20021211000322002121100032CE 2002 12 11 001 120021209G2520SL0230028 LOCK RAYTHNDH125 HAWKER800XP 7150012CE CABIN CHAIR FAILED B K NONE O OTHER ININSP/MAINT 1 SW11833QS2182 2182 258433 CABIN CHAIR WILL FALL BACK WITHOUT USE OF RECLINE BUTTON ACTIVATION. EXCESSIVE SLACK. 2L72 4F RTA3EU 20020312001572002031200157SO 2002 3 12 0202 120020211G5610 WINDSHIELD GULSTMG1159 GIV 3980115SO COCKPIT CRACKED H H DEACTIVATE SYST/CIRCUITS O OTHER CRCRUISE 1 SW99VP-BH 1017 RIGHT FRONT WINDSHIELD OUTER HEATING/PROTECTIVE PLY CRACKED. 2L72 4F RTA12EA 20020201000072002020100007CE 2002 2 1 020231 120020130G32307089850810295 TORQUE LINK BEECH 90 65A901 1152901CE ZONE 700 MISMANUFACTURED B EVGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO3365JA LM34 WE WERE REPLACING THE TORQUE LINKS ON OUR KING AIR 65A90 IN ORDER TO RELIEVE THE REPETITIVE INSPECTION REQUIREMENTS OF AD 2001-01-10. ONE OF THE TWO TORQUE LINKS SENT WAS FINE. THE OTHER APPEARED AT FIRST GLIMPSE TO BE NORMAL. AFTER INSTALLATION, A RETRACTION TEST WAS PERFORMED AND THE FAULTY TORQUE LINK ALLOWED THE GEAR FORK TO OVEREXTEND AND CAUSED SUPERFICIAL DAMAGE TO THE WHEEL WELL. UPON CLOSER EXAMINATION IT WAS DISCOVERED THAT THE ANGLE OF THE STOP BOSS WAS TOO SHALLOW, ALLOWING THE OVEREXTENSION OF THE FORK. 1L72 3T 3A20 20020506000552002050600055CE 2002 5 6 020502 120020502G1430 RIVET HELIO H295 H295 4300802CE ZONE 100 WRONG PART B EVGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO33 1257 DURING ANNUAL INSPECTION IT WAS DISCOVERED THAT A NUMBER OF INDUSTRIAL GRADE POP RIVETS WERE USED IN THE COURSE OF AIRFRAME REPAIR INSTEAD OF AIRCRAFT GRADE RIVETS. INDUSTRIAL GRADE RIVETS WERE REMOVED AND REPLACED WITH PROPER AIRCRAFT QUALITY RIVETS. 1H71 3O 1A8 20020730000072002073000007CE 2002 7 30 0207008 120020729G2800051600918 RESERVOIR CESSNA172 172R 2072401CE FUEL SYSTEM RUPTURED D K NONE K FLUID LOSS ININSP/MAINT 1 CE035172J313 313 17281095 UPON ROUTINE INSPECTION, IT WAS NOTED THAT A FUEL STAIN WAS EVIDENT ON THE UNDERBELLY OF THE AIRCRAFT IN THE FACINITY OF THE FUEL SELEVTOR VALVE. CABIN FLOORING AND UPHOLSTERY WAS REMOVED AND THE FUEL SELECTOR AND FUEL RESEVOIR PN 0516009-18 WAS REMOVED & INSPECTED. THE RESEVOIR WAS PURGED AND PRESSURE TESTED. THE TANK WAS THEN COVERED IN A SOAPY WATER SOLUTION AND A LEAK WAS NOTED COMING FROM A WELDED SEAM. IT IS BELIEVED THAT A MINIMUM .75 INCH CRACK WAS EVIDENT IN A PART WITH ONLY 300 HOURS. 1H71 3O NT3A12 20020205000422002020500042SW 2002 2 5 0216 120020204G3230940024005 PINION GEAR MOONEYM20 M20E 5870212SW MLG FAILED B O OTHER P NO WARNING INDICATION LDLANDING 1 WP272103W4917 90 952 DURING ANNUAL INSPECTION AND AD73-21-01 COMPLIANCE, FOUND END THREE THREADS BROKEN OFF, ACTUATOR BLOCK UNABLE TO RETRACK LANDING GEAR. THREADS WHERE CORRORDED AND SEPERATED FROM GEAR. TIME SINCE LAST ANNUAL INSPECTION - 90 HOURS. PART NOT REPAIRABLE. REPLACED AND RETURNED TO SERVICE. AGE 25 YRS. 1L71 3O 2A3 20020312000032002031200003GL 2002 3 12 0242 320020220G6114 WIRE MOONEYM20 M20E 5870212SW HARTZLHCC2Y HCC2YK1 GL PROP HUB WRONG PART B K NONE W INADEQUATE Q C ININSP/MAINT 1 WP275554Q1450 170 630 DURING ANNUAL INSPECTION, FOUND PROPELLER HUB SAFETY WIRE UNDER SIZE - .032. AIRCRAFT PARTS MANUAL CALLS FOR SIZE - .041 SAFETY. INSTALLED PROPER WIRE AND RETURNED TO SERVICE. SIX PRIOR INCIDENTS IN LAST THREE MONTHS. AC 43.13-1B DOES NOT SPECIFY ANYTHING. 1L71 3O 2A3 5 CP920 20020910001122002091000112CE 2002 9 10 025686FLTLOG 120020716G2840 CONTROL PANEL BEECH 90 C90 1152913CE FUEL PANEL DAMAGED B A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW1521 LJ902 BATTERY CHARGE LIGHT CAME ON IN FLT, LT BOOST PUMP & LT TRANSFER PUMP CIRCUIT BREAKER POPPED : RESET CIRCUIT BREAKER & LANDED ASAP. UPON INSPECTION FOUND FUEL PANEL DIODES AND WIRING CORRODED. R&R DIODES, CIRCUIT BREAKER AND HARDWARE AND CLEANED CORROSION FROM WIRING AND PANEL AND REINSTALLED PANEL. 1L72 3T 3A20 20020419000032002041900003CE 2002 4 19 029041702 120020417G2910306588002087 LINE RKWELLNA265 NA26565 7630107CE ALIDSGTFE731TFE7313AR WP HYD SYSTEM CRACKED B D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CE016NR 9564 46529 PILOTS STARTED TAXI OUT TO TAKEOFF. IN PROCESS CONDUCTED THE LANDING SPOILER EXTENSION OPERATIONAL TEST WHICH SURGES AND SLAMS THE HYDRAULIC SYSTEM FAIRLY HARD. WITHIN A FEW SECONDS RECEIVED MASTER WARNING CAUTION LIGHT AND NOTICED LOW HYDRAULIC PRESSURE. RETURNED TO HANGAR. INSPECTION REVEALED .75 INCH LONG STRESS CRACK IN UPPER FORWARD RADIUS OF ALUMINUM HYDRAULIC LINE THAT WAS UNDETECTABLE TO THE EYE UNTIL UNLESS HYD PUMP WAS ON. PROBABLE CAUSE IS MOST LIKELY WORK HARDENING AND STRESS DUE TO SURGES AND HYDRAULIC SYSTEM SLAM EXPERIENCED WITH SUDDEN SPOILER BOARD EXTENSION ON LANDINGS. 2L72 4J4 F A2WE E6WE 20020423000552002042300055EA 2002 4 23 04230201 220020423G8500SL738190 BUSHING LYC O720 IO720* 41546EA COUNTER WEIGHT FAILED B K NONE O OTHER ININSP/MAINT 1 SW17 250 250 COUNTER WEIGHT BUSHINGS P/N SL73810 HAVE FAILED AT 2 TO 250 HOURS. IT APPEARS THAT THE MATERIAL MAY BE TOO SOFT. BUSHINGS WERE REMOVED BY OPERATOR AND SENT BACK FOR EVALUATION. 3 O 1E15 20020719000782002071900078CE 2002 7 19 0605023221 120020507G2450S13605L CIRCUIT BREAKER CESSNA172 172R 2072401CE ELECTRICAL FAILED D S1XBA UNSCHED LANDING A FLAME/FIRE CLCLIMB 1 SO17972RA 17280412 THE OVERVOLTAGE SENSOR ACTIVATED, CLAMPING THE ACU POWER SUPPLY TO GROUND. THE ALTERNATOR CIRCUIT BREAKER FAILED TO TRIP. THIS RESULTED IN AN INFLIGHT ELECTRICAL FIRE WITH THE HARNESS BETWEEN THE J-BOX AND CIRCUIT BREAKER PANEL DAMAGED AS MULTIPLE CIRCUITS WERE BURNED. AT LEAST THREE OTHER BREAKERS TRIPPED BEFORE THE MAIN BUSS BREAKER LET GO. THE FIRST WIRE BURNING STARTED A CASCADE OF SHORT CIRCUITS. 1H71 3O NT3A12 20020719000802002071900080CE 2002 7 19 0628022541 120020628G3340S13605L CIRCUIT BREAKER CESSNA172 172S 2072439CE NAV LIGHTS FAILED D S1XBO OTHER O OTHER CLCLIMB 1 SO17484SP 172S8030 THE RIGHT WING NAV LIGHT POSITIVE AND NEGATIVE WIRES BURNED TOGETHER, SHORTING THE NAV CIRCUIT. THE 5 AMP NAV LIGHT CIRCUIT BREAKER NEVER TRIPPED. AN INVESTIGATION WAS INITIATED WHEN A PILOT REPORTED THAT THE NAV LIGHT SWITCH WOULD NOT STAY IN THE "ON" POSITION. 1H71 3O NT3A12 20021023000612002102300061CE 2002 10 23 081620027947Q 120020816G522052111302 ESCAPE HATCH CESSNA402 402B 207590PCE FUSELAGE SEPARATED E QTVAO OTHER D INFLIGHT SEPARATION CRCRUISE 1 NM117947Q12782 402B0397 BETWEEN SLC & TWF PILOT REPORTED A LOUD BOOMING/STRIKING NOISE, AS IF HE HAD HIT A BIRD. UPON INVESTIGATION HE NOTICED THE ESCAPE HATCH WAS MISSING. HE NOTIFIED SALT LAKE CENTER OF THE SITUATION. NO OTHER DAMAGE WAS NOTICED. THE PILOT SLOWED THE AIRCRAFT AND CONTINUED SAFELY TO TWF. 1L72 3O A7CE 20020826000062002082600006SO 2002 8 26 1001 120020627G5711 SPAR LKHEED282 C130A 5262502SO LT WING CRACKED B BZBRK NONE O OTHER ININSP/MAINT 1 NM04131HP20230 56534 FORWARD WING SPAR WEB WAS CRACKED IN THE SAME LOCATION BOTH SIDES STA. 85 CENTER WING. 3 DIFFERENT LOWER WING STRINGER ATTACH ANGLES CRACKED IN THE SAME FASHION CWS 216 LT SIDE. LOWER WING STRINGER CRACKED CWS 216 LEFT. LEFT WING LOWER SKIN CRACKED CWS 218. 2H74 4T A31NM 20030106000072003010600007WP 2003 1 6 10090226 220021009G73208961151 GASKET SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP ENGINE LEAKING E HKGAA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW17323BA2436124361 TC280 P54282 P3 AIRLEAK AT PRIMARY BLEED PORT CAUSED ENGINE FIRE INDICATION. NO FIRE WAS DISCOVERED 2L72 4T4 TRTA8SW E4WE 20020812001262002081200126SO 2002 8 12 10991 120020722G7100554321 CONTROL CABLE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360* 17025SO NACELLE DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP234174D303 3449178 CABLE STIFF, THIS CABLE RUNS THROUGH THE FIRE WALL AND WITHIN THE TURBO REGION. HEAT GENERATED FROM TURBO ASSEMBLY AFFECTS INSIDE LINNING. RECOMMEND A FIRE JACKET OR ALTERNATE MEANS TO SHIELD CABLE ASSEMBLY FROM HEAT. 1L72 3O3 O A7SO E9CE 20020812001272002081200127CE 2002 8 12 11482 120020731G3246D30259 WHEEL CESSNA210 T210L 2073449CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 WP25941481899 140 21060519 ON PRECAUTIONARY INSPECTION FOUND CRACKS AT WHEEL/HUB FLANGE MOUNTING BOLT HOLES ON BOTH WHEELS. REPLACED BOTH WHEELS WITH CLEVELAND TWO PIECE WHEELS. WE HAVE FOUND 6 OF THE SAME WHEEL(HUBS)CRACKED ON 172/182/210 CESSNA AIRCRAFT IN THE LAST WEEK. RECOMMEND IMMEDIATE INSPECTION AND OR REMOVAL OF THESE WHEELS FROM SERVICE. 1H71 3O 3A21 20020812001282002081200128CE 2002 8 12 11509 120020731G3246D30259 WHEEL CESSNA182 182P 2075816CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 WP259448M3198 154 18264764 ON REPLACING A WARN OUT TIRE WE FOUND THE CENTER HUB TO HAVE A CRACK AT 9 OF THE FLANGE MOUNTING BOLT HOLES, WE INSPECTED THE OTHER WHEEL/HUB FOUND IT TO HAVE 4 CRACKS. REPLACED BOTH WHEELS WITH CLEVELAND TWO PIECE WHEELS. WE HAVE FOUND 6 OF THE SAME WHEELS (HUBS)CRACKED ON 172/182/210 CESSNA AIRCRAFT IN THE LAST WEEK. 1H71 3O NTTA13 20020812001292002081200129CE 2002 8 12 11510 120020731G3246D30256 WHEEL CESSNA172 172M 2072418CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 WP259682H2725 100 17266311 ON INSPECTION OF CENTER HUBS OF THE TWO MAIN WHEELS FOUND ONE HUB TO HAVE 12 CRACKS ONE AT EA. BOLT HOLE. THE OTHER HUB HAD SIMILAR CRACKING. THESE WHEELS WERE INSPECTED 100 HRS PRIOR WHEN NEW TIRES WERE INSTALLED AND ON CRACKS WERE NOTED. THESE WHEELS/TIRES WERE REMOVED FOR INSPECTION DUE TO THE FACT WE HAVE FOUND 6 OF THE SAME WHEELS (HUBS)CRACKED ON 172/182/210 CESSNA AIRCRAFT IN THE LAST WEEK. 1H71 3O NT3A12 20020826000072002082600007CE 2002 8 26 11518 120020819G3246D30321 HUB CESSNA310 T310R 2074246CE NGL WHEEL CRACKED C K NONE O OTHER ININSP/MAINT 1 WP25500CH4390 350 310R0734 WHEEL REPLACED DUE TO THE FACT WE HAVE FOUND MANY HUBS CRACKED ON THREE PIECE MCCAULEY WHEELS. WE FOUND THE CRACKS AFTER THE WHEEL WAS REMOVED AND COMPLETELY TAKEN APART. RECOMMEND ALL THREE PIECE MCCAULEY WHEELS BE COMPLETELY DISASSEMBLED FOR INSPECTION IMMEDIATELY, AND EACH ANNUAL THERE AFTER OR UNTIL THEY ARE REPLACED WITH A BETTER WHEEL. (IE: TIRE MUST BE REMOVED FROM WHEEL.)WE RECOMMEND CLEVELAND WHEELS AS THEY ARE TWO PIECE WHEELS. 1L72 3O 3A10 20021211000332002121100033CE 2002 12 11 11592 120021202G3246D30259 HUB CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MLG WHEEL CRACKED D K NONE O OTHER ININSP/MAINT 1 WP25351821455 77 177RG1045 CENTER SECTION OF WHEEL FOUND CRACKED BOTH MAIN WHEELS. WHEELS REPLACE WITH NEW CLEVELAND TWO PIECE TYPE WHEELS. 1H71 3O3 O A20CE 1E10 20030106000102003010600010CE 2003 1 6 123002 120021230G5210504300431329 CHANNEL BEECH 200 200BEECH 1152920CE CABIN DOOR CRACKED B K NONE O OTHER ININSP/MAINT 1 SW016509F8276 BB493 WHILE GROUND PRESSURIZING CABIN FOR LEAK CHECK, THE CABIN DOOR WOULD LEAK AT 3 PSI AND APPEARED TO SHIFT WITHIN THE FRAME AS PRESSURE WAS APPLIED.ADJUSTMENTS TO THE LATCHING MECHANISM ALLOWED THE DOOR TO HOLD TILL 5.2 PSI (6 PSI WAS THE TEST TARGET) BUT IT WAS NOTED THAT THE DOOR WAS STILL SHIFTING AFT AT THE UPPER PORTION UNDER PRESSURE.THE DOOR HINGE AFT SECTION HAD EXCESSIVE PLAY. THE DOOR WAS REMOVED AND A CLOSER INSPECTION REVEALED THAT THE DOOR END CHANNEL WAS CRACKED FOR 6 INCHES SPANNING THE AFT 6 RIVETS WHICH ATTACH THE DOOR HINGE TO THE DOOR. REPLACED THE CHANNEL AND HINGE HALF PIECES AND ADJUSTED DOOR LATCHING MECHANISM AS REQUIRED. 1L72 4T A24CE 20020927000182002092700018SO 2002 9 27 16138C 120020918G5730 SKIN LKHEED282 C130A 5262502SO CENTER WING CRACKED B BZBRK NONE O OTHER ININSP/MAINT 1 NM04133HP 570482 LOWER CENTER WING SKIN CRACKED AT FASTINER HOLES. 2H74 4T A31NM 20021023000622002102300062NM 2002 10 23 16214 120021016G5710 STRUCTURE LKHEEDP2V P2V7 5260112NM WRIGHTR3350 R335042 EA LT & RT WING CRACKED B BZBRK NONE O OTHER ININSP/MAINT 1 NM04139HP 145906 IN THE WHEEL WELL AREA OF THE P2V-7 THERE ARE 2 FUEL CELL INTERCONNECT ACCESS PANELS. THE FURTHEST INBOARD PANELS ON EACH SIDE ARE PANEL 53L AND 53R. PANEL 53L, THERE IS A CRACK LOCATED AT THE INBOARD FORWARD CORNER, RUNNING FROM THE RADIUS OF THE DOUBLER CUTOUT FORWARD .3125 INCH TO ONE OF THE DOUBLER ATTACH FASTENERS. IN PANEL 53R, THERE IS A CRACK LOCATED AT THE INBOARD FORWARD CORNER, RUNNING FROM THE RADIUS OF THE DOUBLER CUTOUT FORWARD COMPLETELY THROUGH THE DOUBLER. THERE IS NO DAMAGE FOUND IN THE WING SKIN OR THE HAT SECTION FLANGES. (SW) 2M72 2R4 RRTA1RM 20030106000062003010600006CE 2003 1 6 1B 120021220G325207436242 SHIMMY DAMPENER CESSNA206 U206C 2073332CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL NLG MISINSTALLED B K NONE W INADEQUATE Q C ININSP/MAINT 1 SW016506R U2060969 818948R 731126 SHIMMY DAMPENER SLIDING SHAFT INSTALLED 180 DEGREES OUT. UNIT WAS OVERHAULED. 1H71 3O3 O A4CE E5CE 5 CP21EA 20020625001182002062500118SO 2002 6 25 200202 120020606G2400RSU21 RELAY PIPER PA46 PA46310P 7104605SO ELECTRICAL CHAFED B K NONE O OTHER ININSP/MAINT 1 GL07221TB 468508061 DURING AVIONICS TROUBLE SHOOTING, AN INSPECTION PANEL WAS REMOVED FROM THE COCKPIT FLOOR IN THE AREA JUST FORWARD OF THE CO PILOT'S SEAT TO GAIN ACCESS TO A SWITCHING RELAY MOUNTED ON THE UNDERSIDE OF THAT SAME PANEL. ONCE REMOVED, IT WAS NOTED THAT THE "SWITCHING RELAY" BOX WAS DISPLACING THE OUTER SHEATHING OF THE ENGINE FUEL MIXTURE CABLE UP AGAINST A HYDRAULIC "B" NUT AND WAS IN THE INTIAL STAGES OF CHAFFING ACTIVITY. SPACE IN THIS AREA IS LIMITED AND THE SWITCHING RELAY WAS MOUNTED TO STAND OFF ANGLES ATTACHED TO A LIGHT GAUGE ACCESS PANEL. REPLACEMENT OF THE SWITCHING RELAY INCLUDED THE MANUFACTURE OF A NEW PANEL OF HEAVIER GAUGE THAT NO LONGER REQUIRED "STIFFNERS" AND RESULTED IN ADEQUATE CLEARANCE IN 1L71 3O RTA25SO 20020625001192002062500119CE 2002 6 25 2002F00637 120020516G57510322709 BRACKET CESSNA195 195 2073102CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE053040B 7923 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. REMOVE BRACKETS FROM AIRCRAFT AND BEAD BLAST BODY WHILE PROTECTING BEARING. 1H71 3R NCA790 20020827000022002082700002SO 2002 8 27 2002F00780 120020628G56204AS3134031004 PANEL GULSTMGV GULFSTREAMGV3980116SO PWA 306 PW306B NE FUSELAGE INCORRECT D K NONE O OTHER ININSP/MAINT 1 SW05362GA24 062 WHILE ROUGH FITTING THE RIGHT WINDOW PANEL, IT WAS NOTED THE THE NR 4 WINDOW (FS 7558) WAS 0.75 INCH TOO FAR FORWARD. A CHECK OF AIRCRAFT REVEALED THE SAME CONDITION ON THE LT SIDE OF AIRCRAFT S/N 63 AND 67. (F.S. 7558) PART NUMBER: 4AS3134031-003. SUBSEQUENT TO OUR INVESTIGATION AND ASSEMBLY LINE CHECK (S/N 68 - 80) REVEALED THE SAME CONDITION ON RT SIDE OF SN 68. 2L72 4F4 FRTA12EA E35NE 20021127000332002112700033SO 2002 11 27 2002F01028 120021101G2823 SHUTOFF VALVE PIPER PA28 PA28R200 7102811SO LYC O360 IO360A1A 41514EA FUEL SYSTEM FAILED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NE0156418 28R7335434 FUEL SHUTOFF VALVE UNIVERSAL FAILED WHILE TURNING OFF FUEL. THIS PART IS NO LONGER USED ON NEWER AC AND PART NUMBER NOT LISTED IN THE PARTS BOOK. 1L71 3O3 O 2A13 1E10 20020128000022002012800002CE 2002 1 28 2002FA0000039 120020102G323022411027 PIVOT ASSY CESSNA182 R182 2072734CE LT MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SW15757KP R18201242 FORWARD BEARING AREA OF RIGHT MAIN GEAR PIVOT WAS DETERMINED TO BE CRACKED AND LEAKING BRAKE FLUID. THE PIVOT ASSY WILL BE REPLACED WITH A NEW PIVOT ASSY PART NUMBER 2241102-13 AS OUTLINED IN MFG SB. 1H71 3O RT3A13 20020128000082002012800008CE 2002 1 28 2002FA0000047 120020104G3233S1997C78 BEARING CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA ACTUATOR DAMAGED B X0FRK NONE O OTHER ININSP/MAINT 1 WP076091V3067 172RG0574 FOUND ACTUATOR PISTON 1 RACK SUPPORT BEARING MIGRATED APPROX. .2500 INCH FROM HOUSING. BEARING WAS FOUND UNSERVICEABLE. CAUSE UNKNOWN. 1H71 3O3 O 3A17 E286 20020128000132002012800013EA 2002 1 28 2002FA0000054 220020114G853032000WLA1 CYLINDER BBAVIA7 7AC 2110102SW LYC O320 IO320C1A 41508EA ENGINE CUT D K NONE K FLUID LOSS ININSP/MAINT 1 WP0785664 7AC4409 371355A ENGINE WAS INSTALLED ON THE AIRCRAFT AND RUN UP. AN OIL LEAK WAS NOTICED IN THE LOWER SPARK PLUG BOSS AREA OF NR 1 CYLINDER. FURTHER EXAMINATION REVEALED THAT SOME CUTS BETWEEN FINS ADJACENT TO THE SPARK PLUG HOLE NEARLY PENETRATED THE THREAD AREA OF THE SPARK PLUG HOLE. CYLINDER NR 2 HAD A SIMILAR PROBLEM BUT THE CUTS ONLY PENETRATED HALFWAY THROUGH THE BOSS SURFACE. 1H71 3O3 O A759 1E12 20020128000142002012800014EA 2002 1 28 2002FA0000055 220020114G853032000WLA1 CYLINDER BBAVIA7 7AC 2110102SW LYC O320 IO320C1A 41508EA ENGINE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 WP0785664 7AC4409 371355A ENGINE WAS INSTALLED ON THE AIRCRAFT AND RUN UP. AN OIL LEAK WAS NOTICED IN THE LOWER SPARK PLUG BOSS AREA OF NR 1 CYLINDER. FURTHER EXAMINATION REVEALED THAT SOME CUTS BETWEEN FINS ADJACENT TO THE SPARK PLUG HOLE NEARLY PENETRATED THE THREAD AREA OF THE SPARK PLUG HOLE. CYLINDER NR 2 HAD A SIMILAR PROBLEM BUT THE CUTS ONLY PENETRATED HALFWAY THROUGH THE BOSS SURFACE. 1H71 3O3 O A759 1E12 20020118000292002011800029WP 2002 1 18 2002FA0000077 120020114G2913D5001 PUMP ROBSINR44 R44 7640120WP HYD SYSTEM LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 SW99144JD261 261 0938 HYDRAULIC PUMP LEAKING BETWEEN THE MATING SURFACES OF THE PUMP. 1G71 3O H11NM 20020128000202002012800020WP 2002 1 28 2002FA0000084 120020108G792253E22144 VERNATHERM ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA OIL COOLER STUCK D O OTHER MJ OVER TEMP WARNING INDICATION NRNOT REPORTED 1 NE0549CN 338 0554 L2533240A OPERATOR COMPLAINT, HIGH OIL TEMPERATURES, 245 DEGREES F. VERIFIED BY A DECREASE IN OIL PRESSURE. FOUND VALVE DEFECTIVE. REMOVED AND REPLACED VALVE WITH NEW PART. OPS CHECKED GOOD. 1G71 3O3 O H11NM E295 20020128000212002012800021EA 2002 1 28 2002FA0000086 220020114G853072877 LIFTER PIPER PA28 PA28236 7102815SO LYC O540 O540J3A5 41532EA ENGINE BROKEN B CS3RK NONE O OTHER ININSP/MAINT 1 WP174351D1254 288411016 L2373740A DURING OIL CHANGE FOUND METAL IN OIL FILTER. REMOVED SUCTION SCREEN FOUND .5000 INCH DIAMETER PIECES OF METAL. DISASSEMBLED ENGINE AND FOUND LIFTER FACES BROKEN OFF 3 LIFTERS. 1L71 3O3 O 2A13 E295 20020128000262002012800026CE 2002 1 28 2002FA0000090 120020102G3222 STRUT CESSNA310 310F 2074216CE CONT O470 IO470* 17026SO NLG STUCK D O OTHER O OTHER TXTAXI/GRND HDL 1 NM036721X3167 3100021 THE NOSE STRUT APPEARS TO HAVE GONE FLAT DURING TAXI FOR TAKE OFF. DURING THE GEAR RETRACTION CYCLE THE NOSE STRUT, NOT FULLY EXTENDED, HUNG UP ON THE CENTER ATTACH ARMS OF THE NOSE GEAR DOORS PULLING THE IDLER BELLCRANK (PN 0842102-2) APART. 1L72 3O3 O 3A10 E1CE 20020128000352002012800035 2002 1 28 2002FA0000093 420020110G2561KD9P0101 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED. 20020124000312002012400031CE 2002 1 24 2002FA0000094 120020123G750085300 CHECK VALVE CESSNA501 501 2076603CE WILINTFJ44 FJ44 66000GL RT ENGINE FAILED B O OTHER M OVER TEMP NRNOT REPORTED 1 SW43501GS5690 5010012 6009 CHECK VALVE FAILED AND ALLOWED THE RT ENGINE BLEED AIR TO FLOW UNABATED FROM RT ENGINE ACROSS AND INTO THE LT ENGINE VIA THE AIRCRAFT BLEED AIR LINES DURING IN FLIGHT RESTARTS OF THE LT ENGINE. HOT BLEED AIR GASES DISTURBED THE NORMAL AIRFLOW INTO THE LT ENGINE COMBUSTION CHAMBER AND CAUSED THE LH ENGINE TO HAVE A RAPID ITT RISE RESULTING IN AN ENGINE HOT START AND RESULTANT TEARDOWN/OVERHAUL OF THE ENGINE. 1L72 4F4 F A27CE E3GL 20020128000392002012800039CE 2002 1 28 2002FA0000097 120020114G323024411001 PIVOT ASSY CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA RT MAIN GEAR SHEARED D K NONE O OTHER ININSP/MAINT 1 WP239602B 172RG0912 FOUND PIVOT ASSEMBLY SPINE AREA FAILED, NO WARNING, NO INDICATION OF SPONGY BREAKS, NO SQUAWKS OF HUG GEAR, OR ANY OTHER GEAR PROBLEMS. PERFORMED 3 GEAR SWINGS, AND ONE EMERGENCY GEAR SWING PRIOR TO INCIDENT. GEAR HAD FUNCTION 100 PERCENT, AND WITH IN SERVICE MANUAL RECOMMENDED TIME FRAMES. PERFORMED GEAR SWING AFTER INCIDENT, FOUND PIVOT ASSEMBLY SHEARED. REMAINING LEFT, AND NOSE GEAR FUNCTIONING NORMAL. AD WAS PERFOREMD 103.4 HOURS PRIOR, NO GEAR PROBLEMS NOTED. 1H71 3O3 O 3A17 E286 20020128000402002012800040CE 2002 1 28 2002FA0000098 120020114G323035815129 LEG ASSY BEECH 35 V35B 1151548CE CONT O520 IO520* 17032SO RT MAIN GEAR FROZEN D K NONE O OTHER ININSP/MAINT 1 WP23178145942 D10144 FOUND LEG ASSEMBLY FAULITY. A FALSE INDICATION OF A LOCK OUT MAY BE INDICATED DUE TO A PARTALY FROZEN/BUSHING AND BOLT. EVEN THOUGH THE SERK FITTING RECIEVED GREASE, AND EXPELLED IT FROM THE SIDES OF THE BUSHING. THE FULL EXTENTION OF THE DOWN LOCK WAS COMPROMISED, CORRECT SPRING PRESSURES WERE INDICATED DURING RIGGING, AND 3 GREEN LIGHT INDICATED, BUT THE LEG ASSEMBLY WOULD BIND, CAUSING THE UP LOCK TO DISENGAGE AT THE FIRST INDICATION OF SIDE LOAD (CROSS WIND LANDING). 1L71 3O3 O 3A15 E5CE 20020128000422002012800042CE 2002 1 28 2002FA0000099 120020102G2720 BELLCRANK CESSNA150 A150K 2071824CE CONT O200 O200* 17020SO RUDDER LOOSE D O OTHER O OTHER NRNOT REPORTED 1 SW018458M3500 A15000158 RIGHT RUDDER NOISE, INSPECTED AND FUND RUDDER BELLCRANK LOOSE. RIGHT SIDE, THE RIVETS ON THE RIGHT SIDE WORKING, ALLOWING THE BELLCRNK TO MOVE UP AND DOWN, THAT COULD CATCH BELLCRANK STOP AND RUDDER STOP AND JAM. 1H71 3O3 O 3A19 E252 20020124000642002012400064WP 2002 1 24 2002FA0000114 220020107G725031033021 DEFLECTOR ALIDSG GARRTTTPE331TPE33112UA 01514WP TURBINE NOZZLE DAMAGED B K NONE O OTHER ININSP/MAINT 1 CE03 980134516516 P/N 3103302-1 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERIAL. DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVING INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSEMBLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR. 4 T E4WE 20020124000652002012400065WP 2002 1 24 2002FA0000115 220020107G725031033021 DEFLECTOR ALIDSG ALIDSGTPE331TPE331201A 0517 WP TURBINE NOZZLE DAMAGED B K NONE O OTHER ININSP/MAINT 1 CE03 980134516516 P/N 3103302-1 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERIAL. DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVING INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSEMBLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR. 3 T AEXJ STC 20020124000662002012400066WP 2002 1 24 2002FA0000116 220020107G725031033021 DEFLECTOR ALIDSG ALIDSGTPE331TPE331201A 0517 WP TURBINE NOZZLE DAMAGED B K NONE O OTHER ININSP/MAINT 1 CE03 4013451412 P/N 310330201 DEFLECTOR COMPONENT OF P/N 3103783-9 SECOND STAGE TURBINE NOZZLE ASSEMBLY EXHIBITS WEAR AND MISSING MATERIAL. DAMAGE APPEARS THE RESULT OF INADEQUATE RETENTION AND SPINNING OF THE DEFLECTOR IN SERVICE. DAMAGE NOTED AT RECEIVING INSPECTION BY REPAIR STATION PRIOR TO REPAIR. REPAIR DEVELOPED AND DER-APPROVED TO CORRECT CONDITION IN REPAIRED ASSEMBLIES, HOWEVER DESIGN SHOULD BE REVIEWED AS DISLODGED MATERIAL HAS POTENTIAL TO CONTACT TURBINE ROTOR. 3 T AEXJ STC 20020124000682002012400068CE 2002 1 24 2002FA0000118 120020110G3213 AXLE CESSNA172 172RG 2072438CE MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 NM09 DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN AREA 1A (AXLE SHAFT RADIUS) 1H71 3O 3A17 20020124000692002012400069CE 2002 1 24 2002FA0000119 120020110G3213 AXLE CESSNA177 177RG 2073709CE MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 NM09 DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN RADIUS OF AXLE SHAFT (AREA 1A ) 1H71 3O A20CE 20020124000712002012400071CE 2002 1 24 2002FA0000120 120020110G3213 AXLE CESSNA172 172RG 2072438CE MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 NM09 DURING FLOURESCENT PENETRANT INSPECTION, FOUND CRACK IN AXLE SHAFT RADIUS. 1H71 3O 3A17 20020124000772002012400077CE 2002 1 24 2002FA0000122 120020114G2750151228024 BUSHING CESSNA172 172S 2072439CE TE FLAPS MISSING B O OTHER WF INADEQUATE Q C FLT CONT AFFECTED DEDESCENT 1 WP07521ER342 172S8924 FLAPS FAILED TO RETRACT DURING TOUCH AND GO TRAINING. INSPECTION BY MAINTENANCE FOUND BUSHING (P/N 1512280-24) HAD NOT BEEN INSTALLED AT THE FACTORY. THIS ALLOWED THE FLAP ARM ASSEMBLY (P/N 0560022-8) TO MOVE AWAY FROM FLAP LEVER ASSEMBLY (P/N 0560021-1) PREVENTING PROPER OPERATION OF THE FLAP SWITCHES (P/N S1906-1). 1H71 3O NT3A12 20020124000782002012400078CE 2002 1 24 2002FA0000123 120020108G5610 WINDOW CESSNA150 150M 2071830CE COCKPIT SEPARATED D A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 EA2363206 15077174 PILOT SIDE WINDOW (LOCATED ON PILOT'S DOOR) DEPARTED AIRCRAFT DURING FLIGHT WHEN WINDOW WAS OPENED. FOLLOWING AN EXAMINATION OF THE DOOR ON THE AIRCRAFT, IT APPEARED THAT BOTH THE FORWARD AND REAR HINGE PINS SHEARED ALLOWING THE WINDOW AND WINDOW FRAME TO SEPARATE FROM THE AIRCRAFT. THERE WAS NO DAMAGE TO THE HINGE HALVES SECURED TO THE DOOR FRAME. 1H71 3O 3A19 20020124000832002012400083SO 2002 1 24 2002FA0000125 220020117G741410391586 DISTRIBUTOR BLK CONT S6RN1225 CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO MAGNETO BROKEN D D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 WP23PKMCA452 E259925FR U20601269 THE CENTER BUSHING IN THE DISTRIBUTOR BLOCK IS LOOSE AND SHOWS SIGNS OF OVERHEATING. AS A RESULT THE DISTRIBUTOR GEAR WOBBLED AND THE FINGER CONTACTED ALL THE HIGH TENSION CONTACT TOWERS AND GROUND THEM OFF. 1H71 3O3 O A4CE E8CE 20020124000862002012400086CE 2002 1 24 2002FA0000126 120020109G571257222061 RIB CESSNA441 441 2076020CE LT CENTER WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SO15332DM7401 4410167 DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85 INCHES) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45 ) AND EXTENDING APPROXIMATELY 1 INCH AFT OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. 1L72 3T RTA28CE 20020124000872002012400087CE 2002 1 24 2002FA0000127 120020109G571257222062 RIB CESSNA441 441 2076020CE RT CENTER WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SO15332DM7401 4410167 DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1 INCH AFT OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. CESSNA CURRENTLY DOES NOT HAVE ANY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE, THIS AREA SHOULD BE CLOSELY INSPECTED DURING ROUTINE INSPECTIONS. 1L72 3T RTA28CE 20020124000892002012400089CE 2002 1 24 2002FA0000128 120020118G571257222061 RIB CESSNA441 441 2076020CE LT CENTER WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SO15621SC7401 4410070 DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AFT OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. 1L72 3T RTA28CE 20020124000902002012400090CE 2002 1 24 2002FA0000129 120020118G571257222062 RIB CESSNA441 441 2076020CE RT CENTER WING CRACKED B K NONE O OTHER ININSP/MAINT 1 SO15621SC10559 4410070 DURING A SHCEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCWS 26.85) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45) AND EXTENDING APPROXIMATELY 1.5 INCH AFT OF THE SPAR. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. 1L72 3T RTA28CE 20020124000912002012400091CE 2002 1 24 2002FA0000130 120020123G30102H4814 VALVE CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO DEICE SYSTEM FAULTY D O OTHER O OTHER NRNOT REPORTED 1 GL25340SV 340A1003 REPLACED DEFECTIVE SURFACE DEICE CONTROL VALVE WITH NEW 2H48-14 S/N 2AU 29. ON RUN CHECK FOUND SYSTEM TO HAVE UNCOMMANDED SURFACE DEICE ACTIVATION. CHECKED SYSTEM AND FOUND NEW VALVE LEAKING FROM FAULTY ASSEMBLY AT RIVETED TOP CAP WHERE SOLENOID IS ATTACHED. THIS ALLOWS FAULTY SEAL AND AIR BYPASS TO ACTIVATE VALVE. 1L72 3O3 O 3A25 E8CE 20020124000942002012400094CE 2002 1 24 2002FA0000132 120020123G3340TTGCTA201TWB SWITCH CESSNA172 172N 2072434CE TAXI LIGHT FAILED B O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 WP075124E 17271723 SWITCH ARCED INTERNALLY AND QUIT WORKING. SWITCH TERMINALS WERE CLEAN AND THE WIRE SLIP-ON CONNECTORS WERE CLEAN AND TIGHT. WHEN SWITCH FAILS IT EMITS A BIT OF SMOKE. THESE SWITCHES FAIL ON A REGULAR BASIS. 1H71 3O NT3A12 20020125000012002012500001CE 2002 1 25 2002FA0000134 120020116G7120J96135 SHOCK MOUNT BEECH 55 95A55 1152704CE CONT O470 IO470L 17026SO RT ENGINE MISSING B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO119624Y TC377 1920027LR FOUND RIGHT FORWARD ENGINE VIBRATION ISOLATOR MOUNT AND ATTACH HARDWARE MISSING FROM RIGHT ENGINE. 1L72 3O3 O 3A16 3E1 20020128000442002012800044EU 2002 1 28 2002FA0000135 120020116G2913GHE1004 PUMP UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE HYDRAULIC SYS SLUGGISH C O OTHER O OTHER NRNOT REPORTED 1 WP25266SD346 1133 FLIGHT CONTROLS HAD A SLIGHT RATCHET FEELING AND SLUGGISH. HYDRAULIC OFF CHECKS RESPONDED SLOWLY (10 SECONDS). PROBABLE CAUSE: LOWER THAN NORMAL PRESSURE AND/OR LOWER THAN NORMAL FLOW. 1G72 3U3 UNCR0001RD E34NE 20020128000492002012800049 2002 1 28 2002FA0000137 420020110G2561SMV2102 LIFE VEST CABIN FAILED C KQ1RK NONE L NO TEST ININSP/MAINT 1 EA25 LIFE VEST FAILED, 20020129000012002012900001CE 2002 1 29 2002FA0000138 120020128G5412 FIREWALL CESSNA172 172R 2072401CE NACELLE CRACKED D K NONE O OTHER ININSP/MAINT 1 GL039577F1075 17280526 IT WAS DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LT LOWER FIREWALL HAD A NEARLY 3 INCH CRACK BENEATH THE CENTER, LOWER COWL MOUNT DOUBLER. THIS CONDITION WAS ALSO DISCOVERED ON THE NEXT FOUR LIKE AIRCRAFT AND THEY WERE ALL CORRECTED IN ACCORDANCE WITH SERVICE BULLETIN 98-53-02, REVISION 2, DATED 12/26/00 1H71 3O NT3A12 20020130000042002013000004EU 2002 1 30 2002FA0000139 120020117G3340350A73029001 CONTROL PANEL UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE SEARCH LIGHT FAILED C K NONE L NO TEST ININSP/MAINT 1 WP25277SD58 1134 SX 16 NIGHTSUN QUIT OPERATING. FOUND RELAY PANEL INOPERATIVE. REPLACE RELAY ASSEMBLY. PROBABLE CAUSE: RELAY INTERNAL FAILURE. 1G72 3U3 UNCR0001RD E34NE 20020130000052002013000005EU 2002 1 30 2002FA0000140 120020117G3340350A73029001 CONTROL PANEL UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE SEARCH LIGHT INOPERATIVE C O OTHER L NO TEST NRNOT REPORTED 1 WP25277SD58 1134 SX16 NIGHTSUN QUIT OPERATING. FOUND RELAY PANEL INOPERATIVE, REPLACE RELAY ASSEMBLY. PROBABLE CAUSE: RELAY INTERNAL FAILURE. 1G72 3U3 UNCR0001RD E34NE 20020130000062002013000006EU 2002 1 30 2002FA0000141 120020117G33406485000 LIGHT UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE ANTICOLLISION SHORTED C O OTHER L NO TEST NRNOT REPORTED 1 WP25266SD9 1133 ANTI COLLISION LIGHT POPPED CIRCUIT BREAKER. REPLACED WITH NEW ASSEMBLY. PROBABLY CAUSE: INTERNAL SHORT CIRCUIT. 1G72 3U3 UNCR0001RD E34NE 20020130000072002013000007NE 2002 1 30 2002FA0000142 220020117G7313319307840 NOZZLE UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE TURBINE SECTION BURNED C O OTHER O OTHER NRNOT REPORTED 1 WP25266SD200 1133 34144 ENGINE WOULD NOT START. REPLACED START NOZZLES (START-INJECTORS). POSSIBLE CAUSE: FUEL BURNED IN NOZZLE AT END OF START CYCLE. 1G72 3U3 UNCR0001RD E34NE 20020130000152002013000015SO 2002 1 30 2002FA0000146 120020116G2720317729 CONTROL CABLE MAULE M5 M5235C 5460135SO LYC O540 O540* 41532EA RUDDER LOOSE D O OTHER O OTHER NRNOT REPORTED 1 NM03382X 1660 7021C UPON LANDING, WINDS WERE DOWN RUNWAY AT 15 MPH, THE LEFT RUDDER CABLE CAME LOOSE AT AIRCRAFT NICOPRESS SLEEVE CAUSING AIRCRAFT TO GROUND LOOP. THERE WAS NO EVIDENCE OF CORROSION ON CABLE OR SLEEVE AND SLEEVE WAS PREVIOUSLY INSPECTED FOR CORRECT SWEDGE PER AD. THE AIRCRAFT IS REPAIRABLE AND WILL BE REPLACING ALL CABLES AND DOUBLING THE NUMBER OF NICOPRESS SLEEVES TO ENSURE SECURITY. 1H71 3O3 O 3A23 E295 20020130000022002013000002SO 2002 1 30 2002FA0000147 120020130G2822481780 PUMP PIPER PA28 PA28R201 7102816SO FUEL SYS SHORTED D D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 EA11448PA154 2844063 FUEL PUMP CIRCUIT BREAKER POPS. RESET BREAKER POPS AGAIN WHEN PUMP SWITCH IS TURNED ON. 1L71 3O 2A13 20020130000032002013000003SO 2002 1 30 2002FA0000148 120020130G2140484180 SHUTOFF VALVE PIPER PA44 PA44180 7104402SO HEATER LEAKING C O OTHER KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 SO15432PA474 4496058 CREW REPORTED FUEL FUMES IN COCKPIT WHEN HEATER SELECTED ON. SUBSEQUENT INSPECTION REVEALED THAT FUEL REGULATOR AND SHUTOFF VALVE WAS LEAKING. 