIN REQUIRED PRESSURE AND FLOW.  AT INSTALLATION IN AIRCRAFT, PU	MP WOULD NOT FUNCTION AND WOULD NOT ALLOW FUEL TO BE PUMPED THRU USING BOOST PUMP.					1	L	7	1 	3O	3	O	 	2A13    	1E10				 
2001080200086	20010802	00086	SO  	2001	8	2	SW15200111824    	1	20010425	G	3110		KNOB            			PIPER 	PA46  	PA46310P    	7104605	SO  										MOR CONTROL	INOPERATIVE     	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	184AL					4697026				MANUAL OVER RIDE (MOR) CONTROL LEVER KNOB CAME APART CAUSING THIS SYSTEM TO BE RENDERED INOPERATIVE AND A CERTAIN SAFETY	 ISSUE.  PROBLEM CAN BE SOLVED WITH PROPER INSTALLATION.  THIS AIRCRAFT JUST COMPLETED A PHASE I AND II INSPECTION.					1	L	7	1 	3O			RT	A25SO   					 
2001080200087	20010802	00087	CE  	2001	8	2	SW15200112233    	1	20010423	G	6123	B15941	SPRING          	HARTZL      		BEECH 	95    	95B55       	1152729	CE  										FEATHERING SPRNG	CORRODED        	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	2023Z				EB488	TC2171				UPON DISASSEMBLY OF THIS PROPELLER FOR OVERHAUL IT WAS NOTED THAT THIS FEATHERING SPRING WAS BROKEN AND SHOWS SIGNS THAT	 IT HAS BEEN BROKEN FOR SOME TIME.  THE BREAK WAS BETWEEN THE  1ST AND 2ND COIL AND WAS ALSO CORRODED.					1	L	7	2 	3O			RT	3A16    					 
2001080200089	20010802	00089	SO  	2001	8	2	SW15200112234    	1	20010427	G	6120		FORK            	HARTZL      		PIPER 	PA23  	PA23160     	7102304	SO  										PITCH CHANGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	76HK	3341 			AY34B	231423				AT OVERHAUL THE PITCH CHANGE FORK NR B2457-3 WAS FOUND TO HAVE A CRACK APPROX. .1875 INCHES IN LENGTH LOCATED AT THE LOW	ER INSIDE RADIUS OF THE NR 2 BLADE PITCH CHANGE SLOT.					1	L	7	2 	3O			 	1A10    					 
2001080200091	20010802	00091	GL  	2001	8	2	SW15200112284    	3	20010517	G	6110		BULKHEAD        			CESSNA	172   	172D        	2072410	CE  	LYC   	O320  	O320*       	41508	EA  	MCAULY	1C172	1C172EM     	GL  	PROPELLER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	54855	497  	497  			17275068				FORWARD PROPELLER BULKHEAD HAS BEEN CRACKING WITH MINIMAL HOURS.  BOLTS HAVE BEEN PROPERLY TORQUED AND SAFETY WIND.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910	 
2001080200093	20010802	00093	CE  	2001	8	2	SW15200112285    	1	20010516	G	5541	04330106	SPAR            			CESSNA	150   	152         	2071835	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	49780	4684 				15281314				CRACK IN UPPER LIGHTING HOLE, UNDER THE TOP HINGE, IN THE LEADING EDGE RUDDER SKIN/SPAR.  TO PREVENT RECURRANCE, REMOVE 	OR ELEMINATE LIGHTING HOLE IN NEW OR REPLACEMENT PARTS.					1	H	7	1 	3O			NT	3A19    					 
2001092500058	20010925	00058	EU  	2001	9	25	TI1R001403       	1	20010122	G	6240	1179405303	TACHOMETER      			BOLKMS	117   	BK117A1     	5626010	EU  										COCKPIT	FAILED          	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05										TRIPLE TACHOMETER - ROTOR TACHOMETER FAILED.  REMOVED AND REPLACED.						1	G	7	2 	3U			 	H13EU   					 
2001082100055	20010821	00055		2001	8	21	TI1R001405       	4	20010221	G	3416	1042011968E	ALTIMETER       																	COCKPIT	INOPERATIVE     	B			TI1R	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	05										ALTIMETER, ENCO - CODE OFF FLAG WILL NOT STOW.  REMOVED AND REPLACED.																			 