1L72 3O A19S0 20020130000922002013000092EU 2002 1 30 2002FA0000151 120020127G291342046 PUMP FOKKERF28 F28MK0070 4990811EU RROYCETAY TAY62015 04564NE HYD SYS LEAKING C A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 GL23324K 1490 11545 17107 APPROX. 2 HOURS INTO FLIGHT FROM DTW TO SNA SYSTEM 1 PUMP 1 FAULT LIGHT ILLUMINATED. CREW FOLLOWED THE ABNORMAL PROCEDURES FOR HYDRAULIC SYSTEM 1 LOW PRESSURE. CREW NOTICE SYSTEM NR 1 QUANTITY BEGINING TO DROP. CREW DIVERTED HOPING TO GET ON THE GROUND BEFORE LOSS OF TOTAL SYSTEM 1 QUANTITY AND PRESSURE. 15 - 20 MINUTES LATER SYSTEM 1 LO QUANTITY ALERT ILLIMINATED. GEAR AND FLAPS WERE LOWERED USING THE ALTERNATE PROCEDURES. AIRCRAFT LANDED AT THE SLN AIRPORT. A MAINTENANCE CREW WAS DISPATCED FROM DTW TO REPAIR THE PROBLEM. THE MAINTENANCE CREW INSPECTED THE LEFT ENGINE FOUND THE NR 1 HYD. PUMP LEAKING AT THE PUMP SPLIT LINE. THE PRESSURE FILTER WAS INSPECTED FOR CONTAIMINATION, NONE WAS FOUND. THE PUMP WAS RE2L72 4F4 FRTA20EU E25NE 20020201000012002020100001CE 2002 2 1 2002FA0000152 120020131G2731 PIN CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ELEVTOR TRIM SHEARED B K NONE O OTHER ININSP/MAINT 1 SO0324442474 17280862 L2869351A WHILE REMOVING THE TRIM TAB ACTUATOR FOR SERVICE, BOTH GROOVE-PINS (P/N 3/32X.38TYPE3) WHICH ATTACH THE ROLL CHAIN SPROCKET, (P/N 0310332-0) TO THE SCREW-INTERNAL THREADS (P/N 1260049-1) OF THE TRIM TAB ACTUATOR WERE FOUND TO HAVE SHEARED. THIS ALLOWED THE SPROCKET TO BE SLIPPED OFF BY HAND. ONLY FRICTION BETWEEN THE SPROCKET AND THE SCREW-INTERNAL THREADS WAS ENABLING THE TRIM TAB TO BE MOVED. 1H71 3O3 ONT3A12 1E10 20020201000022002020100002SO 2002 2 1 2002FA0000153 120020131G5600494739 WINDOW PIPER PA46 PA46350P 7104602SO PWA PT6 PT6A34 52043EA HARTZLHCE4N HCE4N3 NE FUSELAGE CRACKED B O OTHER O OTHER CRCRUISE 1 GL099167Q760 15 4622031 PCKRB008 HH1000 WINDOW CRACKED LOWER FORWARD CORNER FROM STORM WINDOW OPENING TO MOUNTING BOLTS. AIRCRAFT WAS AT CRUISE AND 5PSI WHEN INCIDENT OCCURED. 1L71 3O4 TRTA25SO E4EA 5 CP10NE 20020205000442002020500044SO 2002 2 5 2002FA0000156 220020105G8530 CONNECTING ROD CESSNA172 172H 2072424CE CONT O300 O300* 17022SO NR 3 CYLINDER FAILED D O OTHER RY PARTIAL RPM/PWR LOSS ENGINE STOPPAGE NRNOT REPORTED 1 EA233910R 17255410 NR 3 CYLINDER CONNECTING ROD AND CAP FAILED AT THE CRANKSHAFT. CONNECTING ROD FELL TO BOTTOM OF CYLINDER BORE AND WAS REPEATEDLY STRUCK BY THE CRANKSHAFT UNTIL ENGINE WAS SHUT DOWN. THE FAILURE OCCURRED AFTER FINAL POWER REDUCTION DURING A ROUTINE LANDING. PILOT REPORTED HEARING A LOUD BANG FOLLOWED BY POWER LOSS. CAUSE OF FAILURE INDETERMINABLE. PROBABLE CAUSE OF FAILURE DEFECT IN ROD CASTING. NOTED THAT THIS ENGINE HAS A MANUFACTURER RECOMMENDED TBO TIME OF 1800 HOURS. ENGINE HAD 2115 HOURS ON IT SINCE MAJOR OVERHAUL. ENGINE DISASSEMBLY WAS FOUND THAT ONE OF THE TWO ROD CAP BOLTS HAD BACKED OFF, AND THE NUT WAS FOUND IN THE BOTTOM OF THE CASE. 1H71 3O3 ONT3A12 E253 20020205000452002020500045 2002 2 5 2002FA0000157 420020121G3452118280001 TRANSFORMER PIPER PA38 PA38112 7103812SO LYC O235 O235* 41505EA TRANSPONDER SHORTED D K NONE O OTHER ININSP/MAINT 1 GL092509A 3878A0724 TRANSFORMER SHORTED. 1L71 3O3 O A18SO E223 20020312000052002031200005WP 2002 3 12 2002FA0000162 120020114G32461542511 WHEEL DOUG DC8 DC8* WP MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 SO19 DC8, MAIN WHEEL ASSEMBLY, NON DESTRUCTIVE TESTING INSPECTION SHOWED HI-CONDUCTIVITY. 2L74 4J F 4A25 20020312000062002031200006WP 2002 3 12 2002FA0000163 120020114G32462601475 WHEEL DOUG DC8 DC8* WP MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 SO19 DC8, MAIN WHEEL ASSEMBLY, NON DESTRUCTIVE TESTING INSPECTION SHOWED CRACK INDICATION AT TUBE WELL AREA. 2L74 4J F 4A25 20020312000072002031200007 2002 3 12 2002FA0000164 420020119G2561P0201105 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 INDIVIDUAL FLOTATION DEVICE FAILED MFG RECOMMENDED 2 PSI CELL TEST IAW SB. 20020311001052002031100105EU 2002 3 11 2002FA0000165 120020118G2910704A33690004 BELT SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE HYDRAULIC SYS DEBONDED D A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 WP19352NT395 2553 886 WHILE RETURNING FROM STRIP TOURS, THE AIRCRAFT EXPERIENCED A LOSS OF HYDRAULIC POWER. UPON SAFE LANDING ON THE TAXI WAY, THE AIRCRAFT WAS IMMEDIATELY TOWED TO THE MAINTENANCE HANGER AND INSPECTED FOR PROBABLE CAUSES OF THE HYDRAULIC FAILURE. IT WAS FOUND THAT THE BONDED SEAM OF THE HYDRAULIC DRIVE BELT HAD SEPARATED AT THE BOND. POSSIBLE RECOMMENDATIONS TO PREVENT REOCCURRANCE WOULD BE HIGHER QUALITY CONTROL AT THE MANUFACTURER OR A HIGHER QUALITY HYDRAULIC DRIVE BELT. 1G71 3U3 UNCH9EU E19EU 20020312000082002031200008CE 2002 3 12 2002FA0000166 120020109G3230501202015 DRAG BRACE BEECH 200 A200 1152921CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SW01783MC12588 BC02 DURING SCHEDULED LANDING GEAR TIME CHANGE, THE DRAG BRACE SUPPORTS WERE CLEANED AND INSPECTED. THE RIGHT DRAG BRACE SUPPORT APPEARED TO BE CRACKED. A DYE-PENETRANT INSPECTION WAS CONDUCTED AND THE CRACKED CONFIRMED. AT THAT TIME AN ALERT WAS ISSUED TO TEST THE FLEET AND ANOTHER 4 SUPPORTS WERE FOUND CRACKED. THE AREA TO PAY CLOSE ATTENTION TO IS THE RADIUS BETWEEN THE TWO LUGS. THE C12 FLEET BEING USED ARE HIGH TIME AIRCRAFT WITH HIGH LANDING CYCLES. DURING MAINTENANCE INSPECTIONS, CLOSE ATTENTION SHOULD BE PAID TO THE DRAG BRACE SUPPORTS. 1L72 4T A24CE 20020312000092002031200009CE 2002 3 12 2002FA0000167 120020116G2421648843 ALTERNATOR BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO ENGINE FAILED B VJ3RO OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 WP035544A72 CE1343 825767R ALTERNATOR FAILED IN FLIGHT, WILL NOT CARRY THE LOAD. REPLACED ALTERNATOR, GROUND CHECKED OK. RETURNED TO SERVICE. 1L71 3O3 O 3A15 E5CE 20020312000102002031200010 2002 3 12 2002FA0000168 420020120G2561P02301105 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 INDIVIDUAL FLOTATION DEVICE FAILED MFG RECOMMENDED 2 PSI CELL TEST. 20020312000112002031200011CE 2002 3 12 2002FA0000169 120020117G24607014300901 CIRCUIT BREAKER CESSNA500 560CESSNA 2076750CE ELECTRICAL ARCED B O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 EA25CGJEI 5600588 COCKPIT FILLED WITH SMOKE AND ODOR OF BURNING MATERIAL. INSPECTION OF WIRING AND SYSTEM INSTALLATION, FOUND ONE TERMINAL ON POWER CIRCUIT BREAKER PANEL WITH EVIDENCE OF ARCING, BUT NOT RELATED TO THIS UNITS OPERATION SOME INTERNAL FAILURE HAS OCCURRED, W HEN POWERED UP IT STARTS TO SMOKE. 2L72 4F RTA22CE 20020312000122002031200012GL 2002 3 12 2002FA0000170 120020128G2822 PUMP DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO FUEL BOOST INOPERATIVE G A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 EA07645DC C0145 806272 ENGINE QUIT DURING STALL PRACTICE. ENGINE WOULD START BUT NOT RUN. LANDED IN FIELD. FUEL PRESSURE TOO LOW. FACTORY REP INSTALLED SETUP GAGES AND ADJUSTED TO PROPER SPECS. ENGINE RAN GOOD AFTER PROPER ADJUSTMENT. 1L71 3O3 ONTTA4CH E7SO 20020312000132002031200013CE 2002 3 12 2002FA0000171 120020109G276055170115 LINE CESSNA500 550 2076604CE SPEED BRAKES CHAFED B CNQ6K NONE K FLUID LOSS ININSP/MAINT 1 EA25133AV1369 5500847 REPORTED HYDRAULIC LEAK INSPECTED AND FOUND TO BE SPEED BRAKE RETRACT LINE. LINE HAS BEEN CHAFFED THROUGH BY CENTER FLAP BELLCRANK PUSH ROD ATTACH HARDWARE. FABRICATED REPLACEMENT LINE AND MADE APPROPRIATED BENDS TO CLEAR OFFENDING AREA OF FLAP BELLCRANK. 1L72 4F A22CE 20020311001062002031100106 2002 3 11 2002FA0000172 420020201G34225050010902 GYRO SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE COCKPIT PRECESSES D K NONE O OTHER ININSP/MAINT 1 WP13891SA 429 2201 4193 GYRO REMOVED DUE TO EXCESS PRECESSION. 1G71 3U3 UNCH9EU E19EU 20020312000142002031200014CE 2002 3 12 2002FA0000173 120020131G5210504300431291 INTERCOSTAL BEECH 200 B200 1152922CE PAX DOOR CRACKED B KX5RK NONE O OTHER ININSP/MAINT 1 GL15417MC4738 BB1526 UPON PHASE INSPECTION OF CABIN DOOR, FOUND EXCESSIVE MOVEMENT FROM HAND RAIL ASSEMBLIES AT HINGE AREAS ON BOTH FORWARD AND AFT HANDRAILS. UPON FURTHER INSPECTION, FOUND BOTH INTERCOSTAL STRUCTURES CRACKED AROUND RIVETS. 1L72 4T A24CE 20020312000152002031200015CE 2002 3 12 2002FA0000174 120020123G781099102992 EXHAUST PIPE CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO RT ENGINE CRACKED B EWGRO OTHER O OTHER NRNOT REPORTED 1 SO05340WT 340A0332 PILOT OBSERVED RT FUEL QUANTITY INDICATOR FAILED, THEN RT FUEL TRANSFER LIGHT ON AND RT LANDING LIGHT CIRCUIT BREAKER POPPED. AFTER FLIGHT, VISUAL INSPECTION OF THE RT ENGINE NACELLE IDENTIFIED A BURN THROUGH NACELLE SKIN ADJACENT TO THE RT ENGINE OVERBOARD TAILPIPE. INVESTIGATION REVEALED THE TAILPIPE HAD FAILED AT THE OUTBOARD BEND, IN THE ENGINE COMPARTMENT, DAMAGING THE EXTERNAL NACELLE SKIN, FIREWALL, CANTED BULKHEAD, ENGINE BEAM, AND WIRING BEHIND THE FIREWALL. 1L72 3O3 O 3A25 E8CE 20020312000162002031200016SO 2002 3 12 2002FA0000175 220020130G8500IO470D ENGINE CESSNA310 310G 2074218CE CONT O470 IO470D 17026SO 5&6 CYLINDERS FAILED D E ENGINE SHUTDOWN E VIBRATION/BUFFET ININSP/MAINT 1 SO198939Z2642 1170 310G0039 WHILE PERFORMING A STATIC GROUND RUN, AT APPROX. 2200 RPMS THE ENGINE SHOOK VIOLENTLY. THE ENGINE WAS QUICKLY SHUT DOWN AND FUEL SHUT-OFF VALVE SELECTED TO THE OFF POSITION. CLOSE INSPECTION OF THE ENGINE REVEALED THAT THE NR 6 CYLINDER HAD SEPARATED FROM THE ENGINE. THE NR 5 CYLINDER WAS JAMMED WITH THE PISTON CONNECTING ROD SEVERED IN HALF. THE FORWARD ENGINE CASE WAS CRACKED IN SEVERAL PLACES EXPOSING BOTH NR 5 AND NR 6 CYLINDER ASSEMBLIES INNER MECHANISM AND CRANKSHAFT. RECOMMENDATIONS ARE TO REMOVE ENGINE AND SUBMIT IT TO A TEARDOWN INSPECTION ALONG WITH A METALLURGIC EVALUATION ON THE INTERNAL PARTS FOR FAILURE. IN PARTICULAR, THE NR 5 CYLINDER CONNECTING ROD AND FORWARD ENGINE CASE. 1L72 3O3 O 3A10 3E1 20020312000172002031200017NE 2002 3 12 2002FA0000176 220020125G7314025323150 PUMP CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FUEL SYSTEM FAILED C NSPAA UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 SO059454B845 208B0072 HAD AN ENGINE FAILURE WHICH RESULTED IN THE AIRCRAFT LANDING SHORT OF THE AIRPORT. NO ONE WAS INJURED AND THE AIRCRAFT WAS NOT DAMAGED. ENGINE QUIT DUE TO ENGINE DRIVEN FUEL PUMP FAILURE. FUEL PUMP WAS REMOVED, A NEW PUMP INSTALLED, AND THE AIRCRAFT RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 20020208000212002020800021CE 2002 2 8 2002FA0000177 120020205G3240S14953 HOSE CESSNA182 182Q 2072732CE RT MLG OUT OF POSITION C K NONE K FLUID LOSS ININSP/MAINT 1 WP234603N2976 18267280 WHILE BOTH MLG TRUNNION FAIRINGS WERE REMOVED FOR OTHER MAINTENANCE, TRUNNIONS AND BRAKE LINES WERE CLEANED AND INSPECTED. OPERATOR DISCOVERED RT BRAKE LINE CHAFED THROUGH AND WEEPING HYDRAULIC FLUID. CHAFED POINT IN LINE WAS A BEAM FLANGE ON TRUNNION WHICH SUPPORTS COPILOT'S STEP. A HOSE (WHICH SHOULD BE POSITIONED MIDWAY ALONG BRAKE LINE TO PREVENT CONTACT WITH THE STEP STRUCTURE) WAS FOUND AT LOWER END OF BRAKE LINE. HOSE SEGMENT HAD EVIDENTLY MIGRATED DOWN THE LINE AS RESULT OF VIBRATION OR ACCUMULATED LANDINGS. LOGBOOK ENTRIES SUGGEST THIS HOSE COMPONENT WAS PART OF ORIGINAL INSTALLATION. 1H71 3O NT3A13 20020312000182002031200018SO 2002 3 12 2002FA0000180 220020124G74146320 MAGNETO PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520* 17040SO RIGHT FAILED D O OTHER O OTHER NRNOT REPORTED 1 CE0547BC 4608129 PILOT REPORTED FAILED RT MAGNETO. REMOVED MAGNETO FROM ENGINE AND DISASSEMBLED. FOUND ONE OF THE COIL ANCHOR WEDGES WAS DISPLACED AND HAD MIGRATED ONTO THE SECONDARY TOWER. THE TOWER WAS BURNED AND MELTED AND THERE WAS OBVIOUS SIGNS OF A DIRECT SHORT AT THE SECONDARY TERMINAL CONTACT TAB. 1L71 3O3 ORTA25SO E8CE 20020211000182002021100018CE 2002 2 11 2002FA0000181 120020208G5720 BRACKET CESSNA500 560CESSNA 2076750CE RT WING FAILED B A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL09300QS2553 0322 IN-TRANSIT LIGHT STAYED ON AFTER GEAR WAS RETRACTED. GEAR WAS EXTENDED AND A/C LANDED WITHOUT INCIDENT. UPON INSPECTION, THE RT GEAR WELL PLACARD CLOSEOUT PANEL WAS FOUND TORN AND BENT UP. THE INBOARD Z-BRACKET HAD FAILED, AS WELL AS THE LOWER ANGLE, THAT THE PANEL IS RIVETED TO. AFTER FAILURE OF BOTH PANEL MOUNT BRACKETS, AIRLOADS MAY HAVE STARTED TO PULL THE PANEL OUT UNTIL THE LANDING GEAR FINALLY CAUGHT IT AND TORE IT UPWARD WHEN GEAR WAS RETRACTED. REPLACED THE PANEL AND BOTH MOUNT BRACKETS. THE Z-BRACKET IN THIS AREA HAS A HISTORY OF FAILING AND IS REPLACED AT FAIRLY FREQUENT INTERVALS. 2L72 4F RTA22CE 20020211000192002021100019CE 2002 2 11 2002FA0000182 120020208G27201285200041 PUSHROD MTSBSIMU300 MU300 5780602CE RUDDER PEDAL CHAFED C K NONE O OTHER ININSP/MAINT 1 GL09399MM6539 A017 UPON INSPECTION, PILOT AND COPILOT RUDDER PEDAL PUSH RODS WERE FOUND SEVERELY CHAFED ON THE TOP SIDE, EVIDENTLY BY MAKING CONTACT WITH THE FLOOR SKIN. THIS CONDITION HAD BEEN OCCURRING FOR QUITE SOME TIME FOR THE PUSH RODS TO HAVE BEEN CHAFED THIS SEVERELY. REPLACED BOTH PUSH RODS WITH NEW. CORRECTED CHAFE CONDITION WITH FLOOR SKIN. RECOMMEND THIS AREA GET PARTICULAR ATTENTION DURING INSPECTIONS TO LOOK FOR CHAFE CONDITION OF THESE PUSH RODS. 2H72 4F RTA14SW 20020312000192002031200019CE 2002 3 12 2002FA0000186 120020129G5412 FIREWALL CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE03361SA 17280755 DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LEFT LOWER FIREWALL HAD CRACK LOCATED BENEATH THE DOUBLER FOR THE LEFT LOWER COWL MOUNT. IN ONE INSTANCE, CRACK WAS ACTUALLY LOCATED BENEATH THE LEFT FLANGE OF THE BATTERY MOUNT. 1H71 3O3 ONT3A12 1E10 20020312000202002031200020CE 2002 3 12 2002FA0000187 120020210G5412 FIREWALL CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ENGINE BAY CRACKED D K NONE O OTHER ININSP/MAINT 1 GL03364MA 172S8007 IT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER W/O KNOWLEDGE OF THE PROBLEM. 1H71 3O3 ONT3A12 1E10 20020312000212002031200021CE 2002 3 12 2002FA0000191 120020210G5412 FIREWALL CESSNA172 172R 2072401CE ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE039577F 17280526 IT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF PROBLEM. 1H71 3O NT3A12 20020312000222002031200022CE 2002 3 12 2002FA0000193 120020210G5412 FIREWALL CESSNA172 172R 2072401CE ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE039532K 17280475 DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM. 1H71 3O NT3A12 20020312000232002031200023CE 2002 3 12 2002FA0000194 120020210G5412 FIREWALL CESSNA172 172R 2072401CE ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE03361SA 17280755 DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM. 1H71 3O NT3A12 20020312000242002031200024CE 2002 3 12 2002FA0000195 120020210G5412 FIREWALL CESSNA172 172R 2072401CE ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE0324338 17280810 DISCOVERED DURING AN ANNUAL INSPECTION THAT FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER WITHOUT KNOWLEDGE OF THE PROBLEM. 1H71 3O NT3A12 20020312000252002031200025CE 2002 3 12 2002FA0000196 120020201G323008421022 BELLCRANK CESSNA310 310L 2074230CE MLG BROKEN D K NONE O OTHER ININSP/MAINT 1 NM02510V 310L0113 AFTER REPLACING BROKEN SQUAT SWITCH, CONDUCTED ROUTINE RETRACTION TEST TO CHECK FUNCTION OF GEAR. MAINS RETRACTED NORMALLY, NOSE GEAR STARTED TO RETRACT AND THEN BOUND UP. BEFORE LANDING GEAR LEVER COULD BE MOVED TO NEUTRAL POSITION, LOUD BANG AND MOVEMENT OF FLOOR UNDER LEFT SIDE OF CONSOLE NOTED. NOSE GEAR SWUNG FREE, INSPECTION FOUND THAT THE IDLER BELLCRANK HAD A UNSEEN BREAK IN THE METAL AROUND THE REAR BOLT HOLE. THIS ALLOWED THE METAL TO TIP UP AND CONTACT THE BULKHEAD, THE RESULTING BINDING CAUSED THE BOLT AND BEARING IN THE REAR DRIVE TUBE TO BE PULLED OUT OF THE ROD END. FORTUNATELY THIS OCCURRED WHEN AIRCRAFT WAS ON JACKS. 1L72 3O 3A10 20020312000262002031200026CE 2002 3 12 2002FA0000197 120020130G2421 BEARING BEECH 35 S35 1151532CE CONT O520 IO520* 17032SO ALTERNATOR INOPERATIVE B X0FRK NONE L NO TEST ININSP/MAINT 1 WP0710WR 340 A86333 D7689 1203824B AIRCRAFT CAME IN FOR ALTERNATOR FAILURE. TESTED ALTERNERATOR SYSTEM AND DETERMINED ALTERNATOR, FAILED. REMOVED ALTERNATOR, NOTICED THAT THE COTTER KEY, NUT AND WASHER THAT HOLDS THE CLUTCH ON, WAS MISSING. FOUND CLUTCH ASSEMBLY BROKEN AND SHAFT OF ALTERNATOR VERY WORN OUT. REMOVED ENGINE AND OIL PAN. FOUND MISSING HARDWARE IN OIL PAN. APPEARS SHAFT BEARINGS WORN OUT AND SHAFT WAS LOOSE ENOUGH TO BAKE COTTER KEY AND TO DISLODGE NUT AND WASHER. ALTERNATOR INTERIOR OIL SOAKED. FRONT BEARING/SEAL WORN OUT. 1L71 3O3 O 3A15 E5CE 20020312000272002031200027CE 2002 3 12 2002FA0000198 120020115G7120 WASHER CESSNA208 208 2073702CE PWA PT6 PT6A11 52043NE ENGINE BOLTS WRONG PART B K NONE W INADEQUATE Q C ININSP/MAINT 1 AL05208LB801 20800283 DURING A ROUTINE INSPECTION, FOUND THE ENGINE MOUNT BOLTS HAD AN960616L WASHERS INSTALLED UNDER BOLT HEADS (12 BOLTS ) TOTAL. THIS TYPE BOLT MUST HAVE MS20002C6 WASHERS. 1H71 3T3 TNTA37CE E4EA 20020312000282002031200028 2002 3 12 2002FA0000199 420020109G611305503671 SPINNER CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA PROPELLER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL05792SP156 172S8717 FOUND CRACKED PROP SPINNER. 1H71 3O3 ONT3A12 1E10 20020312000292002031200029WP 2002 3 12 2002FA0000201 120020129G2820168863Q01 HOSE NAMER F51 P51D 6402304WP PCKARDV1650 V16507 49001SO FUEL SYSTEM SPLIT D K NONE O OTHER ININSP/MAINT 1 EA1751JB 4473029A UPON INSTALLATION OF A FUEL SELECTOR NOTICED THE OUTER COVER OF THE HOSE SPLIT AS IT WAS INSTALLED ON AN NIPPLE FITTING. AFTER CLOSE EXAMINATION, THE NEW HOSE SHOWS A MARK / CUT GOING THE LENGTH OF THE HOSE. IN SOME AREAS IT IS A MARK AND OTHER AREAS IT IS A CUT THROUGH THE OUTER LAYER OF THE HOSE. THE DEFECT IS STRAIGHT WITH NO WAVERING AND APPEARS LIKE IT CAME FROM THE MANUFACTURES EQUIPMENT THIS WAY. THIS MATERIAL REQUIRED REPLACEMENT OF ALL NEWLY INSTALLED HOSE ON THIS AIRCRAFT. 1L71 4V4 V L113 EXP4V 20020312000302002031200030EA 2002 3 12 2002FA0000204 220020116G8520LW13827 CRANKCASE PIPER PA60 PA60601P 7106012NM LYC O540 IO540S1A5 41532EA RT ENGINE CRACKED G K NONE O OTHER ININSP/MAINT 1 CE07502SB2585 61P0502207 L1784148A CRANKCASE FAILED NEAR NR 2 CYLINDER, CRACKED FROM IN FRONT OF CYLINDER RADIALLY BELOW AND AROUND TO THE REAR OF THE CYLINDER. CRACK EXTENDS MORE THAN 180 DEGREES, ALL 3 UPPER CYLINDER BASE STUDS AND UPPER CRANKCASE THRU BOLT WERE ALL BROKEN. THE ONLY THING STILL HOLDING THE CYLINDER TO THE ENGINE WAS THE LOWER .5000 THRU BOLT. 1M72 3O3 ORTA17WE 1E4 20020312000312002031200031 2002 3 12 2002FA0000205 420020131G2300S28701 SWITCH CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA MICROPHONE INTERMITTENT B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA0735331 17281037 REOCCURING INTERMITTENT PUSH TO TALK SWITCH OPERATION. 1H71 3O3 ONT3A12 1E10 20020312000322002031200032 2002 3 12 2002FA0000206 420020202G2561KS9P0201 LIFE VEST CABIN FAILED B K NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED, MFG RECOMMENDED 2PSI, CELL TEST IAW 25-60-1. 20020312000332002031200033SO 2002 3 12 2002FA0000209 220020123G8520 SLEEVE CONT O520 GTSIO520M 17032SO LIFTER BORE SEPARATED B CQ2RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW15 276346R LIFTER BORES WERE SLEEVED (12 EA) NOTE: SLEEVES CAME LOOSE IN ALL HOLES (EXCEPT 2), ROTATING AND BLOCKING OIL PASSAGE. NO SAFETY PINS IN PLACE TO MAINTAIN SECURITY OF SLEEVES, NO OTHER MEANS OF HOLDING SLEEVES IN PLACE. ONLY THING THAT APPEARED TO HOLD SLEEVES WAS BURR, CREATED WHEN OIL HOLE WAS DRILLED, AND MAYBE DRAIN HOLE AT BOTTOM WAS BURRED. (INTENDED TO HAVE AN INTERFERENCE FIT ONLY, BETWEEN HOLE PREPAIRED FOR SLEEVE AND SLEEVE WAS OF VERY THIN WALL, ALUMINUM SLEEVE MATERIAL HOLE FINISH SIZE IS 1.000 INCH, FOR LIFTER, SLEEVE APPEARS TO HAVE APPROX 1.125 DIAMETER CREATING ONLY A .062 WALL THICKNESS. NOT ENOUGH TO MAINTAIN SECURITY WITHOUT AID OF STABILIZING PIN OR (WELD IN PLACE) OR MEANS OF SAFETY. 3 O E7CE 20020312000352002031200035CE 2002 3 12 2002FA0000211 120020128G3230NAS561P628 PIN CESSNA441 441 2076020CE GARRTTTPE331TPE331* 01514WP LT MLG CRACKED G K NONE O OTHER ININSP/MAINT 1 SW03689AE5026 4410281 DUE TO PIN FAILURE ON AIRCRAFT, PINS WERE REMOVED FOR INSPECTION AND THE LEFT TO THE POINT OF FAILURE . THE FORWARD PIN ON THE RIGHT SIDE WAS INTACT BUT SHOWING SIGNS OF SHEARING. ALL FOUR MAIN LANDING GEAR PIVOT SLOTTED PINS WERE REPLACED WITH NEW NAS561P628. 1L72 3T3 TRTA28CE E2WE 20020312000392002031200039CE 2002 3 12 2002FA0000214 120020213G28201200406131 LINE CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO FUEL VENT CORRODED D K NONE K FLUID LOSS ININSP/MAINT 1 WP09711PJ2500 21061128 LINE DEVELOPED PINHOLE LEAK DUE TO CORROSION WHERE CABIN VENT SCEET HOSE RESTED ON TOP OF IT. 1H71 3O3 O 3A21 E8CE 20020312000402002031200040CE 2002 3 12 2002FA0000216 120020212G3233JE1 ACTUATOR CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520N 17040SO HARTZLHCJ3Y PHCJ3YF2 GL RT MLG BROKEN D O OTHER N FALSE WARNING NRNOT REPORTED 1 CE03340TC9000 3400082 218720R EB1908 RT MLG DOWN LIGHT DID NOT SHOW DOWN AND LOCK. REMOVED RIGHT SWITCH (DOWNLOCK) 1SE1 SWITCH AND ACTUATOR SWITCH LEAF (JE1) FELL OUT. THE JE1 ACTUATOR WAS BROKEN AND PART OF THE ACTUATOR WAS MISSING. ORDERED NEW PARTS,REPLACED 1SE1(SWITCH)AND ACTUATOR JE1 WITH MFG PART, PART NUMBER S2112-1 (ACTUATOR) AND S2088-4(SWITCH). 1L72 3O3 O 3A25 E8CE 5 CP36EA 20020312000412002031200041SO 2002 3 12 2002FA0000217 220020215G8550642841 LINE PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360FB 17025SO ENGINE OIL WORN G A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 NM05113VK2620 450 28R7803352 ENGINE LOST OIL PRESSURE IN CRUISE FLIGHT. THE PILOT MADE AN UNSCHEDULED LANDING. INVESTIGATION REVEALED THAT THE OIL FILLER CAP HAD COME OFF AND THE ENGINE LOST OIL. THE INTERNAL AREA OF THE OIL FILLER TUBE HAD WORN AND WOULD NO LONGER PUT SUFFICIENT PRESSURE ON THE OIL CAP RETAINING SPRING CLIPS. DUE TO THE IMPACT ON SAFETY, THE OIL FILLER TUBE SHOULD BE REPLACED AT ENGINE TBO. 1L71 3O3 O 2A13 E9CE 20020312000462002031200046CE 2002 3 12 2002FA0000223 120020206G57530523921 ROLLER CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA TE FLAP GOUGED B IB1RK NONE O OTHER ININSP/MAINT 1 EA234206K933 17280751 DURING ACCOMPLISHMENT OF SB, THE LT FLAP INBOARD TRACK INBOARD AFT BEARING SUPPORT ARM WAS FOUND TO BE GOUGED .025 INCH DEEP MATCHING THE OUTER RADIUS OF THE ROLLER ASSEMBLY. THE ROLLER ASSEMBLY WAS FOUND TO HAVE THE INNER ROLLER CAGE OFFSET ENOUGH TO ALLOW THE OUTSIDE DIAMETER OF THE ASSEMBLY TO ROTATE AGAINST THE FLAP SUPPORT ARM CAUSING THE GOUGE. THE OFFSET OF THE INNER CAGE WAS FOUND TO BE .025 INCH MATCHING THE DEPTH OF THE GOUGE. PROBABLE CAUSE APPEARS TO BE IMPROPER CENTERING OF THE INNER BEARING CAGE AT INITIAL ASSEMBLY. MFG HAS BEEN NOTIFIED. RECOMMEND BEARING INSPECTION AT FLAP INSTALLATION AND ASSURING CLEARANCE BETWEEN THE BEARING ENDS AND THE FLAP SUPPORT ARMS. 1H71 3O3 ONT3A12 1E10 20020312000472002031200047SO 2002 3 12 2002FA0000224 120020205G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATORS FRAYED B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146D2546 2843153 FOUND THE RT AND LT FORWARD STABILATOR CONTROL CABLES FRAYED AND WORN DURING A 100 HOUR INSPECTION. 1L71 3O3 O 2A13 E286 20020312000492002031200049CE 2002 3 12 2002FA0000226 120020206G7120085112120 BEAM CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO RT ENGINE CORRODED B FCPRK NONE O OTHER ININSP/MAINT 1 NM092696U 340A0780 FOUND RT OUTBOARD ENGINE BEAM CORRODED BEYOND LIMIT, CANTED BULKHEAD WAS ALSO CORRODED BEYOND LIMITS. SUGGEST SHORTER INTERVAL BETWEEN INSPECTIONS. 1L72 3O3 O 3A25 E8CE 20020312000502002031200050 2002 3 12 2002FA0000227 420020129G2561KA9P0101103 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST CELL FAILED. MFG RECOMMENDED 2 PSI TEST IAW MANUAL. DOM OCT 1981. 20020312000512002031200051 2002 3 12 2002FA0000228 420020210G2561KS9P0101 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED THE MFG. RECOMMENDED 2 PSI CELL TEST IAW MANUAL. DOM APRIL 1982. 20020312000542002031200054SO 2002 3 12 2002FA0000230 220020110G8520630393 PUSHROD PIPER PA34 PA34200T 7103406SO CONT O360 LTSIO360EB 17025SO LT ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 EA17912843197 1371 347970111 306764 ON ANNUAL INSPECTION OF THE LT ENGINE (TOTAL TIME 3197.9) THREE PUSH RODS WERE NOTED TO BE CRACKED ALONG ALMOST THE ENTIRE LENGTH OF THE PUSHRODS EXTENDING FROM THE VERY TOP. PUSHRODS REPLACED WITH NEW AND 9 OVERHAULED. BECAUSE OF THIS FINDING ALL 12 PUSHRODS ON RIGHT ENGINE WERE OVERHAULED. CAUSE UNKNOWN. RECOMMEND MORE FREQUENT INSPECTION OF PUSHRODS. CRACK IN PUSHROD EXTENDING FULL LENGTH OF ROD. 1L72 3O3 O A7SO E9CE 20020312000572002031200057SW 2002 3 12 2002FA0000234 120020108G57115147L SPAR BBAVIA7 7AC 2110102SW WING CRACKED D K NONE O OTHER ININSP/MAINT 1 EA23820273528 7AC653 RIGHT REAR SPAR CRACKED ON TOP AT OUTBOARD END OF STRUT ATTACHMENT DUBBLER. TIP OF SPAR HAS DUBBLER PLATES. SPAR HAS BEEN DAMAGED BEFORE. 1H71 3O A759 20020312000722002031200072SW 2002 3 12 2002FA0000249 120020201G5711 SPAR BBAVIA7 7AC 2110102SW CONT A65 A65* 17003SO LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL0383280 1947 DURING INSPECTION OF AD INSPECTION. FOUND LEFT WING FORWARD SPAR CRACKED AT UNDER SIDE OF SPAR OUT BOUND OF LIFT STRUT ATTACH POINT. OWNER WAS CALLED TO INFORM HIM THIS WING WILL BE REPAIRED WITH NEW SPAR INSTALLED. 1H71 3O3 O A759 E205 20020312000772002031200077SW 2002 3 12 2002FA0000254 120020222G5711 SPAR BBAVIA7 7EC 2110120SW CONT C90 C90* 17009SO RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1570824 337 DURING THIS ANNUAL INSPECTION FOUND COMPRESSION CRACKS ON THE RIGHT WING REAR SPAR AT TOP LOCATION ON TOP SIDE OF SPAR. THIS COMPRESSION CRACK WAS HIDDEN UNDER OLD SPAR VARNISH AND WOULD HAVE BEEN MISSED IF TOP INSPECTION HOLES WERE NOT INSTALLED ALSO MANY OTHER CRACKS WERE SPOTTED IN SAME AREAS. BUT WERE NR 2 PENCIL LINES THE MFG USED TO LOCATE THE GLUE LINES. 1H71 3O3 O A759 E252 20020312000812002031200081CE 2002 3 12 2002FA0000257 120020205G561010138402521 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE COCKPIT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NM0963791 BB1100 WINDOW SHATTERED DURING FLIGHT AT ALTITUDE. REPLACED WITH NEW UNIT USING MFG SUPPLIED INSTALLATION KIT. 1L72 4T4 T A24CE E4EA 20020312000832002031200083SO 2002 3 12 2002FA0000259 120020115G322274381 FITTING GULSTMGV GULFSTREAMGV3980116SO RROYCEBR700 BR700710A110 NE NLG CRACKED G O OTHER O OTHER NRNOT REPORTED 1 EA03588GA940 588 AFTER GEAR EXTENSTION, CREW HAD A LOUD BANG, AND NOTICED LOSS OF LEFT HAND HYDRAULIC FLUID. AFTER LANDING INSPECTION SHOWED NOSE GEAR SWIVEL FITTING CRACKED AT FORGED SEAM. 2L72 4F4 FRTA12EA E00057EN 20020312000842002031200084SW 2002 3 12 2002FA0000260 120020201G5710 STRUT BBAVIA7 7CCM 21101MWSW CONT C90 C90* 17009SO WING DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL152762E 7AC6345 WING STRUTS HAD FILLED WITH WATER FROM SITTING OUTSIDE. RUST STAINS VISIBLE FROM OUTSIDE OF STRUT. WHEN POKED WITH AN AWL IT PUSHED A HOLE INTO STRUT AND DRAINED WATER. DRILLED A .0312 HOLE IN BOTTOM OF OTHER 3 STRUTS AND WATER CAME OUT IN EXCESS OF 1 CUP EACH. OWNER NOTIFIED OF UNAIRWORTHY CONDITION. 1H71 3O3 O A759 E252 20020312000852002031200085SW 2002 3 12 2002FA0000261 120020201G5711 SPAR BBAVIA7 7CCM 21101MWSW CONT C90 C90* 17009SO WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL152762E 7AC6345 CRACK ON BOTTOM SURFACE OF SPAR LEFT SIDE REAR. FOUND PRIOR TO CRACK INSPECTION AS PER AD, OWNER DISCONTINUED ANNUAL INSPECTION PRIOR TO FULL INSPECTION. 1H71 3O3 O A759 E252 20020312000882002031200088SO 2002 3 12 2002FA0000266 120020205G5280 BOLT PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA NLG DOOR WORN D K NONE O OTHER ININSP/MAINT 1 WP1957PA 317305081 PILOT REPORTED NOSE WHEEL WOULD NOT LOCK (UP) AND RETURNED TO BASE WITHOUT ABNORMAL INDICATION. MAINTENANCE INSPECTION REVEALED THAT THE BOLTS IN THE NOSE WHEEL RIGHT DOOR WERE WORN AND WERE REPLACED. DOOR WAS STRAIGHTENED AND RERIGGED. RETRACTION AND OPS CHECKED OK. FLOWN AND RELEASED FOR SERVICE. 1L72 3O3 O A20SO E14EA 20020312000902002031200090CE 2002 3 12 2002FA0000268 120020213G324066109 LINER CESSNA172 172N 2072434CE LYC O320 O320* 41508EA BRAKE CYLINDER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW03737ES 17269366 ON INSPECTION OF BRAKE LININGS AT A 100 HOUR INSPECTION, THE RIGHT BRAKE LININGS WERE FOUND CRACKED. UPON REMOVAL, THE THEY WERE FOUND LOOSE ON THE BRAKING PLATE. LINING RIVETS WERE FOUND TO BE IMPROPERLY SWAGED AND APPEARED TO BE COMPRESSED WITH IMPROPER TOOLING. 1H71 3O3 ONT3A12 E274 20020312000912002031200091SO 2002 3 12 2002FA0000269 220020216G8530654441 VALVE SPRING CESSNA188 A188B 2073005CE CONT O240 IO240A SO CYLINDER FAILED D TPMGK NONE L NO TEST ININSP/MAINT 1 SW13731LJ910 18802975T 812753R DURING ANNUAL INSPECTION, PERFORMED A COMPRESSION CHECK ON ALL ENGINE CYLINDERS. TWO CYLINDERS FAILED THE CHECK LEAKING BY THE VALVES. REMOVED CYLINDERS, DISASSEMBLED. CHECKED VALVE SPRINGS INNER AND OUTER TENSION PER CONT OVERHAUL MANUAL USING A VALVE SPRING TESTER AND FOUND THAT THE INNER AND OUTER VALVE SPRINGS FAILED. TOTAL TIME ON THESE SPRINGS 910 SINCE NEW. REPLACED INNER AND OUTER VALVE SPRINGS WITH NEW SPRINGS AFTER CHECKING SPRING TENSIONS. 1L71 3O3 O A9CE E7SO 20020312000922002031200092WP 2002 3 12 2002FA0000270 220020118G725030606901 BLADE GARRTTTFE731TFE7315R 01518WP TURBINE SECTION DAMAGED B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL19 1842 1196 P91152 3RD LPT BLADE SEPARATED AT MID-SPAN CAUSING DAMAGE BEYOND LIMITS TO 7EA 3RD LPT BLADES. ALSO DAMAGED THE EXHAUST NOZZLE AND 3RD LPT NOZZLE BEYOND LIMITS. 4 F E6WE 20020312000932002031200093CE 2002 3 12 2002FA0000272 120020218G8120 CROSSOVER TUBE BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO TURBOCHARGER BROKEN B YEBRK NONE O OTHER ININSP/MAINT 1 CE057254T315 CE1065 813757R DURING AN ANNUAL INSPECTION, THE TURBOCHARGER CROSSOVER TUBE WAS FOUND DAMAGED FROM THE AIRCRAFT DRIVE PULLEY. THIS AIRCRAFT HAS BEEN MODIFIED BY TURBO FLITE STC SA5223NM AND SE5222NM. UPON REMOVAL OF THE TUBE A HOLE WAS DISCOVERED BELOW THE DAMAGED AREA THAT WAS APPARENTLY CAUSED FROM THE INSTALLER DEFORMING THE TUBE TO GAIN CLEARANCE FOR THE DRIVE PULLEY. AFTER ORDERING A REPLACEMENT PART FROM THE MANUFACTURER, I WAS INSTRUCTED TO DEFORM THE TUBE TO GAIN CLEARANCE BETWEEN THE REPLACEMENT TUBE AND AIRCRAFT DRIVE PULLEY. THIS ACTION IS LIKELY TO CAUSE THE TUBE TO FAIL AS MENTIONED ABOVE. 1L71 3O3 O 3A15 E5CE 20020312000942002031200094SO 2002 3 12 2002FA0000273 120020214G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194144K2480 2843145 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS, FAIR LEADS OR ANYPLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE. 1L71 3O 2A13 20020312000952002031200095SO 2002 3 12 2002FA0000274 120020214G270062701114 CONTROL CABLE PIPER PA28 PA28181 7102807SO STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194144K2480 2843145 DURING A ROUTNE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS, FAIR LEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. 1L71 3O 2A13 20020312000962002031200096SO 2002 3 12 2002FA0000275 120020214G270062701123 CONTROL CABLE PIPER PA28 PA28181 7102807SO STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194144K2480 2843145 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMULAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS, FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE. 1L71 3O 2A13 20020312000972002031200097SO 2002 3 12 2002FA0000277 120020220G2701D31 SPROCKET MAULE M6 M6235 5460160SO CONTROL YOKE BROKEN D K NONE O OTHER ININSP/MAINT 1 NE059219Y872 7514C LEFT AILERON CONTROL SPROCKETS STOP PIN WAS FOUND BROKEN OFF. THIS ALLOWED BALANCE WEIGHTS TO HIT UPPER WING SKIN AND AILERON TRAVEL TO 60 BEYOND RECOMMEND UP/DOWN MOVEMENT. SUSPECT PIN WAS BROKEN OFF WITH AIRCRAFT OUTSIDE IN WINDY CONDITIONS WITH NO GUST LOCK INSTALLED. 1H71 3O 3A23 20020312000982002031200098CE 2002 3 12 2002FA0000278 120020202G280025765362 SERVO CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA FUEL SYSTEM MALFUNCTIONED B AP1RO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 EA112317U 17280695 L2802451A REPORTED ENGINE LOST POWER TWICE (ENG RUNNING 1 HOUR). 1H71 3O3 ONT3A12 1E10 20020313000012002031300001CE 2002 3 13 2002FA0000279 120020214G8000S1577A1 CONTACTOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA STARTER STUCK B LV0RK NONE O OTHER ININSP/MAINT 1 CE018908747 15282625 STARTER ENGAGED UPON CLOSING AIRCRAFT MASTER SWITCH. FOUND S1577A1 CONTACTOR IN THE STUCK CLOSED POSITION, WITH NO ELECTRICAL POWER APPLIED. REPLACED CONTACTOR. 1H71 3O3 ONT3A19 E223 20020313000022002031300002EA 2002 3 13 2002FA0000282 220020214G741410357584 GEAR PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA RT MAGNETO DAMAGED D K NONE O OTHER ININSP/MAINT 1 EA039614J1684 283767 RT MAGNETO WAS INTERMITTENT, AND FINALLY FAILED. DISTRIBUTOR GEAR ALMOST HALF OF THE TEETH WERE MISSING. NO RELATED PROBLEMS WITH MAGNETO OR VISIBLE CAUSE. POSSIBLY DAMAGED AT SAME PREVIOUS INSTALLATION. 1L71 3O3 O 2A13 E286 20020313000032002031300003 2002 3 13 2002FA0000283 420020218G3416AR850 ENCODER PIPER PA28 PA28181 7102807SO COCKPIT LEAKING B LV0RK NONE O OTHER ININSP/MAINT 1 CE014143A 2843217 UPON CERTIFYING STATIC SYSTEM THAT THE ENCODER HAD AN INTERNAL LEAK, ENCODER WAS REPLACED WITH NEW. 1L71 3O 2A13 20020313000042002031300004SO 2002 3 13 2002FA0000284 120020218G3710842CW PUMP PIPER PA31 PA31P 7103120SO LYC O541 TIO541E1A4 41536EA VACUUM SYSTEM SEIZED B EKIRK NONE O OTHER ININSP/MAINT 1 WP07648SC 31P7300143 L55562 BOTH PUMPS FAILED WITHIN 30 MINUTES OF EACH OTHER. BOTH LOW TEMPERATURE PUMPS OVERLOADED. 1L72 3O3 O A8EA E10EA 20020313000052002031300005SO 2002 3 13 2002FA0000285 120020219G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194145X2536 2843152 DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLES WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. 1L71 3O3 O 2A13 E286 20020313000062002031300006SO 2002 3 13 2002FA0000286 120020219G270062701114 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194145X2536 2843152 DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E286 20020313000072002031300007SO 2002 3 13 2002FA0000289 120020215G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO STAILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194164Y1258 2843317 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN ANDFRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. 1L71 3O 2A13 20020313000082002031300008CE 2002 3 13 2002FA0000293 120020226G812063272913 TURBOCHARGER BEECH 36 B36TC 1151609CE CONT O520 TSIO520* 17040SO ENGINE LEAKING B EKGRK NONE K FLUID LOSS ININSP/MAINT 1 WP07234PT56 EA662 527458 TURBOCHARGER WAS FOUND TO BE LEAKING OIL INTO INDUCTION SYSTEM. CHECKED SYSTEMS AS PER MFG AND MM. THIS IS NR 1 OF SEVERAL REPLACED ON THIS ENGINE. 1L71 3O3 O 3A15 E8CE 20020313000102002031300010CE 2002 3 13 2002FA0000295 120020122G57510322709 BRACKET CESSNA195 195A 2073110CE JACOBSR755 R7559 35003EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE03195DH 7588 INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERELY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONLY BE SEEN AFTER BEAD BLASTING. THESE BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING COMPLETELY ACROSS THE RETAINING BOSS FOR THE BEARING. SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS. APPROXIMATELY 80 PERCENT OF THE ORIGINAL BRACKETS WE HAVE INSPECTED HAVE BEEN SEVERELY CORRODED/ CRACKED. 1H71 3R3 R A790 TC121 20020313000112002031300011CE 2002 3 13 2002FA0000296 120020122G575103227091 BRACKET CESSNA195 195A 2073110CE JACOBSR755 R7559 35003EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE03195DH 7588 INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERLY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONLY BE SEEN AFTER BEAD BLASTING. THESES BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING COMPLETELY ACROSS THE RETAINING BOSS FRO THE BEARING. SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS. THE ORIGINAL BRACKETS, WE HAVE INSPECTED, HAVE BEEN SEVERELY CORRODED/ CRACKED. 1H71 3R3 R A790 TC121 20020313000122002031300012SO 2002 3 13 2002FA0000297 120020225G29101776604 HOSE PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA HYD SYSTEM DAMAGED G A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 SW114106F6363 318252034 HOSE ASSEMBLY FAILED AFTER TAKE-OFF AND NOSE GEAR WOULD NOT RETRACT. PILOT TRIED TO HAND PUMP THE MANUAL HYDRAULIC PUMP WITH SO SUCCESS. INSPECTION NOTED LINE BLEW A HOLE BELOW THE TSO TAG AREA. IT IS RECOMMENDED THAT ON ANNUAL INSPECT BOTH ACTUATOR HOSE ASSEMBLY SHOULD BE INSPECTED BELOW THE TSO TAG AND SPIRAL WRAP FOR DAMAGE. 1L72 3O3 O A20SO E14EA 20020313000152002031300015 2002 3 13 2002FA0000300 420020204G6113C5046 PLATE CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C218 GL PROP SPINNER CRACKED B OF1RK NONE W INADEQUATE Q C ININSP/MAINT 1 EA174770T750 R18201758 L2392340A 993189 DURING A 50 HOUR INSPECTION THE SPINNER ASSEMBLY WAS DETECTED TO BE VERY LOOSE ON THE PROP. UPON FURTHER EXAMINATION BOTH SPINNER ATTACH PLATES WERE FOUND CRACKED ALL THE WAY AROUND FOUR OF SIX PROP ATTACH BOLT HOLES. CRACKS EMANATED FROM THE CORNER OF EACH BOLT HEAD AND WENT IN EACH DIRECTION ALL THE WAY TO THE EDGE OF THE ATTACH PLATES (3 CRACKS ON ONE PLATE AND ONE ON THE OTHER). AFTER CHECKING THE PARTS CATALOG IT WAS DETERMINED THAT THE SIX WASHERS REQUIRED FOR THE ATTACH BOLTS HAD BEEN OMITTED DURING THE PROPELLER ASSEMBLY. DURING REPAIR OF AC, INSTALLED THE SIX WASHERS REQUIRED BY THE MFG CATALOG. BELIEVE IT WILL PREVENT FUTURE REOCCURRENCE. 1H71 3O3 ORT3A13 E295 5 CP7EA 20020313000162002031300016CE 2002 3 13 2002FA0000303 120020207G812063272913 TURBOCHARGER BEECH 36 B36TC 1151609CE CONT O520 TSIO520* 17040SO ENGINE LEAKING B EKGRK NONE K FLUID LOSS ININSP/MAINT 1 WP07234PT21 EA662 527458 TURBOCHARGER LEAKING OIL IN INDUCTION. THIS UNIT WAS REMOVED AND RETURNED DIRECTLY TO MFG FOR INVESTIGATION. THIS IS NR 3 FOR THIS ENGINE. NO WORD FROM MFG ON CAUSE OF PROBLEM. ENGINE IS TO BE REPLACED BY MFG. 1L71 3O3 O 3A15 E8CE 20020311001102002031100110EU 2002 3 11 2002FA0000306 120020117G2435M20014 BRUSHES UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE STARTER GEN WORN C K NONE O OTHER ININSP/MAINT 1 WP25255SD300 1618XL 1102 34117 DEFECT FOUND DURING SCHEDULED MAINTENANCE, 100 HOUR INSPECTION. STARTER GENERATOR HAD PRIOR OVERHAUL AND MODIFICATION TO (XL) CONFIGURATION. FOUND 4 BRUSHES WORN LIMIT, 4 WITH UNDER 10 HOURS APPROXIMATE TIME LEFT. STARTER REPAIRED, NEW BRUSHES INSTALLED. POSSIBLE WRONG OR TOO SOFT CARBON COMPOUND. 1G72 3U3 UNCR0001RD E34NE 20020313000182002031300018CE 2002 3 13 2002FA0000307 120020304G5610511604202 WINDSHIELD CESSNA421 421B 2076014CE CONT O360 TSIO360* 17025SO COCKPIT DEPARTED D O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 SW01421LP 421B0323 AT APPROXIMATELY 17,000 FEET CO-PILOTS WINDSHIELD DEPARTED AIRCRAFT, RECOMMEND LARASCOPE INSPECTION OF WINDSHIELD HOLES. TOTAL TIME ON PART 6,234.9. 1L72 3O3 O A7CE E9CE 20020311001112002031100111WP 2002 3 11 2002FA0000308 120020209G3246369A795149 BEARING HUGHES369 369D 4470706WP ALLSN 250C 250C20 03013GL MLG INOPERATIVE B EOORK NONE O OTHER ININSP/MAINT 1 AL035074R 1151D FOUND LEFT FRONT MAIN LANDING GEAR KEEL BEARING AND RETAINER BACKED OUT OF KEEL FITTING. IT IS NORMALLY RETAINED WITH A CIRCLIP BUT IT WAS NOT ENGAGED BUT IT WAS CAPTURED BY THE BOLT. THE LIMIT OF REMOVAL WAS DEFINED BY THE FORK ON THE END OF THE LANDING GEAR LEG. THE ID OF THE BORE IN THE KEEL FITTING WAS WITHIN LIMITS AND A NEW RETAINER AND BEARING WERE INSTALLED WITH A NEW CIRCUP. 1G71 3U3 U H3WE E4CE 20020311001122002031100112WP 2002 3 11 2002FA0000309 120020212G3210369HG20073 GUIDE HUGHES369 369D 4470706WP ALLSN 250C 250C20 03013GL MLG BROKEN B EOORK NONE O OTHER ININSP/MAINT 1 AL035074R 1151D DURING 100/300 ROUTINE INSPECTION THE GUIDE TUBE FOR THE SPRING LOADED FILLETS WERE FOUND BROKEN ON (3) THREE LANDING GEAR. 1G71 3U3 U H3WE E4CE 20020313000192002031300019SO 2002 3 13 2002FA0000310 120020222G3110587837 MASTER SWITCH PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO COCKPIT BROKEN B CTURK NONE O OTHER ININSP/MAINT 1 GL213054K 347970102 307788 THE MASTER SWITCH IS DIVIDED INTO TWO SWITCHES A THAT ARE COUPLED TOGETHER WITH A PLASTIC TAB. THE HALF OF THE SWITCH THAT CONTROLS THE ALTERNATOR FIELDS IS HIDDEN UNDER THE SIDE PANEL. WHEN THE TAB THAT COUPLES THE TWO TOGETHER BROKE, THE ALTERNATORS DROPPED OFF LINE. 1L72 3O3 O A7SO E9CE 20020311001612002031100161SO 2002 3 11 2002FA0000311 120020311G2700 COTTER PIN PIPER PA28 PA28161 7102803SO BRAKE BROKEN D K NONE O OTHER ININSP/MAINT 1 GL11 2842096 DURING ROUTINE CABIN INSPECTION THE COTTER PIN THAT CONNECTS THE PILOT RT PEDAL AND THE TOE BRAKE CLEVIS TO THE BRAKE MASTER CYLINDER WAS FOUND MISSING AT THE TOP OF THE ASSEMBLY. UPON FURTHER INSPECTION THE WASHER WAS ALSO MISSING AND THE PIN WAS BACKING OUT. THE COTTER PIN WAS DISCOVERED ON THE FLOOR ALONG WITH THE WASHER, THE CONDITION OF THE COTTER PIN WAS WORN SUGGESTING THAT THE PILOTS FEET HAD COME INTO CONTACT WITH THE COTTER PIN REPETIVATILY CAUSING THE PIN TO FAIL AND BACK OUT. THE FLAT HEAD PIN WAS REINSTALLED TOWARD THE CENTER OF THE CABIN, PREVENTING FEET FROM COMING IN CONTACT WITH THE COTTER PIN, AND THE COTTER PIN WAS REPLACED WITH THE WASHER. SUBMITTER SUGGESTS THAT PA28-161 WARRIOR III'S B1L71 3O 2A13 20020311001622002031100162SO 2002 3 11 2002FA0000312 120020311G2720 COTTER PIN PIPER PA28 PA28161 7102803SO PEDAL BROKEN D K NONE O OTHER ININSP/MAINT 1 GL11 2842098 DURING ROUTINE CABIN INSPECTION IT WAS DISCOVERED THAT THE COTTER PIN WHICH HOLDS THE PILOTS RIGHT PEDAL AND CLEVIS ASSEMBLY TO THE BRAKE CYLINDER WAS DAMAGED AND BACKING OUT. THE DAMAGE WAS APPENTLY CAUSED BY THE PILOTS RIGHT FOOT COMING IN CONTACT WITH THE COTTER PIN AND RUBBING IT. SUBMITTER SUGESTS INSTALLING THE FLAT HEAD PIN SO THAT THE COTTER PIN WILL BE TO THE CENTER OF THE AIRCRAFT AND FEET WILL NO LONGER COME INTO CONTACT WITH IT. 1L71 3O 2A13 20020311001642002031100164SO 2002 3 11 2002FA0000315 120020225G71608624534 AIR BOX PIPER PA44 PA44180 7104402SO ENGINE BROKEN B K NONE O OTHER ININSP/MAINT 1 SO157707B122 60 4496090 THE CARBURETOR AIR BOX AIR INLET TUBE BROKE OFF. THE WELD ON THE INSIDE OF THE BOX HAD BEEN GROUND OFF AT THE FACTORY. THE BOX ASSY NR WAS 86245-34 AND THE PART THAT BROKE OFF HAD A NR OF 86245-035. 1L72 3O A19S0 20020311001652002031100165CE 2002 3 11 2002FA0000316 120020208G32405100106159 LINE CESSNA414 414A 2075907CE BRAKE SYSTEM FAILED D K NONE K FLUID LOSS ININSP/MAINT 1 SO1127340 414A0462 DURING MAXIMUM POWER MAINTENANCE GROUND RUNUP AFTER ROUTINE OIL CHANGE, THE RIGHT BRAKE FAILED. QUICK ACTION BY THE MECHANIC RUNNING THE AIRCRAFT AVOIDED A POTENTIAL ACCIDENT. FOUND BRAKE LINE UNDER COPILOTS FLOORBOARD TO HAVE A HOLE CORRODED IN IT. THIS ALUMINUM TUBE RUNS BELOW A SECTION OF STEEL WIRE SUPPORTED SCAT HOSE. SUSPECT THAT THE CONTACT WAS MADE BETWEEN THE TUBE AND HOSE CAUSING CORROSION. AREA WHERE DAMAGE OCCURED IS NOT VISUALLY ACCESSABLE, EXCEPT BY BORESCOPE. REPLACED TUBE & MADE SURE NO FURTHER CONTACT IS MADE BETWEEN THE HOSE & TUBE. SUBMITTED BY: JOHN D. TOBIN A&P 2250313 EPPS AIR SERVICE INC. 1L72 3O A7CE 20020311001682002031100168EA 2002 3 11 2002FA0000317 220020225G8520 BEARING MOONEYM20 M20M 5870222SW LYC 0540 TIO540AF1B 41532EA MCAULY3D32C B3D32C417 GL ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 NM01355RZ399 DURING A REGULER OIL CHANGE INTERVAL. METAL CONTAMINATS WER NOTED IN THE FOLDS OF THE OIL FILTER. THEY APPEARED TO BE OF ALUMINUM. FURTHER INVESTIGATION INTO THE PICK UP SCREEN FOUND A LARGER AMOUNT OF DEBRIS. SIZE OF THE DEBRIS APPEARED TO BE AROUND 1/16 OF AN INCH IN SIZE. IN ACCORDANCE WITH TEXTRON LYCOMING SERVICE INSTRUCTION THE AIRCRAFT WAS GROUNDED. SAMPLEL FROM BOTH THE FILTER AND PICK UP SCREEN WERE PACKAGED SEPERATLY AND SENT TO TEXTRON LYCOMING IN THE SAME PACKAGE BUT SEPERATED. TEXTRON CALLED BACK AND SAID THE CONTENS OF THE SAMPLE WERE BEARING MATERIAL. AT THE SAME TIME AS THE OIL WAS DRAINED FROM THE ENGINE, A SAMPLE WAS TAKEN FOR ANALYSIS. THE OIL SAMPLE WAS SHIPPED TO AOA. THE OIL ANALYSIS CAME 1L71 3O3 ORT2A3 E14EA 5 CP58GL 20020313000202002031300020CE 2002 3 13 2002FA0000318 120020208G32405100106159 LINE CESSNA414 414A 2075907CE BRAKE SYSTEM CORRODED D E ENGINE SHUTDOWN K FLUID LOSS ININSP/MAINT 1 SO1127340 414A0462 DURING MAXIMUM POWER RUNUP, AFTER ROUTINE OIL CHANGE, THE RIGHT BRAKE FAILED. QUICK ACTION BY THE MECHANIC RUNNING THE AIRCRAFT AVOIDED A POTENTIAL ACCIDENT. FOUND BRAKE LINE UNDER COPILOTS FLOORBOARD TO HAVE A HOLE CORRODED IN IT. THIS ALUMINUM TUBE RUNS BELOW A SECTION OF STEEL WIRE SUPPORTED SCAT HOSE. SUSPECT THAT THE CONTACT WAS MADE BETWEEN THE TUBE AND HOSE CAUSING CORROSION. AREA WHERE DAMAGE OCCURED IS NOT VISUALLY ACCESSABLE, EXCEPT BY BORESCOPE. REPLACED TUBE & MADE SURE NO FURTHER CONTACT IS MADE BETWEEN THE HOSE & TUBE. 1L72 3O A7CE 20020313000212002031300021CE 2002 3 13 2002FA0000320 120020226G3397TTGCTA201TWB SWITCH CESSNA172 172N 2072434CE INSTRUMENT PANELFAILED B O OTHER B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 WP07739LD 17270620 DURING LANDING APPROACH SMOKE WAS DETECTED IN THE COCKPIT COMING FROM THE LOWER PILOT SIDE INSTRUMENT PANEL FROM THE LANDING / TAXI LIGHT COMBINATION SWITCH. THIS IS AN ONGOING PROBLEM WITH THESE SWITCHES. 1H71 3O NT3A12 20020313000222002031300022SO 2002 3 13 2002FA0000323 120020227G57536559100 STRUCTURE PIPER PA28 PA28R180 7102809SO RT WING FLAPS CORRODED D K NONE O OTHER ININSP/MAINT 1 GL03953CA 28R30214 CORROSION INSIDE FLAPS. CORROSION SEEMS TO BE AGGRAVATED WHERE THE ALUMINUM RIBS BUTT UP AND ARE RIVETED TO THE FLAP STEEL MATERIAL HINGES. 1L71 3O 2A13 20020313000332002031300033CE 2002 3 13 2002FA0000324 120020228G2842C6680500802 TRANSMITTER CESSNA172 172P 2072436CE FUEL QUANTITY DETERIORATED D K NONE O OTHER ININSP/MAINT 1 NM036601K2941 17274218 FUEL QUANTITY TRANSMITTER REMOVED TO REPLACE LEAKING BASE GASKET. FOUND COMPOSITE FLOAT ON TRANSMITTER ARM WAS DETERIORATED DUE TO CONTACT WITH THE TOP OF FUEL TANK WHEN FULL. APPROXIMATELY 1/4 INCH OF FLOAT DETERIORATED ON ONE CORNER. SUBSEQUENTLY FOUND FINE BLACK RESIDUE IN FUEL STRAINER. TRANSMITTER WAS INSTALLED PROPERLY AND NO ADJUSTMENT PROVISIONS ALLOWED. 1H71 3O NT3A12 20020313000362002031300036GL 2002 3 13 2002FA0000325 320020225G61101A105SCM7153 PROPELLER AMRGENAA1 AA1 0630610SO LYC O235 O235C 41505EA MCAULY1A105 1A105SCM GL NOSE SEPARATED G A UNSCHED LANDING ED VIBRATION/BUFFET INFLIGHT SEPARATION CRCRUISE 1 EA215999L2642 142 AA10299 G7005 WHILE CRUISING AT 5000 FEET THE PILOT REPORTED SEVERE VIBRATION. AFTER PERFORMING AN UNEVENTFUL LANDING AND ENGINE SHUT DOWN, THE PILOT OBSERVED THAT APPROXIMATELY 4 INCH INCHES OF ONE BLADE TIP WAS MISSING. FURTHER INVESTIGATION REVEALED THAT A SMALL STONE HAD LEFT A SMALL NICK IN THE LEADING EDGE OF THE PROPELLER BLADE WHICH IS WHERE THE TIP SEPPARATED FROM THE REST OF THE BLADE. 1L71 3O3 O A11EA E223 5 NP918 20020313000372002031300037SO 2002 3 13 2002FA0000326 220020226G8530CN635448FC CYLINDER CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520K 17040SO RT ENGINE BROKEN B A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 SO11986CB 1401 3400328 R21752771K PILOT REPORTED PARTIAL LOSS OF POWER AND VIBRATION FROM RIGHT ENGINE ON CLIMB-OUT. UPON INSPECTION FOUND RIGHT ENGINE NR 2 CYINDER HEAD BROKEN IN THE AREA OF THE FOURTH AND FIFTH COOLING FINS. HEAD WAS COMPLETELY SEPARATED FROM THE BARREL AND WAS HELD IN PLACE ONLY BY THE ENGINE COOLING BAFFLES. 1L72 3O3 O 3A25 E8CE 20020312000012002031200001CE 2002 3 12 2002FA0000327 120020306G3500120041787 LINE CESSNA206 T206H 2073303CE OXYGEN SYS DAMAGED D K NONE W INADEQUATE Q C ININSP/MAINT 1 WP232647U148 T20608105 OXYGEN LINE WAS PERFORATED BY AN UPHOLSTERY TRIM SCRE. DURING THE PROCESS OF A ROUTINE ANNUAL INSPECTION, THE LEFT SIDE TRIM PANES WAS REMOVED AND THE HOLE WAS DISCOVERED. THE LINE SHOULD HAVE BEEN RUN LOWER AND TIED TO A GLUED ON SKIN ATTACH POINT, BUT WAS NOT, PRESUMABLE FROM THE FACTORY SINCE THIS PANEL HAD MOST LIKELY NOT PREVIOUSLY BEEN REMOVED. 1H71 3O RTA4CE 20020312000022002031200002CE 2002 3 12 2002FA0000328 120020307G2822 PUMP BEECH 35 V35 1151538CE FUEL BOOST FAILED C K NONE O OTHER ININSP/MAINT 1 CE05 FUEL PUMP WOULD NOT PRODUCE FUEL FLOW OR PRESSURE. ENGINE WOULD NOT IDLE BELOW 1000 RPM AND WOULD NOT PRODUCE POWER. 1L71 3O 3A15 20020313000382002031300038NE 2002 3 13 2002FA0000329 220020215G73103037088 LINE CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE FUEL BYPASS LEAKING B PB8RK NONE K FLUID LOSS ININSP/MAINT 1 SO15999AD 5600136 LT ENGINE HAD A FUEL LEAK. FOUND FUEL BYPASS TUBE LEAKING. LEAK AT SOLDIER JOINT, CRACK OR OTHER DEFECT. INSTALLED NEW TUBE. 2L72 4F4 FRTA22CE E25EA 20020313000392002031300039CE 2002 3 13 2002FA0000330 120020220G2720100600012 BELLCRANK BEECH 100 B100 1152919CE RUDDER CORRODED B QRXRK NONE O OTHER ININSP/MAINT 1 SW09568K 6662 BE106 REMOVED RUDDER FROM AIRCRAFT FOR OTHER MAINTENANCE. DISCOVERED RUDDER BELLCRANK SEVERELY CORRODED IN THE AREA BENEATH THE RUDDER ATTACH FITTING. REPLACED PART WITH NEW ITEM. 1L72 4T A14CE 20020313000402002031300040CE 2002 3 13 2002FA0000331 120020207G1400 NUT CESSNA210 210D 2073414CE CONT O520 IO520* 17032SO ELT ANTENNA LOOSE B W1NRK NONE O OTHER ININSP/MAINT 1 SW11375HW157 21058251 THE ELT ANTENNA WAS FOUND TO BE LOOSE ON VISUAL INSPECTION. REMOVED ELT ANTENNA ASSEMBLY, FOR PROGRESSIVE INSPECTION. FOUND SHIELD LOCKING NUT SECURING METAL RADIATING ROD TO ANTENNA BASE ASSEMBLY WAS LOOSE. WHEN RADIATING ROD WAS REMOVED FROM ANTENNA BASE ASSEMBLY, THE FEMALE BNC BARREL CONNECTOR SOLDIER JOINT WAS BROKEN. THE SECURING OF THE 24 INCH RADIATING ROD IS ACCOMPLISHED ONLY BY MEANS OF AN INSULATING PLASTIC HOUSING AT THE ANTENNA BASE IN A COMPRESSION NUT. THE FEMALE BNC BARREL SHOULD HAVE BEEN CRIMPED. 1H71 3O3 O 3A21 E5CE 20020313000412002031300041CE 2002 3 13 2002FA0000332 120020207G3710442CW12 PUMP BEECH 58 58 1152740CE CONT O520 IO520* 17032SO VACUUM SYS INOPERATIVE B ODARO OTHER J WARNING INDICATION NRNOT REPORTED 1 EA2158WC TH766 PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS. 1L72 3O3 O 3A16 E5CE 20020313000422002031300042CE 2002 3 13 2002FA0000333 120020207G3700442CW12 PUMP BEECH 58 58 1152740CE CONT O520 IO520* 17032SO VACUUM PUMP INOPERATIVE B ODARK NONE O OTHER ININSP/MAINT 1 EA2158WC TH766 PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS. 1L72 3O3 O 3A16 E5CE 20020313000622002031300062SO 2002 3 13 2002FA0000334 120020110G2140A23D0475 SHUTOFF VALVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA FUEL REGULATOR LEAKING B DQIRO OTHER J WARNING INDICATION NRNOT REPORTED 1 NM074089Y4 318152101 CREW REPORTED FUEL PRESSURE FOR RIGHT ENGINE WOULD DROP INTERMITTENTLY, THE HEATER FUEL SUPPLY COMES FROM FUEL FOR RIGHT ENGINE. TURNED HEATER ON, AND FUEL LEAKED FROM FUEL REGULATOR/SHUTOFF VALVE. THIS WAS A NEW VALVE THAT REPLACED A NEW VALVE PER THE REQUIREMENTS OF AD. 1L72 3O3 O A20SO E14EA 20020313001182002031300118CE 2002 3 13 2002FA0000335 120020308G1420A60088 AMMETER CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP MCAULY4HFR344HFR34C660 NE INST PANEL BLEW OUT G H DEACTIVATE SYST/CIRCUITS P NO WARNING INDICATION CRCRUISE 1 WP17442HA960 4410243 N442HA A CESSNA 441 WAS DECENDING THROUGH APPROX. 12000 FT WHEN THE PROPELLER DE-ICE AMP METER EXPLODED SENDING BROKEN GLASS INTO THE PILOT FACE JUST MISSING HIS EYES. PRIOR TO THE FAILURE THE PILOT HAD SELECTED THE PROPELLER DE-ICE SYSTEM TO THE ON POSITION. TO CYCLE THE SYSTEM PRIOR TO LANDING. THE PILOT SHUT DOWN THE PROPELLER DE-ICE SYSTEM FOLLOWING THIS INCIDENT. THE CIRCUIT PROTECTOR DID NOT OPEN WITH THIS FAILURE. THE GAGE WAS REMOVED AND INSPECTED THE SHUNT LOCATED IN THE BACK OF THE GAGE HAD BURNED AND MELTED OPENING THE CIRCUIT. 1L72 3T4 TRTA28CE E4WE 5 C3PNE 20020313001192002031300119 2002 3 13 2002FA0000336 420020305G2330 CONNECTOR SOCATATBM TBM700 8682000EU PWA PT6 PT6* 52043EA WIRE HARNESS LOOSE B G1KRK NONE O OTHER ININSP/MAINT 1 SO11703QD 129 OPERATOR REPORTED INTERMITTENT DME AND HEADPHONE JACK PROBLEMS. UPON TROUBLESHOOTING, TECHNICIAN DISCOVERED 21 LOOSE CONNECTORS ON THE SYMBOL GENERATOR DUE TO BAD CRIMPING TECHNIQUES. WIRING WAS REPAIRED AND OPERATIONAL CHECKED OK. 1L71 3T3 TRTA60EU E2NE 20020313001202002031300120CE 2002 3 13 2002FA0000337 120020304G32409638003425 MASTER CYLINDER BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO BRAKE SYS INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP078242T CE1610 820462R BRAKE MASTER CYLINDER WILL NOT HOLD PRESSURE, WHEN PRESSURE IS APPLIED TO THE BRAKE IT BLEEDS DOWN. REMOVED AND INSTALLED NEW MASTER CYLINDER, OPERATION CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020314000032002031400003NE 2002 3 14 2002FA0000341 220020226G7314025323150 PUMP CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE FUEL SYSTEM SHEARED D A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 WP11121HA 208B0069 ENGINE FAILED IN FLIGHT DUE TO SHEARED FUEL PUMP DRIVE, AIRCRAFT LANDED SAFELY IN FARMERS FIELD. NO AIRCRAFT DAMAGE. SUGGEST MANDATORY DRIVE REPLACEMENT AT EACH OVERHAUL. 1H71 3T3 T A37CE E4EA 20020314000042002031400004SW 2002 3 14 2002FA0000342 120020219G32324196001C ACTUATOR MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA MLG FAILED D O OTHER J WARNING INDICATION NRNOT REPORTED 1 WP1779830 494 AC MADE GEAR UP LANDING DUE TO FAILURE OF GEAR TO EXTEND EITHER ELEC OR MAN. FAILURE TO OPERATE ELEC WAS NOT DETERMINED BUT PROBABLY IN AC GEAR CONTROL SYS. FAILURE TO EXTEND WITH MAN SYS (EMERGENCY) WAS CAUSED BY A STRIPPED GEAR IN MAN DISENGAGE ASSY MOUNTED ON THE GEAR ACT. WHEN ENGAGEING MAN SYS A LEVER IS MOVED AT DISENGAGE UNIT TO SLIDE FEMALE SPLINED GEAR ONTO SPLINED MALE END OF EXTEN CABLE ALLOWING GEAR TO BE EXTENDED WITH HAND CRANK. ENGAGE LEVER IN CABIN OR LEVER ON DISENGAGE ASSY WAS LOOSE IT WOULD ALLOW FEMALE GEAR TO PARTIALLY ENGAGE CABLE AND DURING ELEC OP FEMALE GEAR WOULD GRIND AGAINST END OF EXTEN CABLE TO POINT THERE WOULDN`T BE ENOUGH TEETH LEFT FOR EMER SYS TO OP. 1L71 3O3 O 2A3 1E10 20020314000022002031400002SO 2002 3 14 2002FA0000343 120020313G7910 SUMP PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA ENGINE OIL CRACKED P K NONE O OTHER ININSP/MAINT 1 WP23137JT1300 4622151 L946761A OIL SUMP CRACKED AT TURBOCHARGER MOUNTING BRACKET ATTACHMENT POINT. 1L71 3O3 ORTA25SO E14EA 20020327000932002032700093CE 2002 3 27 2002FA0000346 120020226G5712082217569 RIB CESSNA310 310P 2074238CE CONT O470 IO470* 17026SO LT WING CRACKED G K NONE O OTHER ININSP/MAINT 1 SW11310GR8825 310P0064 NR 8 RIB, LT WING SIDE BRACE LOCATION HAD CRACK THAT PROPAGATED THE FULL UPPER AREA OF THE SIDE BRACE. THE FORWARD ATTACH BOLT WAS MISSING AND EVIDENCE OF SPINNING ON THE SURFACE OF THE RIB. AFT BOLT WAS HELD BY 2 THREADS. INSPECTED AREA AT ANNUAL. 1L72 3O3 O 3A10 E1CE 20020327000952002032700095SO 2002 3 27 2002FA0000348 120020305G76031159P200597 THROTTLE CABLE GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY5118 54523EU NR 2 ENGINE BROKEN C K NONE O OTHER ININSP/MAINT 1 SO07949NA 221 8974 DURING NORMAL MAINTENANCE INSPECTION THE NR 2 ENGINE THROTTLE CABLE (FS-512 R) WAS FOUND TO BE SEVERELY FRAYED WITH APPROXIMATELY 50 PER CENT OF THE STRANDS BROKEN. THE OTHER CABLES DID NOT HAVE ANY BROKEN STRANDS BUT DID HAVE SOME WIRES BROKEN. 2L72 4F4 FRTA12EA E2EU 20020327000962002032700096EU 2002 3 27 2002FA0000349 120020128G6520350A33109100 GEAR SNIAS 350 AS350B2 8680813EU T/R GEARBOX ROUGH B FF6RK NONE O OTHER ININSP/MAINT 1 NM11 TEETH ON RING AND PINION DO NOT HAVE A POLISHED SURFACE ON FACE OF TEETH. SURFACE IS NOT SMOOTH. 1G71 3U H9EU 20020327000972002032700097EU 2002 3 27 2002FA0000350 120020129G6520350A33109100 PINION GEAR SNIAS 350 AS350B2 8680813EU T/R GEARBOX ROUGH B FF6RK NONE O OTHER ININSP/MAINT 1 NM11 TEETH ON RING AND PINION DO NOT HAVE A POLISHED FINISH ON FACE OF TEETH. SURFACE IS NOT SMOOTH. 1G71 3U H9EU 20020327000982002032700098SO 2002 3 27 2002FA0000351 120020301G571128018 SPAR LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 SO05134K 1821 4072 DURING ANNUAL INSPECTION OF THE CARRY THROUGH SPARS, INTER GRANULAR CORROSION WAS FOUND IN THE BOTTOM WEB OF THE AFT SPAR, NONE FOUND IN THE FORWARD SPAR. PROBABLE CAUSE WAS IN MANUFACTURING. RECOMMEND CONTINUED INSPECTION OF OLD SPARS. 1H71 3O3 O A694 E205 20020327000992002032700099SO 2002 3 27 2002FA0000352 120020301G531228007 BULKHEAD LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO051345K1821 4072 BULKHEAD WAS FOUND CRACKED DURING THE REPLACEMENT OF THE VERTICAL ATTACH FITTING PER AD. PROBABLE CAUSE WAS AN EARLIER GROUND LOOP THIS AIRCRAFT SUFFERED IN 1959. THE CRACK WAS IN BETWEEN TWO BOLT HOLES AND WAS UNNOTICEABLE UNLESS THE VERTICAL FIN WAS REMOVED. 1H71 3O3 O A694 E205 20020327001102002032700110EA 2002 3 27 2002FA0000355 220020201G8500B1741 WHEEL ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE FAN CRACKED D K NONE O OTHER ININSP/MAINT 1 SO062359T3646 2359 1438039A DURING REMOVAL OF FAN ASSEMBLY WHICH IS MOUNTED ON A TAPERED SHAFT, THE FAN MOUNTING WAS FOUND TO BE CRACKED THROUGH. ALSO THE REINFORCEMENT PLATE WHICH IS USED TO STRENGTHEN THE FAN ASSEMBLY WAS FOUND TO BE SEVERELY CRACKED. THIS SIDE OF THE FAN ASSEMBLY MOUNTS TO THE FAN NUT WAS OVER TORQUED CAUSING UNDUE STRESS ON THE TAPERED SHAFT CAUSING THE FAILURE. THIS AREA IS HARD TO INSPECT WITHOUT FAN REMOVAL, THEREFORE IT WENT UNDETECTED WHICH EVENTUALLY LEAD TO THE REINFORCEMENT PLATE CRACKING. SUGGEST USING APPROPRIATE TORQUE ON RETENTION NUT. 1G71 3O3 O H10WE E274 20020327001122002032700112SW 2002 3 27 2002FA0000356 120020318G5711 SPAR BBAVIA7 7ECA 21101NNSW CONT O200 O200* 17020SO RT WING DAMAGED D K NONE O OTHER ININSP/MAINT 1 CE079571S 7ECA379 WHILE RECOVERING WINGS FOUND NUMEROUS LOOSE RIBS THAT HAD RUBBED GROVES IN THE SPARS. SOME SMALL CRACKS ORIGINATING FROM THE NAIL HOLES. AIRPLANE HAD BEEN USED IN AEROBATICS. REPLACED ALL FOUR WING SPARS. 1H71 3O3 O A759 E252 20020320000122002032000012CE 2002 3 20 2002FA0000363 120020319G3010 DUCT CESSNA750 750 2076810CE WING OUT OF POSITION D K NONE O OTHER ININSP/MAINT 1 SW11551AM365 7500155 LEADING EDGES REMOVED FOR INSPECTION IT WAS DISCOVERED THE BLEED AIR TUBE IN BOTH SIDES, P/N UNAVAILABLE, HAD MIGRATED OUTBOARD. THE RETAINING SHEET METAL DIFFUSER WAS GOUGING INTO THE WELDED -T-. 2L72 4J RTT00007WI 20020327001162002032700116CE 2002 3 27 2002FA0000364 120020228G56105116052 WINDOW CESSNA425 425 2076018CE PWA PT6 PT6A60 52043NE FUSELAGE CRACKED B CTYRK NONE O OTHER ININSP/MAINT 1 GL2183GF 4250132 WINDOW, LOCATED IN UPPER CABIN DOOR, WAS FOUND TO HAVE 4 CONSECUTIVE MOUNTING HOLES BROKEN ALONG LOWER EDGE. A RETAINING RING, CALLED OUT IN PARTS BOOK, WAS NOT INSTALLED ON THIS WINDOW. THE INSTALLATION APPEARS TO HAVE BEEN DONE AT THE FACTORY, DUE TO DATE ON WINDOW. NOTE: OTHER WINDOWS ON THIS AIRCRAFT USE RETAINING RINGS. 1L72 3T4 TRTA7CE E4EA 20020327001182002032700118CE 2002 3 27 2002FA0000365 120020214G323050810323 LANDING GEAR BEECH 90 E90 1152914CE PWA PT6 PT6A60A 52043NE MLG FAILED B QH5RK NONE O OTHER ININSP/MAINT 1 NM07727MT LW271 MAIN LANDING GEAR A LOWER TORQUE KNEE, FAILED. 1L72 3T4 T 3A20 E4EA 20020327001192002032700119CE 2002 3 27 2002FA0000366 120020319G3397TTGCTA201TWB SWITCH CESSNA172 172N 2072434CE INSTRUMENT PANELBURNED B K NONE B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 WP079963E 17272301 SWITCH WAS STUCK IN THE OFF POSITION DURING PREFLIGHT.MAINTENANCE FOUND SWITCH INTERNALLY BURNED. UNKNOWN TIME ON SWITCH. 1H71 3O NT3A12 20020327001202002032700120SO 2002 3 27 2002FA0000368 120020307G273062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001212002032700121SO 2002 3 27 2002FA0000369 120020307G2730627701114 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE- SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001222002032700122SO 2002 3 27 2002FA0000370 120020307G271062701123 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001232002032700123SO 2002 3 27 2002FA0000371 120020307G271062701124 CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001242002032700124SO 2002 3 27 2002FA0000372 120020227G273062701113 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE. 1L71 3O3 O 2A13 E286 20020327001252002032700125SO 2002 3 27 2002FA0000373 120020227G273062701114 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE. 1L71 3O3 O 2A13 E286 20020327001262002032700126SO 2002 3 27 2002FA0000374 120020227G271062701123 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA LT AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. 1L71 3O3 O 2A13 E286 20020327001282002032700128EA 2002 3 27 2002FA0000376 220020301G7322MA4SPA TUBE PIPER PA23 PA23160 7102304SO LYC O320 O320* 41508EA CARB DISCHARGE DAMAGED D K NONE O OTHER ININSP/MAINT 1 SW013326P 231277 ENGINE WILL NOT START, FOUND ACCELERATING PUMP DISCHARGE TUBE IN AIR BOX. REMOVE CARBURETOR FOR OVERHAUL. 1L72 3O3 O 1A10 E274 20020327001312002032700131CE 2002 3 27 2002FA0000377 120020302G5550354051303 FITTING BEECH 35 B35 1151506CE CONT E185 E185* 17014SO STAB ATTACH MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 SW015208C D2553 LOOKED AT RUDDERVATORS MOVEMENT, THIS FITTING WAS MOVING, CALLED MANUFACTURER FOR INFORMATION ON THIS FITTING. 1L71 3O3 O A777 E246 20020327001342002032700134EA 2002 3 27 2002FA0000378 220020301G850056A2263401 BOSS PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA RT TURBO STUD CRACKED D K NONE O OTHER ININSP/MAINT 1 SO16727MC460 4636085 L978661A INSPECTOR FOUND LOOSE RIGHT TURBO BOTTOM ATTACHMENT STUD, CAUSED BY CRACKED MOUNTING BOSS IN MAGNESIUM OIL SUMP ASSEMBLY. 1L71 3O3 ORTA25SO E14EA 20020327001352002032700135CE 2002 3 27 2002FA0000380 120020321G3397CM358910 SWITCH CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA TAXI LIGHT FAILED B K NONE L NO TEST TXTAXI/GRND HDL 1 WP07502ER2845 172S8002 TAXI LIGHT SWITCH FAILED IN THE OFF POSITION. 1H71 3O3 ONT3A12 1E10 20020327001362002032700136CE 2002 3 27 2002FA0000381 120020319G2150M5862AR6B MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ACM BLOWER MISOVERHAULED B K NONE O OTHER ININSP/MAINT 1 SW096001L 9 5500169 NR 1 ACM BLOWER MOTOR WAS REPLACED WITH A FRESH OVERHAULED UNIT. THE OVERHAULED BLOWER MOTOR FLEW 9.1 HOURS BEFORE FAILING. WHILE PREPARING TO REPLACE UNIT, IT WAS DISCOVERED THAT THERE HAD BEEN SEVERE ELECTRICAL ARCING TAKING PLACE, AFTER INITIAL INSTALLATION & INSPECTION. THE BLOWER MOUNT CRADLES AND RETENTION STRAPS WERE BURNT IN HALF. DISASSEMBLY OF THE BLOWER MOTOR REVEALED THAT THE POSITIVE WIRE INSIDE THE MOTOR HAD BEEN PINCHED BETWEEN HOUSING LUGS AND HAD CHAFED THRU DURING OPERATION AND HAD GROUNDED TO THE MOTOR CASE. IT WAS FOUND THAT DURING OVERHAUL, THE MOTOR HAD BEEN INCORRECTLY ASSEMBLED. 