2001082100063	20010821	00063		2001	8	21	TI1R001428       	4	20010409	G	3421	5040017926	LIGHT           			BOLKMS	117   	BK117B2     	5626013	EU  										ATTITUDE GYRO	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117MK					7196				ATTITUDE GYRO, INTERNAL LIGHTING, INOPERATIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
2001091300273	20010913	00273	EU  	2001	9	13	TI1R001441       	1	20010407	G	7810	3039621	CLAMP           			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					EXHAUST	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					0070				EXHAUST CLAMP, CRACK ON BAND END.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500101	20010925	00101	EU  	2001	9	25	TI1R001442       	1	20010424	G	2810	L281M20C1002	TANK            			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN FUEL CELL	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	911SV					0070				MAIN TANK LEAKING.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300275	20010913	00275	EU  	2001	9	13	TI1R001444       	1	20010409	G	6230	L623M2005101	SWASHPLATE      			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	EXCESS PLAY     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV	1034 				0070				SWASHPLATE, REMOVED AT AEC REQUEST, EXCESSIVE PLAY.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500102	20010925	00102	EU  	2001	9	25	TI1R001445       	1	20010409	G	5320	4649305034	SUPPORT         			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					SUPPORT TUBE	LOOSE           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					0070				SUPPORT TUBE,  REMOVED AT AEC REQUEST, EXCESSIVE PLAY BETWEEN SUPPORT TUBE AND SLIDING TUBE.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500103	20010925	00103	EU  	2001	9	25	TI1R001446       	1	20010409	G	6220	L623M1002105	CLAMP           			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					MAIN ROTOR	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					0070				ROTOR SCISSOR CLAMP, REMOVED AT AEC REQUEST, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500104	20010925	00104	EU  	2001	9	25	TI1R001447       	1	20010422	G	3240	10477665	CYLINDER        			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					BRAKE ASSY	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	911SV	1231 				0070				BRAKE CYLINDER, LEAKING FLUID, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001092500106	20010925	00106	EU  	2001	9	25	TI1R001449       	1	20010503	G	5320	11780184111	SPACER          			BOLKMS	117   	BK117A1     	5626010	EU  										FUSELAGE	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05										SPACER - SPACERS HAVE NO GROOVE CUT INTO THEM FOR THE ORING.  REMOVED AND REPLACED.						1	G	7	2 	3U			 	H13EU   					 
2001092500113	20010925	00113	EU  	2001	9	25	TI1R001464       	1	20010428	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					FUEL PUMP	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					0070				FUEL PUMP CARTRIDGE, PUMP INOPERATIVE, TRIPS CIRCUIT BREAKER.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300283	20010913	00283		2001	9	13	TI1R001467       	4	20010512	G	3421	5040017926	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										ATTITUDE	TUMBLES         	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117MK					7196				ATTITUDE GYRO, TUMBLING, REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU   					 
2001091300285	20010913	00285	EU  	2001	9	13	TI1R001471       	1	20010522	G	7714	L771M40C1005	INDICATOR       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					TRIPLE TACH	ERRATIC         	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV					0070				TRIPLE TACHOMETER INDICATOR, NR NEEDLE ERRATIC, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300286	20010913	00286	EU  	2001	9	13	TI1R001472       	1	20010526	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					FUEL PUMP	FAULTY          	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV					0070				FUEL PUMP CARTRIDGE, POSITIVE TERMINAL GROUNDED, TRIPS BREAKER.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300287	20010913	00287	EU  	2001	9	13	TI1R001473       	1	20010526	G	2822	9A2045	CARTRIDGE       			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					FUEL PUMP	INTERMITTENT    	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV					0070				FUEL PUMP CARTRIDGE, MOTOR INTERMITTENT, REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300295	20010913	00295		2001	9	13	TI1R001481       	4	20010618	G	3160	066040211411	SYMBOL GENERATOR			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	117MK									SIGNAL GENERATOR, INTERMITTENTLY CAUSES EFIS TO GO TO (TEST IN PROGRESS)-THEN ERROR OF SIGNAL ON EFIS T, REMOVED AND REP	LACED.					1	G	7	2 	3U			NC	H13EU   					 
2001091300296	20010913	00296		2001	9	13	TI1R001482       	4	20010616	G	3425	4021541671	INDICATOR       																	COCKPIT	DEFECTIVE       	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05										ARTIFICIAL HORIZON, HSI - WILL NOT STABILIZE, ROLLING RIGHT/ DIVING.  REMOVED AND REPLACED.																			 