1L72 4F4 F A22CE E1NE 20020327001372002032700137WP 2002 3 27 2002FA0000382 120020213G5313 STINGER LKHEED1011 10113851 5265010WP FUSELAGE CORRODED G K NONE O OTHER ININSP/MAINT 1 GL11188AT70757 193C1078 FORWARD FUSELAGE SECTION, FORWARD E/E, SURFACE CORROSION ON TOP OF STRINGER 38, FS 297 TO FS 312, BL 45. MAINTENANCE REPAIRED STRINGER AT FS 297 TO 312 IAW SB. 2L73 4F A23WE 20020327001382002032700138EA 2002 3 27 2002FA0000383 220020201G8500B1741 WHEEL ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE FAN CRACKED D K NONE O OTHER ININSP/MAINT 1 SO062359T3646 2359 L1438039A DURING REMOVAL OF FAN ASSEMBLY WHICH IS MOUNTED ON A TAPERED SHAFT, THE FAN MOUNTING HUB WAS FOUND TO BE CRACKED THROUGH. ALSO THE REINFORCEMENT PLATE WHICH IS USED TO STRENGTHEN THE FAN ASSEMBLY WAS FOUND TO BE SEVERELY CRACKED. THIS SIDE OF THE FAN ASSEMBLY MOUNTS TO THE FAN SHAFT BEARING ASSEMBLY. SUSPECT THAT TAPERED SHAFT RETAINING NUT WAS OVERTORQUED CAUSING UNDUE STRESS ON THE TAPERED SHAFT CAUSING THE FAILURE. THIS AREA IS HARD TO INSPECT WITHOUT FAN REMOVAL, THEREFORE IT WENT UNDETECTED WHICH EVENTUALLY LEAD TO THE REINFORCEMENT PLATE CRACKING SUGGEST USING APPROPRIATE TORQUE ON RETENTION NUT. 1G71 3O3 O H10WE E274 20020327001392002032700139CE 2002 3 27 2002FA0000384 120020321G3397TTGCTA201TWB SWITCH CESSNA172 172N 2072434CE TAXI LIGHT BURNED B K NONE B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 WP0738ER 17270698 LANDING/TAXI LIGHT SWITCH QUIT WORKING. SWITCH STUCK IN THE ON POSITION. SWITCH BURNED INTERNALLY. 1H71 3O NT3A12 20020327001402002032700140CE 2002 3 27 2002FA0000385 120020311G28410023810025 GAUGE BEECH 58 58 1152740CE CONT O550 IO550* SO FUEL SIGHT GAUGEMISMANUFACTURED D K NONE O OTHER ININSP/MAINT 1 WP17872AN TH1679 WHILE REPLACING LEFT WING FUEL SIGHT GAUGE IT WAS FOUND THE NEW PART HAD FLOAT ARM INDEXED 180 DEGREE FROM ORIGINAL GAUGE. THIS DIFFERENCE CAUSED FLOAT ARM TO CONTACT LEADING EDGE CURVE AND GAUGE WOULD NOT READ BELOW 45 GALLONS. WHEN ADDITIONAL PART WAS ORDERED, ANOTHER GAUGE WAS ALSO INDEXED WRONG. PARTS RETURNED TO FACTORY. 1L72 3O3 O 3A16 E3SO 20020327001412002032700141CE 2002 3 27 2002FA0000386 120020204G812063272913 TURBOCHARGER BEECH 36 B36TC 1151609CE CONT O520 TSIO520UB 17040SO INDUCTION SYSTEMLEAKING B W45RK NONE K FLUID LOSS ININSP/MAINT 1 WP07234PT EA662 527458 TURBOCHARGER LEAKING OIL IN INDUCTION SYSTEM. RECHECKED SYSTEMS AS PER MFG. AND MM. THIS IS NR2 OF SEVERAL ON THIS ENGINE. 1L71 3O3 O 3A15 E8CE 20020327001422002032700142CE 2002 3 27 2002FA0000387 120020319G561010138402515 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A11 52043NE COCKPIT BROKEN G O OTHER O OTHER NRNOT REPORTED 1 NM07969WB BB969 INNER PANE OF PILOT WINDSHIELD SHATTERED IN CRUISE FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENT. WINDSHIELD HEAT CONTROLLER CHANGED IN CONJUNCTION WITH WINDSHIELD. 1L72 4T3 T A24CE E4EA 20020327001432002032700143CE 2002 3 27 2002FA0000389 120020311G282264621216A2 PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO FUEL SYSTEM INACCURATE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP071568P1 CE1298 825776R UNABLE TO ADJUST FUEL PUMP PRESSURE. PRESSURE IS TO HIGH AT LOW RPM AND THE ADJUSTMENT SCREW BACK ALL THE WAY OUT. PUMP REMOVED AND SENT IN FOR WARRANTY. 1L71 3O3 O 3A15 E5CE 20020327001442002032700144 2002 3 27 2002FA0000391 420020305G6113055036711 SPINNER CESSNA172 172S 2072439CE MCAULY1C160 1C160DTM GL PROPELLER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL0335339149 172S8891 DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED A .7500 INCH CRACK IN THE CORNER OF SPINNER (PN 0550367-1) AND BULKHEAD (PN 0550321-11). 1H71 3O NT3A12 5 NP910 20020327001452002032700145SO 2002 3 27 2002FA0000393 220020313G8520639292 COTTER PIN MOONEYM20 M20K 5870220SW CONT O360 TSIO360LB 17025SO CONNECTING ROD BROKEN D K NONE O OTHER ININSP/MAINT 1 SW13231NJ207 250324 247358R DURING ANNUAL INSPECTION FOUND COTTER PIN IN THE OIL SUCTION SCREEN. THE COTTER PIN WAS BROKEN INTO THREE PIECES. FURTHER INSPECTION OF THE ENGINE FOUND THE COTTER PIN MISSING FROM CYLINDER NUMBER FOURS LOWER CONNECTING ROD BOLT. I BELIEVE THE COTTER PIN WAS IMPROPERLY INSTALLED DURING A PROPELLER STRIKE INSPECTION WHICH ALLOWED THE COTTER PIN TO MOVE WEARING THE PIN TO THE POINT OF FAILURE. 1L71 3O3 O 2A3 E9CE 20020327001462002032700146CE 2002 3 27 2002FA0000395 120020319G561010138402515 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A11 52043NE COCKPIT BROKEN F O OTHER O OTHER NRNOT REPORTED 1 NM07969WB BB969 INNER PANE OF PILOT WINDSHIELD SHATTERED IN CRUISE FLIGHT. AIRCRAFT LANDED WITHOUT INCIDENCE. WINDSHIELD HEAT CONTROLLER CHANGED IN CONJUNCTION WITH WINDSHIELD. NO PROBABLE CAUSE FOR BREAKAGE. 1L72 4T3 T A24CE E4EA 20020327001472002032700147GL 2002 3 27 2002FA0000396 220020315G7261222065505161 OIL TANK BELL 430 430 1182150SW ALLSN 250C 250C* GL ENGINE OIL CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA19430Q 1570 49002 OIL LEAKING AROUND NR 1 INPUT DRIVE ON MAIN TRANSMISSION. DISCOVERED CRACK IN THE BOTTOM OF NR 1 ENGINE OIL TANK APPROXIMATELY 1.5000 INCHES LONG AT THE BOTTOM OUTLET. 1G72 3U3 URTH9SW E4CE 20020327001482002032700148CE 2002 3 27 2002FA0000397 120020307G792030725911 TUBE RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE7315BR WP OIL SYSTEM CRACKED B O OTHER O OTHER APAPPROACH 1 EA2584BA 2110 258313 P107191 ON APPROACH PBI, THE RIGHT ENGINE OIL PRESSURE STARTED TO DROP, OIL TEMP WAS NORMAL. ENGINE WAS SHUTDOWN BY CREW WHEN OIL PRESSURE DROPPED TO 20 PSI. TOUCH DOWN AND DROPPED TO 20 PSI. TOUCH DOWN AND ROLLOUT WAS UNEVENTFUL. FOUND OIL TRANSFER TUBE CRACKED AT FLARE. REMOVED AND REPLACED TUBE (PN 30725911). OIL SERVICED AND LEAK CHECKED. CRACKED TUBE SHOWED NO SIGNS OF IMPROPER INSTALLATION. 2L72 4F4 FRTA3EU E6WE 20020327001502002032700150CE 2002 3 27 2002FA0000398 120020301G289757181061 WIRE CESSNA441 441 2076020CE BOOST PUMP CHAFED B PAZRK NONE O OTHER ININSP/MAINT 1 CE03441SX8332 4410248 FOUND RT WING AUXILLARY BOOST PUMP WIRING, CHAFING ON BOOST PUMP HOUSING CAUSING AN ELECTRICAL ARCING INSIDE OF FUEL BAY. 1L72 3T RTA28CE 20020327000702002032700070CE 2002 3 27 2002FA0000399 120020326G37101H525 MANIFOLD CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA VACUUM SYSTEM DETACHED B K NONE O OTHER ININSP/MAINT 1 SO15482ER2921 17280631 L2780151A THIS AIRCRAFT USES DUAL VACUUM PUMPS. THESE PUMPS ARE CONNECTED TO THE VACUUM SYSTEM VIA A MANIFOLD ASSEMBLY. THIS MANIFOLD PERFORMS TWO IMPORTANT FUNCTIONS, ONE TO ALLOW FOR A COMBINED SOURCE OF VACUUM FROM THESE TWO PUMPS, AS WELL AS PROVIDE AN ISOLATION FUNCTION SHOULD ONE PUMP FAIL. THIS MANIFOLD VALVE, IS ASSEMBLED USING SMALL ALUMINUM RIVETS. THEY HAVE BEEN FAILING ALLOWING THE MANIFOLD VALVE TO SEPARATE WHILE MOUNTED ON THE FIREWALL. THIS RENDERS THE ENTIRE VACUUM SYSTEM INNOPERATIVE, AND COMPLETELY DISCONNECTS THE TWO PUMPS FROM THE SYSTEM. 1H71 3O3 ONT3A12 1E10 20020328000032002032800003SW 2002 3 28 2002FA0000400 120020315G27205420014157 TORQUE TUBE GULSTM560 560 0141402SW LYC O480 GO480* 41527EA RUDDER WORN D UUMRK NONE O OTHER ININSP/MAINT 1 GL072705B6247 205 L115628 DURING AN ANNUAL INSPECTION, WHILE MEASURING RUDDER TRAVELS IT WAS FOUND THAT IF A LITTLE EXTRA PRESSURE WAS APPLIED TO THE RUDDER TRAILING EDGE, ONCE IT HAD REACHED ITS STOP, THE RUDDER TRAVELED AN EXTRA INCH PAST THE SPECIFIED TRAVELS. WHILE THE STOP REMAINED STATIONARY UPON INSPECTION, IT WAS FOUND THAT ALL THE RIVETS ON THE TOP AND BOTTOM OF THE RUDDER TORQUE TUBE WERE LOOSE AND WORN. THE CAUSE IS MORE THAN LIKELY FROM WIND DAMAGE. RECOMMENDATIONS: MAKE SURE THAT THE RUDDER GUST LOCK IS INSTALLED AFTER A FLIGHT. 1H72 3O3 O 6A1 E275 20020328000042002032800004SO 2002 3 28 2002FA0000401 120020206G272066661000 ARM PIPER PA28 PA28236 7102815SO LYC O540 O540* 41532EA RUDDER TRIM BROKEN D K NONE O OTHER ININSP/MAINT 1 EA252147D 287911034 RUDDER TRIM ARM BROKEN OFF WHERE PILOTS TRIM CONTROL ASSY IS CONNECTED. PEDAL TORQUE TUBE ASSY. HAS EXCESSIVE WEAR AND SCORING AT PIVOT BEARING POINTS DUE TO LACK OF LUBRICATION. BROKEN ARM ASSY. SUGGESTED DUE TO OPERATING TRIM CONTROL ON GROUND PREVENTING NLG STEERING FROM MOVING PUTTING EXCESSIVE LOADS ON TRIM ARM. SUGGEST TRIM BE NEUTRALED FRO TAKEOFF WHILE TAXING ALLOWING STEERING TO MOVE FREELY. DEFECT FOUND DURING ANNUAL INSPECTION. 1L71 3O3 O 2A13 E295 20020328000052002032800005SO 2002 3 28 2002FA0000402 120020311G32223503002 ACTUATOR PIPER PA23 PA23160 7102304SO LYC O320 O320* 41508EA NLG BROKEN D K NONE O OTHER ININSP/MAINT 1 SW073285P1572 231233 PILOT WAS TAXIING OFF OF RUNWAY ON AN UNIMPROVED AREA. THE NOSE GEAR DOWN LOCK WAS RELEASED DUE TO ROUGH TERRAIN AND THE NOSE GEAR ACTUATOR ROD WAS BENT APPROXIMATELY 60 DEGREES. 1L72 3O3 O 1A10 E274 20020329001522002032900152SO 2002 3 29 2002FA0000403 120020110G3230HP70310052711 CONTROL VALVE GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY5118 54523EU MLG LEAKING D K NONE O OTHER ININSP/MAINT 1 WP2333PJ 57 L8618 THE VALVE DESCRIBED AT LEFT, WAS INSTALLED DUE TO THE UNIT INSTALLED PRIOR HAVING AN EXTERNAL LEAK. DURING INSTALLATION THE VALVE WAS ADJUSTED TO THE SPECIFICATION DESCRIBED IN THE CMP CODE (ATA CODE) ABOVE. THE AIRCRAFT WAS THEN PUT THROUGH A GEAR SWING (10) TEN TIMES WITH THE UNIT OPERATING NORMALLY. THE AIRCRAFT AND PART DESCRIBED WERE INSPECTED AND THE AIRCRAFT DISPATCHED. 2L72 4F4 FRTA12EA E2EU 20020329001542002032900154CE 2002 3 29 2002FA0000405 120020307G3610CM36914 TUBE CESSNA425 425 2076018CE PNEUMATIC TUBE MELTED D CNQRK NONE O OTHER ININSP/MAINT 1 CE0771HE 4250085 RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT. FOUND PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED. REPLACED TUBING. 1L72 3T RTA7CE 20020329001552002032900155CE 2002 3 29 2002FA0000406 120020307G3610CM36914 TUBE CESSNA425 425 2076018CE PNEUMATIC TUBE MELTED D CNQRK NONE O OTHER ININSP/MAINT 1 CE07425GM 4250033 RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT. FOUND PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED. REPLACED TUBING. 1L72 3T RTA7CE 20020329001562002032900156CE 2002 3 29 2002FA0000407 120020307G3610CM36914 TUBE CESSNA425 425 2076018CE PNEUMATIC TUBE MELTED D CNQRK NONE O OTHER ININSP/MAINT 1 CE07168MA 4250155 RIGHT INSTRUMENT AIR PRESSURE WAS AT ZERO ON THE GROUND AND WOULD INCREASE AS CABIN PRESSURE INCREASED IN FLIGHT. FOUND PNEUMATIC SUPPLY LINE FROM COMMON TEE TO FORWARD PRESSURE BULKHEAD MELTED. REPLACED TUBING WITH SUPERSEDED (PN P610051) TWICE. BOTH TIMES THE LINE MELTED ON POWER APPLICATION. 1L72 3T RTA7CE 20020329001582002032900158EU 2002 3 29 2002FA0000408 120020207G33973057992 TRANSFORMER AIRBUS320 A320232 3930326EU LANDING LIGHT ARCED D K NONE O OTHER ININSP/MAINT 1 WP28437UA 655 OUTPUT TERMINALS ON THE TRANSFORMER ASSEMBLY SHOWS A CLEAR EVIDENCE OF ARCING ONE OF THE TERMINALS HAD BURNED OFF. MFG HAS A SIL. REGARDING THIS CONDITION. 2L72 4F RTA28NM 20020329001602002032900160SO 2002 3 29 2002FA0000409 120020328G5711620540062054 SPAR PIPER PA28 PA28180 7102808SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 EA015160S5277 287105014 REAR SPAR SEVERELY CORRODED UNDER STEEL ATTACH PLATES, P/N 66762-00. DAMAGE WAS FOUND WITH A FLASHLIGHT AND MIRROR, LOOKING AT THE FORWARD SIDE OF THE SPAR THROUGH THE INBOARD RIB LIGHTENING HOLES AND WAS SO FAR PROGRESSED THAT THE EXFOLITATION PROCESS HAD BULDGED AND SPLIT THE SPAR MAKING IT VISIBLE FROM INSIDE THE WING. NO EXTERNAL CORROSION WAS NOTED DUE TO A SIX YEAR OLD PAINT JOB. STEEL PLATES ON FUSELAGE CARRY-THROUGH STRUCTURE ALSO REMOVED TO REVEAL SIMILAR CORROSION WHICH WAS LESS SERVERE. 1L71 3O 2A13 20020329001622002032900162EU 2002 3 29 2002FA0000410 120020307G6730AC67032 SERVO SNIAS 350 AS350B2 8680813EU TAIL ROTOR CRACKED B QH5RK NONE O OTHER ININSP/MAINT 1 NM07 SERVO BODY, CRACKED EXTENSION END. 1G71 3U H9EU 20020329001632002032900163SO 2002 3 29 2002FA0000411 220020115G7414441 MAGNETO CESSNA150 150F 2071814CE CONT O200 O200* 17020SO ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 NM013539L 15062339 INSTALLED NEW CONDENSER DURING MAGNETO INSPECTION. RUN-UP WAS NORMAL. FULL POWER DURING TAKE-OFF SHOWED ROUGH RUNNING ENGINE. FURTHER INSPECTION OF MAGNETO REVEALED THAT NEW M3064 CONDENSER HAD FAILED. 1H71 3O3 O 3A19 E252 20020329001642002032900164SO 2002 3 29 2002FA0000412 120020223G2420 VOLT REGULATOR PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA ELECTRICAL MISSING D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM019395J 283499 OWNER COMPLAINED OF OVERVOLTAGE. FOUND REGULATOR HAD BEEN REMOVED FROM SYSTEM. ALTERNATOR RECENTLY REPLACED. OLD ALTERNATOR MAY HAVE BEEN AUTOMOTIVE WITH INTERNAL REGULATOR. PREVIOUS OWNER PERFORMED MUCH OF THE MAINTENANCE. SUGGEST VERIFYING AIRCRAFT, COMPLETE CHARGING SYSTEM WHEN REPLACING COMPONENTS. 1L71 3O3 O 2A13 E286 20020329001652002032900165SO 2002 3 29 2002FA0000413 220020221G7414M3050 IMPULSE COUPLING CESSNA206 U206F 2073333CE CONT O520 IO520* 17032SO MAGNETOR DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SO191003V483 U20602388 THE WOODRUFF KEY (M2536) THAT LOCKS THE IMPULSE COUPLING ON THE SHAFT WAS FOUND LODGED UNDERNEATH THE IMPULSE COUPLING PAWL, RENDERING ONE OF THE TWO PAWLS IMMOBILE. THE PIN ATTACHING THE PAWL WAS BENT AND THE GAP BETWEEN THE PAWL BOSS AND PLATE WAS NEAR LIMITS. A POSSIBLE CAUSE WAS THAT WOODRUFF KEY WAS NOT PROPERLY SEATED, AND INSTALLATION OF IMPULSE COUPLING DISLODGED THE WOODRUFF KEY. EVENTUALLY THE WOODRUFF KEY LODGE ITSELF UNDER THE PAWL. 1H71 3O3 O A4CE E5CE 20020329001492002032900149EA 2002 3 29 2002FA0000419 220020329G732236596 CHECK VALVE PRECISION HA6 SCWZER269 269D 8059501EA LYC O360 HIO360C1A 41514EA CARBURETOR BACKED OUT D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 SO192039Y927 75114110 0115 L3765036A AIRCRAFT EXPERIENCED A PARTIAL POWER FAILURE ALONG WITH A SUDDEN VIBRATION. DURING THE SUBSEQUENT INSPECTION, THE ACCELERATOR PUMP DISCHARGE CHECK VALVE IN THE CARBURETOR WAS FOUND TO HAVE BACKED OUT OF ITS CHAMBER. RECOMMEND REDESIGNING ALL THE CHECK-VALVES AND JETS IN THE CARBURETOR TO INCORPORATE A PERMANENT NYLON THREAD LOCK IN THE THREADS. 1G71 3U3 O0 4H12 1E10 20020329001512002032900151CE 2002 3 29 2002FA0000420 120020326G2710 TURNBUCKLE BEECH BEECH 35 S35 1151532CE AILERON CABLE SEPARATED D K NONE O OTHER ININSP/MAINT 1 SO192JX 5050 D7811 WHILE IN LEVEL FLIGHT AT 5500FT MSL, ATTEMPTING TO TURN THE AIRCRAFT LEFT WITH THE AILERON A SMALL BUMP/BANG WAS FELT. THE CONTROL WHEEL WENT FULL LEFT,AND THE AIRCRAFT COMMENCED ROLLING TO THE RIGHT. APPLICATION OF HARD RIGHT RUDDER STOPPED THE ROLL AT ABOUT 70 DEGREES RIGHT WING DOWN. AIRCRAFT WAS RECOVERED AFTER LOSING 2200FT. FLEW TO RSW BY KEEPING 20 TO 25 DEGREES LEFT YAW, WITH THE RUDDER, AND 12 TO 15 DEGREES RT WING DOWN. LANDING WAS ACCOMPLISHED USING THE SAME TECHNIQUE. ON GROUND, RIGHT AILERON WAS HELD FULL UP AND LEFT AILERON FULL DOWN BY SPRING TENSION. 1L71 3O 3A15 20020402000232002040200023CE 2002 4 2 2002FA0000421 120020325G531250351101 BULKHEAD WTHRLY620 620B 9630605CE PWA R985 R985* 52008NE FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW13902751015 1637 DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER. THIS AREA IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR. ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND (PN 50351-133) CRACKED AND TABS WHERE BULKHEAD IS RIVETED TO THE BELLY SKIN BROKEN. SUGGEST A THROUGH INSPECTION OF THIS AREA USING A FLASHLIGHT AND MIRROR. 1L71 3R3 RNCA26WE 5E1 20020402000242002040200024CE 2002 4 2 2002FA0000422 120020325G531250351105 BULKHEAD WTHRLY620 620B 9630605CE PWA R985 R985* 52008NE TAIL CONE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW13902751015 1637 DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER. THIS AREA IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR. ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND (PN 50351-133) CRACKED AND TABS WHERE BULKHEAD IS RIVETED TOT HE BELLY SKIN BROKEN. SUGGEST A THOROUGH INSPECTION OF THIS AREA USING A FLASHLIGHT AND MIRROR. 1L71 3R3 RNCA26WE 5E1 20020402000252002040200025CE 2002 4 2 2002FA0000423 120020325G531250351133 BULKHEAD WTHRLY620 620B 9630605CE PWA R985 R985* 52008NE TAIL CONE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW13902751015 1637 DURING ANNUAL INSPECTION FOUND FUSELAGE BELLY PAN BULKHEAD (PN 50351-101) CRACKED UPPER LEFT AND RIGHT CORNER. THIS AREA IS HARD TO SEE WITHOUT FLASHLIGHT AND MIRROR. ALSO FOUND TAIL CONE BULKHEADS (PN 50351-105) AND (PN 50351-133) CRACKED AND TABS WHERE BULKHEAD IS RIVETED TO THE BELLY SKIN BROKEN. SUGGEST A THROUGH INSPECTION OF THIS AREA USING A FLASHLIGHT AND MIRROR. 1L71 3R3 RNCA26WE 5E1 20020402000012002040200001CE 2002 4 2 2002FA0000424 120020228G3340C4559X LIGHT CESSNA500 560CESSNA 2076750CE PWA 545 PW545A NE LANDING LIGHT EXPLODED D K NONE O OTHER ININSP/MAINT 1 SW99398RS650 5605009 THE LANDING LIGHT IN AIRCRAFT BELLY FAILED. 2L72 4F4 FRTA22CE E00059EN 20020404000702002040400070EA 2002 4 4 2002FA0000429 220020401G73213011849 LINE BEECH 90 F90 1152909CE PWA PT6 PT6A28 EA FUEL CONTROL DAMAGED D K NONE K FLUID LOSS ININSP/MAINT 1 CE07107AJ6208 LA189 RIGHT ENGINE, FUEL RETURN TUBE TO FCU CRACKED AT B-NUT AND FUEL WAS BEING PUMPED OUT. FORWARD END OF LINE GOES TO A TEE AND IT LOOKS LIKE, WHEN THE LINE COMING IN FROM THE TOP WAS TIGHTENED THE TEE, WAS NOT HELD AND THE TUBE WAS BENT AND CRACKED. INSPECTED LEFT ENGINE AND FOUND THIS SAME TUBE BENT BY TEE FITTING AND REPLACED IT ALSO. 1L72 4T4 T A31CE E4EA 20020404000712002040400071CE 2002 4 4 2002FA0000430 120020314G3213998201005 CYLINDER BEECH 90 F90 1152909CE PWA PT6 PT6A60A 52043NE MLG CORRODED B S1FRK NONE O OTHER ININSP/MAINT 1 SO336749E7201 LA43 WHILE PERFORMING 6 YEAR LANDING GEAR INSPECTION IAW MFG SPECIAL INSPECTION, FOUND CYLINDER ASSEMBLY IN NOSE GEAR HAD SEVERE CORROSION ON INTERNAL BORE. 1L72 4T4 T A31CE E4EA 20020405000042002040500004SO 2002 4 5 2002FA0000431 120020326G716099047000 ADAPTER PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA ALT AIR DOOR BENT D K NONE O OTHER ININSP/MAINT 1 SW0953276513 2844049 INSPECTED AND FOUND AIR DOOR AND HINGE BENT AND ALLOWING UNFILTERED AIR TO ENTER THE INTAKE SYSTEM. 1L71 3O3 O 2A13 1E10 20020405000052002040500005CE 2002 4 5 2002FA0000437 120020207G3220 LINK CESSNA210 210D 2073414CE CONT O520 IO520* 17032SO NLG FAILED D K NONE O OTHER ININSP/MAINT 1 CE093806Y 21058306 112765R NOSE GEAR FAILED TO EXTEND FOR LANDING, DAMAGING ENGINE, PROPELLER, GEAR DOORS AND NOSE TIRE. AFTER JACKING AIRCRAFT IT WAS DISCOVERED THAT ROLLER ON MECHANICAL LINKAGE FOR NOSE GEAR DOORS HAD MOVED ON MECHANICAL LINKAGE FOR NOSE GEAR DOORS HAD MOVED FORWARD AND LOCKED ITSELF UNDER NOSE GEAR FORK. THIS LINKAGE IS ALSO SPRING LOADED. IT WAS ALSO FOUND THAT THIS LINKAGE HAD ANOTHER LINK ADDED TO IT WHICH LOWER ROLLER AND ALLOWED ROLLER TO CONTACT NOSE GEAR FORK EARLY. EXTRA LINK WAS ATTACHED WITH ONLY ONE BOLT AND THIS ALLOWED LINK AND ROLLER TO MOVE FORWARD, GETTING LOCKED UNDER NOSE GEAR FORK WHEN GEAR WAS RETRACTED. 1H71 3O3 O 3A21 E5CE 20020405000062002040500006CE 2002 4 5 2002FA0000439 120020221G78304510000501 THRUST REVERSER LEAR 55 55LEAR 5170702CE ENGINE MISINSTALLED B JGVRK NONE W INADEQUATE Q C ININSP/MAINT 1 CE0955HL 7052 046 DOOR POSITION INDICATOR WIRING HARNESS WAS CUT AT RECEPTACLE. DOOR POSITION INDICATOR RECEPTACLE INSTALLED UPSIDE DOWN, CAUSING DAMAGE TO MALE PINS IN RECEPTACLE. DOOR POSITION INDICATOR WIRING HARNESS RETAINING CLAMP RIVET REPLACED WITH SCREW AND NUT. DISCREPANCIES DISCOVERED DURING 1400 HOUR INSPECTION. 2L72 4F A10CE 20020405001022002040500102NE 2002 4 5 2002FA0000444 220020104G731030366441 FLOW DIVIDER BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE DUMP VALVE LEAKING B ML2RK NONE O OTHER ININSP/MAINT 1 GL11520DG BB1753 PCBPJ0491 RECEIVED NEW FLOW DIVIDER TO REPLACE FLOW DIVIDER WITH SUSPECTED LEAKING DUMP VALVE. AT MFG REQUEST, A LEAK CHECK WAS PERFORMED ON THE NEW FLOW DIVIDER. IT WAS FOUND THAT THE NEW FLOW DIVIDER LEAKED AT THE DUMP VALVE AND IS NOT SERVICEABLE. THIS IS SECOND FLOW DIVIDER RECEIVED THAT HAS FAILED THIS LEAK CHECK. NO CAUSE OF LEAKAGE KNOWN AT THIS TIME. 1L72 4T4 T A24CE E4EA 20020405001032002040500103CE 2002 4 5 2002FA0000445 120020319G2510551900921 SEAT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE05778JM 5500072 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. (PHOTOS) STRESS ON CHAIR BACK AND METAL FATIQUE PROBABLE CAUSE. CHAIR WAS REPAIRED. 1L72 4F4 F A22CE E1NE 20020405001042002040500104CE 2002 4 5 2002FA0000446 120020312G30606592SW BOOT CESSNA310 310R 2074245CE CONT O520 IO520* 17032SO LT PROP BOOT DESTROYED D O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CE034264J479 310R0201 DURING FLIGHT, ONE PROP BOOT DEPARTED AIRCRAFT. UPON INSPECTION IT WAS DETERMINED THAT THE PAINT DID NOT ADHERE TO THE BLADE PROPERLY AND THE BOOT CAME LOOSE. 1L72 3O3 O 3A10 E5CE 20020405000022002040500002NM 2002 4 5 2002FA0000447 120020404G5530600N38001 STABILIZER DOUG 600N 600N 3027377NM CRACKED D K NONE O OTHER ININSP/MAINT 1 WP05957SD2348 RN011 DURING A ROUTINE INSPECTION WE FOUND THE UPPER AND LOWER VERTICAL STABILIZERS TO HAVE CRACKS IN THE MOUNTING BORE EMANATING FROM THE BOLT HOLES THAT ATTACH THE STABILIZER TO THE TORQUE TUBE.THE BORE HAS A CASTED LOOKING FITTING FOR EACH OF THE TWO MOUNTING BOLTS AND APPEARS TO BE A PLASTIC OR COMPOSITE TYPE MATERIAL. IT IS THIS CASTING THAT IS CRACKED, AND BOTH UPPER AND LOWER CASTINGS IN SOME CASES.WE HAVE ORDERED 4 EACH REPLACEMENT STABILIZERS AND NOTIFIED MDHI. 1G71 3U NCH3WE 20020405000032002040500003NM 2002 4 5 2002FA0000449 120020404G5530600N38001 STABILIZER DOUG 600N 600N 3027377NM TAIL CRACKED D K NONE O OTHER ININSP/MAINT 1 WP05959SD2193 RN019 DURING A ROUTINE INSPECTION WE FOUND THE UPPER AND LOWER VERTICAL STABILIZERS TO HAVE CRACKS IN THE MOUNTING BORE EMANATING FROM THE BOLT HOLES THAT ATTACH THE STABILIZERS TO THE TORQUE TUBE.THE BORE HAS A CASTED LOOKING FITTING FOR EACH OF THE TWO MOUNTING BOLTS AND APPEARS TO BE A PLASTIC OR COMPOSITE TYPE MATERIAL. IT IS THIS CASTING THAT IS CRACKED, BOTH UPPER AND LOWER IN SOME CASES. WE HAVE NOTIFIED MDHI AND HAVE ORDERED REPLACEMENT STABS. 1G71 3U NCH3WE 20020405001012002040500101CE 2002 4 5 2002FA0000450 120020405G554010164001419 HINGE BEECH 200 A200 1152921CE RUDDER CORRODED H K NONE O OTHER ININSP/MAINT 1 SW991547 12787 BC50 THE CENTER RUDDER HINGE ASSEMBLY WAS REMOVED FROM THE AIRCRAFT FOR REPLACEMENT DUE TO VISIBLE CORROSION NEAR THE EDGE OF THE LOWER RIGHT HAND BOLT HOLE ON THE TEE. WHEN THE TEE WAS DERIVETED FROM THE HINGE SUBSTANTIAL EXFOLIATION WAS FOUND ON THE TEE SURFACE WHICH BUTTS UP AGAINST THE HINGE. SUBSTANTIAL PITTING WAS FOUND ON THE ADJOINING SURFACE OF THE HINGE. THE EXFOLIATED AND PITTED AREAS ARE NOT VISIBLE WHEN THE HINGE IS IN THE ASSEMBLED POSITION. EXFOLIATION AND PITTING COULD HAVE PROPAGATED UNDETECTED TO THE POINT OF HINGE FAILURE. THE HINGE/TEE INTERFACE SHOULD BE SEALED UPON ASSEMBLY TO PREVENT CORROSION. 1L72 4T A24CE 20020408000012002040800001CE 2002 4 8 2002FA0000451 120020327G2150MCB69738150 COUPLING CESSNA500 560CESSNA 2076750CE ACM LOOSE B PAZRB EMER. DESCENT J WARNING INDICATION CRCRUISE 1 CE03592M 5600338 DURING CRUISE FLIGHT, AFTER PHASE INSPECTIONS WERE COMPLETED, FLIGHT CREW REPORTED A "BUMP" AT AN ALTITUDE OF 31,000 FT, CABIN ALT STARTED TO CLIMB UNCONTROLLABLY, WARNING ANNUNCIATOR SHOWING "CABIN ALT. 10,000 FT.". CREW PERFORMED AN EMERGENCY DESCENT TO 15,000 FT. AND CONTINUED FLIGHT TO DESTINATION AIRPORT. AFTER LANDING, MECHANIC FOUND A COUPLING LOOSE ON THE REFRIGERATION PACK (ACM) WHICH SHOWED EVIDENCE OF LEAKING. ALSO, THE MECHANIC FOUND TWO AN737TW58 CLAMPS LOOSE ON THE ACM. 2L72 4F RTA22CE 20020411000442002041100044SO 2002 4 11 2002FA0000452 220020322G8530SA52000A1 CYLINDER CESSNA340 340A 2076405CE CONT O520 TSIO520E 17040SO LT ENGINE FAILED B CTURA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 GL21234PS 340A0368 IN FLIGHT, PILOT NOTICED REDUCTION IN MANIFOLD PRESSURE. PILOT DESCENDED WHEN COMPLETE FAILURE AND SEPARATION OF THE NR 4 CYLINDER ON THE LEFT ENGINE OCCURRED. CYLINDER HEAD SEPARATED FROM BARREL. ENGINE WAS SECURED AND SHUT DOWN. PROP WAS FEATHERED. THE AIR CRAFT LANDED SAFELY. 1L72 3O3 O 3A25 E8CE 20020411000452002041100045SO 2002 4 11 2002FA0000453 120020326G7160 HINGE PIPER PA28 PA28R201 7102816SO LYC O360 IO360A1A 41514EA INDUCTION SYSTEMBENT B K NONE O OTHER ININSP/MAINT 1 SW09730X 98 2844066 DURING 100 HOUR INSPECTION NOTED ALTERNATE AIR DOOR AND HINGE BENT AND ALLOWING UNFILTERED AIR TO ENTER THE INTAKE SYSTEM. 1L71 3O3 O 2A13 1E10 20020411000462002041100046SO 2002 4 11 2002FA0000454 120020301G7120 BOLT PIPER PA42 PA42720 7104212SO PWA PT6 PT6A11 52043NE ENGINE MOUNT BROKEN D K NONE O OTHER ININSP/MAINT 1 GL2575FL 4455 428301002 UPON INSPECTION, FOUND RIGHT TOP ENGINE MOUNT BOLT BROKEN AT FIREWALL. 1L72 4T3 T A23SO E4EA 20020411000472002041100047CE 2002 4 11 2002FA0000455 120020403G323335810083 SHAFT BEECH 36 A36TC 1151603CE MLG ACTUATOR OVERSIZED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO053872W3049 3049 EA225 THE ORIGINAL LANDING GEAR ACTUATOR GEARBOX WAS BEING REMOVED AND DISASSSMBLED FOR A ROUTINE OVERHAUL. DIFFICULTY WAS ENCOUNTER WHEN TRYING TO REMOVE THE ACTUATOR SHAFT FROM THE GEARBOX HOUSING. IT WAS NOTED THAT THE FORCE REQUIRED TO SLIDE THE SHAFT OUT WAS UNUSUAL. NO DAMAGE TO THE SHAFT WAS VISABLE. THE ENTIRE ASSMBLY WAS FORWARDED TO AN APPROVED OVERHAUL FACILITY. FURTHER INSPECTION REVEALED THAT THE SPLINED END OF THE SHAFT HAD BEEN MANUFACTURED TO APPROXIMATELY .002 - .003 OVERSIZE. THE SHAFT WILL BE REPLACED DURING THIS OVERHAUL. IT APPEARS THAT THIS IS THE ORIGINAL GEARBOX INSTALLED AT MANUFACTURE AS THERE IS NO RECORD INDICATING PRIOR REPLACEMENT. 1L71 3O 3A15 20020411000482002041100048CE 2002 4 11 2002FA0000456 120020408G8011642087A10 ADAPTER BEECH 58 58P 1152744CE CONT O520 TSIO520WB 17040SO STARTER FAILED D K NONE O OTHER ININSP/MAINT 1 NM07 493 TJ372 274383R PILOT REPORTED ENGINE WOULD NOT START. FOUND THAT PROP WOULD NOT TURN BACKWARDS. REPLACED STARTER ADAPTER WITH A REBUILT AND OPS CHECKED OK. THIS IS THE SECOND ADAPTER REPLACED ON THIS ENGINE. THE FIRST ONE FAILED ON A FACTORY REBUILT/ZERO TIME ENGINE WITH 402 HOURS ON IT. THE SECOND ONE,WHICH WAS A FACTORY REBUILT ADAPTER,FAILED WITH 493 HOURS ON IT. 1L72 3O3 O A23CE E8CE 20020411000492002041100049CE 2002 4 11 2002FA0000457 120020408G7160ASSYBA2405 AIR FILTER CESSNA210 T210K 2073447CE AIR INLET MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SW018251M 21059251 FOUND (BRACKETT) AIR FILTER ASSEMBLY (NR-BA-2405) INSTALLED BACKWARDS. THE MESH SAFTEY SCREEN WAS AT THE FRONT OF THE FOAM FILTER, AND THE INLET GRID WAS INSTALLED AT THE BACK OF THE ASSEMBLY. INSPECTED ONE OTHER FILTER ASSEMBLY ON LIKE AIRCRAFT AND FOUND IT WAS ALSO MISINSTALLED. 1H71 3O 3A21 20020411000502002041100050CE 2002 4 11 2002FA0000458 120020401G3260204101744 SUPPORT CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA RT DOWNLOCK BROKEN B A5ORO OTHER O OTHER NRNOT REPORTED 1 SO098253G 177RG0153 PILOT REPORTED THAT THE LANDING GEAR PUMP MOTOR CONTINUED TO RUN AFTER THE GEAR WAS PUT IN THE DOWN POSITION AND THAT THE GEAR DOWN LIGHT DID NOT COME ON. THE PILOT MADE AN UNEVENTFUL LANDING AFTER A LOW PASS AND GROUND PERSONNEL VERIFIED THE LANDING GEAR APPEARED TO BE DOWN. TROUBLESHOOTING FOUND THAT THE RIGHT LANDING GEAR DOWN LOCK SWITCH WAS NOT MAKING DUE TO A BROKEN DOWN LOCK SUPPORT BRACKET. THE BROKEN SUPPORT BRACKET ROTATED IN THE HOUSING AND DID NOT ALLOW THE RIGHT MAIN LANDING GEAR TO LOCK DOWN. REPLACED THE BROKEN PART WITH A NEW MFG PART AND RIGGED IAW SM. OPS CHECKED GOOD. THE BROKEN PART HAD THE LOWER PIN SHEARED OFF. IT ALSO SHOWED SIGNS OF HEAT WHERE IT WAS WELDED. 1H71 3O3 O A20CE 1E10 20020411000512002041100051SO 2002 4 11 2002FA0000459 220020401G8530653816A7BP CYLINDER CONT O200 O200A 17020SO NR 1 ENGINE DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP25 627926A USING COMPLETE CYLINDER AND VALVE ASSEMBLYS, ENGINE SCREEN PLUGGED WITH BLACK FLAKES AND STARVED ENGINE IN INITIAL HOUR OF BREAKING. RESULTED IN OIL STARVATION TO MAINS, ROD BEARINGS, CYLINDER WALLS, CAMSHAFT, ROCKERS AND TAPPETS. OIL PUMP DAMAGED DUE TO ABRASION. RINGS LOST MATERIAL, ROD BEARINGS LOST PLATING, ONE ROD BEARING SPUN. CRANKSHAFT SEVERELY UNDERCUT. ANOTHER ENGINE REBUILT USING SAME ASSEMBLYS, ON BREAKING, AFTER TWO RUNS TOTALING 15 MINUTES SCREEN CHECKED AND FOUND WITH BLACK FLAKING, CLEANED AND ANOTHER RUN MADE. MORE PARTICLES OF BLACK FLACK FOUND. OIL REMOVED AND ENG FILLED WITH MORE FRESH BREAKIN OIL, ENGINE RUN, SCREEN CHECKED AND CLEANED. TEST FLIGHT MADE. 3 O E252 20020411000522002041100052GL 2002 4 11 2002FA0000461 120020328G3210MM6 ROD END AMTR VIPER VIPERJET 05607UFGL MLG FAILED G K NONE O OTHER ININSP/MAINT 1 NM07520VF150 0001 ROD END FAILED DUE TO SIDE LOADS AFTER LANDING (OR DURING). 1L71 4U RTEXPA1L71 20020411000532002041100053WP 2002 4 11 2002FA0000462 120020322G3213161909 STRUT GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 R182082 EA MLG DAMAGED C F1DMK NONE O OTHER ININSP/MAINT 1 WP11404DF 215 455 BL516924 DURING A FLEETWIDE NDT INSPECTION OF OUR MAIN LANDING GEAR STRUTS, FOLLOWING A STRUT FAILURE ON T-86 (N433DF SN 149855) A CRACK WAS FOUND IN THIS HOUSING. IT WAS INSTALLED ON THE RIGHT SIDE STRUT ASSEMBLY. IT WAS FOUND BY INSPECTION OF THE DISASSEMBLED STRUT ASSEMBLY. 2H72 4R4 R A25WE 20020411000542002041100054SO 2002 4 11 2002FA0000463 220020410G8540649866 SHAFT BEECH 36 A36 1151604CE CONT O550 TSIO550B 17043SO ENGINE FAILED G A UNSCHED LANDING KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 GL0329TC E2644 AIRCRAFT ENGINE EXPERIENCED A LOSS OF OIL PRESSURE AND SUBSEQUENT LOSS OF POWER. ENGINE TEARDOWN INSPECTION REVEALED A FAILURE OF THE STARTER ADAPTER SHAFT. 1L71 3O3 O 3A15 E5SO 20020411000432002041100043CE 2002 4 11 2002FA0000464 120020410G3010PO67L015 PRESSURE SWITCH CESSNA500 S550 2076607CE DEICE SYSTEM FAILED B O OTHER N FALSE WARNING NRNOT REPORTED 1 NE05126QS S5500126 TKS DEICE SYSTEM PRESSURE SWITCHES ARE FAILING IN THE OPEN POSTION. WHEN THE SWITCHES FAIL OPEN THEY CAN NOT ILLUMINATE THE DEICE PRESSURE FAIL LIGHTS ON THE ANNUCIATOR. THE LIGHTS ILLUMINATE TO INDICATE LOW PRESSURE. THERE IS NO WAY TO TELL LOW PRESSURE IN THE SYSTEM WITH THESE SWITCHES FAILED OPEN. WE HAVE REPLACED THREE SWITCHES IN THE ENGINE DEICE SYSTEM, ALL FAILED IN THE OPEN POSITION ON THIS TKS DEICE SYSTEM. 1L72 4F RTA22CE 20020412000642002041200064SO 2002 4 12 2002FA0000465 120020227G3213170420 STRUT MARSH S2F S2F3S 3951007SO GARRTTTPE331TPE33114GR 01514NE MLG FAILED C K NONE O OTHER ININSP/MAINT 1 WP11433DF 149855 P104026 DURING A MAINTENANCE RUN-UP OF THE ENGINES, THE RIGHT STRUT OUTER HOUSING FAILED CAUSING THE STRUT TO COLLAPSE. DAMAGE WAS CAUSED TO THE PROPELLER, ENGINE, NACELLE, WING, AND FUSELAGE. 2H72 4O4 TRTA51NM E18NE 20020412000652002041200065CE 2002 4 12 2002FA0000467 120020401G2421X610007 CONTACTOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ALTERNATOR FAILED B AI4RO OTHER O OTHER NRNOT REPORTED 1 NM01447SP116 172S8311 ALTERNATOR FIELD C/B POPPED DURING FLIGHT. TROUBLESHOT ALTERNATOR AND RELATED COMPONENTS. DISCOVERED DEFECTIVE ALTERNATOR CONTACTOR. (RESISTANCE CHECK OF ENERGIZED CONTACTOR (ACROSS LARGE TERMINALS) INDICATED AS HIGH AS 150 OHMS. LIGHTLY TAPPING THE CONTACTOR REDUCED RESISTANCE TO .6 OHMS). THIS COMPONENT WAS IN SERVICE 116.8 HOURS. RECOMMEND HEAVIER DUTY CONTACTOR. 1H71 3O3 ONT3A12 1E10 20020412000662002041200066EA 2002 4 12 2002FA0000469 220020401G7414M3525 COIL SLICK CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA LEFT MAGNETO BURNED D O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 NE0580657 17266693 L2853627A DURING ROUTINE FLIGHT ENGINE BECAME ROUGH. PILOT CONTINUED TOWARDS AIRPORT, WITH NO OTHER OPTIONS, AND LANDED SAFELY. ONCE ON THE GROUND, THE PILOT/ MECHANIC DID AN ENGINE RUN-UP AND FOUND LEFT MAGNETO DEAD. FURTHER INSPECTION REVEALED A HOLE BURNED THROUGH THE COIL CASE INSIDE THE MAGNETO. NEW COIL AND INSPECTION PUT AIRCRAFT BACK IN SERVICE. 1H71 3O3 ONT3A12 E274 20020418000572002041800057SO 2002 4 18 2002FA0000470 220020402G7414 BRUSHES SLICK BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO MAGNETO CAP WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP078268T475 01090978 CE1547 825755R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBTOR BLOCK FROM MAGNETO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. THE WEARER ON THIS BRUSH IS ABOVE NORMAL FOR 500 HRS. (PN M3004 BRUSH). 1L71 3O3 O 3A15 E5CE 20020418000582002041800058SO 2002 4 18 2002FA0000471 220020402G7414 BRUSHES BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO MAGNETO CAP WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP078268T CE1547 MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNETO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. THE WEARER ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS (PN M3004 BRUSH). 1L71 3O3 O 3A15 E5CE 20020418000592002041800059CE 2002 4 18 2002FA0000472 120020405G272004115261 TORQUE TUBE CESSNA150 152 2071835CE LYC O235 O235* 41505EA LT RUDDER PED BROKEN D K NONE O OTHER ININSP/MAINT 1 EA214725B5941 15283599 PILOT LEFT RUDDER PEDAL TORQUE TUBE BROKE AT WELD FOR PEDAL ARM. RESULTING IN PILOT HAVING REDUCED OR NO LEFT RUDDER OR NOSE STEERING. POSSIBLY CAUSED BY A DEFECTIVE WELD. 1H71 3O3 ONT3A19 E223 20020418000602002041800060CE 2002 4 18 2002FA0000473 120020402G3600RA216CW PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO AIR SYSTEM INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP075609S370 CE1454 825756R LOW OUT PUT FROM PUMP TO AIRCRAFT, REMOVED PUMP AND INSTALLED NEW PUMP, OPERATION WAS NORMAL. PUMP SENT IN FOR WARRANTY. 1L71 3O3 O 3A15 E5CE 20020418000612002041800061EA 2002 4 18 2002FA0000474 220020402G7414103572101 SWITCH GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA MAGNETO FAILED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07865AF6 85005 L2826448A MAGNETO SWITCH FAILED TO START ENGINE, FOUND BAD SWITCH. NEW SWITCH INSTALLED, OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000622002041800062SO 2002 4 18 2002FA0000475 220020402G7414 BRUSHES BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO MAGNETO CAP WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP076322A CE998 820466R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNETO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. THE WEARER ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH) 1L71 3O3 O 3A15 E5CE 20020418000632002041800063SO 2002 4 18 2002FA0000476 220020402G7414 BRUSHES SLICK BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO DISTRIBUTOR WORN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP076322A504 01051685 CE998 820466R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNETO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. THE WEARER ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH) 1L71 3O3 O 3A15 E5CE 20020418000642002041800064 2002 4 18 2002FA0000477 420020401G3120 PIN GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA CLOCK BROKEN B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07861AF116 85001 L2802348A LEFT HAND STOP PIN BROKEN OFF, REMOVED AND INSTALLED NEW CLOCK. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000652002041800065EU 2002 4 18 2002FA0000478 120020401G36001U128006 PUMP GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA DRY AIR DAMAGED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07861AF116 85001 L2802348A METAL SHAFT SHEARED IN PUMP. REMOVED AND INSTALLED NEW PUMP, SYSTEM OPERATIONAL CHECKED NORMAL. PUMP SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020417000912002041700091CE 2002 4 17 2002FA0000479 120020406G3244178K431 TIRE LEAR 60 60LEAR 5170707CE LANDING GEAR SEPARATED E K NONE O OTHER LDLANDING 1 SO1560UJ 102 007 TREAD SEPARATED ON LANDING. CARCUS REMAINED IN TACT. 2L72 4F RTA10CE 20020418000662002041800066EU 2002 4 18 2002FA0000480 120020401G2711G1204105 SERVO GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA AILERON TRIM STICKING B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07862AF59 85002 L2802448A TRIM SERVO STICKING IN OPERATION AND FAILS TO MOVE THE AILERON TRIM TAB. REMOVED AND INSTALLED NEW TRIM SERVO ASSEMBLY. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000672002041800067EU 2002 4 18 2002FA0000481 120020402G32331145 ACTUATOR GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA MLG FAILED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07862AF59 85002 L2802448A NOSE LANDING GEAR HYDRAULIC ACTUATOR BOTTOM SEAL AROUND SHAFT BLOW OUT AND LEAKING FLUID FROM CYLINDER. ACTUATOR REMOVED AND A NEW ACTUATOR INSTALLED. ACTUATOR SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000682002041800068EU 2002 4 18 2002FA0000482 120020401G2913X030001 PUMP GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA HYD SYSTEM INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07863AF36 85003 L2802548A ELECTRIC MOTOR SLOW IN FLIGHT, OVER 25 TO 30 SECONDS TO RETRACT AND EXTENT THE LANDING GEAR. NEW HYDRAULIC PUMP ASSEMBLY INSTALLED, CYCLED GEAR IAW MAINTENANCE MANUAL, LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000692002041800069 2002 4 18 2002FA0000483 420020401G230002908000062 FILTER GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA RADIO INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07863AF35 85003 L2802548A FEED BACK IN THE RADIOS, NEW FILTER INSTALLED, OPERATIONAL CHECK NORMAL. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000702002041800070EU 2002 4 18 2002FA0000484 120020405G3150120A913150 AUDIO PANEL GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA COCKPIT FAILED B VJ3RO OTHER N FALSE WARNING NRNOT REPORTED 1 WP07863AF18 85003 L2802548A AUDIO PANEL FAIL INTERNALLY GIVING AND UNSAFE GEAR INDICATION LIGHT, AND WHEN THE THROTTLE WAS PULLED TO IDLE, THE HYDRAULIC PUMP WOULD START TO RUN. REMOVED AND INSTALLED NEW AUDIO PANEL. THE LANDING GEAR OPERATIONAL CHECKED NORMAL. PART SENT IN FOR WARRANTY. 1K00 3 O G33EU 1E4 20020418000712002041800071CE 2002 4 18 2002FA0000485 120020404G321122411001 FITTING CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA RT MLG CRACKED G K NONE O OTHER ININSP/MAINT 1 EA275227U8288 172RG0290 THIS FITTING, WITH 3 CRACKS, IS PART OF THE RIGHT MAIN LANDING GEAR SPRING WHICH ATTACHES TO THE AXLE. 1H71 3O3 O 3A17 E286 20020418000562002041800056EA 2002 4 18 2002FA0000488 220020415G7414103572101 SWITCH PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA MAGNETO DEFECTIVE B O OTHER R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 EA235002T54 54 287205237 PILOT REPORTED THE ENGINE WAS DIFFICULT TO "TURN OVER". PROBLEM WAS FOUND TO BE THE START POSITION OF THE MAG SWITCH. IGNITION FUNCTIONS OF THE SWITCH WERE NORMAL. THIS SWITCH WAS REPLACED 54.49 HOURS EARLIER FOR THE SAME PROBLEM. INSTALLED A NEW SWITCH. OPERATIONAL CHECK WAS O.K. 1L71 3O3 O 2A13 E286 20020419000042002041900004GL 2002 4 19 2002FA0000491 220020408G741467542 BEARING BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL MAG DRIVE WORN B MY2RK NONE O OTHER ININSP/MAINT 1 GL11675M 1063 2894 BOTH MAGNETO DRIVE BEARINGS WERE LOOSE, REMOVED AND FOUND BOTH BEARINGS WORN AND ROUGH. 1G71 3U3 U H2SW E4CE 20020419000052002041900005SW 2002 4 19 2002FA0000492 120020312G272026720025 BELLCRANK SWRNGNSA226 SA226TB 8780406SW GARRTTTPE331TPE331* 01514WP RUDDER PEDAL CRACKED B OF1RK NONE O OTHER ININSP/MAINT 1 EA17999MM4792 T309 HOLE IN RUDDER PEDAL ARM WHERE RUDDER PEDAL PIVOT POST GOES IS CRACKED. 2L72 4T3 TRTA5SW E2WE 20020419000062002041900006SW 2002 4 19 2002FA0000493 120020401G57122731023016 RIB SWRNGNSA227 SA227AC 8780603SW RT WING CRACKED B XVIRK NONE O OTHER ININSP/MAINT 1 NM01787C AC550 LOCATED AND MARKED END OF CRACKS AT WS 81.174 ON RIGHT AND LEFT WINGS IN THE LOWER RADIOUS OF THE WING RIBS. BOTH CRACKS WERE APPROX. 6 INCHES LONG AND FOLLOWED THE RADIUS FORWARD AND AFT. 2L72 4T RTA8SW 20020419000072002041900007SO 2002 4 19 2002FA0000495 220020412G8530SA24122 BUSHING CESSNA150 150M 2071830CE CONT O200 O200A 17020SO ROCKER ARMS FAILED B YYBRK NONE O OTHER ININSP/MAINT 1 GL038778U14 15077986 EIGHT BUSHINGS FAILED WITHIN 15 HOURS OF OPERATION. THE PROBLEM WAS INDICATED BY BRASS METALIC DUST IN THE OIL FILTER. THIS LOOKED SIMILAR TO METALIC PAINT FLAKE SUSPENDED IN THE OIL. THE ROCKER ARMS WERE REMOVED AND BUSHING CLEARANCE WAS MEASURED. THE WEAR WAS BETWEEN .006 AND .009. MANUFACTURERS NEW LIMIT IS .0025 AND SERVICE LIMIT IS .004. PROBABLE CAUSE MAY BE DEFECTIVE MATERIAL. 1H71 3O3 O 3A19 E252 20020419000082002041900008 2002 4 19 2002FA0000497 420020402G3421060001700 GYRO PIPER PA31 PA31350 7103110SO COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE05275CF 318252017 GYRO FAILURE. 1L72 3O A20SO 20020419000092002041900009 2002 4 19 2002FA0000498 420020402G3422060001700 GYRO BEECH 58 58 1152740CE COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE056726S134 TH1390 GYRO FAILURE. 1L72 3O 3A16 20020419000102002041900010 2002 4 19 2002FA0000499 420020402G3421060001700 GYRO BEECH 58 58 1152740CE CONT O550 IO550* SO COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE056726S TH1390 GYRO FAILURE. 1L72 3O3 O 3A16 E3SO 20020419000112002041900011 2002 4 19 2002FA0000500 420020402G3421060001700 GYRO BEECH 58 58 1152740CE CONT O550 IO550* SO COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE056726S93 TH1390 GYRO FAILURE. 1L72 3O3 O 3A16 E3SO 20020419000122002041900012 2002 4 19 2002FA0000501 420020402G3421060001700 GYRO PIPER PA31 PA31325 7103105SO LYC O540 TIO540* 41532EA COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE054101841 318212006 GYRO FAILURE. 1L72 3O3 O A20SO E14EA 20020419000132002041900013 2002 4 19 2002FA0000502 420020402G3421060001700 GYRO PIPER PA31 PA31325 7103105SO LYC O540 TIO540* 41532EA COCKPIT FAILED B C42RK NONE O OTHER ININSP/MAINT 1 CE0541018 318212006 GYRO FAILURE. 1L72 3O3 O A20SO E14EA 20020419000012002041900001NE 2002 4 19 2002FA0000503 220020418G7261AE7013002K024 HOSE CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE ENGINE OIL FAILED D A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 EA2350JN 365 4250232 HOSE WAS INSTALLED ON 10-15-99 1869.1TT. CURRENT AIRCRAFT TIME 2234.8 HRS. THIS HOSE LASTED 365.7 HRS. THIS HAS BEEN AN ON GOING PROBLEM WITH THIS AIRCRAFT. CESSNA SUPERSEEDED THE ORIGNAL HOSE P/N AS705976-1 TO THE AE7013002K024 WHICH IS SLIGHTLY LONGER,IN HOPES TO CORRECT THE PROBLEM,BUT THE PROBLEM STILL EXIST. THESE HOSES ARE BLOWING OUT AT THE BEND RADIOUS. THE HOSES NEED TO BE LONGER OR A DIFFERENT STYLE. THIS IS THE SECOND M&D REPORT ON THIS AIRCRAFT. 1L72 3T3 TRTA7CE E4EA 20020419000022002041900002SO 2002 4 19 2002FA0000504 120020418G7430103572101 SWITCH PIPER PA28 PA28180 7102808SO IGNITION SYS FAILED B K NONE O OTHER ININSP/MAINT 1 EA235002T102 102 287205237 PILOT REPORTED DIFFICULTY IN STARTING (CRANKING) OF ENGINE. PROBLEM WAS DISCOVERED TO BE THE START POSITION OF THE IGNITION SWITCH. THIS IS THE THIRD SWITCH FAILURE FOR THE SAME PROBLEM IN THE LAST 157HRS OF OPERATION. THE FIRST REPLACEMENT SWITCH LASTED 54HRS BEFORE FAILURE AND THE SECOND SWITCH LASTED 102.81HRS. UPON RECEIVING THE NEW SWITCH, IT WAS TESTED AND FOUND TO BE FAULTY ACROSS THE START CONTACTS AS WELL. THE LATEST NEW SWITCH WAS ALSO TESTED AND FOUND TO BE ACCEPTABLE AND WAS INSTALLED. POSSIBLE POOR MANUFACTURER QUALITY CONTROL OR POSSIBLE FAULTY MATERIALS ARE SUSPECTED. 1L71 3O 2A13 20020422000332002042200033CE 2002 4 22 2002FA0000505 120020403G7160LW18101 HOSE CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA INDUCTION SYS SATURATED B VIB3K NONE O OTHER ININSP/MAINT 1 SO03739BP61 17270415 L272276 THE RUBBER INDUCTION COUPLING HOSES ON THE ENGINE WERE FOUND TO BE SATURATED WITH FUEL. IT APPEARS THE FUEL WAS PERMEATING RIGHT THROUGH THE HOSE. FOUND THEY WERE REPLACED AT 62 FLIGHT HOURS AND 9 MONTHS EARLIER. INSTALLED LW18101 HOSES AT THIS TIME. 1H71 3O3 ONT3A12 E274 20020422000342002042200034CE 2002 4 22 2002FA0000506 120020403G7332UMA33112 INDICATOR CESSNA182 R182 2072734CE FUEL PRESSURE MISREPAIRED B VIB3K NONE W INADEQUATE Q C ININSP/MAINT 1 SO037139T R18200025 A FUEL PRESSURE GAUGE WAS RETURNED TO MFG. FOR REPAIR. THEY SENT A REPLACEMENT GAUGE IN ITS PLACE. THE NEW GAUGE CAME WITH AN AN816-2D NIPPLE THREADED IN THE PRESSURE INLET PORT. THE PROBLEM IS THE TEFLON THREAD TAPE WAS IMPROPERLY APPLIED. NOT ONLY DID IT COVER ALL THE THREADS, IT COVERED ABOUT 75 PERCENT OF THE HOLE IN THE END OF THE FITTING. THERE WERE ALSO SMALL TORN PIECES THAT WOULD HAVE BROKEN OFF AND ENTERED THE GAUGE. 1H71 3O RT3A13 20020422000352002042200035CE 2002 4 22 2002FA0000507 120020401G5730 SKIN CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA LT WING CRACKED B DVPRK NONE O OTHER ININSP/MAINT 1 SO032384U590 17280708 CRACKS DEVELOPED IN TOP T/E LT WING SKIN AT EXTREME IB END OF WING AROUND 4 OF AN426AD4 RIVETS WHICH JOIN T/E STIFFENER TO UPPER AND LOWER WING SKINS JUST ABOVE FLAP. CRACKS RANGED FROM .500 INCH TO 1 INCH AND ONLY 1 PENETRATED A RIVET HOLE. ONE OF RIVETS, JOINING EXTREME IB RIB TO UPPER SKIN HAD CRACK NEXT TO IT 1 INCH LONG. CAUSED BY THE EXTREME AFT WING ROOT FAIRING SCREW CONTACTING THE UPPER SKIN (SCREW INSTALLED WAS TOO LONG). FLUSH PATCH APPROX 9 INCH X 4 INCH, WITH DOUBLER, WAS INSTALLED AFTER REMOVING THE WING TO GAIN ACCESS TO AREA. WING REMOVAL NECESSARY DUE TO FILLET ASSY OF THE FUSELAGE WHICH OVERLAPS WING AND COVER THE RIVET LINE OF EXTREME IB RIB. 1H71 3O3 ONT3A12 1E10 20020422000362002042200036CE 2002 4 22 2002FA0000508 120020330G326013771 SWITCH CESSNA210 T210M 2073451CE CONT O520 TSIO520* 17040SO MLG UPLOCK FAILED C O OTHER N FALSE WARNING NRNOT REPORTED 1 SW05732YK3121 21061879 GEAR FAILED TO INDICATE UP AND LOCKED ON RETRACTION. 1H71 3O3 O 3A21 E8CE 20020423000242002042300024CE 2002 4 23 2002FA0000509 120020320G2421E0FF10300BA ALTERNATOR CESSNA210 210L 2073448CE CONT O520 IO520* 17032SO ENGINE FAILED D O OTHER O OTHER NRNOT REPORTED 1 CE072177S4 21061138 ALTERNATOR UNIT FAILED ENROUTE. 1H71 3O3 O 3A21 E5CE 20020423000252002042300025SO 2002 4 23 2002FA0000511 120020322G3010210174 POPPET VALVE LKHEED1329 132923E 5263116SO GARRTTTFE731TFE731* 01518WP NR 4 ENGINE INOPERATIVE D K NONE O OTHER ININSP/MAINT 1 SO17511TS14 5101 VALVE JUST REPLACED AFTER OVERHAUL. VALVE INOPERATIVE, POPPET VALVE FROZEN OR STIFF TO MOVE . CAN FEEL IT GRIND AND NOT GOING CLOSE AFTER PUSHING POPPET. OVERHAUL PROCESS NOT CORRECT OR NOT ENOUGH CLEAR INTERNALLY. 2L74 4J4 F 2A15 E6WE 20020423000262002042300026SO 2002 4 23 2002FA0000512 120020415G3260 SWITCH PIPER PA28 PA28R180 7102809SO LYC O360 IO360A1A 41514EA MLG DOWN BROKEN D O OTHER N FALSE WARNING LDLANDING 1 SO163788T4000 28R30101 NOSE AND RIGHT MAIN GEAR COLLAPSED ON LANDING. GEAR SWING AFTER INCIDENT APPEARED NORMAL WITH FAA OBSERVER. FURTHER INSPECTION FOUND RIGHT MAIN SWITCH DAMAGED AND COMING ON EARLY. NOSE SWITCH INTERMITTENTLY EARLY. 1L71 3O3 O 2A13 1E10 20020423000272002042300027CE 2002 4 23 2002FA0000513 120020319G2110 COMPRESSOR BEECH 90 E90 1152914CE PWA PT6 PT6A60A 52043NE AIR CONDITIONER BROKEN B EHHRK NONE B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 EA1774VR 1000 LW135 AFTER LANDING AND ENGINE SHUTDOWN, AIRCRAFT OBSERVED TO HAVE SMOKE COMING OUT OF NOSE SECTION. ON INSPECTION, FOUND AIR CONDITIONER COMPRESSOR SEIZED. SMOKE WAS CAUSED BY COMPRESSOR DRIVE MOTOR BELTS DRIVING THE SEIZED PULLEY ON COMPRESSOR, MELTING THE BELTS. OPENING COMPRESSOR FOUND CONNECTING ROD PIECES IN BOTTOM OF CRANKCASE. 1L72 3T4 T 3A20 E4EA 20020424000342002042400034EU 2002 4 24 2002FA0000514 120020412G3234GH115TA HANDLE GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA MLG FAILED G VJ3RO OTHER J WARNING INDICATION NRNOT REPORTED 1 WP07862AF87 85002 L2802448A LANDING GEAR WAS CYCLED TO THE DOWN POSITION IN FLIGHT, BOTH MAIN GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS CAME ON AND THE NOSE GEAR DOWN LIGHTS FAILED TO COME ON. THE SYSTEM WAS TESTED IAW FLIGHT MANUAL PROCEDURES AND THE LIGHTS FOR THE NOSE GEAR DOWN HAD FAILED. A SAFE LANDING WAS MADE. INSPECTION OF THE GEAR SYSTEM FOUND THAT BOTH LIGHTS IN THE GEAR HANDLE HAD FAILED. NEW GEAR HANDLE CONTROL ASSEMBLY WAS INSTALLED, SYSTEM CHECKED NORMAL. 1K00 3 O G33EU 1E4 20020424000352002042400035EU 2002 4 24 2002FA0000515 120020415G2913X030001 PUMP GROB ASTIR G102ASTIR 1660104EU LYC O540 AEIO540D4A5 41532EA HYD SYSTEM FAILED G VJ3RO OTHER FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 WP07865AF14 85005 L2826448A THE LANDING GEAR WAS SWLECTED IN FLIGHT TO THE DOWN POSITION; THE RIGHT MAIN GEAR LIGHT FAILED TO COME ON IN THE DOWN AND LOCKED POSITION. THE AIRCRAFT WAS YAWED AND THE DOWN AND LOCK GEAR LIGHT CAME ON. A SAFE LANDING WAS MADE. AIRCRAFT WAS TAKEN TO MAINTENANCE AND PLACED ON JACKS, THE SYSTEM CHECKED AND FOUND THE GEAR HYDRAULIC MOTOR HAD FAILED (BURNED UP), A NEW HYDRAULIC ASSEMBLY WAS INSTALLED. THE LANDING GEAR WAS CYCLED IAW MM, SYSTEM CHECKED NORMAL. 1K00 3 O G33EU 1E4 20020424000362002042400036SO 2002 4 24 2002FA0000517 120020416G32136682000 NUT PIPER PA28 PA28RT201 7102818SO LYC O360 IO360A1A 41514EA MAIN AXLE MISINSTALLED G K NONE O OTHER ININSP/MAINT 1 GL258288L5554 28R8118011 DURING ANNUAL INSPECTION, MAIN AXLE NUTS WERE INSTALLED BACKWARDS. ONLY WAY COTTER KEY HOLES WOULD ALIGN, WAS TO BACK OFF NUT TO WHERE MAIN WHEEL WAS NOT TIGHT ON AXLE. ONLY THING RETAINING WHEEL ONTO AXLE WAS BRAKE ASSEMBLY. MAIN AXLE TABS WERE DEEPLY GROOVED BY WHEEL BEARINGS. 1L71 3O3 O 2A13 1E10 20020424000372002042400037SO 2002 4 24 2002FA0000518 120020416G32206705403 TRUNNION PIPER PA28 PA28RT201 7102818SO LYC O360 IO360A1A 41514EA NLG BROKEN G K NONE O OTHER ININSP/MAINT 1 GL258288L5554 28R8118011 DURING ANNUAL INSPECTION, FOUND NOSE STRUT HOUSING BOSS WHERE LOWER DRAG LINK ATTACHES, BROKEN. HALF OF BOSS WAS MISSING, THE ASSEMBLY WAS SO COVERED WITH GREASE, MISSING PORTION OF BOSS WASNT VISABLE UNTIL CLEANED OFF. UNKNOWN HOW LONG HAD BEEN WHEN, SPECULATE, HARD LANDING OR MISRIGGED SYSTEM COULD HAVE CONTRIBUTED TO FAILURE. 1L71 3O3 O 2A13 1E10 20020424000382002042400038SO 2002 4 24 2002FA0000519 120020416G78206751700 MUFFLER PIPER PA28 PA28RT201 7102818SO LYC O360 IO360A1A 41514EA ENG EXHAUST DAMAGED G K NONE O OTHER ININSP/MAINT 1 GL258288L1409 28R8118011 DURING ANNUAL INSPECTION, CRACK AROUND REAR MUFFLER LEFT HAND STEEL TUBE FOUND. STEEL TUBE AND MUFFLER INTERNAL FLAME TUBE COULD BE PULLED OUT OF MUFFLER END. BOTH MUFFLER INTERNAL FLAME TUBES FOUND DISTORTED, WHEN VIEWED FROM TAIL PIPE. REAR MUFFLER TT IN SERVICE IS 1409 HOURS. FRONT MUFFLER TT IN SERVICE IS 1306 HOURS. 1L71 3O3 O 2A13 1E10 20020424000502002042400050SO 2002 4 24 2002FA0000520 120020416G7920LCV13775660746 IMPELLER PIPER PA28 PA28RT201 7102818SO LYC O360 IO360C1C6 41514EA OIL PUMP WORN G K NONE O OTHER ININSP/MAINT 1 GL258288L2690 28R8118011 L2208451A DURING ANNUAL INSPECTION, FOUND OIL PUMP ASSEMBLY CONTAINED ALUMINUM DRIVEN IMPELLER AND INTERNAL IRON DRIVEN IMPELLER. AD REQUIRES REPLACEMENT OF THESE IMPELLERS. TBO, HAD MISTAKENLY BEEN CARRIED FORWARD. REPLACEMENT PAST DUE BY 690 HOURS AND 18 MONTHS. MODERATE TO SEVERE WEAR ON DRIVE IMPELLERS AND SHAFT. 1L71 3O3 O 2A13 1E10 20020424000512002042400051EU 2002 4 24 2002FA0000521 120020319G2435410965 BEARING AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7312B WP STARTER GEN OVERHEATED C K NONE W INADEQUATE Q C ININSP/MAINT 1 GL03138M 253 THE SUBJECT STARTER-GEN WAS TEMPORARILY REMOVED FROM SERVICE FOR A PRECAUTIONARY BEARING INSPECTION. NEW BEARINGS, FROM AN AUXILEC APPROVED VENDOR, WERE INSTALLED DURING THAT OVERHAUL. INSPECTION OF THE SUBJECT BEARING BY THE OVERHAUL FACILITY FOUND IT STIFF TO ROTATE AND FELT VERY ROUGH WHEN ROTATED. THE SEALS WERE REMOVED AND THE GREASE (WHITE COLOR) APPEARED NORMAL. THE BEARING HAD NO RADIAL CLEARANCE, AND THE INNER RACE WAS OVERHEATING AS INDICATED BY LOCALIZED DARK PURPLE TO LIGHT BLUE COLOR. THE COLOR OF THE BEARING RETAINERS ALSO INDICATED OVERHEATING. THE ARMATURE SHAFT SHOWED NO EVIDENCE OF THE BEARING RACE SPINNING. A NEW BEARING WAS INSTALLED AND THE PART WAS RETURNED TO SERVICE. 2L73 4F4 F A46EU E6WE 20020425000522002042500052CE 2002 4 25 2002FA0000522 120020311G5320 SUPPORT CESSNA402 402C 207590RCE CONT O520 TSIO520* 17040SO COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 SW073246M18394 402C0294 CRACKS IN PILOTS SEAT PEDESTAL SUPPORTS FOUND AT ANNUAL INSPECTION. SUPPORTS AREA BOX STRUCTURE AND CRACKS CANNOT BE SEEN ON NORMAL VISUAL INSPECTION. A CRACK IN THE FLOOR SKIN COVERING THESE SUPPORTS WAS FOUND. WHEN FLOOR WAS CUT AND FOLDED UP, THE SEVERITY OF THE PROBLEM WAS REVEALED. INSPECT FOR EXCESS MOVEMENT WHERE THE PEDESTAL ATTACHES THROUGH THE FLOOR. THIS MAY INDICATE PROBLEMS BELOW THE FLOOR. 1L72 3O3 O A7CE E8CE 20020425000532002042500053CE 2002 4 25 2002FA0000523 120020311G5320 SUPPORT CESSNA402 402C 207590RCE CONT O520 TSIO520* 17040SO COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 SW073246M18394 402C0294 CRACKS IN PILOTS SEAT PEDESTAL SUPPORTS FOUND AT ANNUAL INSPECTION. SUPPORTS AREA BOX STRUCTURE AND CRACKS CANNOT BE SEEN ON NORMAL VISUAL INSPECTION. A CRACK IN THE FLOOR SKIN COVERING THESE SUPPORTS WAS FOUND. WHEN FLOOR WAS CUT AND FOLDED UP, THE SEVERITY OF THE PROBLEM WAS REVEALED. INSPECT FOR EXCESS MOVEMENT WHERE THE PEDESTAL ATTACHES THROUGH THE FLOOR. THIS MAY INDICATE PROBLEMS BELOW THE FLOOR. 1L72 3O3 O A7CE E8CE 20020425000552002042500055CE 2002 4 25 2002FA0000525 120020401G275014601007 CABLE CESSNA336 336 2075602CE CONT IO360 IO360* 17025CE RT BELLCRANK BROKEN G O OTHER F FLT CONT AFFECTED APAPPROACH 1 EA09108RJ2892 3360067 ON FINAL APPROACH, AIRCRAFT EXPERIENCED A SPLIT FLAP CONDITION, CAUSED BY BROKEN CABLE ASSEMBLY. FLAP ACTUATOR INBOARD (PN 14601007). CABLE HAD BROKEN ON RIGHT SIDE, 1 INCH FROM CABLE END, AT BELLCRANK ENTRY POINT. INSPECTION OF LEFT SIDE FLAP CABLE ASSEMBLY WITH A MIRROR, REVEALED NO NOTICEABLE DAMAGE. ALL CABLES FOR RIGHT AND LEFT FLAP SYSTEM WERE REMOVED AND INSPECTED. LEFT CABLE ASSEMBLY. FLAP ACTUATOR INBOARD, WAS FRAYED AT SAME CONTACT POINT AS RIGHT, (NOT DETECTED BY MIRROR INSPECTION). DUE TO AREA OF BREAKAGE, HAVING LIMITED POSSIBLY FOR VISUAL INSPECTION, RECOMMEND SET TIME PERIOD FOR CABLES TO BE REMOVED FOR INSPECTION OR TIME IN SERVICE REQUIREMENTS SET FOR REMOVAL. 1H72 3O3 O A2CE E1CE 20020425000562002042500056SO 2002 4 25 2002FA0000526 120020326G716099047000 ADAPTER PIPER PA28 PA28R201 7102816SO INDUCTION SYSTEMSHEARED D K NONE O OTHER ININSP/MAINT 1 SW05670X 272 2844055 THE ALTERNATE AIR DOOR HINGE IS ATTACHED BY 3 (AN470AD3) SOLID RIVETS. THE 3 RIVETS SHEARED AND THE AIR DOOR BECAME LODGED IN THE FUEL CONTROL SERVO THROTTLE BODY. THIS OCCURRED ON TAKEOFF AND THE PILOT WAS ABLE TO SET THE AIRCRAFT BACK DOWN SAFELY. RECOEND LARGER SUPPORT FOR HINGE AND MORE RIVETS OF LARGER SIZE. 1L71 3O 2A13 20020425000572002042500057SW 2002 4 25 2002FA0000528 120020313G5711 SPAR BBAVIA7 7GC 2110126SW LYC O290 O290* 41506EA RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL257587E1725 7GC19 WHIN WAS INSPECTED PRIOR TO RECOVER. THIS INSPECTION SHOWED NO CRACKS. WING WAS RECOVERED AND STORED PRIOR TO SINTALLATION. THE WIND BLEW WING AND STORAGE RACK OVER. THE RACK FELL ONTO THE WING. AN INSPECTION WAS DONE. INSPECTION FOUND TWO CRACKS AT THE BUTT END OF THE SPAR, ONE CRACK WAS UNDER THE WING ATTACH FITTING AND ONE CRACK JUST BELOW THE FIRST. BOTH CRACKS IN LINE WITH THE BOLT HOLES AS SHOW IN SL406, THE SPAR WAS CRACKED BADLY ENOUGH THAT A .006 FEELER GAUGE COULD BE PUSHED IN ABOUT 1 INCH. THE SPAR MUST BE REPLACED. 1H71 3O3 O A759 E229 20020425000582002042500058 2002 4 25 2002FA0000529 420020411G34177000700964 ADC GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU COCKPIT INOPERATIVE D K NONE O OTHER ININSP/MAINT 1 EA2363MU 1152 DIGITAL AIR DATA COMPUTER, INOPERATIVE. 2L72 4F4 FRTA12EA E25NE 20020425000592002042500059 2002 4 25 2002FA0000530 420020411G34175224701001 ADC GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY5118 54523EU COCKPIT FAILED D K NONE O OTHER ININSP/MAINT 1 EA23668JT 162 AIR DATA COMPUTER, INTERMITTENT, FAILED. 2L72 4F4 FRTA12EA E2EU 20020425000602002042500060EU 2002 4 25 2002FA0000531 120020220G6220350A31190703 STARFLEX SNIAS 350 AS350B3 8680954EU M/R HEAD DEBONDED D R7MRK NONE O OTHER ININSP/MAINT 1 NM07105LN1157 3249 BUSHING ON END OF STARFLEX HAVE DEBONDED. 1G71 3U H9EU 20020425000612002042500061EU 2002 4 25 2002FA0000532 120020327G6700 BEARING SNIAS 350 AS350B2 8680813EU YAW CONTROL FROZEN B RC0RK NONE O OTHER ININSP/MAINT 1 SW176103X3849 2723 DURING A SCHEDULED INSPECTION ON THIS AIRCRAFT, AEC SL WAS BEING COMPLIED WITH. THIS LETTER HAS LOOKING FOR OUT OF ROUND HOLE CONDITION ON THE YAW CONTROL LOAD COMPENSATOR LEVER. THE ARM ONLY MOVES APPROXIMATELY .30 DEGREES. WHEN THE CONTROL WAS REMOVED, IT WAS FOUND THAT THE BEARING HAD FROZEN. IT STILL MOVED IN ITS .30 DEGREE RANGE BUT THE REST OF THE BEARING WAS FROZEN AND ROUGH. 1G71 3U H9EU 20020425000622002042500062CE 2002 4 25 2002FA0000533 120020325G2742 BUSHING BEECH BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE ACTUATOR LOOSE B RC0RK NONE O OTHER ININSP/MAINT 1 SW17311MP3246 BB1112 BB1112 DURING A SCHEDULED CORROSION INSPECTION THE RIGHT ELEVATOR WAS REMOVED. UPON REMOVAL THE BUSHING IN THE END OF THE ACTUATOR WAS FOUND TO BE LOOSE ON THE SHAFT. WITH THIS BUSHING NOT INSTALLED THE POSSIBILITY OF TAB FLUTTER OR NOT ALLOWING THE TAB ITS FULL MOVEMENT IS POSSIBLE. MFG SHOULD INSTALL A ROLL PIN TO HOLD THIS BUSHING IN PLACE. A ONE-TIME INSPECTION SHOULD BE DOEN ON THESE ACTUATORS TO MAKE SURE THIS IS IN PLACE AS THIS IS A HARD AREA TO SEE ON A DAILY INSPECTION. 1L72 4T4 T A24CE E4EA 20020426000312002042600031CE 2002 4 26 2002FA0000534 120020402G215010138001313 A/C PACK BEECH 200 B200 1152922CE PWA PT6 PT6* 52043EA CABIN MALFUNCTIONED B DFZRK NONE O OTHER ININSP/MAINT 1 EA0987SA BB1089 FLOW PACK HAS LOW FLOW TO CABIN. 1L72 4T3 T A24CE E2NE 20020426000322002042600032CE 2002 4 26 2002FA0000535 120020206G2910 WIRE CESSNA210 T210N 2073456CE CONT O520 TSIO520* 17040SO POWERPACK CUT B Y4MRO OTHER O OTHER TXTAXI/GRND HDL 1 SO096359Y 21064351 AIRCRAFT HAD THE LEFT GEAR COLLAPSE ON ROLLOUT. PLACED AIRCRAFT ON JACKS AND CHECKED RETRACT SYSTEM. FOUND POWER PACK NOT RUNNING DUE TO A CUT WIRE IN THE NOSE WHEEL WELL. THE WIRING TO THE NOSE DOWN LOCK SWITCH WAS MISROUTED AND WAS CUT IN THE DOWN LOCK ASSEMBLY. DUE TO THE CUT WIRE, THE LANDING GEAR MOTOR STOPPED RUNNING, THE GEAR POSITION GREEN LIGHTS FAILED AND THE WARNING HORN DID NOT SOUND. ALL THESE SYSTEMS ARE CONTROLLED BY THE SAME CIRCUIT BREAKER. REPAIRED WIRING AND CHECKED SYSTEMS AND FOUND THEM ALL OPERATING NORMALLY. 1H71 3O3 O 3A21 E8CE 20020426000332002042600033 2002 4 26 2002FA0000536 420020416G341845150320 SENSOR AOA SENSOR MISINSTALLED B OZRRO OTHER W INADEQUATE Q C NRNOT REPORTED 1 SW11 AOA SENSOR, AN ANGLE OF ATTACK (AOA) SENSOR WAS IMPROPERLY INSTALLED ON AN AIRCRAFT BY INSTALLING IT ONE HOLE OFF IN THE COUNTER CLOCKWISE DIRECTION. THE IMPROPER INSTALLATION OF THE AOA SENSOR RESULTED IN A FALSE STALL WARNING INDICATION DIRECTLY AFTER TAKEOFF. DISPARITIES BETWEEN THE A320 AMM 34-11-19, AND THE PHYSICAL CONDITION OF THE AIRFRAME AND THE PART, DIRECTLY CONTRIBUTED TOT THE IMPROPER INSTALLATION. THE AMM INDICATES THAT THE SENSOR ITSELF HAS ONLY ONE COUNTER SUNK HOLE, HOWEVER, THE SENSOR ACTUALLY HAS EIGHT MOUNTING HOLES IN THE AIRFRAME STRUCTURE THAT WOULD ALLOW FOR THE INSTALLATION OF THE ALIGNMENT PINS, HOWEVER THIS TOO IN INCORRECT. 20020426000342002042600034EU 2002 4 26 2002FA0000537 120020308G25205048284011544185SEAT BELT ISRAELGALAXYGALAXY 4500307EU CABIN FAILED G K NONE O OTHER ININSP/MAINT 1 GL2583EJ 009 PASSENGER SEAT BELT BUCKLE FALLS APART. THIS IS THE 4TH INSTANCE OF THIS. 2L72 4F RTA53NM 20020426000652002042600065EA 2002 4 26 2002FA0000538 220020402G7322 FLOAT PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA CARBURETOR INOPERATIVE B ECQRK NONE O OTHER ININSP/MAINT 1 SO15611FT 2841223 L809339A CARBURETOR WAS FOUND INOPERABLE CONDITION ON AIRCRAFT. UPON INSPECTION, A PARK FUEL STAIN WAS NOTED DEAR AIRBOX IN THE CARBURETOR THROAT. CLOSER INSPECTION REVEALED A SMALL HOLE IN THROAT PASSING INTO BOWL. OTHER SMALL CRACKS AND A VERY ROUGH CASTING WAS NOTICED IN SAME AREA OF THROAT. 1L71 3O3 O 2A13 E274 20020506000562002050600056SO 2002 5 6 2002FA0000539 120020330G2750552615 MOTOR PIPER PA32 PA32R301T 7103220SO LYC O540 TIO540* 41532EA TE FLAPS INOPERATIVE B FCPRK NONE L NO TEST ININSP/MAINT 1 NM094163E352 3257136 FLAPS INOPERATIVE, TROUBLESHOOTING, FOUND FLAP MOTOR INOPERATIVE. REPLACED MOTOR ASSEMBLY. 1L71 3O3 O A3SO E14EA 20020506000572002050600057EA 2002 5 6 2002FA0000540 220020402G8550CP48110 OIL FILTER LYC O360 O360A4M 41514EA ENGINE MISMANUFACTURED B UC2RK NONE W INADEQUATE Q C ININSP/MAINT 1 GL19 DURING A PREINSTALLATION INSPECTION ON A MFG. SPIN ON OIL FILTER THE CENTER ATTACH STUD WAS FOUND TO BE ONLY FINGER TIGHT. THIS DEFECT COULD HAVE CAUSED LOSS OF ENGINE OIL AND POSSIBLY ENGINE FAILURE IF THE DEFECT GOES UNDETECTED. 3 O E286 20020506000582002050600058EU 2002 5 6 2002FA0000541 120020417G272027220 CONTROL CABLE AIMM AMT200AMT200 05630AZEU RT RUDDER PEDAL BROKEN D K NONE O OTHER ININSP/MAINT 1 CE09757DM900 200047 RIGHT RUDDER PEDAL CABLE, BROKEN. 1L71 3I NC 20020506000592002050600059CE 2002 5 6 2002FA0000542 120020426G27100510105224 CONTROL CABLE CESSNA172 172N 2072434CE LYC O320 O320A2D 41508EA AILERON BROKEN G O OTHER F FLT CONT AFFECTED APAPPROACH 1 SO15759087000 17268032 LEFT AILERON DIRECT CONTROL CABLE SEPARATED IN FLIGHT RESULTING IN A FATAL ACCIDENT. THE CABLE P/N 0510105-224 WAS VERY BADLY RUSTED AT THE POINT OF FAILURE LOCATED ABOVE THE RIGHT DOORPOST WHERE THE CONTROL CABLE RIDES OVER A PULLEY. THE PULLEY IN THIS AREA WAS VERY STIFF DUE TO A BADLY CORRODED BEARING. THIS APPEARS TO BE A RESULT OF POOR INSPECTION PROCEDURES. THE DOORPOST TRIM MUST BE REMOVER AND THE HEADLINER MUST BE OPENED TO PROPERLY INSPECT THIS AREA. IT IS A REQUIREMENT OF THE ANNUAL INSPECTION TO INSPECT THE FLIGHT CONTROL SYSTEMS, THE ENTIRE SYSTEM, NOT JUST THE EASY PART. THINK TWICE BEFORE YOU SIGN OFF YOUR NEXT INSPECTION. 1H71 3O3 ONT3A12 E274 20020506000962002050600096GL 2002 5 6 2002FA0000544 220020322G7532 BLEED VALVE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE ERRATIC B EOORO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 AL035074R 450 1151D CAE830448 DURING FLIGHT THE COMPRESSOR STALLED A COUPLE OF TIMES. BOTH DURING A POWER CHANGE AND IN A STABLE POWER SETTING. REMOVED BLEED VALVE AND REPLACED WITH A SERVICEABLE UNIT AND THE PROBLEM WAS CORRECTED. 1G71 3U3 U H3WE E4CE 20020506000972002050600097WP 2002 5 6 2002FA0000545 120020315G3213369H600152 STRUT HUGHES369 369D 4470706WP ALLSN 250C 250C20 03013GL MLG BROKEN B EOORK NONE O OTHER ININSP/MAINT 1 AL0390431 1100833D FOUND LANDING STRUT BROKEN AT THE DRAG BRACE BOLT HOLE. REMOVED AND REPLACED STRUT. 1G71 3U3 U H3WE E4CE 20020506000982002050600098CE 2002 5 6 2002FA0000546 120020416G2432G35 BATTERY BEECH 35 M35 1151526CE CONT O470 IO470* 17026SO MAIN SHORTED B NM4RK NONE O OTHER ININSP/MAINT 1 SO15711DU D6538 LANDING GEAR FAILED TO EXTEND ALL THE WAY. AIRCRAFT LOST ELECTRICAL POWER. REMOVED BATTERY AND FOUND LOW VOLTS WITH NO CAPACITY, BATTERY WOULD NOT CHARGE ON BENCH INTERNALLY SHORTED INSTALLED NEW BATTERY, AIRCRAFT AND FOUND. FIELD CIRCUIT BREAKER POPPED RESET AND CHARGING SYSTEM OPS CHECK NORMAL. GEAR SWING WAS NORMAL AFTER REPLACING BENT LEFT GEAR PUSH ROD EMERGENCY EXTENSION NORMAL. 