2001091300297	20010913	00297		2001	9	13	TI1R001483       	4	20010606	G	3422	060001500	GYRO            																	DIRECTIONAL GYRO	DAMAGED         	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05										KG102A DIRECTIONAL GYRO - RECEIVED WITH CONNECTOR GUIDE PIN BROKEN AND LOOSE HARDWARE INSIDE AND SEAL ON BOTTOM.  REMOVE	D AND REPLACED.																		 
2001091300301	20010913	00301	EU  	2001	9	13	TI1R001488       	1	20010410	G	2435	23081057	STARTER GEN     			UROCOP	EC135 	EC135P1     	8680990	EU  	PWA   	PW206 	PW206A      	 	NE  					ENGINE	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911SV	1231 				0070				STARTER GENERATOR, NEEDS BRUSH REPLACEMENT AND RUN-IN.  2000 TBO  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	O	H88EU   	E42NE				 
2001091300302	20010913	00302		2001	9	13	TI1R001489       	4	20010628	G	3442	066308432	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					RADAR	INOPERATIVE     	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	313LS	2773 				7509				IN FLIGHT 6,  INDICATION UNIT STOPS FUNCTIONING.  SCREW FELL OUT FROM INSIDE.  REMOVED AND REPLACED COLOR RADAR IND.						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU				 
2001080900257	20010809	00257	EU  	2001	8	9	TXEA81788        	1	20010423	G	6420	350A33200406	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										T/R SPIDER	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	22TV	10   				1591				BEARING HAS PLAY.						1	G	7	1 	3U			NC	H9EU    					 
2002020500052	20020205	00052	GL  	2002	2	5	V5MR198Y         	1	20010924	G	3220	11799001	BRACKET         			CIRRUS	SR    	SR22        	2130001	GL  										NLG	DAMAGED         	B			V5MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	705CD	54   				0005				NOSE WHEEL PANT BRACKETS, QTY 2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE.  AIRCRAFT HAS BEEN OPERATED BY A 	SINGLE INDIVIDUAL WITH MINIMAL TAKEOFFS AND LANDING IN APPROXIMATELY FOUR MONTHS TIME.  FURTHERMORE, THE MOUNTING HOLES 	IN THE NEW REPLACEMENT PART ARE  LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY.  THE HOLE	 IS LARGER THAN .1875 OF INCH (AN3) BUT SMALLER THAN .2500 OF AN INCH.  NO BUSHINGS ARE SPECIFIED IN THE MFG IPC.			1	L	7	1 	3O			NT	A00009CH					 
2002020500053	20020205	00053	GL  	2002	2	5	V5MR198Y1        	1	20010924	G	3220	11799001	BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	ELONGATED       	B			V5MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	6000C	244  				1037				NOSE WHEEL PANT BRACKETS, QTY2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE.  AIRCRAFT HAS BEEN OPERATED BY A S	INGLE INDIVIDUAL WITH MINIMAL TAKEOFFS AND LANDING IN APPROXIMATELY ONE YEARS TIME.  FURTHERMORE, THE MOUNTING HOLES IN 	THE NEW REPLACEMENT PART ARE APPRECIABLY LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY.  	THE HOLE IS LARGER THANT .1875 OF INCH BUT SMALLER THAN .2500 OF AN INCH.			1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2002020500054	20020205	00054	GL  	2002	2	5	V5MR198Y2        	1	20010924	G	3220	12936001	BUMPER BLOCK    			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	DETERIORATED    	B			V5MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2014Y	344  				1078				REBOUND BUMPERS, QTY 2, FOUND VERY DETERIORATED UNDER NORMAL USE.  THEY WERE IN SERVICE FOR 344.4 HOURS IN LESS THAN ONE	 YEAR.  THE AIRCRAFT IS OPERATED AS PART OF A CLUB AND SEES MANY TAKEOFF AND LANDING CYCLES.  THE DETERIORATION COULD BE	 DUE TO INTERACTION WITH ENGINE SOLVENTS AND/OR HEAT.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2002020500055	20020205	00055	GL  	2002	2	5	V5MR198Y3        	1	20010924	G	3220	11799001	BRACKET         			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	ELONGATED       	B			V5MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2014Y	402  				1078				NOSE WHEEL PANT BRACKETS, QTY 2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE.  AIRCRAFT HAS BEEN OPERATED AS A 	CLUB AIRCRAFT WITH MANY TAKEOFFS AND LANDING IN LESS THAN ONE YEARS TIME.  FURTHERMORE, THE MOUNING HOLES IN THE NEW REP	LACEMENT PART ARE APPRECIABLY LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY.				1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2002020500057	20020205	00057	GL  	2002	2	5	V5MR198Y5        	1	20010924	G	3220	12936001	BUMPER BLOCK    			CIRRUS	SR    	SR20        	05628AJ	GL  	CONT  	IO360 	IO360*      	17025	CE  					NLG	DETERIORATED    	B			V5MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	197CD	344  				1098				REBOUND BUMPERS, QTY 2, FOUND MISSING SINCE LAST INSPECTION.  THEY WERE IN NORMAL SERVICE FOR 223.7 HOURS IN LESS THAN O	NE YEAR.  AIRCRAFT SEES MINIMAL TAKEOFF AND LANDING CYCLES.  THE DETERIORATION AND SUBSEQUENT LOSS OF THE PARTS IN QUEST	ION COULD BE DUE TO INTERACTION WITH ENGINE SOLVENTS AND/OR HEAT.  DUE TO VIBRATION CAUSED BY SHIMMY OF THE NOSE LANDING	 GEAR STRUT ASSEMBLY PN 11907-003 OR BY SHIMMY OF A NOES WHEEL PANT THAT IS LOOSE ON ITS PANT BRACKETS PN 1179-001.			1	L	7	1 	3O	3	O	NT	A00009CH	E1CE				 
2001050900290	20010509	00290	SO  	2001	5	9	WI2              	2	20010422	G	7260	632617	GEAR            			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  					ACCESSORY DRIVE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2364S	104  				0664	060696R			ACCESSORY DRIVE GEAR TEETH WORN AWAY 104 HOURS SINCE INSTALLATION.  GEAR HAD BEEN INSTALLED DUE TO FAILURE OF PREVIOUS G	EAR FOR THE SAME REASON.  DRIVEN GEAR WAS NOT WORN.					1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001050900291	20010509	00291	SO  	2001	5	9	WI3              	2	20010427	G	7260	632617	GEAR            			CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  					ACCESSORY DRIVE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2397S	317  				0697	060694R			ACCESSORY DRIVE GEAR TEETH WORN AWAY 317 HOURS SINCE FACTORY REBUILD OF ENGINE.  DRIVEN GEAR WAS NOT WORN.						1	H	7	2 	3O	3	O	 	A6CE    	E1CE				 
2001051500084	20010515	00084	SO  	2001	5	15	WP012001B1728    	1	20010102	G	3244	850X6	TIRE            			PIPER 	PA12  	PA12        	7101202	SO  										MLG	MISMANUFACTURED 	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	3021M					121576				MOUNTED TWO GOODYEAR 8.50 X 6 6PR TIRES,  PN856C61-3, ON CLEVELAND WHEELS.  ONE TIRE APPEARED LARGER IN DIAMETER THAN TH	E OTHER.  MEASURED BOTH TIRES, AT 25PSI ONE TIRE IS 20.1250 AND THE OTHER IS 20.9375 IN DIAMETER.					1	H	7	1 	3O			 	A780    					 
2001100900036	20011009	00036	SW  	2001	10	9	WTXR200100277    	1	20010926	G	2820	31024691	LINE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					FUEL MANIFOLD	CRACKED         	B			WTXR	K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			SW	99	332BA					TC222E	P54132			AFTER LANDING AND TAXING TO RAMP, PILOT NOTICED FLUID RUNNING OUT OF BOTTOM OF ENGINE COWLING. ENGINE WAS SHUT DOWN AND 	MAINTENANCE WAS CALLED.MAINTENANCE FOUND A CRACK IN THE FUEL MANIFOLD AT THE 6 O'CLOCK POSITION,IN THE "B" NUT FITTING N	ECK. INSTALLED SERVICABLE MANIFOLD, LEAK CHECKED OK.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE				 