1L71 3O3 O 3A15 E1CE 20020506000992002050600099WP 2002 5 6 2002FA0000547 120020221G6330369A2029 STUD HUGHES369 369D 4470706WP XMSN MOUNT CRACKED B EOORK NONE O OTHER ININSP/MAINT 1 AL03CGPHC9759 180257D FOUND ON OF THE FOUR MAIN ROTOR TRANSMISSION MOUNTING STUDS CRACKED IN THE RADIUS OF THE SHOULDER TO THE WRENCHING FLAT FLANGE. REMOVED AND REPLACED WITH SERVICEABLE PART. 1G71 3U H3WE 20020506001102002050600110CE 2002 5 6 2002FA0000549 120020329G531411498002412 KEELBEAM BEECH 1900 1900D 1154162CE FUSELAGE CRACKED B K NONE O OTHER ININSP/MAINT 1 SO0861HA UE175 SMALL CRACK FOUND ON RIGHT HAND FORWARD OUTBOARD WHEEL WELL KEEL AT UPPER GEAR FENDER SUPPORT ANGLE (SUPPORT ANGLE IS PART OF KEEL CASTING). 2L72 4T RTA24CE 20020506001152002050600115GL 2002 5 6 2002FA0000550 320020422G6114D6382 HUB CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE HARTZLH3B3M HCB3M GL PROPELLER CRACKED B K NONE O OTHER ININSP/MAINT 1 SO17701SE3450 3063 208B0701 PROPELLER WAS DISASSEMBLED AND INSPECTED FOR OVERHAUL. PROPELLER HUB WAS STRIPPED, ETCHED AND DYE PENETRANT INSPECTED. INDICATIONS OF CRACKS WERE APPEARANT AT 5 LOCATIONS ON THE REAR HALF OF THE HUB NEXT TO THE REAR BETA ROD BUSHING SOCKETS. EDDY CURRENT INSPECTION VERIFIED ALL LOCATIONS WERE CRACKED. PART WAS RETIRED FROM SERVICE. 1H71 3T3 T A37CE E4EA 5 CP9NE 20020506001162002050600116EA 2002 5 6 2002FA0000551 220020401G8550S33461 GASKET CESSNA206 206H 2073301CE LYC O540 IO540AC1A5 EA VACUUM PUMP FAILED D A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 AL037254H670 20608036 DURING CRUISE FLIGHT LOST OIL PRESSURE INDICATION, MADE A PRECAUTIONARY LANDING ON A SNOW COVERED REMOTE RUNWAY, AIRCRAFT NOSED DOWN AND HAD A PROP STRIKE, BENDING BLADES. THE MECHANIC REMOVED THE ENGINE, DISCOVERED THE LOWER VACUUM PUMP GASKET WAS BLOWN OUT. THIS BLOWN GASKET ALLOWED OIL TO BE PUMPED OUT PAST THE DRIVE ASSEMBLY INTO THE LOWER COWL. LOSS OF OIL CAUSED NO OIL PRESSURE CONDITION. NOTE: A ONE TIME INSPECTION OF THE LOWER VACUUM PUMP INSTALLATION 1) PROPER GASKET 2) PROPER NUT TORQUE. 1H71 3O3 ORTA4CE 1E4 20020506001172002050600117 2002 5 6 2002FA0000554 420020409G2561KSD35P0723105 LIFE VEST CABIN FAILED B K NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED, MFG ECOMMENDED PRESSURE TEST. DOM: FEB 1985 20020506001182002050600118SO 2002 5 6 2002FA0000555 220020404G8530SA52000A20P CYLINDER BEECH 36 A36 1151604CE CONT O520 IO520BA 17032SO ENGINE LEAKING D JZRRK NONE K FLUID LOSS ININSP/MAINT 1 EA07323GB63 E647 280914R NOTICED OIL SEEPAGE BETWEEN THE HEAD AND BARREL OF THE NR 5 CYLINDER BETWEEN THE PUSH ROD TUBES DURING THE FIRST OIL CHANGE. DURING THE SECOND OIL CHANGE, NOTICED A SUBSTANTIAL INCREASE IN OIL LEAKAGE AT THE SAME PLACE ON THE NR 5 CYLINDER, ALSO NOTICED OIL LEAKING FROM THE NR 3 CYLINDER IN THE SAME AREA. BOTH CYLINDER REPLACED AND RETURNED TO MFG. 1L71 3O3 O 3A15 E5CE 20020506001192002050600119SO 2002 5 6 2002FA0000556 220020404G8530SA52000A2OP CYLINDER BEECH 36 A36 1151604CE CONT O520 IO520BA 17032SO ENGINE LEAKING B JZRRK NONE K FLUID LOSS ININSP/MAINT 1 EA07323GB63 E647 280914R NOTICED OIL SEPPAGE BETWEEN THE HEAD AND BARREL OF THE NR 5 CYLINDER BETWEEN THE PUSH ROD TUBES DURING THE FIRST OIL CHANGE. DURING THE SECOND OIL CHANGE, NOTICED A SUBSTANTIAL INCREASE IN OIL LEAKAGE AT THE SAME PLACE ON THE NR 5 CYLINDER, ALSO NOTICED OIL LEAKING FROM THE NR 3 CYLINDER IN THE SAME AREA. BOTH CYLINDERS REPLACED AND RETURNED TO MFG. 1L71 3O3 O 3A15 E5CE 20020506001202002050600120NE 2002 5 6 2002FA0000557 220020429G72409824053225 BOLT TMECA ARRIELARRIEL1D1 NE ENGINE BROKEN B K NONE O OTHER ININSP/MAINT 1 SO194068W1931 1931 9444 AFTER A MAINT FLIGHT, FOLLOWING THE CLEANING OF THE NR 4 BEARING, THE MAINT TECH FOUND THE OUTSIDE OF THE ENGINE COWLING DELAMINATED. DURING INSPECTION TO DETERMINE THE CAUSE, THE MECHANIC NOTICED THE ENGINE SPLIT LINE BETWEEN MO3 AND MO4 DEVELOPED A BLEED AIR LEAK. UPON EXAMINATION OF THE ATTACHMENT FLANGE BOLTS ONE WAS FOUND TO BE BROKEN IN THE AREA OF THE LEAK. THE BOLT HAD BROKEN FAR ENOUGH INTO THE CASE THAT THE MODULES WHERE REMOVED AND SENT TO TURBOMECA TO ELIMINATE THE POSSIBILITY OF FURTHER DAMAGE. THE ENGINE WAS REASSEMBLED IAW MM CHAPTER 72 AND ALL PROCEDURES WHERE FOLLOWED, QUALITY CONTROL WAS ON HAND AND VERIFIED ALL PROCEDURES WHERE FOLLOWED DURING THE ASSEMBLY PROCESS. 3 U E19EU 20020506001472002050600147CE 2002 5 6 2002FA0000566 120020430G323398820152 HOUSING CESSNA172 172RG 2072438CE MLG ACTUATOR CRACKED B K NONE O OTHER ININSP/MAINT 1 GL095169V7794 496 0458 ACCOMPLISHED 500 HR REINSPECTION OF THE LANDING GEAR ACTUATOR HOUSINGS. FOUND THE LEFT AND RIGHT HOUSINGS TO BE CRACKED. THE RIGHT HOUSING WAS REPLACED AT THE INITIAL INSPECTION WITH A USED, SERVICEABLE HOUSING P/N: 9882015-2. REPLACED BOTH HOUSINGS WITH NEW STYLE HOUSINGS P/N: 1281001-6. 1H71 3O 3A17 20020506001482002050600148CE 2002 5 6 2002FA0000567 120020501G2497 WIRE CESSNA172 172S 2072439CE VOLTAGE REG SHORTED D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 GL07 172S8202 ALTERNATOR FIELD C/B POPED IN FLIGHT. PILOT RESET C/B, SMELLED SMOKE IN THE COCKPIT, C/B POPED AGAIN. THE PILOT MADE A PRECAUTIONARY LANDING AT MNN. AN INVESTIGATION OF THE PROBLEM DETERMINED THAT THE RED VOLTAGE REGULATOR WIRE HAD SHORTED ON THE GROUNDING POST OF THE RELAY BELOW CAUSING A SHORTED WIRE FROM THAT POINT TO THE 5 AMP C/B, ALTERNATOR FIELD. 1H71 3O NT3A12 20020506000522002050600052EA 2002 5 6 2002FA0000568 220020501G7230T102401100A BLADE AIRTRCAT500 AT502 0390303SW PWA PT6 PT6A34 52043EA COMPRESSOR DISK FAILED G C ABORTED TAKEOFF G MULTIPLE FAILURE TOTAKEOFF 1 SO079185F29 5020206 PCE56893 DURING TAKE OFF THE ENGINE LOST ALL POWER. ENGINE WAS SHIPPED TO CERTIFIED REPAIR STATION. THE PRELIMINARY ANALYSIS IS IN THE ENGINE TURBINE SECTION: THE COMPRESSOR TURBINE DISC P/N 3013411, S/N 2P609, HAD SEVERAL BLADES (BLADES 9,11 THRU 19, 21, 44, AND 45) FRACTURED AT THERE ROOTS. UNDER UNAIDED VISUAL AND MACROSCOPIC INSPECTION THE ROUTE FRACTURE SURFACES DISPLAYED COURSE GRANULAR FEATURES. THE BLADE P/N (T-102401-100A) BEING PREFIXED WITH A "T" DENOTES THE BLADES TO BE NON-PWC MANUFACTURED UNITS.THESE BLADES WERE CHANGED AT LAST HSI ON 6 FEBRUARY 2002 AND HAD ONLY 28.7 HOURS TO THIS FAILURE. 1L71 3T4 TNCA9SW E4EA 20020506000542002050600054SO 2002 5 6 2002FA0000569 120020502G2711 COTTER PIN MAULE MX7 MX7235 5460180SO LYC O540 IO540* 41532EA TRIM WHEEL MISSING C O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 EA21 149 PILOT REPORTED HE COULD NOT TRIM ALERIONS. REMOVED COVER AND FOUND BOLT HOLDING LARGE, GEARED TRIM WHEEL WAS MISSING COTTER KEY AND NUT HAD BACKED OFF, ALLOWING LARGE GEAR TO SLIDE TO SIDE ABOUT 3/8 IN. HAD TO COME FROM FACTORY THIS WAY. TIGHTENED NUT AND PLACED COTTER KEY IN SLOT. 1H71 3O3 ONC3A23 1E4 20020507000032002050700003CE 2002 5 7 2002FA0000570 120020416G3213 SNAP RING BEECH 50 D50 1152512CE MLG STRUT FAILED D MJ1RK NONE O OTHER ININSP/MAINT 1 GL11632Z DH113 AIRCRAFT WAS PARKED IN HANGAR, NO MAINTENANCE BEING PERFORMED. UPON 1ST INVESTIGATION LT MAIN LANDING GEAR STRUT WAS BOTTOMED. UPON FURTHER INVESTIGATION UPPER STRUT CAP SNAP RING HAD COME LOOSE AND CAP EJECTED THROUGH UPPER WING SKIN CAUSING A 3 INCH HOLE IN UPPER WING SKIN. NO OTHER DAMAGE NOTED ON AIRCRAFT. UPON FURTHER INSPECTION NO SIGN OF COMPONENT FAILURE TO LEFT MAIN LANDING GEAR STRUT NOTED. 1L72 3O 5A4 20020507000012002050700001EU 2002 5 7 2002FA0000575 120020506G5730ER863072500 SKIN RHNFLUEXT300EA300L 70218DGEU LYC O540 AEIO540L1B5 41532NE WING DELAMINATED B A UNSCHED LANDING K FLUID LOSS ABAEROBATIC 1 WP28161FC504 133 WING SKIN DELAMINATION OCCURRED IN FLIGHT. CRACKS IN PAINT AND FUEL SEEPAGE FROM AREA WAS REASON FOR DISCOVERY. DELAMINATION AREA IS 72 INCHES OUTBOARD ON TOP SIDE OF RIGHT WING AND EXTENDS APPROXIMATELY 30 INCHES FURTHER OUTBOARD. DELAMINATION AREA STARTS 2.25 INCHES AFT OF THE LEADING EDGE AND EXTENDS 11.5 INCHES AFT CORDWISE. THIS PROBLEM IS ALSO DEVELOPING IN TWO OTHER AIRCRAFT OF THE SAME MODEL, AND OPERATED BY THE SAME OWNER. CAUSE UNKNOWN AT THIS TIME, BUT COULD BE FUEL TANK-RELATED DUE TO THE AREA OF DAMAGE. AIRCRAFT IS GROUNDED AND AWAITING REPAIR INSTRUCTIONS FROM THE MANUFACTURER. 1M71 3O3 ONCEA67U 1E4 20020507000022002050700002EU 2002 5 7 2002FA0000577 120020506G5700ER863072500 SKIN EXTRA EA300 EA300 70218DIEU WING DELAMINATED C K NONE O OTHER ININSP/MAINT 1 WP28477SF210 088 POSSIBLE WING SKIN DELAMINATION DISCOVERED. CRACKS IN PAINT IS REASON FOR DISCOVERY. POSSIBLE DELAMINATION AREA IS 72" OUTBOARD ON TOP SIDE OF RIGHT WING AND EXTENDS APPROXIMATELY 30" FURTHER OUTBOARD. DELAMINAITON AREA STARTS 2.25" AFT OF THE LEADING EDGE AND EXTENDS 11.5" AFT CORDWISE. ACTUAL DELAMINATION FOUND IN TWO OTHER AIRCRAFT OF THE SAME MODEL, AND OPERATED BY THE SAME OWNER. CAUSE UNKNOWN AT THIS TIME, BUT COULD BE FUEL TANK RELATED DUE TO THE AREA OF DAMAGE. 1M71 3O NCA67EU 20020514000362002051400036GL 2002 5 14 2002FA0000578 120020419G7810 BAFFLE AVIAT A1 A1B 2210406GL LYC O360 O360A1D 41514EA EXHAUST DUCT MISSING D K NONE O OTHER ININSP/MAINT 1 AL0337HY 588 2037 REMOVED MUFFLER/ EXHAUST DUCT ASSEMBLY INTERNAL BAFFLES MISSING, AND NR 4 CYLINDER LOWER SLIP JOINT LEAKING. 1H71 3O3 ONCA22NM E286 20020514000372002051400037GL 2002 5 14 2002FA0000579 120020419G781035651 SLIP JOINT AVIAT A1 A1B 2210406GL LYC O360 O360A1D 41514EA EXHAUST DUCT LEAKING C K NONE O OTHER ININSP/MAINT 1 AL0337HY 588 2037 REMOVED MUFFLER/ EXHAUST DUCT ASSEMBLY INTERNAL BAFFLES MISSING, AND NR 4 CYLINDER LOWER SLIP JOINT LEAKING. 1H71 3O3 ONCA22NM E286 20020514000382002051400038EU 2002 5 14 2002FA0000580 120020412G2910F10A751108 LINE AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE731* 01518WP HYD SYSTEM CHAFED B UO2RK NONE K FLUID LOSS ININSP/MAINT 1 GL1942EH 28 NR 1 HYDRAULIC SYSTEM LOST ALL FLUID ON FLIGHT. DISCOVERED HYDRAULIC LINE CHAFFED THROUGH. LINE HAD CHAFFED AGAINST ANOTHER LINE (PN F10A751127) IN AFT BAY. INSPECT SYSTEM COMPONENTS FOR POTENTIAL DAMAGE. 2L72 4F4 F A33EU E6WE 20020514000402002051400040SO 2002 5 14 2002FA0000583 220020402G7314 SPRING CESSNA421 421C 2076016CE CONT O520 GTSIO520* 17032SO FUEL PUMP MISINSTALLED B G6NRK NONE LW NO TEST INADEQUATE Q C ININSP/MAINT 1 CE09246MF 421C1406 AUXILIARY FUEL PUMP WAS RECEIVED NEW FROM SUPPLIER. ONCE INSTALLED , IT FAILED MFG SM CHECK . WHEN REMOVED FOR BENCH CHECK, IT WAS DISCOVERED, SPRING IN THE OUTLET SIDE IS MISINSTALLED. 1L72 3O3 O A7CE E7CE 20020514000412002051400041EA 2002 5 14 2002FA0000586 220020301G8520 CONNECTING ROD ENSTRMF28 280C 3300505GL LYC O360 HIO360E1AD 41514EA ENGINE FAILED G K NONE O OTHER ININSP/MAINT 1 SW0951657200 1097 L2006151A NR 2 CONNECTING ROD BOLT FAILED CAUSING CONNECTING ROD TO GO THROUGH CRANK CASE CAUSING MAJOR ENGINE FAILURE. ENGINE DESTROYED. TOP OF BOLT FAILED CAUSING ROD CAP TO BEND BACK AND EVENTUALLY FAIL. THREADED END OF THE BOLT FOUND IN BOTTOM OF ENGINE CASE IN GOOD CONDITION. NO SIGN OF OVERREV COULD BE FOUND IN OTHER BOLTS OR RODS. 1G71 3O3 O H1CE 1E10 20020509000592002050900059WP 2002 5 9 2002FA0000587 220020504G720030756842 RETAINER AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP NR 1 ENGINE BROKEN B K NONE O OTHER NRNOT REPORTED 1 GL09523AC1697 139 P101216 UPON AIRCRAFT ARRIVAL AND SUBSEQUENT SHUTDOWN, MECHANICS HEARD A SCRAPING AND A THUNKING SOUND FROM THE NR 1 ENGINE AS THE ENGINE WAS SPOOLING DOWN. WHEN THE FAN ASSY WAS TURNED BY HAND, THE SAME NOISES CAN BE HEARD AND FELT. INSPECTION OF THE OIL FILTER REVEALED MANY FERROUS CHUNKS. A SOAP ANALYSIS WAS PERFORMED AND THE METAL TURNED OUT TO BE 17-4PH : CHUNKS. TEARDOWN OF THE FRONT END REVEALED THAT THE NR 3 BEARING SEAL ROTOR RETAINER WAS BROKEN, WITH PARTS MISSING. THE RETAINER EXHIBITED DISCOLORATION FROM OVERHEATING. SOAP ANALYSIS 70 HOURS PRIOR WAS NORMAL. 2L73 4F4 FRTA46EU E6WE 20020514000422002051400042CE 2002 5 14 2002FA0000588 120020422G2421646843 ALTERNATOR CESSNA210 T210L 2073449CE CONT O550 IO550* SO ENGINE FAILED B O OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 SO051226M 21061272 ALTERNATOR FAILED IN FLIGHT. PILOT SMELLED ELECTRICAL BURNING ODOR. FLIGHT COMPLETED WITHOUT INCIDENT. ALTERNATOR REPLACEMENT CORRECTED PROBLEM. THIS IS THE 2ND ALTERNATOR FAILURE ON THIS ENGINE WITHIN 300.7 HOURS. FAILED ALTERNATOR NOT DISASSEMBLED TO DETERMINE FAULT AT THIS FACILITY. FAILED ALTERNATOR WAS RETURNED TO VENDOR. 1H71 3O3 O 3A21 E3SO 20020514000442002051400044CE 2002 5 14 2002FA0000589 120020410G7160075014421 AIR BOX CESSNA182 182G 2072716CE CONT O470 O470* 17026SO ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 GL233736U 18255136 849983 SEVERAL CRACKS IN HOUSING, BOTH IN ALUMINUM AND STAINLESS STEEL. SERVICEABLE PART INSTALLED ABOUT 375 HOURS OPERATING TIME. SUGGEST MORE ATTENTION BE GIVEN THIS ITEM AND THE WAY IT IS ATTACHED, FOR SECURITY. HIGH VIBRATION AREA. CHECK PROPELLER FOR BALANCE. 1H71 3O3 ONT3A13 E273 20020514000652002051400065SO 2002 5 14 2002FA0000590 120020508G3210 UPLOCK BRACKET PIPER PA31 PA31350 7103110SO MLG SHEARED E K NONE O OTHER ININSP/MAINT 1 GL09200VW7556 318052011 SHEAR FAILURE OF RIVETS ATTACHING PIPER UPLOCK BRACKETS TO ATTACHING RIB. 1L72 3O A20SO 20020515000032002051500003 2002 5 15 2002FA0000593 420020308G342252D189 INDICATOR CESSNA206 206H 2073301CE LYC O540 IO540* 41532EA HSI MALFUNCTIONED B HI1RK NONE L NO TEST ININSP/MAINT 1 NE052448Z78 20608141 ON AN ILS FREQUENCY, WITH A VALID SIGNAL THE UNIT WILL PULL THE FLAG BUT GIVE THE FLY DOWN COMMAND ALL THE TIME, EVEN WHEN IT SHULD BE CENTERED. 1H71 3O3 ORTA4CE 1E4 20020515000042002051500004NM 2002 5 15 2002FA0000594 120020320G3240 HOUSING BOEING737 737 UTILSYSNM SHUTTLE VALVE FATIGUED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 PIN HOLE IN MOUNT HOLE, FATIGUE. REMOVED AND REPLACED. (JN 166395) 2L72 4F RTA16WE 20020515000052002051500005NM 2002 5 15 2002FA0000595 120020320G3240 HOUSING BOEING737 737 UTILSYSNM SHUTTLE VALVE PIN HOLE B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 SHUTTLE VALVE HAS A PIN HOLE IN MOUNT HOLE, FATIGUE. REMOVED AND REPLACED. 2L72 4F RTA16WE 20020515000062002051500006NM 2002 5 15 2002FA0000596 120020320G2910 HOUSING BOEING737 737 UTILSYSNM RESTRICTOR BROKEN B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 HOUSEING IS BROKEN. BODY IS TOO WEAK. 2L72 4F RTA16WE 20020515000072002051500007NM 2002 5 15 2002FA0000597 120020320G3230 HOUSING BOEING737 737 UTILSYSNM REGULATOR ERODED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 HOUSING EXTRUSION PORT IS ERODED. 2L72 4F RTA16WE 20020515000082002051500008NM 2002 5 15 2002FA0000598 120020320G3230200496 HOUSING BOEING737 737* NM EXTRUSION PORT ERODED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 HOUSING EXTRUSION PORT IS ERODED. 2L72 4F RTA16WE 20020515000092002051500009NM 2002 5 15 2002FA0000599 120020319G3230654466925 HOUSING BOEING737 737200 1384453NM MODULE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 UNIT IS CRACKED IN BOTH PRIORTY PORTS. 2L72 4F A16WE 20020515000102002051500010NM 2002 5 15 2002FA0000600 120020319G3230 HOUSING BOEING737 737* NM MODULE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 HOUSING CRACKED IN (D) PRIORTY PORT. 2L72 4F RTA16WE 20020515000112002051500011NM 2002 5 15 2002FA0000601 120020312G323065446924 HOUSING BOEING BOEING737 737* NM MODULE PIN HOLE B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 271 PIN HOLE LEAK BELOW PORT NR 2. 2L72 4F RTA16WE 20020515000122002051500012NM 2002 5 15 2002FA0000602 120020311G3230511531 HOUSING PNEUDRAULICS BOEING737 737* NM SHUTTLE VALVE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 118559 BODY ITEM (15) IS CRACKED ON ID MOUNTING HOLE. 2L72 4F RTA16WE 20020515000132002051500013NM 2002 5 15 2002FA0000603 120020318G2923654468311 HOUSING BOEING BOEING737 737* NM HYD PACK CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 3032 HAIR LINE CRACK JUST BELOW THREADS OF PORT NR 1. OCCURED DURING NORMAL OPERATION. 2L72 4F RTA16WE 20020515000142002051500014NM 2002 5 15 2002FA0000604 120020218G7830122510 HOUSING BOEING737 737* NM SOLENDOID VALVE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 1829 HAIR LINE CRACK ON SEAM OF BODY ON PORT NR 1 NEAR MOUNTING LUG. OCCURED DURING NORMAL OPERATION. 2L72 4F RTA16WE 20020515000152002051500015NM 2002 5 15 2002FA0000605 120020213G3230 HOUSING BOEING BOEING737 737200 1384453NM MODULE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 46209 1028 HOUSING IS CRACKED. 2L72 4F A16WE 20020515000162002051500016NM 2002 5 15 2002FA0000606 120020206G323065446925 HOUSING BOEING BOEING737 737200 1384453NM MODULE CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 67565 0779 HOUSING, UNIT IS CRACKED IN (D) PRIORTY PORT. 2L72 4F A16WE 20020515000172002051500017NM 2002 5 15 2002FA0000608 120020211G3230 CAP SARGENT BOEING727 727* NM ACTUATOR ERODED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 4195CB ACTUATOR CAP PORT HAS EROSION INTERNALLY. 2L73 4F RTA3WE 20020515000182002051500018NM 2002 5 15 2002FA0000609 120020211G3230631415710 CAP SARGENT BOEING727 727* NM PORT C ERODED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 3117 ACTUATOR CAP PORT (C) HAS EROSION INTERNALLY. 2L73 4F RTA3WE 20020515000192002051500019NM 2002 5 15 2002FA0000610 120020107G274069778552 SPRING BOEING BOEING737 737* NM HORIZONTAL STAB CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 22868 KE00511 23776 SPRINGS ARE BROKEN IN THE AUXILIARY BRAKE SYSTEMS. IMPROPER HEAT-TREATING, AUSTENITE, FATIGUE AND INCREASED SPRING COIL. SPRINGS (PN 69-77855-1) ARE TO BE REPLACED WITH (PN 69-77855-2). SPRINGS ON ACTUATOR ASSEMBLIES MANUFACTURED PRIOR TO SERIAL NUMBER KEO1730 PER MFG SL. 2L72 4F RTA16WE 20020515000202002051500020NM 2002 5 15 2002FA0000611 120020123G3240511531 HOUSING PNEUDRAULICS BOEING737 737* NM SHUTTLE VALVE PIN HOLE B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 651 SHUTTLE VALVE HAS A CRACKED HOUSING. 2L72 4F RTA16WE 20020515000212002051500021NM 2002 5 15 2002FA0000612 120020307G276165C268636 HOUSING BOEING BOEING737 737* NM ACTUATOR CRACKED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 48893 1246 ACTUATOR HOUSING IS CRACKED AT THE TOP SHOULDER. 2L72 4F RTA16WE 20020515000222002051500022NM 2002 5 15 2002FA0000613 120020228G3240511531 HOUSING PNEUDRAULICS BOEING737 737* NM SHUTTLE VALVE PIN HOLE B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 4603 PIN HOLE IN MOUNTING LUG HOLE. LEAKS HYDRAULIC FLUID, FATIGUED. 2L72 4F RTA16WE 20020515000232002051500023NM 2002 5 15 2002FA0000614 120020327G2822209739WE NUT BOEING727 727* NM FUEL PUMP FRACTURED B IU6RK NONE O OTHER ININSP/MAINT 1 NM01 NUT FRACTURED INTO THREE PIECES UNDER NORMAL TORQUE OF (75-80 IN-LBS). 2L73 4F RTA3WE 20020514000522002051400052CE 2002 5 14 2002FA0000615 120020509G1430 RIVET BEECH B300 B300 1159232CE WING LOOSE B K NONE O OTHER ININSP/MAINT 1 EA21160AR FL154 UNDERSIDE OF WINGS AT WING STATION 209 HAVE LOOSENING RIVETS (CRACKED PAINT AND SMOKING), 45 OF 66 ON LEFT WING, 30 OF 66 ON RIGHT WING. 2L72 4T RTA24CE 20020514000532002051400053CE 2002 5 14 2002FA0000616 120020509G1430 RIVET BEECH B300 B300 1159232CE WING LOOSE B K NONE O OTHER ININSP/MAINT 1 EA21272SW FL228 UNDERSIDE OF WINGS AT WING STATION 209 HAVE LOOSENING RIVETS (CRACKED PAINT AND SMOKING). APPROXIMATELY HALF THE RIVETS SHOW SYMPTOMS. 2L72 4T RTA24CE 20020515000242002051500024 2002 5 15 2002FA0000617 420020411G2561GA12PO201 LIFE VEST CELL FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 FLOTATION DEVICE FAILED MFG RECOMMEDNED 2 PSI PRESSURE TEST. 20020515000252002051500025CE 2002 5 15 2002FA0000618 120020425G572051220466 BRACKET CESSNA402 402C 207590RCE CONT O520 TSIO520* 17040SO RT WING BROKEN D K NONE O OTHER ININSP/MAINT 1 CE016764C6950 402C0628 LOWER RIGHT FLAP BELLCRANK BRACKET BROKE DUE TO CORROSION FROM ENGINE EXHAUST. LEFT WING INSPECTED, PARTS SHOW NO CORROSION. 1L72 3O3 O A7CE E8CE 20020515000262002051500026EA 2002 5 15 2002FA0000619 220020418G853068510 STUD CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA NR 3 CYLINDER BROKEN D K NONE O OTHER ININSP/MAINT 1 NM0975844150 17267998 L64176 THE STUD THAT HOLDS DOWN THE EXHAUST ROCKER SNAPPED OFF, CAUSING ROCKER AND RELATED PARTS TO FLOAT AROUND IN VALVE COVER. LOOSE PARTS THEN LODGED BETWEEN INTAKE ROCKER CAUSING 30 DEGREE BEND IN PUSH ROD AND SHROUD. THE STUD THAT BROKE, BROKE AT THREADS WITHIN THE CYLINDER HEAD. PARTIAL POWER LOSS IN FLIGHT, PILOT MADE AN EMERGENCY LANDING AT 4S2. 1H71 3O3 ONT3A12 E274 20020515000272002051500027EU 2002 5 15 2002FA0000620 120020412G770064031122101 DISPLAY AMD FALC2020F5 2730105EU GARRTTTFE731TFE731* 01518WP COCKPIT MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 GL19757CX 408 WHEN LEFT FUEL FEEDER TANK IS DRAINED COMPLETELY, RIGHT FUEL FEEDER TANK DROPS TO ZERO (QUANTITY INDICATOR). WHEN YOU PULL LEFT FUEL FEEDER TANK CIRCUIT BREAKER THE LEFT FUEL QUANTITY GOES TO RED X AS IT SHOULD AND RIGHT FUEL QUANTITY INDICTOR DROPS TO ZERO. IT WAS FOUND TO BE A SOFTWARE PROBLEM IN THE EEI (ELECTRONIC ENGINE DISPLAY) 2L72 4F4 FRTA7EU E6WE 20020515000312002051500031 2002 5 15 2002FA0000621 420020222G2211 COMPUTER CESSNA182 182S 2072701CE LYC O540 TIO540* 41532EA AUTOFLIGHT FAILED B Z08SK NONE O OTHER ININSP/MAINT 1 CE0797TD 18280012 THE AC WAS IN LEVEL FLIGHT WITH AUTOPILOT TURNED OFF. WHEN THE AUTOPILOT COMPUTER, WITHOUT INPUT FROM THE PILOT GAVE AN INDICATION THAT (PITCH WARNING) LIGHT CAME ON WITH A (UP) ARROW. THE PILOT PULLED THE AUTOPILOT CIRCUIT BREAKER TO TURN OFF SYSTEM. ANOTHER FLIGHT WITH THE AUTOPILOT SYSTEM (ON) THE ELECTRIC TRIM STARTED TO RUN AWAY IN THE NOSE UP ATTITUDE AND THE PILOT WENT TO PRESS THE AUTOPILOT DISCONNECT ON THE CONTROL WHEEL, WITH NO RESULTS. THE PILOT PULLED THE AUTOPILOT CIRCUIT BREAKER TO STOP THE OCCURRENCE AND MANUALLY TRIMMED AS REQUIRED. MAINTENANCE DISABLED AUTOPILOT SYSTEM WHICH INCLUDES THE ELECTRIC TRIM. 1H71 3O3 ONT3A13 E14EA 20020515000662002051500066SO 2002 5 15 2002FA0000623 120020416G3230PA6469100 TORQUE LINK PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA LT MLG STRUT DAMAGED D QVVSK NONE O OTHER ININSP/MAINT 1 WP13261FC6416 2824697 DURING LANDING LT LOWER STRUT ASSEMBLY SEPERATED FROM UPPER CYLINDER. LOWER TORQUE LINK FAILED IN AREA ABOVE MACHINED BOSS AT THE LOWER STRUT ATTACHMENT END, ALLOWING THE LOWER STRUT / WHEEL ASSEMBLY TO BLOW OUT OF THE UPPER CYLINDER. THIS PN TORQUE LINK REQUIRES 500 HOUR RECURRING INSPECTION IAW AD. PROBABLE CAUSE, FATIGUE. REMOVE FROM SERVICE AND REPLACE WITH LATEST TORQUE LINK DESIGN. 1L71 3O3 O 2A13 E274 20020515000672002051500067SW 2002 5 15 2002FA0000624 120020426G3233 COUPLING MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA MLG ACTUATOR FAILED B PHKRK NONE O OTHER ININSP/MAINT 1 SW09315SB4997 700005 WHEN PILOT SELECTED GEAR DOWN, INCOMPLETE EXTENSION OCCURRED. ATTEMPTS TO EXTEND THE GEAR MANUALLY ALSO FAILED. GEAR COLLAPSED ON LANDING. Z AN INSPECTION FOUND THAT THE COUPLING BETWEEN THE GEAR MOTOR AND ACTUATOR WAS SEPARATED. THE MOTOR WAS FOUND NOT TO OPERATE ALSO. THE ACTUATOR ASSEMBLY IS 30+ YEARS OLD. 1L71 3O3 O 2A3 1E10 20020515000682002051500068SW 2002 5 15 2002FA0000625 120020426G323341960016 ACTUATOR MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA MLG FAILED B PHKRK NONE O OTHER ININSP/MAINT 1 CE01315SB4997 700005 WHEN PILOT SELECTED GEAR DOWN INCOMPLETE EXTENSION OCCURRED. ATTEMPTS TO EXTEND THE GEAR MANUALLY ALSO FAILED. AFTER THE AIRCRAFT WAS RETREIVED, PLACED ON JACKS AND BELLY PANELS REMOVED, IT WAS DISCOVERED THE MAIN LANDING GEAR ACTUATOR (DUKES) COUPLING BETWEEN THE MOTOR AND TRANSMISSION WAS SEPARATED, ALSO, THE MOTOR WAS FOUND NOT TO RUN ELECTRICALLY. PROBABLE CAUSE: MOTOR/ TRANSMISSION COUPLING SEPARATED, CAUSING MOTOR TO SEIED. COUPLING IS 30+YEARS OLD. 1L71 3O3 O 2A3 1E10 20020515000692002051500069CE 2002 5 15 2002FA0000626 120020430G2420AN66A BOLT CESSNA500 550 2076604CE PWA 530 PW530A NE GENERATOR WRONG PART B CNQRK NONE O OTHER ININSP/MAINT 1 CE07721T 5500993 A LOOSE GENERATOR GROUND CABLE BOLT WAS DISCOVERED WHILE TROUBLESHOOTING AN AMMETER SPLIT BETWEEN THE LEFT AND RIGHT ENGINE GENERATORS. AN AN610A BOLT WAS FOUND INSTALLED INSTEAD OF THE CORRECT AN6-6A BOLT. THE BOLT WAS TOO LONG AND TORQUE COULD BE REACHED. 1L72 4F4 F A22CE E00053EN 20020515000702002051500070CE 2002 5 15 2002FA0000627 120020423G55206732030 HINGE CESSNA650 650 2076802CE GARRTTTFE731TFE731* 01518WP ELEVATOR CRACKED B CNQRK NONE O OTHER ININSP/MAINT 1 CE07789QS 6507089 CRACKS WERE FOUND IN BOTH INBOARD ELEVATOR HINGES DURING A SCHEDULED INSPECTION. THE HINGES ARE ATTACHED TO THE HORIZONTAL STABILIZER AND ARE LOCATED AT THE INBOARD END OF EACH ELEVATOR. THE CRACKS EXTEND APPROXIMATELY .20 INCH IN LENGTH AND ARE LOCATED ON THE UPPER AFT END OF THE INBOARD HINGE FITTING. 2L72 4F4 F A9NM E6WE 20020515001342002051500134GL 2002 5 15 2002FA0000628 120020408G6500E181150 BELT AMTR RWEXECROTORWAYEXEC GL TAIL ROTOR BROKEN D K NONE O OTHER ININSP/MAINT 1 WP2821901208 CENTER TAIL ROTOR BELT FAILED RESULTING IN NO TAIL ROTOR CONTROL. BELT LIKELY FAILED DUE TO IMPROPER BELT ROUTING THROUGH TAILBOOM FROM ONE IDLER PULLEY TO NEXT IDLER PULLEY. 1G71 3O EXPA1G71 20020515001352002051500135CE 2002 5 15 2002FA0000629 120020429G27100860207180 CONTROL CABLE CESSNA310 T310R 2074246CE CONT O520 TSIO520* 17040SO AILERON BROKEN D K NONE O OTHER ININSP/MAINT 1 SO15310RH1950 310R1878 ALL FOUR CONTROL CABLES HAD STRANDS BROKEN. THE LEFT FORWARD CARRY THRU CONTROL CABLE HAD APPROXIMATELY 70 PERCENT OF ITS STRANDS BROKEN DUE TO CONTACT WITH PULLEY GUARD. THE OTHER PROBLEM IS WHERE CONTROL CABLES COME OUT OF FUSELAGE RUBBING ON PHENOLIC BLOCK. 1L72 3O3 O 3A10 E8CE 20020515001362002051500136CE 2002 5 15 2002FA0000630 120020501G3010510010718 LINE CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO UNDER FLOOR DAMAGED D K NONE O OTHER ININSP/MAINT 1 NM0935DR 4300 414A0628 LINE ASSEMBLY STA 229-289, FOUND TO HAVE HOLE IN IT DIRECTLY ABOVE THE AIR DISTRIBUTION DUCTS. HOLE IN LINE CAUSED DEICE BOOTS TO PARTIALLY INFLATE UN-COMMANDED IN FLIGHT. 1L72 3O3 O A7CE E8CE 20020514000302002051400030CE 2002 5 14 2002FA0000631 120020405G243523085004 STARTER GEN CESSNA500 S550 2076607CE PWA JT15 JT15D4 52112NE ENGINE FAILED C O OTHER O OTHER TXTAXI/GRND HDL 1 SW09200CV 60 S5500064 STATER GEN UNIT FAILED TO START ENGINE. NO OTHER OPERATION PROBLEM NOTED. SUBSEQUENT TEARDOWN REVEALED WORN AND / OR DAMAGED PARTS. UNIT WAS REPORTED AND TAGGED OVERHAULED 60 HRS PRIOR TO FAILURE BY WECO OF LINCOLN, CA. 1L72 4F4 FRTA22CE E1NE 20020514000312002051400031SO 2002 5 14 2002FA0000633 220020511G7322CF30764 FLOAT FACET MA45 CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO CARBURETOR WORN C K NONE K FLUID LOSS ININSP/MAINT 1 WP234603N3063 1382 CO43640 18267280 469241 AFTER A SERIES OF INTERMITTANT FUEL LEAKS FOLLOWING ENGINE SHUTDOWNS, CARBURETOR WAS REMOVED AND SUBMITTED TO REPAIR STATION (FK3R504L) FOR TROUBLESHOOTING AND/OR OVERHAUL. SHOP FOUND THE FLOAT ASSEMBLY PIVOT TAB (WHERE FLOAT IS ANCHORED WITHIN THE CARBURETOR HOUSING) WAS WORN DOWN. ON SHUTDOWN THE FLOAT'S MOVABLE "TAB" WOULD NOT LEVER THE NEEDLE VALVE TO THE FULLY-CLOSED POSITION ALLOWING FUEL TO BYPASS IT INTO THE VENTURI AND TRICKLE OUT OF THE AIRBOX. RECORDS (FROM CBIR054K) SUGGEST THIS FLOAT WAS NOT REPLACED AT ITS PREVIOUS OVERHAUL, 9 DEC 94. WHILE CARBURETOR HAD ACCUMULATED 1382 HOURS SINCE OVERHAUL IT APPEARS ITS FLOAT DEVICE HAD ACCUMULATED 3063 HOURS. 1H71 3O3 ONT3A13 E273 20020514000322002051400032 2002 5 14 2002FA0000634 420020513G3452 COAX PIPER PA28 PA28181 7102807SO TRANSPONDER WRONG PART B K NONE W INADEQUATE Q C ININSP/MAINT 1 GL19 2592 2843150 DISCOVERED INCORRECT COAX USED IN FACTORY INSTALLATION OF ATCRBS TRANSPODNER SYSTEM. COAX INSTALLED IN AIRCRAFT OF TYPE NOT APPROVED BY EQUIPMENT MANUFACTURER. THIS LEAD TO TRANSPONDER SYSTEM FAILURE. 1L71 3O 2A13 20020514000332002051400033CE 2002 5 14 2002FA0000635 120020503G321365412045 STUD CESSNA500 550 2076604CE RT MLG STRUT BROKEN E K NONE O OTHER ININSP/MAINT 1 EA2387SF 3673 3673 5500096 DURING SCHEDULED REPLACEMENT OF THE MLG STRUT CYLINDERS, THE HYD ACTUATOR ATTACH STUD WAS BEING REMOVED FOR RE-USE. UPON APPLYING A TENSION LOAD ON THE STUD TO REMOVE IT, PER MM, THE STUD SEPARATED ALONG THE THREADS WELL BELOW THE MAX TORQUE LIMIT, THE CRACK BEGAN APPROX 1 THREAD UP FROM THE BASE AND EXTENDED UP THREE THREADS, STOPPING APPROX 1 THREAD BEFORE THE COTTER PIN HOLE. EXAMINATION REVEALED THAT THE FRACTURE HAD EXISTED FOR SOME TIME AND THAT IT EXTENDED THROUGH APPROXIMATELY 80 PERCENT OF THE STUD. THE POINT AT WHICH THE FRACTURE BEGAN IS THE SAME POINT AT WHICH THE NUT CONTACTS THE ROD END. 1L72 4F A22CE 20020515001372002051500137CE 2002 5 15 2002FA0000636 120020411G3320 BATTERY PACK CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE CABIN MISREPAIRED B JGVRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW09825JW 5500266 BATTERY HAS BEEN REPAIRED WITH NON-PMAD CELLS. 1L72 4F4 F A22CE E1NE 20020515001382002051500138SW 2002 5 15 2002FA0000637 120020422G5711 SPAR BBAVIA7 7EC 2110120SW CONT C90 C90* 17009SO RIGHT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SW994351C 370 IN COMPLYING WITH AD, FOUND CRACK AT BUTT OF MAIN SPAR JUST UNDER ATTACH FITTING TO FUSELAGE ON RIGHT WING TRAVELING SEVERAL INCHES LONGITUDINALLY. SEVERAL RIB NAILS LOOSE ON BOTH WINGS. AIRCRAFT HANGARED-CAUSE UNKNOWN, (HOURS ON WINGS 5000 TO 6000), REPAIR OF WINGS REQUIRED. 1H71 3O3 O A759 E252 20020515001432002051500143EA 2002 5 15 2002FA0000639 120020429G2913887138 BEARING VICKERS CNDAIRCL600 CL6002B19 1900309EA HYD PUMP FAILED B K NONE O OTHER ININSP/MAINT 1 WP27 MV595355 BEARING WAS FOUND IN PIECES. INNER RACE OF BEARING STILL ATTACHED TO ROTOR LINER. NO LUBRICANT VISIBLE. 2L72 4F RTA21EA 20020515001442002051500144CE 2002 5 15 2002FA0000641 120020423G7603363800843 CONTROL CABLE BEECH 36 A36 1151604CE CONT O550 IO550B SO THROTTLE FAILED G K NONE O OTHER ININSP/MAINT 1 SW014151Q6088 E2679 END OF THROTTLE CABLE CAME APART A SURAGE. 1L71 3O3 O 3A15 E3SO 20020515000012002051500001SW 2002 5 15 2002FA0000642 120020514G2731550000151 CONTROL CABLE GULSTM500 500B 0141106SW ELEVATOR TRIM BROKEN D O OTHER F FLT CONT AFFECTED APAPPROACH 1 SO1124KM 8150 500B129611 ELEVATOR TRIM CABLE BROKE WHILE ON APPROACH. CABLE BROKE WHERE IT WRAPPED AROUND AN AUTOPILOT TRIM ACTUATOR THAT HAD BEEN DEACTIVATED. CORRECTIVE ACTION WAS TO REMOVE THE OLD TRIM ACTUATOR AND REPLACE ALL 4 ELEVATOR TRIM CABLES. AS A PRECAUTION ALSO REPLACED THE RUDDER TRIM CABLES. 1H72 3O 6A1 20020516000012002051600001CE 2002 5 16 2002FA0000645 120020411G5521 SPAR BEECH 90 E90 1152914CE PWA PT6 PT6A60A 52043NE ELEVATOR CRACKED D K NONE O OTHER ININSP/MAINT 1 SW99355JS LW257 END RIB CRACKED SEVERAL PLACES. FORWARD SPAR, INBOARD END CRACKED. 1L72 3T4 T 3A20 E4EA 20020516000022002051600002EA 2002 5 16 2002FA0000646 220020225G8500 BEARING MOONEYM20 M20M 5870222SW LYC 0540 TIO540AF1B 41532EA ENGINE FAILED D GJASK NONE O OTHER ININSP/MAINT 1 NM01355RZ 270235 L982961 DURING REGULARLY SCHEDULED OIL CHANGE AT 399.5 HRS, UPON EXAM OF OIL FILTER, METAL CONTAMINATES WERE DISCOVERED IN THE ELEMENT FOLDS. CONTACTED MFG, ADVISED THERE WAS A SERVICE INSTRUCTION THAT PERTAINED TO THIS ENGINE THAT OUTLINES INSPECTION PROCEDURE FOR OIL FILTER/OIL SCREEN DEBRIS INSPECTION. WE HAD WASHED THE FILTER CONTAMINATES INTO A CLEAN COFFEE FILTER. AFTER PULLING THE PICK UP SCREEN FROM THE BOTTOM OF THE OIL SUMP. WE DISCOVERED A LARGER AMOUNT OF DEBRIS IN THE SCREEN. OIL SAMPLE INITINITALLY TAKEN FROM OIL SUMP. CAME BACK STATING THAT MATERIAL FROM SAMPLES SENT WERE BEARINGMATERIAL FROM ROD, MAIN OR NOSE BEARINGS. SENT ENGINE BACK TO MFG. FOR WARRANTY AND REPAIR. 1L71 3O3 ORT2A3 E14EA 20020516000032002051600003CE 2002 5 16 2002FA0000647 120020426G2510551900921 SEAT BACK CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 CE05196JS 5500196 UPPER SEAT BASE ASSEMBLY CRACKED AT SEAT BACK ATTACH POINTS. STRESS ON SEAT BACK AND METAL FATIGUE PROBABLE CAUSE. SEAT WAS REPAIRED. 1L72 4F4 F A22CE E1NE 20020516000042002051600004SW 2002 5 16 2002FA0000649 120020430G5711S147 SPAR BBAVIA7 7AC 2110102SW LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 EA27838514379 7AC2257 LEFT WING REAR SPAR COMPRESSION CRACK AT STRUT ATTACH POINT BETWEEN DOUBLER ON UPPER SURFACE. 1H71 3O A759 20020517000012002051700001CE 2002 5 17 2002FA0000652 120020425G329732600101 WIRE CESSNA500 560CESSNA 2076750CE MLG MISINSTALLED D A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 NM09398RS 5605009 LANDING GEAR SELECTED. UNLOCK LIGHT ON, RT MAIN GEAR, NOT LOCKED. CREW DID THE CHECKLIST, BLEW GEAR, ABOVE CONDITION REMAINED. CREW DECLARED EMERGENCY AND HAD TO LAND WITH GEAR UNSAFE. MAINTENANCE TRACED PROBLEM TO A BAD GROUND WIRING. THIS WIRE TERMINATED IN THE RIGHT FLAP WELL. AS FLAPS ARE LOWERED THE AIR LOADS VIBRATE THE VERY SMALL 22 GAGE WIRE UNTIL IT BREAKS AT THE ATTACHING TERMINAL. THE TIE WRAP ATTACH POINT WAS INCORRECTLY INSTALLED AND THIS WIRE WAS NOT EVEN SECURED AT MANUFACTURER. SECURED THE WIRE TIE WRAP AND ITS ATTACH POINT CORRECTLY AND PROSEALED ALL WIRES TO THE ADJOINING SHEETMETAL SO THAT IT CANNOT (FLAP IN THE BREEZE). 2L72 4F RTA22CE 20020517000022002051700002SO 2002 5 17 2002FA0000653 120020429G716086245834 AIR BOX PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENG CARBURETOR CRACKED D K NONE O OTHER ININSP/MAINT 1 SW15355AB 4496093 DURING 100 HOUR INSPECTION, TECH FOUND RIGHT AND LEFT ENGINE CARBURETOR HEAT AIRBOXES CRACKED. RIGHT AIRBOX WAS CRACKED AT HOT AIR INLET, LOCATED AT THE POINT WHERE TUBE IS WELDED TO AIRBOX AND EXTENDING HALFWAY AROUND THE TUBE. LEFT AIRBOX WAS CRACKED AT THE COLD AIR INLET AND EXTENDED ALMOST ALL THE WAY AROUND THE TUBE, RESULTING IN ALMOST COMPLETE SEPARATION OF THE TUBE FROM AIRBOX. CAUSE: MAY BE POOR DESIGN OF AIRBOX, WEAK WELDS AT BOTH HOT AND COLD AIR TUBES. 1L72 3O3 O A19S0 E286 20020517000032002051700003EA 2002 5 17 2002FA0000654 220020501G8520SL13S19646 GEAR PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA CRANKSHAFT MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM104640R 2821393 L2415627A FOUND CRANKSHAFT GEAR TO HAVE ITS TIMING MARK OFF BY ONE TOOTH. FAA INSPECTOR NOTE: MECHANIC SAID ENGINE WOULD NOT DEVELOP FULL POWER. 1L71 3O3 O 2A13 E274 20020523000062002052300006SO 2002 5 23 2002FA0000655 220020503G8550B1119M SEPARATOR BEECH 35 E35 1151512CE CONT E225 E225* 17015SO AIR/OIL LEAKING B MI3RK NONE O OTHER ININSP/MAINT 1 NM093311C1291 D3977 40150D DURING ENGINE RUNUP OIL WAS OBSERVED LEAKING FROM SEPARATOR LOWER OUTBOARD CORNER. INSPECTION REVEALED SEPRATOR CORRODING/ RUSTING FROM INSIDE OUT. OIL LEAKING THROUGH CORROSION PINTS IN BOTTOM ONTO EXHAUST. REPLACED WITH NEW UNIT. RECOMMEND INSPECTION AT EACH ANNUAL INSPECTION. 1L71 3O3 O A777 E267 20020523000072002052300007CE 2002 5 23 2002FA0000656 120020508G7130 INSULATOR CESSNA421 421C 2076016CE CONT O520 GTSIO520C 17032SO NACELLES BURNED D K NONE O OTHER ININSP/MAINT 1 WP09241MW4789 421C0030 610478 ON REPLACING LEFT WING LOCKER FUEL CELL, DISCOVERED (PN 5656006-2), FIREWALL FIRE SCREEN COATING BURNED THROUGH BEHIND TURBOCHARGER. REMOVED RIGHT NACELLE TOP SKIN AND DISCOVERED OTHER (PN 5656006-2) FIREWALL FIRE SCREEN IN SIMILAR CONDITION. INSTALLED NEW SCREENS, BOTH NACELLES. 1L72 3O3 O A7CE E7CE 20020523000082002052300008CE 2002 5 23 2002FA0000657 120020513G2751503800135 INDICATOR BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO TE FLAPS INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07 THIS IS NEW FROM STOCK AND WAS JUST ORDER FROM MFG. WAS INSTALLED AND THE METER MOVEMENT WAS ONLY .5 OF THE TRAVEL. PART WAS REMOVED AND TESTED ON THE BENCH AND HAD A HIGH AMP DRAW. 1L71 3O3 O 3A15 E5CE 20020523000092002052300009SO 2002 5 23 2002FA0000658 120020429G716086245834 AIR BOX PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA CARB HEAT CRACKED D K NONE O OTHER ININSP/MAINT 1 SW15355AB323 4496093 DURING 100 HOUR INSPECTION, TECHNICIAN FOUND BOTH RIGHT AND LEFT ENGINE CARBUETOR HEAT AIRBOXES CRACKED. THE RIGHT AIRBOX WAS CRACKED AT THE HOT AIR INLET, LOCATED AT THE POINT WHERE TUBE IS WELDED TO AIRBOX AND EXTENDING HALFWAY AROUND THE TUBE. THE ALMOST ALL THE WAY AROUND THE TUBE, RESULTING IN ALMOST COMPLETE SEPARATION OF THE TUBE FROM THE AIRBOX. A POSSIBLE BOTH COLD AND HOT AIR TUBES. 1L72 3O3 O A19S0 E286 20020523000012002052300001CE 2002 5 23 2002FA0000659 120020516G270105117821 YOKE CESSNA172 172M 2072418CE COCKPIT CORRODED D K NONE O OTHER ININSP/MAINT 1 SO134574V6493 17266358 UPON COMPLETION OF THE INITIAL INSPECTION FOR SEB01-3,THE CONTROL YOKE WAS FOUND TO BE INTERNALLY CORRODED. ULTRASONIC INSPECTION REVEALED WALL THICKNESS DETERIORATION TO LESS THAN 0.030 INCH. 1H71 3O NT3A12 20020523000022002052300002GL 2002 5 23 2002FA0000660 120020510G551081611 TERMINAL AVIAT A1 A1A 2210405GL HORIZONTAL BROKEN C K NONE O OTHER ININSP/MAINT 1 SW05478DM420 1450 LEFT LOWER FORWARD TAIL STRUT THREADED ROD DISCOVERED BROKEN ON PREFLIGHT. (NO ADVERSE FLIGHT CHARACTERISTICS NOTED ON PREVIOUS FLIGHT.) ROD BROKEN AT END OF 5/16 INCH X 24 THREADS NEXT TO 5/16 INCH HEX SHAFT. 1H71 3O NCA22NM 20020523000032002052300003CE 2002 5 23 2002FA0000661 120020521G575145135031139 SKIN BEECH 95 95B55 1152729CE LT AILERON CRACKED D K NONE O OTHER ININSP/MAINT 1 WP13161DP3128 TC2151 AILERON SKIN CRACKS OBSERVED PROPAGATING LATERALLY IN UPPER AND LOWER AREAS FOWARD OF SPAR AND AFT OF BALLANCE WEIGHTS. 1L72 3O RT3A16 20020523000052002052300005GL 2002 5 23 2002FA0000662 220020521G72604252071 MAGNETIC SEAL CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL ACCESSORY G/B WORN D O OTHER J WARNING INDICATION CRCRUISE 1 NM09551AM460 7500155 300329 CREW RECEIVED ENGINE CHIP-L CAS MESSAGE. AIRCRAFT LANDED AT DESTINATION. MAGNETIC INDICATOR PLUG INSPECTED AND SINGLE SLIVER FOUND. 3RD INCIDENT OF THIS NATURE ON THIS ENGINE. ANALYSIS BY ROLL-ROYCE ON 2ND INCIDENT SLIVER SHOWED STAINLESS 410 ALLOY. FOUND WAVE SPRING AND MAGNETIC SEAL BADLY WORN. 2L72 4J4 FRTT00007WITE6CH 20020523001042002052300104GL 2002 5 23 2002FA0000663 220020425G723023031938 TURBINE WHEEL ALLSN 250C 250C20B 03013GL ENGINE DESTROYED B YKERK NONE O OTHER ININSP/MAINT 1 EA17 163 TURBINE WAS RECEIVED FOR REPAIR DUE TO N1 LOCK-UP. UPON DISASSEMBLY FOUND THAT THE DIAPHRAGM HAD SEPARATED FROM THE CASTING AND WAS REDUCED TO SEVERAL SMALL PIECES. ALSO FOUND THE FIRST AND SECOND STAGE TURBINE WHEELS HAD SUSTAINED SEVERE DAMAGED DUE TO CONTACT WITH THE DIAPHRAGM. THE WHEELS WERE SCRAPPED. 3 U E4CE 20020523001062002052300106SO 2002 5 23 2002FA0000666 120020501G553266975 SKIN PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA VERTICAL STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 GL235613614077 287305538 VERTICAL STABILIZER - ON BOTTOM TRAILING EDGE OF VERTICAL STABILIZER. THE SKIN APPEARED TORN, UPON REMOVAL OF RUDDER. THE STRUCTURE INSIDE THE VERTICAL STABILIZER APPEARED TO HAVE FATIGUE AND WAS CRACKED TO MIDPOINT OF VERTICAL WIDTH. NO DAMAGE TO RUDDER. 1L71 3O3 O 2A13 E286 20020523001032002052300103CE 2002 5 23 2002FA0000667 120020523G2400W31X2M1G50 MASTER SWITCH CESSNA175 175 2072502CE INSTRUMENT PANELFAILED E D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 SW017535M2947 55835 WHILE TAXING FOR DEPARTURE AT TAOS AIRPORT. THE PILOT EXPERIENCED AN AVIONICS MASTER SWITCH FAILURE. UPON SEEING A SMALL AMOUNT OF SMOKE AT THE UPPER AREA OF THE INSTRUMENT PANEL THE PILOT IMMEDIATELY SHUT DOWN THE AIRCRAFT AND TAXIED BACK TO THE FBO 1H71 3O NT3A17 20020606000062002060600006CE 2002 6 6 2002FA0000668 120020222G551004320049 BRACKET CESSNA150 152 2071835CE LYC O235 O235* 41505EA HORIZ STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 AL034878714000 15280967 WHILE INSPECTING THE NUTPLATES IAW AD. WE FOUND THAT THE FORWARD UPPER WELD JOINT HAD CRACKED ADJACENT TO THE NUTPLATES THEMSELVES. THIS AIRCRAFT IS OPERATED IN A TRAINING ENVIRONMENT AND IS SUBJECTED TO A LOT OF ABRUPT MANEUVERS INCLUDING SPINS. DUE TO THE LOCATION OF THE CRACKS, MORE EMPHASIS SHOULD BE PLACED ON INSPECTING THE ENTIRE BRACKET AND NOT JUST THE NUTPLATES, ESPECIALLY AIRCRAFT THAT HAVE HAD THE NUT PLATES REMOVED TO DO AWAY WITH THE AD INSPECTION. 1H71 3O3 ONT3A19 E223 20020606000102002060600010CE 2002 6 6 2002FA0000669 120020414G7921635996 OIL COOLER CESSNA310 310R 2074245CE ENGINE DAMAGED D K NONE O OTHER ININSP/MAINT 1 SW05 THE LISTED OIL COOLER WAS OVERHAULED. PROBLEM: THE THREADS FOR THE OIL TEMP PROBE WAS 40 PERCENT DESTROYED OR GONE. THIS AREA WAS NOT INSPECTED OR OVERLOOKED, WAS NOT POSSIBLE TO INSTALL OIL TEMP PROBE. RETURNED OIL COOLER TO OVERHAUL COMPANY. 1L72 3O 3A10 20020606000112002060600011SO 2002 6 6 2002FA0000670 220020419G74146310 MAGNETO BEECH 36 A36 1151604CE CONT O550 IO550B SO LEFT SHORTED G K NONE O OTHER ININSP/MAINT 1 WP17810NH1347 E2819 DURING ROUTINE INSPECTION WHITE POWDER WAS NOTICED AT LEFT MAGNETO VENT. REMOVED MAGNETO FOR INTERNAL INSPECTION AND FOUND COIL HAD SHORTED OUT, ARCING AND MELTING DISTRIBUTOR BLOCK AND GEAR ASSEMBLY. INSTALLED NEW MAGNETO ASSEMBLY. 1L71 3O3 O 3A15 E3SO 20020606000122002060600012CE 2002 6 6 2002FA0000671 120020225G551004320049 BRACKET CESSNA150 152 2071835CE LYC O235 O235* 41505EA HORIZ STAB CRACKED G K NONE O OTHER ININSP/MAINT 1 AL03757GQ10000 15279732 WHILE INSPECTING THE NUTPLATES IAW AD, WE FOUND THAT THE FORWARD UPPER WELD JOINT HAD CRACKED ADJACENT TO THE NUTPLATES THEMSELVES. THIS AIRCRAFT IS OPERATED IN A TRAINING ENVIRONMENT AND IS SUBJECTED TO A LOT OF ABRUPT MANEUVERS INCLUDING SPINS. DUE TO THE LOCATION OF THE CRACKS, MORE EMPHASIS SHOULD BE PLACED ON INSPECTING THE ENTIRE BRACKET AND NOT JUST THE NUTPLATES, ESPECIALLY AIRCRAFT THAT HAVE HAD THE NUTPLATES REMOVED TO DO AWAY WITH THE AD INSPECTION. 1H71 3O3 ONT3A19 E223 20020606000132002060600013 2002 6 6 2002FA0000672 420020409G2350S28701 SWITCH CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA COCKPIT FAILED B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA0735331 17281037 REPLACED PILOTS PUSH TO TALK SWITCH. 0510.2 TACH. 1H71 3O3 ONT3A12 1E10 20020606000142002060600014 2002 6 6 2002FA0000673 420020409G2350S28701 SWITCH CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA COCKPIT INOPERATIVE B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA0735331510 17281037 REPLACED COPILOTS PUSH TO TALK SWITCH. 1H71 3O3 ONT3A12 1E10 20020606000152002060600015 2002 6 6 2002FA0000674 420020415G2350S28701 SWITCH CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA COCKPIT INOPERATIVE B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA0735331517 17281037 HAD TO REPLACE THE PILOTS PUSH TO TALK SWITCH. 1H71 3O3 ONT3A12 1E10 20020606000162002060600016 2002 6 6 2002FA0000675 420020402G2561FV353500101 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED, MFG RECOMMENDED CELL PRESSURE TEST. 20020606000202002060600020EA 2002 6 6 2002FA0000676 220020502G8550MS913401 GASKET CESSNA206 206CESSNA 2073302CE LYC O540 TIO540AJ1A EA ENGINE LEAKING G O OTHER O OTHER UKUNKNOWN 1 EA07206YK328 T20608125 L1034661A GASKET FAILED CAUSING LOSS OF ENGINE OIL LEADING TO CATASTROPHIC ENGINE FAILURE. AIRCRAFT LANDED SAFELY IN FIELD. THERE IS NO REQUIREMENT TO GO BACK AND REPLACE THESE GASKETS. 1H71 3O3 O A4CE E14EA 20020606000242002060600024SO 2002 6 6 2002FA0000677 120020501G1430 RIVET PIPER PA34 PA34200T 7103406SO HORIZ STAB LOOSE G K NONE O OTHER ININSP/MAINT 1 GL232849P2780 347970280 ON BOTH LEFT AND RIGHT STABILIZER TRIM SURFACES THE RIVETS HOLDING THE BRACKET FOR THE TRIM PUSH RODS WHERE LOOSE IN THE EXISTING HOLES. 1L72 3O A7SO 20020529000652002052900065CE 2002 5 29 2002FA0000678 120020528G29106207023202 HYDRAULIC LINE CESSNA650 650 2076802CE HYD SYSTEM CRACKED G K NONE K FLUID LOSS ININSP/MAINT 1 SW093184Z 6500032 LINE WAS CRACKED BEHIND AN ADEL CLAMP. MINOR PITTING AND CORROSION WAS EVIDENT ONCE CLAMP WAS REMOVED FROM LINE. LINE HAD BEEN PREVIOUSLY REPLACED ON 01/02. TWO OTHER HYDRAULIC LINES, P/N 6207023-154 AND 6207021-152 WERE REMOVED AND FOUND TO HAVE SIMILAR CORROSION AND PITTING. 2L72 4F A9NM 20020612001202002061200120SO 2002 6 12 2002FA0000679 120020510G2450W58X10095 CIRCUIT BREAKER PIPER PA28 PA28161 7102803SO ELECTRICAL SYS FAILED B SL5RK NONE O OTHER ININSP/MAINT 1 NE038179G7620 288016297 AIRCRAFT WAS NOT USED FOR APPROXIMATELY (7) MONTHS. AIRCRAFT WAS TIED DOWN OUTSIDE, NEAR SALT WATER ENVIRONMENT. NEW OWNER HAD ANNUAL INSPECTION DONE. DURING ANNUAL INSPECTION FOUND CORROSION ON BELLY HAT SECTION STIFFENER. NO OTHER UNUSUAL CORROSION NOTED. AFTER ANNUAL INSPECTION ELECTRICAL EQUIPMENT BEGAN TO FAIL THAT WAS WORKING DURING ANNUAL INSPECTION. RADIO , LIGHTS, T AND B, AUTO PILOT AND SMU WARNING. FOUND CIRCUIT BREAKERS DEFECTIVE FOR EACH OF THESE CIRCUITS. 1L71 3O 2A13 20020612001212002061200121SO 2002 6 12 2002FA0000681 220020417G8530 EXHAUST VALVE PIPER PA28 PA28151 7102805SO CONT O550 IO550B SO ENGINE DAMAGED B O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 GL03322461045 287515103 675942 NR 2 EXHAUST VALVE HEAD MISSING A SECTION (OVERHEATED AND TORCHED AWAY). TRACED TO EXCESSIVE VALVE STEM/GUIDE CLEARANCE. ALL OTHER CYLINDERS WERE REMOVED AND REPORTED TO HAVE EXCESSIVE WEAR, REQUIRING VALVE AND GUIDE REPLACEMENT. 655 HOURS SHORT OF TBO. PLANE WAS 2 MONTHS SINCE LAST ANNUAL AND AT THAT TIME STATIC COMPRESSIONS WERE WITHIN LIMITS. 1L71 3O3 O 2A13 E3SO 20020612001322002061200132SO 2002 6 12 2002FA0000682 120020515G3010474142 VALVE PIPER PA46 PA46310P 7104605SO DEICE SYS BROKEN B BNGRO OTHER O OTHER NRNOT REPORTED 1 GL19251203975 468508097 DE-ICE BOOTS INOPERATIVE, FOUND AIRBORN MANIFOLD VALVE BROKEN IN TWO. 1L71 3O RTA25SO 20020619002312002061900231CE 2002 6 19 2002FA0000683 120020523G2434632050 BUSHING CESSNA172 R172K 2072431CE CONT O360 IO360K 17025SO ALTERNATOR WORN B BNGRK NONE O OTHER ININSP/MAINT 1 GL193712V1205 R1722261 ENGINE DRIVEN ALTENATOR DRIVE FOUND WORN. 1H71 3O3 O 3A17 E1CE 20020619002322002061900232SO 2002 6 19 2002FA0000684 120020506G3230AN2321A BOLT PIPER PA28 PA28R201 7102816SO CLEVIS FAILED B UC2RK NONE O OTHER ININSP/MAINT 1 GL195321U820 2844042 DURING CLIMB OUT, THE PILOT HEARD A LOUD BANG. WHEN THE LANDING GEAR WAS RETRACTED, THE PILOT REPORTED THAT THE NOSE GEAR DOWN AND LOCKED LIGHT ILLUMINATED A FEW SECONDS LATER. THE LANDING GEAR WAS EXTENDED BY THE PILOT AND A SAFE LANDING WAS MADE. A POST FLIGHT INSPECTION FOUND THAT THE CLEVIS BOLT THAT ATTACHES THE NOSE GEAR ACTUATOR TO THE NOSE GEAR DOWNLOCK ASSEMBLY TO BE SHEARED OFF. THE DOWNLOCK ASSEMBLY PARTIALLY DAMAGED WHEN THE BOLT DEPARTED. THE BOLT AND DOWNLOCK ASSEMBLY WERE REPLACED AND THE AIRPLANE WAS PUT BACK INTO SERVICE. RECOMMEND REMOVING THE CLEVIS BOLT AND INSPECTING EVERY 100 HOURS. 1L71 3O 2A13 20020619002332002061900233GL 2002 6 19 2002FA0000685 220020515G725023031938 NOZZLE ALLSN 250C 250C20B 03013GL TURBINE DETACHED B TU3RA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 WP07CCCMV3803 CAE840678 A FOREIGN OPERATOR REPORTED A SUDDEN LOSS OF POWER IN-FLIGHT WITH NOISE FROM IDLE TO SHUTDOWN. THE TURBINE ASSEMBLY WAS REMOVED AND RETURNED TO THE US REPAIR FACILITY THAT PERFORMED THE LAST OVERHAUL. THE NR 1 SECTION MADE NOISE WHILE TURNING BY HAD AFTER TURBINE WAS REMOVED FROM THE ENGINE. AT DISASSEMBLY, IT WAS NOTED THAT THE NR 2 NOZZLE DIAPHRAGM BRAZE JOINT WAS COMPLETELY GONE, ALLOWING THE DIAPHRAGM TO DETACH AND MOVE INTO NR 1 AND NR 2 TURBINE WHEELS. SEPARATION OF THE DIAPHRAGM FROM THE NOZZLE INNER BAND DOES NOT ALLOW PROPER AIRFLOW THROUGH THE NOZZLE VANES. THIS FAILURE OF THE BRAZE JOINT CAUSED EXTENSIVE DAMAGE THOUGHT THE TURBINE ASSEMBLY, INCLUDING REPLACEMENT OF NR 1 AND NR 2 TURBINE WHEELS. 3 U E4CE 20020619002342002061900234CE 2002 6 19 2002FA0000686 120020404G3220124340216 TRUNNION CESSNA210 T210N 2073456CE CONT O520 TSIO520R 17040SO NLG COLLAPSED B JZRRK NONE O OTHER ININSP/MAINT 1 EA075132C3437 21063708 293952R WHILE RETRIEVING AIRCRAFT FROM NOSE GEAR COLLAPSE, FOUND LOWER TRUNNION ASSEMBLY. BROKEN AT AFT SIDE WHERE COLLAR WRAPS AROUND GEAR. APPEARS THERE WERE CRACKS AT LEFT AND RIGHT TOP CORNERS JUST FORWARD OF THE BRACE SUPPORT MOUNTS. THEY ARE IN A VERY DIFFICULT AREA TO SEE. 1H71 3O3 O 3A21 E8CE 20020619002352002061900235CE 2002 6 19 2002FA0000687 120020507G7160BA7210 FILTER BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO INDUCTION SYS CRACKED B CGORK NONE O OTHER ININSP/MAINT 1 GL037RQ CE1622 DURING INSPECTION OF BRACKET ENGINE INDUCTION AIR FILTER FRAME ASSEMBLY FOUND THE (STEEL) SCREEN CRACKED AND SECTIONS MISSING NEAR THE RIVET RETAINING AREAS. SEE BRACKET AIR FILTER DOCUMENT. 1L71 3O3 O 3A15 E5CE 20020619002362002061900236SO 2002 6 19 2002FA0000688 120020503G551143001083 RIB PIPER PA22 PA22 7102202SO LYC O290 O290 41506EA HORIZONTAL STAB CRACKED B MV5RK NONE O OTHER ININSP/MAINT 1 GL11690A 4756 2293 RT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE. (MV5R055N) 1H71 3O3 O 1A6 E229 20020619002372002061900237SO 2002 6 19 2002FA0000689 120020503G551143001077 RIB PIPER PA22 PA22 7102202SO LYC O290 O290 41506EA HORIZONTAL STAB CRACKED B MV5RK NONE O OTHER ININSP/MAINT 1 GL11690A 4756 2293 RIGHT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE. (MV5R055N) 1H71 3O3 O 1A6 E229 20020603000052002060300005NE 2002 6 3 2002FA0000690 220020522G7250 TURBINE AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE73121C NE NR 1 ENGINE DAMAGED E EA ENGINE SHUTDOWN UNSCHED LANDING MR OVER TEMP PARTIAL RPM/PWR LOSS CLCLIMB 1 EA2377SF 141 P73394 AFTER TAKEOFF AND DURING CLIMBOUT, THE PILOT EXPERIENCED A COMPUTER GENERATED AUTOMATIC ROLL BACK OF POWER ON THE NR 1 ENGINE. THE NR 2 ENGINE WAS BROUGHT BACK TO A MATCHING POWER SETTING. IT WAS THEN NOTICED THAT THE NR 1 ENGINE ITT WAS MORE THAN 100 DEGREES HIGHER THAN THE NR 2 ENGINE. THE NR 1 ENGINE WAS SHUT DOWN AS A PRECAUTIONARY MEASURE, AND AN UNEVENTFUL LANDING WAS MADE. AFTER SEVERAL GROUND MAINTENANCE RUNS FOR TROUBLESHOOTING, IT WAS DETERMINED THAT SEVERE HOT SECTION DISTRESS HAD OCCURRED. THE ENGINE WAS REMOVED FOR REPAIR. CAUSE OF PROBLEM UNKNOWN. 2L72 4F4 F A33EU E6WE 20020619002382002061900238SO 2002 6 19 2002FA0000691 120020503G551143001081 RIB PIPER PA22 PA22 7102202SO LYC O290 O290* 41506EA HORIZONTAL STAB CRACKED B MV5RK NONE O OTHER ININSP/MAINT 1 GL11690A 4756 2293 RIGHT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE. (MV5R055N) 1H71 3O3 O 1A6 E229 20020619002392002061900239SO 2002 6 19 2002FA0000692 120020503G551143001079 RIB PIPER PA22 PA22 7102202SO LYC O290 O290* 41506EA HORIZONTAL STAB CRACKED B MV5RK NONE O OTHER ININSP/MAINT 1 GL11690A 4756 2293 RIGHT HORIZONTAL STABILIZER RIB CRACKED. RIB LOCATED AT LEADING EDGE. 1H71 3O3 O 1A6 E229 20020619002402002061900240SO 2002 6 19 2002FA0000695 220020513G8520633620 CRANKSHAFT BEECH 58 58TCA 1152747CE CONT O520 TSIO520L 17040SO ENGINE SHEARED D K NONE O OTHER ININSP/MAINT 1 GL19942CP800 TK61 227658R AIRCRAFT LANDED WITH RIGHT ENGINE FEATHERED. REMOVED COWLING TO INVESTIGATE ENGINE STOPPAGE REMOVED TOP SPARK PLUGS, FOUND WHEN TURNING PROPELLER THAT IT WOULD ONLY MOVE ONE REVOLUTION THEN LOCKUP. WHEN LOOKING IN CYLINDERS ONLY FRONT TWO, NR 5 AND NR 6 PISTONS WERE MOVING. NOTIFIED OWNER THAT CRACKSHAFT APPEARED TO BE BROKEN. BY CRANKSHAFT CHEEK NR 7. 1L72 3O3 O A23CE E8CE 20020619002412002061900241CE 2002 6 19 2002FA0000696 120020322G561010138402521 WINDSHIELD BEECH B300 B300 1159232CE PWA PT6 PT6A11 52043NE COCKPIT FAILED C BA EMER. DESCENT UNSCHED LANDING O OTHER CRCRUISE 1 SW15350WH1395 FL210 WAS AT FL 280 WHEN LOUD POP WAS HEARD AND SAW THE PILOT FRONT WINDSHIELD WAS SHATTERED. INITIATED AND EMERGENCY DESCENT AND LANDED AT AIRPORT FOR REPAIRS. 2L72 4T3 TRTA24CE E4EA 20020619002422002061900242CE 2002 6 19 2002FA0000697 120020513G282305131206 SELECTOR VALVE CESSNA172 172D 2072410CE CONT O300 O300* 17022SO COCKPIT MISINSTALLED D K NONE O OTHER ININSP/MAINT 1 SO012538U 17250138 SPRING WAS INSTALLED BACKWARD. FUEL WOULD NOT SHUT OFF LEFT TANK. TO PREVENT RECURRENCE VALVE SHOULD BE INSPECTED AFTER OVERHAUL. 1H71 3O3 ONT3A12 E253 20020619002432002061900243EA 2002 6 19 2002FA0000700 220020515G8520 CAMSHAFT PIPER PA32 PA32300 7103212SO LYC O540 IO540K1G5 41532EA ENGINE WORN B SL5RK NONE O OTHER ININSP/MAINT 1 NE0338996495 327740104 L1558148A DURING NORMAL INSPECTION, FOUND FERROUS METAL SLIVERS IN OIL FILTER, FUTHER INSPECTION BY REMOVING NR 1 AND NR 3 CYLINDER SHOWED, METAL IMBEDED IN PISTON SKIRTS, AND CAM LOBE SHAIRED BY NR 3 CYLINDER INTAKE AND NR 4 CYL EXHAUST SEVERELY WORN AND PITTED AND CAM FOLLOWERS PITTED. THIS IS THE 2ND OCCURRENCE OF A PREMATURE CAM LOBE FAILURE FOUND IN A 12 MONTH PERIOD. REMOVAL NR 1 CYLINDER FOR REPAIRS FOR HIGH OIL CONSUMPTION, FOUND NR 3 CYLINDER INTAKE CAM LOBE SEVERLY WORN. 1L71 3O3 O A3SO 1E4 20020620000022002062000002CE 2002 6 20 2002FA0000701 120020516G57510322709032270 BRACKET CESSNA195 195A 2073110CE JACOBSR755 R7557 35003EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE031532D 7754 THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE. THE ORIGINAL ALUMINUM PAINT ALONG WITH TODAYS MODERN URETHANES ARE CONCEALING THE MAGNITUDE OF THIS PROBLEM. APPROX 80 PERCENT OF THE BRACKETS WE HAVE INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. THEN THERE IS THE PROBLEM OF CORROSION BETWEEN THE BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. THE SEPERATION OF THE AILERON FROM THE REAR WING SPAR WHILE STILL ATTACHED TO THE STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS. BEAD BLAST BODY WHILE PROTECTING THE BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE THE CORROSION BY PRODUCTS. 1H71 3R3 R A790 5E11 20020611000422002061100042SW 2002 6 11 2002FA0000704 120020508G5320206031202015S SUPPORT BELL 206 206B3 1181506SW FUSELAGE MISMANUFACTURED D ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 SUPPORT, NEW PART. LOCATING NEW PART ON AIRCRAFT. PILOT HOLES MISDRILLED FROM FACTORY. 1G71 3U H2SW 20020611000462002061100046GL 2002 6 11 2002FA0000705 220020513G7210E6898785 GEAR BELL 206 206L 1181522SW ALLSN 250C 250C28B 03013GL PTO GEAR TEETH DAMAGED B ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 (PTO GEAR) UPON VISUAL INSPECTION OF PART AFTER BEING CHECKED OUT OF STOCK. DAMAGE TO 4 EA SMALL GEAR TEETH AND 1 EACH TOOTH HAS ARC LIKE RECESSED AREA. 1G71 3U3 U H2SW E1GL 20020611000472002061100047GL 2002 6 11 2002FA0000706 220020514G721023071895 GEAR BELL 407 407 1182206SW ALLSN 250C 250C47B GL GEARBOX ROUGH B ALGRK NONE O OTHER ININSP/MAINT 1 SO03 (TM GEAR) UPON VISUAL INSPECTION OF PART. FOUND EXTREMELY ROUGH GEAR TEETH EDGES AT RADIUS ON FORWARD TEETH. SENT FOR WARRANTY. 1G71 3U3 UO H2SW E1GL 20020611000482002061100048GL 2002 6 11 2002FA0000707 220020227G721023071895 GEAR BELL 407 407 1182206SW ALLSN 250C 250C47B GL GEARBOX MISMANUFACTURED B ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 (TM GEARS) UPON VISUAL INSPECTION OF NEW PART FROM STOCK. IMPROPER AND UNFINISHED MACHINING ON GEAR TEETH AT RADIUS. 1G71 3U3 UO H2SW E1GL 20020611000492002061100049GL 2002 6 11 2002FA0000708 220020416G721023071896 GEAR BELL 407 407 1182206SW ALLSN 250C 250C47B GL GEARBOX MISMANUFACTURED B ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 UPON VISUAL INSPECTION OF NEW PARTS FROM STOCK, IMPROPER AND UNFINISHED MACHINING AND MESHING OF GEAR TEETH AT RADIUS. 1G71 3U3 UO H2SW E1GL 20020611000502002061100050GL 2002 6 11 2002FA0000709 220020410G721023071896 GEAR BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL GEAR TEETH ROUGH B ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 UPON RECEIVING AND INSPECTION, ROUGH EDGES OF RADIUS OF GEAR TEETH AFT SIDE. 1G71 3U3 U H2SW E1GL 20020620000032002062000003EU 2002 6 20 2002FA0000711 120020531G7820115TA601004 BAFFLE GROB 120 G120A EU NR 3 CYLINDER CRACKED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07862AF218 85002 ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY. 1L71 3O RTA49CE 20020620000042002062000004EU 2002 6 20 2002FA0000712 120020604G7820115TA601003 BAFFLE GROB 120 G120A EU NR 1 CLYINDER CRACKED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07861AF193 85001 ENGINE BAFFLE CRACKED ON NUMBER 1 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. 1L71 3O RTA49CE 20020620000052002062000005EU 2002 6 20 2002FA0000713 120020504G2434115TA6003 SUPPORT BRACKET GROB 120 G120A EU ALTERNATOR CRACKED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07864AF194 85004 ALTERNATOR SUPPORT BRACKET CRACKED. PART REMOVED AND A NEW SUPPORT BRACKET INSTALLED. 1L71 3O RTA49CE 20020620000072002062000007EU 2002 6 20 2002FA0000714 120020604G7820115TA601004 BAFFLE GROB 120 G120A EU ENGINE CRACKED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07861AF193 85001 ENGINE BAFFLE CRACKED ON NUMBER 3 CYLINDER. PART REMOVED AND NEW BAFFLE INSTALLED. PART SENT IN FOR WARRANTY. 1L71 3O RTA49CE 20020620000082002062000008SO 2002 6 20 2002FA0000715 220020606G73226299042 FUEL CONTROL BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO ENGINE INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP078240T CE1542 FLUCTUATION IN FUEL FLOW AND UNABLE TO ADJUST IDLE MIXTURE. THEY FOUND THAT THE MIXTURE CONTROL WAS STIFF WHEN MOVED, (POSSIBLE GALLING). FUEL CONTROL WAS REMOVED AND A NEW ONE INSTALLED, ENGINE WAS TRIMMED, TEST FLIGHT CHECKED NORMAL. FUEL CONTROL WAS SENT IN FOR WARRANTY. 1L71 3O3 O 3A15 E5CE 20020620000092002062000009SO 2002 6 20 2002FA0000716 220020604G73147429322 PUMP BEECH 33 F33A 1151425CE CONT O520 IO520* 17032SO ENGINE DRIVEN FAILED B VJ3RA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 WP078240T312 CE1542 IN FLIGHT, THE ENGINE WAS ROUGH AND FUEL FLOW WAS BELOW NORMAL AND FLUCTUATING AT THAT POWER SETTING. A SAFE LANDING WAS MADE. A GROUND CHECK OF THE ENGINE OPERATION WAS PERFORMED. IT WAS FOUND THAT THE ENGINE DRIVEN FUEL PUMP WAS SUCKING AIR THRU THE CASE DRAIN VENT. PUMP WAS REMOVED AND AN NEW PUMP INSTALLED. PUMP SENT IN FOR WARRANTY. 1L71 3O3 O 3A15 E5CE 20020620000102002062000010EA 2002 6 20 2002FA0000717 220020605G741401081792 MAGNETO PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE FAILED B VJ3RK NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 WP079299B69 2843116 ROUGH ENGINE ON GROUND RUN, A MAGNETO CHECK WAS PERFORMED AND THE LEFT MAGNETO HAD EXCESSIVE MAGNETO DROP. MAGNETO WAS REMOVED AND A REPAIRED MAGNETO INSTALLED. MAGNETO OPERATION CHECK OF THE ENGINE WAS PERFORMED AND CHECKED NORMAL. 1L71 3O3 O 2A13 E286 20020621000082002062100008EU 2002 6 21 2002FA0000718 120020605G7820120A6401 MUFFLER GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA ENGINE EXHAUST CRACKED C VJ3RK NONE O OTHER ININSP/MAINT 1 SW99861AF193 85001 TAIL PIPE SUPPORT BRACKET CRACKED AT WELD. REMOVED MUFFLER AND INSTALLED NEW MUFFLER ASSEMBLY. PART SENT IN FOR WARRANTY. 1L71 3O3 ORTA49CE 1E4 20020620000352002062000035WP 2002 6 20 2002FA0000720 120020602G5313 LONGERON DOUG DC8 DC873F 302199FWP FUSELAGE CORRODED B T64RK NONE O OTHER ININSP/MAINT 1 SO03961R 84102 46133 (LONGERON/BATHTUB FITTING) FOUND DURING (D) CHECK INSPECTION, LEFT LONGERON, LEFT LONGERON, 24 STA. 960. 2L74 4F RT4A25 20020620000362002062000036WP 2002 6 20 2002FA0000721 120020508G5313 LONGERON DOUG DC8 DC873F 302199FWP FUSELAGE CORRODED B T64RK NONE O OTHER ININSP/MAINT 1 SO03961R 46133 (LONGERON 24) FOUND DURING (D) CHECK INSPECTION, LEFT WHEEL WELL STA. 902 FITTING AND LONGERON 24 CORROSION EMINATING FROM BETWEEN FITTING AND LONGERON LOWER SURFACE. 2L74 4F RT4A25 20020620000372002062000037WP 2002 6 20 2002FA0000722 120020508G5320 WEB DOUG DC8 DC873F 302199FWP MLG WW CORRODED B T64RK NONE O OTHER ININSP/MAINT 1 SO03961R 84102 46133 (WEB SKIN) FOUND DURING (D) CHECK INSPECTION, RIGHT W/W STA. 980 CNAT BULKHEAD WEB SKIN AND ANGLES HAS SURFACE CORROSION FROM LONGERON 24 TO LONGERON 27R. 2L74 4F RT4A25 20020620000382002062000038WP 2002 6 20 2002FA0000723 120020608G5320 PANEL DOUG DC8 DC873F 302199FWP RT MLG WW CORRODED B T64RK NONE O OTHER ININSP/MAINT 1 SO03961R 84102 46133 (BULKHEAD PANELS) FOUND DURING (D) CHECK INSPECTION. RIGHT W/W STA. 980 CNAT BULKHEAD PANELS HAVE CORROSION SPOTS FROM LONG 24R TO LONGERON 25R. 2L74 4F RT4A25 20020620000432002062000043SO 2002 6 20 2002FA0000728 220020524G8530654972A1 CYLINDER CESSNA305 305A 2074002CE CONT O470 O47011B 17026SO NR 6 POSITION FAILED D K NONE O OTHER ININSP/MAINT 1 EA25305A 714 23182 (CYLINDER) FOUND HEAD OF CYLINDER NR6 SEPARATING FROM THE BARREL AT THE THREADED PORTION OF HEAD. VERIFIED ENGINE TIMING WAS CORRECT. NO EVIDENCE OF DETONATION FOUND. AL CYLINDER NEW AT OVERHAUL. AT 570 HOURS NR4 CYLINDER FAIL THE SAME WAY. ALL CYLINDERS HAD SAME DATE CODE 5-99. APPEARS TO BE A MFG DEFECT. 1H71 3O3 O 5A5 E269 20020621000912002062100091CE 2002 6 21 2002FA0000729 120020509G575316916000511 RIB BEECH 23 C24R 1151254CE TE FLAP CORRODED B JZRRK NONE O OTHER ININSP/MAINT 1 EA07910JM2951 MC683 DURING DISASSEMBLY FROM A BELLY LANDING, FOUND SEVERE CORROSION BETWEEN INBOARD FLAP HINGE (PN 169-160005-20). PARTS WERE ON THE VERGE OF FAILURE. THEIS AREA IS TOTALLY INACCESSABLE FOR INSPECTION WITHOUT DRILLING THE FLAP APART. 1L71 3O A1CE 20020625001212002062500121CE 2002 6 25 2002FA0000731 120020612G2434991059111 ALTERNATOR CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE FAILED D CMRRO OTHER O OTHER NRNOT REPORTED 1 GL25809SP1172 172S8112 2802351A CHARGING SYSTEM CEASED TO FUNCTION. DIAGNOSIS WAS ALTERNATOR FAILURE, PROBABLY BREAKDOWN OF DIODES. NO EXTERNAL SIGNS OF FAILURE. 1H71 3O3 ONT3A12 1E10 20020625001222002062500122CE 2002 6 25 2002FA0000732 120020520G2434991059111RX ALTERNATOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ENGINE MALFUNCTIONED D ALFGK NONE O OTHER ININSP/MAINT 1 SW15166ME721 172S8446 ALTERNATOR MALFUNCTIONED. NO OUTPUT. DISASSEMBLED, FOUND ONE BRUSH WORN AND OTHER MISSING. I SUSPECT BRUSH WAS WORN TO THE POINT THAT THE SPRING FOUND ITS WAY TO THE COMMUTATOR, WRAPPING ITSELF AROUND IT. BRUSH NOT LOCATED. 1H71 3O3 ONT3A12 1E10 20020625001232002062500123CE 2002 6 25 2002FA0000733 120020516G57510322709 BRACKET CESSNA195 195A 2073110CE JACOBSR915 L6 35005EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 WP289869A 7571 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. IF BRACKETS ARE GOOD, 1H71 3R3 R A790 TC195 20020625001242002062500124CE 2002 6 25 2002FA0000734 120020516G57510322709 BRACKET CESSNA195 195A 2073110CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 SW093462V 7187 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001252002062500125CE 2002 6 25 2002FA0000735 120020516G57510322709 BRACKET CESSNA190 190 2072902CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE019872A 7574 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001272002062500127CE 2002 6 25 2002FA0000736 120020516G57510322709 BRACKET CESSNA195 195B 2073112CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL031LA 7908 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001282002062500128CE 2002 6 25 2002FA0000737 120020516G57510322709 BRACKET CESSNA195 195B 2073112CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL25195HJ 7880 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001292002062500129CE 2002 6 25 2002FA0000738 120020516G57510322709 BRACKET CESSNA195 195 2073102CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 SW05211RD 7294 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. WE HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001302002062500130CE 2002 6 25 2002FA0000739 120020516G57510322709 BRACKET CESSNA195 195B 2073112CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE09302GT 7910 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIR CRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020624001262002062400126GL 2002 6 24 2002FA0000740 120020523G3245 TUBE CIRRUSSR SR22 2130001GL NOSE TIRE LEAKING B K NONE O OTHER ININSP/MAINT 1 GL01279DV31 0196 FOUND THE 5.00-5 NOSE TIRE TO HAVE A VERY SLOW LEAK. REMOVED TUBE AND FOUND IT TO BE LEAKING OUT OF SEVERAL ESTREMELY SMALL PIN HOLES WHERE THE VALVE STEM RUBBER IS BONDED TO THE TUBE. A BRAND NEW REPLACEMENT TUBE WAS FOUND TO HAVE THE SAME PROBLEM RIGHT OUT OF THE BAG. A THIRD REPLACEMENT TUBE TESTED SATISFACTORY. 