2001080200117	20010802	00117		2001	8	2	WVBA2001034      	4	20010521	G	2210	KA132	SWITCH          	ALIDSG      		PIPER 	PA31  	PA31350     	7103110	SO  										ACCEL SWITCH	FAILED          	C			WVBA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	01	42WP	2305 	2305 		3512	318252038				PILOT REPORTED SWITCH WOULD NOT TEST IN EITHER POSITION.  SWITCH WAS REMOVED FROM SERVICE.  PARTS TAKE FROM 3 TO 12 WEEK	S TO BE DELIVERED RENDERING THE AUTOPILOT INOPEATIVE FOR THAT TIME FRAME.  WITH SWITCHES FAILING RIGHT OUT OF THE BOX OR	 VERY FEW HOURS IN SERVICE, WE RECOMMEND ELIMINATING THIS SWITCH FRO THE SYSTEM AS THE AUTOPILOT CAN STILL BE PHYSICALLY	 OVERCOME OR MANUALLY CUT OFF BY A SWITCH ON THE YOKE.			1	L	7	2 	3O			 	A20SO   					 
2001080200118	20010802	00118	SO  	2001	8	2	WVBA2001035      	1	20010521	G	2913	1213HBG310	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC SYS	FAILED          	C			WVBA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	01	300ED		192  			317852008				PILOT REPORTED RIGHT HYDRAULIC PUMP FAILED CHECK DURING RUN UP.  PUMP WAS REMOVED AND IT WAS DISCOVERED THAT THE SHAFT H	AD SHEARED.  DURING REMOVAL OF THE FITTINGS IT WAS DISCOVERED THAT THE SMALL PRESSED IN NOZZLE, SPRING AND BALL HAD COME	 LOOSE WITH THE BALL JAMMING THE PUMP VANES AND CAUSING THE SHAFT TO SHEAR.  NOTE:  THIS WAS ON THE PRESSURE OUTLET SIDE	.  THE PUMP WAS REMOVED AND REPLACED.			1	L	7	2 	3O			 	A20SO   					 
2001080200119	20010802	00119	SO  	2001	8	2	WVBA2001036      	1	20010529	G	2140	A23D04	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	LEAKING         	C			WVBA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	01	42WP	160  				318252038				DURING INSPECTION IT WAS NOTICED THAT FUEL STAIN WAS IN THE DRAIN TUBE OF THE FUEL PRESSURE REGULATOR OF THE FRONT COMBU	STION HEATER.  THE REGULATOR WAS INSPECTED AND FOUND TO BE LEAKING FROM THE GASKET OF THE UPPER PARTING SURFACE.  UNIT W	AS REMOVED AND REPLACED.  IT SHOULD BE NOTED THAT THIS UNIT WAS INSPECTED PER SB WHICH INCLUDES A PRESSURE CHECK TO COMP	LY WITH AD AND WAS DETERMINED SERVICABLE.  TIME SINCE INSPECTION WAS 59 HOURS.			1	L	7	2 	3O			 	A20SO   					 
2002012400025	20020124	00025	SW  	2002	1	24	YTRR077311       	1	20011129	G	6330		BEARING         			BELL  	206   	206L1       	1182107	SW  										RESTRAINT	WORN            	H			YTRA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	142DP	331  			LK0765	45585				SPHERICAL BEARING CAME UNSTAKED WHICH ALLOWED THE BEARING TO FLOAT IN THE LATERAL SPRING ARM.						1	G	7	1 	3U				H2SW    					 
2002012400028	20020124	00028	SW  	2002	1	24	YTRR077356       	1	20011206	G	6710	206062721103	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	SEIZED          	H			YTRA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	142DP	386  				45585				THE LINEAR ACTUATOR OPERATED FOR APPROXIMATELY 3 MONTHS BEFORE FAILING. CAUSE OF THE FAILURE IS UNKNOWN. PART RETURNED T	O PRECISION HELIPARTS FOR EVALUATION.					1	G	7	1 	3U				H2SW    					 
2001050200041	20010502	00041	SO  	2001	5	2	ZVSR409Y         	1	20010220	G	5522		SKIN            			GULSTM	G1159 	G1159       	3953505	SO  										ELEVATOR	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	117JJ					163				EXTENSIVE SURFACE CORROSION ON HORIZONTAL STABILIZER AND ELEVATORS. CORROSION ON ELEVATORS EXTENDED THROUGH THE SKIN SUR	FACE. CORROSION WAS FOUND WHILE AIRCRAFT WAS IN MAINTENANCE FOR AN EXTERIOR PAINT JOB. CORROSION WAS FOUND AFTER PAINT W	AS STRIPPED AND A VISUAL INSPECTION WAS PREFORMED.				2	L	7	2 	4F			RT	A12EA