1L71 3O NTA00009CH 20020625001372002062500137SO 2002 6 25 2002FA0000741 220020531G73148773 PUMP BEECH 35 D35 1151510CE CONT E185 E18511 17014SO ENGINE FUEL BROKEN G A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 SW092966B D3607 FOLLOWING AN INFLIGHT ENGINE STOPPAGE, THE AIRCRAFT WAS FORCED TO MAKE AN UNSCHEDULED LANDING CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT. THE AIRCRAFT ENGINE WAS SENT TO A FACILITY APPROVED BY THE NTSB TO DETERMINE CAUSE OF THE ENGINE FAILURE. DURING THIS TIME IT WAS DISCOVERED THAT THE ENGINE DRIVEN FUEL PUMP WAS BROKEN. THE AIRCRAFT HAD PLENTY OF FUEL AT THE TIME OF THE ACCIDENT. THE FUEL PUMP WAS SENT TO THE NTSB LABORATORY FOR EXAMINATION BY THE METALLURGISTS. 1L71 3O3 O A777 E246 20020625001382002062500138CE 2002 6 25 2002FA0000742 120020516G57510322709 BRACKET CESSNA195 195B 2073112CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 SW099800V 16163 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEARD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001392002062500139CE 2002 6 25 2002FA0000743 120020516G57510322709 BRACKET CESSNA195 LC126C 2073108CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 WP151064D 7676 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 90 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001402002062500140CE 2002 6 25 2002FA0000744 120020516G57510322709 BRACKET CESSNA195 195 2073102CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL033457V 7154 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001422002062500142CE 2002 6 25 2002FA0000745 120020516G57510322709 BRACKET CESSNA190 190 2072902CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL03190EC 7653 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001432002062500143CE 2002 6 25 2002FA0000746 120020516G57510322709 BRACKET CESSNA195 195 2073102CE AILERON HINGE CORRODED C K NONE O OTHER ININSP/MAINT 1 GL031533D 7755 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001452002062500145CE 2002 6 25 2002FA0000747 120020516G57510322709 BRACKET CESSNA195 195B 2073112CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL03195WT 16128 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R A790 20020625001462002062500146CE 2002 6 25 2002FA0000748 120020516G57510322709 BRACKET CESSNA190 190 2072902CE AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 GL114411C 7996 BRACKETS ARE MADE OF MAGNESIUM, CORRODING AND CRACKING. APPROXIMATELY 80 PERCENT OF THE BRACKETS INSPECTED BY BEAD BLASTING ARE UN-AIRWORTHY. PROBLEM OF CORROSION BETWEEN BEARING AND BOSS WHICH EXPANDS AND CRACKS THE BOSS. SEPARATION OF AILERON FROM REAR WING SPAR WHILE STILL ATTACHED TO STEEL ACTUATOR ROD WOULD MOST LIKELY RENDER THE AIRCRAFT UNCONTROLLABLE. HAVE BEEN URGING EVERYONE TO REMOVE THESE BRACKETS FROM THE AIRCRAFT AND BEAD BLAST THE BODY WHILE PROTECTING BEARING. CHEMICALLY STRIPPING DOES NOT REMOVE CORROSION BY PRODUCTS. 1H71 3R NCA790 20020625001482002062500148CE 2002 6 25 2002FA0000749 120020326G7603311AS3146780 CONTROL CABLE MTSBSIMU2 MU2B35 5780411CE GARRTTTPE331TPE331* 01514WP THROTTLE FRAYED E HMNAK NONE O OTHER ININSP/MAINT 1 SW15840MA9970 612 DURING ROUTINE MAINTENANCE FOUND A FRAYED ENGINE CONTROL CABLE. THE FRAYED PORTION WAS LOCATED IN THE AFT FUSELAGE WHERE THE CABE GOES OVER A 90DEGREE TURN PULLEY. THIS IS THE FIRST OF THREE CABLE PROBLEMS THIS OPERATOR HAS FOUND IN THE LAST 90 DAYS 1H72 3T3 TRTA10SW E2WE 20020625000952002062500095SO 2002 6 25 2002FA0000751 220020603G732216A30 NOZZLE CESSNA182 182L 2072726CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C203 GL CARBUETOR LOOSE D C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 NM0142397435 18259003 811774R 922654 AIRCRAFT MADE AN EMERGENCY LANDING DUE TO LOSS OF POWER. FOUND CARBURETOR MAIN JET VERY LOOSE (REQUIRED TWO COMPLETE FINGER TIGHT TURNS TO TIGHTEN). THE TAB WASHER THAT LOCKS THE MAIN JET HAD NOT BEEN LOCKED, ALL THE TABS WERE FLAT IN A "AS NEW" CONDITION. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020701000222002070100022EU 2002 7 1 2002FA0000752 120020615G7333P16575GB4A TRANSDUCER GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA FUEL SYSTEM FAILED G VJ3RO OTHER O OTHER TXTAXI/GRND HDL 1 WP07865AF 85005 L2856448A AFTER START UP OF THE ENGINE THE FUEL FLOW INDICATION WENT TO ZERO. AIRCRAFT WAS TAKEN TO MAINTENANCE AND FOUND THAT IF YOU TAPPED ON THE UNIT IT WILL WORK. FUEL FLOW TRANSDUCER WAS REMOVED AND AN NEW FUEL FLOW TRANSDUCER WAS INSTALLED. GROUND RUN OF THE ENGINE AND AN OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL. 1L71 3O3 ORTA49CE 1E4 20020625000962002062500096SW 2002 6 25 2002FA0000753 120020508G3230F3114MPB ROD END LUSCMB1 PHANTOM1 5350102SW CONT O550 IO550G 17042SO MCAULY2A34C 2A34C* GL MLG BROKEN B O OTHER O OTHER LDLANDING 1 GL011008 321 77 108 679476 000374 ROD-END BEARING FAILED ON RIGHT RETRACT ROD. 1H71 3R3 O ATC552 E3SO 5 CP3EA 20020625000972002062500097SW 2002 6 25 2002FA0000755 120020508G3230F3114MPB ROD END MOONEYM20 M20R 5870225SW CONT O550 IO550G 17042SO MCAULY2A34C D2A34C* GL MLG BROKEN C O OTHER O OTHER LDLANDING 1 GL0110081321 77 290245 679476 000374 ROD-END BEARING FAILED ON RIGHT RETRACT ROD. 1L71 3O3 ORT2A3 E3SO 5 CP3EA 20020625000992002062500099CE 2002 6 25 2002FA0000756 120020605G3340CM358910 SWITCH CESSNA172 172S 2072439CE LANDING LIGHT FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 NM03789EP1660 172S8135 LANDING LIGHT SWITCH FAILED IN THE ON POSITION. THE SWITCH WAS TURNED OFF AFTER LANDING AND WHILE TAXI TO PARKING NOTED THE LIGHT WAS STILL ON AND THE SWITCH WAS IN THE OFF POSITION. THE LANDING LIGHT WOULD ONLY TURN OFF WITH THE BATTERY SWITCH. THIS IS A CIRCUIT BREAKER SWITCH, IF A SHORT HAD OCCURED THE WIRES WOULD HAVE BURNED UP. 1H71 3O NT3A12 20020625001012002062500101CE 2002 6 25 2002FA0000757 120020605G3340CM358910 SWITCH CESSNA172 172S 2072439CE LANDING LIGHT FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 NM03789EP 172S8135 TAXI LIGHT SWITCH FAILED WITH THE LIGHT IN THE OFF POSITION. THIS IS A CIRCUIT BREAKER SWITCH AND THIS OPERATOR HAS HAD THREE PREVIOUS FAILURES THE OTHER FAILURES WERE WITH THE SWITCH IN THE ON POSITION. 1H71 3O NT3A12 20020625001022002062500102CE 2002 6 25 2002FA0000758 120020605G3340CM358910 SWITCH CESSNA172 172S 2072439CE LANDING LIGHT FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 NM03789EP1660 172S8135 TAXI LIGHT SWITCH FAILED WITH THE LIGHT IN THE OFF POSITION. THIS IS A CIRCUIT BREAKER SWITCH. THIS OPERATOR HAS HAD THREE PREVIOUS FAILURES, THE FAILURES WERE WITH THE SWITCH IN THE ON POSITION. 1H71 3O NT3A12 20020625001062002062500106SW 2002 6 25 2002FA0000759 120020605G3220540015001 STRUT MOONEYM20 M20J 5870219SW MLG CORRODED D K NONE O OTHER ININSP/MAINT 1 EA23564331800 241381 DURING ROUTINE REPLACEMENT OF NOSE STRUT LORD SHOCK DISCS, SEVERE CORROSION WAS FOUND INSIDE THE STRUT ASSEMBLY. CORROSION PENETRATED 30 PERCENT OF WALL THICKNESS. PART IS ALMOST 20 YEARS OLD. RECOMMEND LOOKING INSIDE TUBE DURING ANNUALS WITH MIRROR. 1L71 3O 2A3 20020625001082002062500108 2002 6 25 2002FA0000760 420020531G2562EBC102A ELT UNIVAR415 415E 0420308NM CONT C85 C85* 17008SO CABIN ACTIVATED G O OTHER O OTHER TOTAKEOFF 1 SW1194769 4880 THE ELT SWITCH WAS IN THE ON POSITION BUT THE ELT DID NOT ACTIVATE DURING THE ACCIDENT SEQUENCE. THE REASON WAS NOT IMMEDIATELY KNOWN. 1L71 3O3 O A787 E233 20020625001102002062500110 2002 6 25 2002FA0000761 420020613G2562AK450 ELT CABIN FAULTY C K NONE O OTHER ININSP/MAINT 1 WP30 50 11 ELT INSTALLED NEW JUNE 2001, WITH NEW BATTERIES. IN MAY 2002, IT WAS FOUND THAT THE UNIT DID NOT TRANSMIT WHEN THE G SWITCH WAS ACTIVATED. THE BATTERIES ARE STILL GOOD AND THE UNIT APPEARS TO BE GOOD. IT HAS BEEN RETURNED TO AMERI-KING FOR REPAIR. FURTHUR INQUIRY BY THE TECHNICIAN FOUND THREE OTHER UNITS INSTALLED IN AIRCRAFT THAT DID NOT WORK. 20020625001132002062500113EA 2002 6 25 2002FA0000762 120020614G5711 SPAR ARONCA15 15AC 0191202EA WING CRACKED D K NONE O OTHER ININSP/MAINT 1 SW0986189 11AC620 DURING INSPECTION PER AD2000-25-02 R1 CRACKS FOUND IN LT FRONT SPAR APPROXIMATELY THE OUTBOARD 3 FEET AND ON THE RT FRONT SPAR FROM THE STRUT ATTACH POINT OUTBOARD. RIB NAILS MISSING ON THE RIB JUST OUTBOARD OF THE STRUT ATTACH POINT AND SPAR DAMAGE ACROSS THE TOP OF THE SPAR UNDER THE RIB. 1H71 3O A802 20020701000232002070100023EU 2002 7 1 2002FA0000763 120020615G7333P16575GB4A TRANSDUCER GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA FUEL SYSTEM FAILED G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07865AF 85005 2856448A FUEL PRESSURE INDICATION WAS 75 PSI WITH THE ENGINE SHUT DOWN AND THE FUEL BOOST PUMP SHUT OFF. REMOVED TRANSDUCER AND INSTALLED NEW FUEL PRESSURE TRANSDUCER. GROUND OPERATION OF FUEL SYSTEM CHECKED NORMAL. 1L71 3O3 ORTA49CE 1E4 20020701000242002070100024CE 2002 7 1 2002FA0000765 120020617G3230 RELAY BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO LANDING GEAR FAILED G VJ3RO OTHER J WARNING INDICATION APAPPROACH 1 WP075609S518 CE1454 825756R LANDING GEAR FAILED TO EXTEND IN FLIGHT, GEAR WAS HAND CRANKED DOWN AND A SAFE LANDING WAS MADE. AIRCRAFT WAS PLACED ON JACKS AND THE LANDING GEAR CYCLED IAW MM. THE RELAY CONTROL STICK IN THE UP POSITION WHEN THE GEAR WAS CYCLED. RELAY WAS REMOVED AND A NEW RELAY INSTALLED. LANDING GEAR OPERATIONAL CHECK OF THE SYSTEM WAS MADE. LANDING GEAR CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020701000252002070100025EU 2002 7 1 2002FA0000766 120020612G7333201030W TRANSDUCER GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA FUEL SYSTEM LEAKING G VJ3RO OTHER K FLUID LOSS CRCRUISE 1 WP07865AF99 85005 2826448A FUEL FLOW INTERMITTENT WENT TO ZERO IN FLIGHT. ENGINE FUEL FLOW SYSTEM WAS INSPECTED AND FOUND THAT FUEL FLOW TRANSDUCER WAS LEAKING FUEL. REMOVED TRANSDUCER AND INSTALLED NEW TRANSDUCER. OPERATIONAL CHECK OF THE ENGINE ON THE GROUND CHECKED NORMAL. 1L71 3O3 ORTA49CE 1E4 20020701000772002070100077EU 2002 7 1 2002FA0000767 120020611G3110B10X15M4X10 SHOCK MOUNT GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA COCKPIT BROKEN G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07865AF99 85005 2856448A INSTRUMENT SHOCK MOUNT BROKEN, IT SUPPORTS THE UPPER RIGHT HAND SIDE. REMOVED BROKEN SHOCK MOUNT AND INSTALLED NEW SHOCK MOUNT. 1L71 3O3 ORTA49CE 1E4 20020711001642002071100164EU 2002 7 11 2002FA0000768 120020611G2434115TA600009 BRACKET GROB 120 G120A 1660208EU LYC O540 AEIO540D4D5 EA ALTERNATOR CRACKED G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP07864AF194 85004 2826348A ALTERNATOR BRACKET CRACKED, THIS BRACKET IS USED TO ADJUST THE BELT TENSION. REMOVED BRACKET AND INSTALLED NEW BRACKET. ADJUSTED BELT TENSION IAW MM. 1L71 3O3 ORTA49CE 1E4 20020711001662002071100166CE 2002 7 11 2002FA0000769 120020611G3230583800901 MOTOR BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO LANDING GEAR NOISY G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP078252T CE1545 820446R GEAR MOTOR MAKES GRINDING NOISE WHEN THE GEAR IS RETRACTED. MOTOR WAS REMOVED AND A NEW MOTOR INSTALLED OPERATION OF THE GEAR SYSTEM IAW MM, CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020711001682002071100168CE 2002 7 11 2002FA0000770 120020611G3230SM50D7 RELAY BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO LANDING GEAR STICKS G VJ3RO OTHER O OTHER CLCLIMB 1 WP071569A162 CE1328 820447R LANDING GEAR WOULD NOT RETRACT AFTER TAKE OFF. AIRCRAFT WAS PLACED ON JACKS AND THE LANDING GEAR CYCLED IAW MM. INSPECTION OF THE SYSTEM FOUND THAT THE DYNAMIC RELAY WOULD STICK IN THE DOWN POSITION. A NEW DYNAMIC RELAY WAS INSTALLED AND THE SYSTEM OPERATIONAL CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020711001712002071100171SO 2002 7 11 2002FA0000771 220020611G73246314272A20 FLOW DIVIDER BEECH 33 F33A 1151425CE CONT O520 IO520B 17032SO ENGINE FLUCTUATES G VJ3RO OTHER O OTHER CRCRUISE 1 WP078240T318 CE1542 825758R FUEL FLOW FLUCTUATES IN-FLIGHT AND THE ENGINE WAS ROUGH RUNNING AT ALTITUDE, AT LOW ALTITUDE THE ENGINE WAS SMOOTH IN OPERATION. OPERATION CHECK OF ENGINE ON THE GROUND FOUND THE FUEL FLOW DIVIDER WOULD FLUCTUATE. REMOVED FLOW DIVIDER AND INSTALLED A NEW OVERHAULED ASSEMBLY. GROUND OPERATION OF ENGINE CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020715001672002071500167CE 2002 7 15 2002FA0000772 120020610G3710RA216CW PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO VACUUM SYS FAILED G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP071568P213 CE1298 825776RR UNABLE TO MAKE INSTRUMENT AIR PRESSURE AT LOW RPM, INSPECTED SYSTEM AND FOUND THAT THE PUMP WAS MAKING SMALL CHUNKS OF CARBON FOUNDED IN THE REGULATOR AND INLET FILTER. PURGED SYSTEM AND CLEANED LINES IN SYSTEM. NEW INLET AND INLINE FILTER INSTALLED. NEW PUMP INSTALLED, SYSTEM GROUND CHECKED, CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020715001682002071500168SO 2002 7 15 2002FA0000773 120020612G792185487012 BRACKET PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA ENGINE FAILED G VJ3RO OTHER O OTHER NRNOT REPORTED 1 WP074175V107 2843126 RL2833836A THIS BRACKET ATTACHES TO THE LEFT SIDE OF ENGINE COOLING BAFFLE AND ALSO SUPPORTS THE OIL COOLER ON THE LEFT HAND REAR CORNER. BRACKET REMOVED AND A NEW BRACKET INSTALLED. 1L71 3O3 O 2A13 E286 20020711001752002071100175SW 2002 7 11 2002FA0000774 120020312G3246 SPLICE BBAVIA8 8GCBC 1220803SW LYC O360 O360* 41514EA RT MLG SKI LOOSE D O OTHER O OTHER NRNOT REPORTED 1 AL05695AC 39498 RIGHT LANDING GEAR, SKI CABLE CAME LOOSE. AERO SKI R2800 SKIS INSTALLED. CABLE IS SMALLER THAN MOST SKI INSTALLATIONS. THE NICOPRESS SLEEVE ON THE THIMBLE EYE SPLICE ON THE CABLE END SLIPPED OFF THE CABLE. CABLE CAME LOOSE FROM AIRFRAME. 1H71 3O3 O A21CE E286 20020715001692002071500169SW 2002 7 15 2002FA0000775 120020312G2910 FITTING BBAVIA8 8GCBC 1220803SW LYC O360 O360* 41514EA HYD SYSTEM BROKEN D O OTHER K FLUID LOSS NRNOT REPORTED 1 AL05695AC 39498 PLASTIC T FITTING IN HYDRAULIC LINE BETWEEN RESERVOIR AND BRAKE CYLINDERS BREAKS OFF. THIS ALLOWS THE BRAKE FLUID TO ESCAPE. 1H71 3O3 O A21CE E286 20020717000972002071700097CE 2002 7 17 2002FA0000776 120020313G3010 DUCT BEECH 90 E90 1152914CE PWA PT6 PT6* 52043EA DEICE SYSTEM COLLAPSED G O OTHER F FLT CONT AFFECTED APAPPROACH 1 WP11948CC8773 LW236 AT STATION 277 IS THE HEATER REGISTER LOCATED FORWARD OF THE LAVATORY. TWO INCHES FROM THE HEAT DUCTING IN THIS AREA IS THE (1010 EV A .6250 IMPERIAL) TUBING THAT SUPPLIES PNEUMATIC PRESSURE TO THE EMPENNAGE DEICE BOOTS. THIS EMPENNAGE DEICE BOOT TUBING WAS COLLAPSED FROM APPROXIMATELY 11 INCHES AFT OF STATION 277 TO APPROXIMATELY NINE INCHES FORWARD OF STATION 277. THIS DUCTING SHOWED SIGNS OF HEAT DISTRESS THROUGHOUT THE RUN UNDER THE RIGHT CABIN FLOORBOARDS, THOUGH NOT AS SEVERE AS WHERE THE DUCTING NECKS DOWN TO A SMALLER DIAMETER. 1L72 3T3 T 3A20 E2NE 20020708000582002070800058WP 2002 7 8 2002FA0000779 120020426G2822 SEAL HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL FUEL PUMP LEAKING B EOORK NONE K FLUID LOSS ININSP/MAINT 1 AL035074R 1151D AFTER OIL SEAL REPLACEMENT, AND REINSTALLATION OF FUEL PUMP, THE PUMP SHAFT SEAL WAS DISCOVERED LEAKING. DURING BOOST PUMP OPERATION FOR BLEEDING , FUEL SYSTEM ABOUT 50/60 + PER MINUTE DROP LATE. REPLACED PUMP 1G71 3U3 U H3WE E4CE 20020711001762002071100176EA 2002 7 11 2002FA0000780 220020514G7314LW15473 PUMP LYC O540 IO540* 41532EA ENGINE FAILED D K NONE O OTHER CRCRUISE 1 NE03 318 L1852248A PILOT REPORTS FUEL PRESSURE WAS LESS AND LESS WITH EACH FLIGHT. PILOT STATED: A PROGRESSIVE FAILURE MODE. INSTALLED NEW PUMP AND FOUND FUEL PRESSURE NORMAL. 3 O 1E4 20020715001702002071500170NE 2002 7 15 2002FA0000781 220020601G853045937 ROCKER SHAFT SCWZERG164 G164B 3952802EA PWA R1340 R1340* 52016NE ENGINE DEPARTED D UJBGA UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CE0948485185 44B 15771 WHILE FLYING, NR 3 ROCKER SHAFT ON EXHAUST VALVE EXITED THE AIRCRAFT CAUSING THE ENGINE TO LOSE POWER. AIRCRAFT MADE A FORCED LANDING INTO A PLOWED FIELD CAUSING THE AIRCRAFT TO FLIP OVER. THE ENGINE HAD 185 HOURS SINCE OVERHAUL, PART COULD NOT BE FOUND, BUT SUSPECT IT FAILED IN THE THREAD AREA NEXT TO THE SMALL NUT. 1Q71 3R3 R 1A16 5E2 20020711001772002071100177SO 2002 7 11 2002FA0000783 220020122G7421RHB32E SPARK PLUG CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO RT ENGINE FOULED G O OTHER O OTHER CRCRUISE 1 NE0137150400 414A0251 PILOT REPORTED ROUGH RUNNING ENGINE (RIGHT SIDE) AT ALTITUDE. LANDED AND FOUND SPARK PLUGS WORN AND FOULED, INSTALLED CLEAN AND GAPED SET. RUN UP AND REMAINDER OF FLIGHT NORMAL. 1L72 3O3 O A7CE E8CE 20020711001782002071100178CE 2002 7 11 2002FA0000784 120020612G2510051422713 SEAT CESSNA172 172R 2072401CE COPILOT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 GL1598682779 17280604 1.5 INCH CRACKS ON COPILOTS SEAT CUSHION BASE. REPLACED WITH NEW PART WHICH IS TWICE AS THICK. 1H71 3O NT3A12 20020711001792002071100179CE 2002 7 11 2002FA0000785 120020608G3230089400011 GEAR CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO LANDING GEAR WORN D O OTHER O OTHER CLCLIMB 1 WP135403M 402B0003 7910838 DURING LANDING GEAR RETRACTION PILOT REPORTED LAND GRINDING NOISE. CAUSED BY WORN OUT GEAR BOX INTERNAL SYSTEM. INSPECTED WORN OUT GEARS TOOTH. 1L72 3O3 O A7CE E8CE 20020711001802002071100180SO 2002 7 11 2002FA0000787 120020604G71208193702 MOUNT PIPER PA46 PA46350P 7104602SO LYC O540 IO540* 41532EA ENGINE BROKEN G O OTHER O OTHER LDLANDING 1 SW05529TX1835 4622045 FAILURE DURING LANDING. ENGINE MOUNT REVEALED THAT THE RIGHT SIDE OF THE NOSE GEAR ACTUATOR, AFT ATTACH POINT, HAD SEPARATED FROM THE TUBE CLUSTER ON THE MOUNT ASSEMBLY. 1L71 3O3 ORTA25SO 1E4 20020715001722002071500172CE 2002 7 15 2002FA0000790 120020606G551012326241 BRACKET CESSNA210 T210N 2073456CE CONT O550 IO550* SO HORIZ STAB BROKEN B MI2RK NONE O OTHER ININSP/MAINT 1 CE076468N 21063042 289167R AIRCRAFT UNDERGOING ANNUAL INSPECTION. HORIZONTAL STABILIZER FOUND LOOSE. INSPECTED AND FOUND REAR MOUNTING REINFORCEMENT BRACKET BOTH SIDES BROKEN AND THE FORWARD ATTACHMENT FITTINGS LOOSE. INSTALLED REAR BRACKETS AND PN SK210-126. 1H71 3O3 O 3A21 E3SO 20020717001012002071700101SO 2002 7 17 2002FA0000794 120020601G2810 TANK LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO LT WING LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 WP0771170 2597 WING TANKS INSTALLED IN THIS AIRCRAFT DURING 200-2001 WING RECOVER. TANKS REMOVED FOR REPAIR AFTER COMPLAINT ABOUT LEAKAGE. RIGHT TANK HAD LEAKED AT WELD SEAM AND WAS PREVIOUSLY REPAIRED BY OWNER. LEFT TANK HAD A LEAK AT THE ROOT OF TANK IN THE WELD BEAD WHERE FLANGES WERE JOINED BY WELDING THE BASE METALS TOGETHER AT A PARALLEL LAP JOINT (NO FILLER). THIS JOINT APPEARS TO BE SMOOTH AND WELL FORMED. NOTED DAMAGE IN THE FORM OF SOME TOOL MARKS, PART DEFORMITIES, BENDING AND BULGES WHICH WOULD INCREASE STRESS TO THE WELD JOINTS IN SERVICE. 1H71 3O3 O A694 E205 20020711001812002071100181CE 2002 7 11 2002FA0000795 120020606G7111S13602AL CIRCUIT BREAKER CESSNA337 337D 2075717CE COWL FLAP SYS FAILED D O OTHER O OTHER NRNOT REPORTED 1 WP098607675 3371067 CIRCUIT BREAKER FAILED INTERNALLY WITHOUT TRIPPING. CAUSED OPEN CIRCUIT TO COWL FLAP MOTORS. FAILURE OCCURRED DURING GROUND MAINTENANCE. NEED TO IMPROVE QUALITY CONTROL IN PRODUCTION. 1H72 3O A6CE 20020719000952002071900095SO 2002 7 19 2002FA0000796 220020328G73146381563 PUMP CESSNA210 2105 2073404CE CONT O470 IO470S 17026SO FUEL SYSTEM FAILED B RV3RA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SW158130Z 2050130 77235OE ENGINE LOST POWER, AIRCRAFT LANDED OFF AIRPORT. FOUND FUEL CONTAMINATION AND FUEL PUMP PRESSURE RELIEF VALVE STUCK. AD841001, WAS SIGNED OFF BUT FUEL HEADER TNKS WERE CONTAMINATED AND NO DRAIN VALVES HAD BEEN INSTALLED. CUSTOMER WAS NOTIFIED THAT PUMP HAD TRASH IN AND AROUND RELIEF VALVE AREA. SAMPLES WERE TAKEN AND SENT TO CUSTOMER FOR IDENTIFICATION. ENTIRE FUEL SYSTEM MUST BE CLEANED TO REMOVE ALL OF THIS MATERIAL OR IT WILL GET INTO THE PUMP AGAIN, VOIDING ANY WARRANTY ON FUEL PUMP, AND COULD POSSIBLY CAUSE ENGINE FAILURE. 1H71 3O3 O 3A21 3E1 20020715001732002071500173SO 2002 7 15 2002FA0000798 120020619G2460150905 RELAY PIPER PA28 PA28RT201T 7102817SO CONT O360 TSIO360* 17025SO ELECTRICAL SYS BURNED B RSURO OTHER O OTHER NRNOT REPORTED 1 EA218106H 28R8031012 HAVE FOUND 2-3 RELAYS WITHIN PAST MONTH WITH BURNED CONNECTION TO MFG. THE MAIN BUSS CONNECTIONS OVER TIME HAVE TURNED BLACK AND HAVE ULTIMATELY FAILED. 1L71 3O3 O 2A13 E9CE 20020711001822002071100182CE 2002 7 11 2002FA0000800 120020516G575103225709 HINGE BRACKET CESSNA190 190 2072902CE AILERON CRACKED D O OTHER O OTHER NRNOT REPORTED 1 WP239854A 7547 THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE. 1H71 3R NCA790 20020711001832002071100183CE 2002 7 11 2002FA0000801 120020516G57510322709 HINGE BRACKET CESSNA195 195B 2073112CE AILERON CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SW092165C 16150 THESE BRACKETS ARE MADE OF MAGNESIUM AND ARE CORRODING AND CRACKING TO AN ALARMING DEGREE. 1H71 3R A790 20020711001842002071100184 2002 7 11 2002FA0000803 420020503G2561PA5 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED. THE MANUFACTURER RECOMMENDED PRESSURE TEST. DOM: JUNE 1983 20020711001852002071100185 2002 7 11 2002FA0000804 420020503G2561KS35P0701117 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 LIFE VEST FAILED. THE MANUFACTURER RECOMMENDED PRESSURE TEST. DOM: JUNE 1983. 20020715001742002071500174EA 2002 7 15 2002FA0000807 220020618G8540LW15659 DRIVE GEAR PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENGINE SEIZED G O OTHER O OTHER NRNOT REPORTED 1 GL038154J219 448095020 23572T MAGNETO DRIVE GEAR WAS SEIZED TO CRANKCASE BUSHING WHICH WAS SPINNING IN ITS CRANKCASE BORE. THIS ENGINE HAD ONLY 219 HOURS SINCE FACTORY REMANUFACTURE. THE OPPOSITE ENGINE WHICH ALSO HAD 219 HOURS SINCE FACTORY REMANUFACTURE EXHIBITED THE EXACT SAME PROBLEM. BOTH ENGINES WERE REMOVED AND SENT OUT FOR REPAIR. 1L72 3O3 O A19S0 E286 20020719001042002071900104EA 2002 7 19 2002FA0000808 220020701G8520 CRANKSHAFT MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA ENGINE FAILED B K NONE O OTHER ININSP/MAINT 1 NM085859Q 795 NR 3 CYLINDER AND ROD LOOSE FROM CRANKSHAFT AND CASE HALF SENT TO HALF SENT TO REPAIR FACILITY. THEY SAID WRONG OIL PUMP GEARS. FAILED PUMP OIL STARVATION DESTROYED CRANK SHAFT AND ENGINEER. 1L71 3O3 O 2A3 1E10 20020715001752002071500175EA 2002 7 15 2002FA0000810 220020618G853070310 SEAL AMTR S1C S1C GL LYC O360 IO360B4A 41514EA ENGINE FAILED G O OTHER K FLUID LOSS NRNOT REPORTED 1 WP056DD 1DD PUSH ROD SHROUD SEAL FAILED, CAUSING OIL LEAK. 1Q71 3O3 ONCEXPA1Q711E10 20020719001072002071900107EU 2002 7 19 2002FA0000812 120020605G3520 DOOR AMD FALC90FALCON900EX 2730009EU OXYGEN SYSTEM STUCK C K NONE L NO TEST ININSP/MAINT 1 SO11404A 1512 56 WHILE PERFORMING MAINTENANCE TASK 35.200, ITEM 6, SELECTION OF OXYGEN CONTROLLER TO OVERIDE, SIX PASSENGER OXYGEN MASK DOORS FAILED TO OPEN FULLY AND DEPLOY THE MASKS. FIVE OF THE DOORS OPENED APPROXIMATELY .250 INCHES AND THE SIXTH DOOR FAILED TO OPEN. INSPECTION OF THE OXYGEN MASK DOORS INDICATED THAT THEY WERE STICKING TO THE LEATHER COVERING ON THE DOORS OR ON INTERIOR FOAM. THE OXYGEN MASKS WERE INSPECTED AND RE-SECURED. MAINTENANCE TASK 35.200, ITEM 6 WAS REPEATED AND ALL PASSENGER OXYGEN MASKS DEPLOYED PROPERLY. DURING THE INITIAL INSPECTION, IT WAS ALSO NOTED THAT FORWARD CABIN SEAT R2 OXYGEN MASK'S FLEXIBLE OXYGEN SUPPLY HOSE WAS NOT CONNECTED TO THE OXYGEN SUPPLY FIRTREE. 2L73 4F RTA46EU 20020718001882002071800188EA 2002 7 18 2002FA0000818 220020625G7314 WASHER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FUEL PUMP BROKEN B K NONE O OTHER ININSP/MAINT 1 WP28503ER1071 172S8003 L2267651A DURING SCHEDULED TIME CHANGE OF THE ENGINE-DRIVEN FUEL PUMP, THE SMALL RETAINING WASHER FOR THE PUMP SHAFT SPRING WAS FOUND BROKEN. 1H71 3O3 ONT3A12 1E10 20020718001892002071800189CE 2002 7 18 2002FA0000819 120020627G32461228100781 WHEEL BEECH 2000 2000 1152000CE MLG DESTROYED G A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 SO35786BP346 71 NC28 RIGHT INBOARD WHEEL AND TIRE ASSEMBLY DEPARTED THE AIRCRAFT AFTER TAKEOFF. WHEEL BEARING HAD DISINTEGRATED. INSPECTION REVEALED NR 2 WHEEL BEARINGS SPALLED AND NR 4 WHEEL BEARINGS OVERHEATED. 71 HOURS SINCE INSPECTION AND LUBE. RECOMMEND MORE FREQUENT LUBE INTERVAL OR REDESIGN WITH LARGER BEARING. 1L72 4T RTA38ACE 20020719001182002071900118 2002 7 19 2002FA0000820 420020628G3422S25031 ELBOW CESSNA172 172S 2072439CE GYRO CRACKED B K NONE O OTHER ININSP/MAINT 1 WP2817ER 838 172S8921 FOUND PLASTIC ELBOW AT DIRECTIONAL GYRO CRACKED CAUSING INSTRUMENT TO PRECESS. 1H71 3O NT3A12 20020719000342002071900034EA 2002 7 19 2002FA0000821 220020629G853019001 EXHAUST VALVE LYC O320 O320E2G 41508EA NR 3 CYLINDER BROKEN D A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 EA05 2351 466 L4805127A REPLACED NR 3 CYLINDER & PISTON DUE TO EXHAUST VALVE SEPARATION & DAMAGE TO CYLINDER CAUSED BY NOT REPLACING NEEDED PARTS AT M.O.H. (466.6-HRS S.M.O.H.) TOTAL TIME ON P/N 19001 EXHAUST VALVES 2351.6-HRS. THERE IS NO RECORD OF THE EXHAUST & INTAKE VALVES, EXHAUST GUIDES OR PISTONS REPLACED AT M.O.H. WE ACCOMPISHED T.O.H. ON ALL CYL'S BY REPLACING ALL VALVES, EXHAUST GUIDES, PISTONS, RINGS, GASKETS & SEALS. ON TEAR-DOWN WE FOUND INTAKE & EXHAUST ROCKERS REVERSED, INVERTED VALVE SPRINGS, ROCKER SHAFT THRUST BUTTONS DETERIORATED & WRONG SIZE PUSH RODS. ALSO NO ORANGE PAINT TO DESEGINATE CHROME CYLINDERS'S. 3 O E274 20020719000352002071900035CE 2002 7 19 2002FA0000822 120020702G7602S29991 SWIVEL CESSNA337 T337G 2075726CE CONT O520 TSIO520NB 17040SO MIXTURE CABLE FAILED B K NONE O OTHER ININSP/MAINT 1 WP17265 150 P3370232 THIS ITEM IS INSTALLED ON A CESSNA T337G THAT HAS HAD TCM TSIO-520 ENGINES INSTALLED AS AN STC MODIFICATION. THE PART IS A BALL-TYPE SWIVEL THAT CONNECTS THE MIXTURE CABLE TO THE MIXTURE CONTROL ARM. THE BALL HAS PULLED OUT OF ITS SWAGED HOUSING. THIS IS THE THIRD SUCH FAILURE IN 177 HOURS. 1H72 3O3 O A6CE E8CE 20020719000362002071900036CE 2002 7 19 2002FA0000823 120020705G321305412024 BUSHING CESSNA172 172S 2072439CE LT MLG DEBONDED D K NONE O OTHER ININSP/MAINT 1 WP28243SP1928 172S8212 DURING A PHASE INSPECTION FOUND THE RUBBER TYPE BUSHING HAD BECOME LOOSE AND SLID DOWN THE LEFT GEAR LEG, RESULTING IN METAL TO METAL CONTACT OF THE GEAR LEG AND BUSHING SLEEVE. JACKED A/C, REMOVED GEAR LEG AND OLD BUSHING. INSPECTED GEAR LEG, FOUND DAMAGE LIMITED TO PAINTED SURFACES, REPAINTED GEAR LEG AS NEEDED, INSTALLED NEW BUSHING ASSEMBLY, REINSTALLED GEAR LEG. BLED BRAKES AND RETURNED TO SERVICE. 1H71 3O NT3A12 20020719000372002071900037CE 2002 7 19 2002FA0000824 120020708G3110S337711 SWITCH CESSNA172 172S 2072439CE INTRUMENT PANEL FAILED D K NONE L NO TEST ININSP/MAINT 1 WP30948SP1652 172S8144 DURING MAINTENANCE PRE-RUN FOR PHASE INSPECTION, WHEN MASTER AVIONICS SWITCH WAS TURNED OFF, ONLY HALF OR THE AVIONICS COMPONENTS TURNED OFF. ONE SIDE OF THE SWITCH FAILED IN THE ON POSITION. REPLACED SWITCH, OPERATIONAL CHECKED SAT. 1H71 3O NT3A12 20020719000382002071900038SO 2002 7 19 2002FA0000825 220020523G8530652541 NUT CESSNA182 182J 2072722CE CONT O470 O470S 17026SO CYLINDER CRACKED C K NONE O OTHER ININSP/MAINT 1 GL193090F73 18257190 226264R DURING CYLINDER INSTALLATION P/N 652541 NUT CRACKED DURING TORQUEING OPERATION. FAILURE AT ABOUT 60 FT/LBS 1H71 3O3 ONT3A13 E273 20020719001192002071900119SO 2002 7 19 2002FA0000830 220020717G8530 PISTON PIN CESSNA172 R172E 2072413CE CONT O360 IO360DB 17025SO NR 6 CYLINDER FAILED D K NONE O OTHER ININSP/MAINT 1 WP30146AC1051 R1720147 808811R ENGINE OIL FILTER INSPECTED DURING 100 HOUR INSPECTION, FOUND EXCESSIVE AMOUNT OF ALUMINUM FLAKES IN FILTER. CAUSE OF METAL IN OIL FILTER TRACED TO NR 6 CYLINDER PISTON PIN PLUG. WHEN CYLINDER WAS REMOVED THE FWD PLUG HAD EXCESSIVE WEAR. THIS WAS A FACTORY REMANUFACTURED ENGINE AND THIS CYLINDER WAS NOT REMOVED SINCE REMANUFACTURE. THE PISTON PIN PLUGS WERE REPLACED AND THE CYLINDER OVERHAULED & REINSTALLED. NO MORE METAL HAS BEEN DETECTED IN THE OIL FILTER. 1H71 3O3 O 3A17 E1CE 20020719000762002071900076SW 2002 7 19 2002FA0000831 120020718G57115263 SPAR CAP BBAVIA7 7ECA 21101NNSW RT WING CRACKED D K NONE Z SIGNIFICANT FAILURE REPORT ININSP/MAINT 1 WP296312N2593 4 308 DURING COMPLIANCE WITH AD 00-25-02R1, THE RIGHT WING REAR SPAR WAS FOUND TO HAVE A COMPRESSION CRACK AT THE AILERON CENTER HINGE ATTACH BRACKET, UPPER HOLE. THE CRACK IS VISIBLE ON THE FORWARD AND AFT FACE OF THE SPAR EXTENDING UP FROM THE BOLT HOLE AND ACROSS THE SPAR CAP. THE INSPECTION WAS ACCOMPLISHED USING A FLEXIBLE BORESCOPE AS PER SERVICE BULLETIN 406 INSTRUCTIONS. 1H71 3O A759 20020719001672002071900167SO 2002 7 19 2002FA0000832 220020702G7414 MAGNETO BEECH 58 58 1152740CE CONT O520 IO520* 17032SO ENGINE FAILED B FFKRK NONE O OTHER ININSP/MAINT 1 SO0511HW 3 TH271 ON A GROUND RUN UP, PILOT REPORTED A BAD MAG DROP. AFTER PULLING MAGNETO OFF OF THE ENGINE, IT APPEARS THE MAGNETO FAILED. THE PLASTIC DRIVE GEARS WERE STRIPPED AS WELL AS THE MAGNETO RETAINER DRIVE COUPLING AND DRIVE COUPLING RUBBER BUSHING WERE DAMAGED. NO OTHER DAMAGE WAS FOUND ON THE ENGINE. 1L72 3O3 O 3A16 E5CE 20020719001692002071900169SO 2002 7 19 2002FA0000833 220020530G8530SA539988 INTAKE VALVE CESSNA180 180K 2072624CE CONT O470 O470* 17026SO ENGINE FAILED B ZKGRK NONE O OTHER ININSP/MAINT 1 NE0561858563 18052807 THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION, IT NOW HAS 563 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EXHAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD. CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY. THIS AIRCRAFT HAS NOT SET FOR OVER 1 MONTH AT A TIME, USED HEAVY IN THE SUMMER. THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 ENGINES, ALL GOING ABOUT 600 HOURS. 1H71 3O3 O 5A6 E273 20020719001702002071900170SO 2002 7 19 2002FA0000834 220020530G8530SA643767 GUIDE CESSNA180 180K 2072624CE CONT O470 O470* 17026SO ENGINE FAILED B ZKGRK NONE O OTHER ININSP/MAINT 1 NE0561858563 18052807 THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION. IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EXHAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD. CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLIER. THIS AIRCRAFT HAS NOT SET FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER. THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 ENGINES ALL GOING ABOUT 600 HOURS. 1H71 3O3 O 5A6 E273 20020719001712002071900171SO 2002 7 19 2002FA0000835 220020530G8520SA646277 LIFTER CESSNA180 180K 2072624CE CONT O470 O470* 17026SO ENGINE FAILED B ZKGRK NONE O OTHER ININSP/MAINT 1 NE0561858563 18052807 THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION. IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EXHAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD. CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY. THIS AIRCRAFT HAS NOT SET FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER. THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 ENGINES ALL GOING ABOUT 600 HOURS. 1H71 3O3 O 5A6 E273 20020719001722002071900172SO 2002 7 19 2002FA0000836 220020530G8520SA628488 LIFTER CESSNA180 180K 2072624CE CONT O470 O470* 17026SO ENGINE FAILED B ZKGRK NONE O OTHER ININSP/MAINT 1 NE0561858563 18052807 THIS ENGINE WAS OVERHAULED 6/10/99 BY REPAIR STATION. IT NOW HAS 563.3 HOURS AND ALL THE INTAKE VALVES WERE BAD, ALL EXHAUST GUIDES WERE BAD, AND ALL LIFTERS ARE BAD. CYLINDERS WERE NEW FROM PARTS MFG AND SUPPLY. THIS AIRCRAFT HAS NOT SET FOR OVER 1 MONTH AT A TIME USED HEAVY IN THE SUMMER. THIS IS THE 3RD TIME THIS AIRFRAME HAS HAD LIFTER TROUBLES IN 3 ENGINES ALL GOING ABOUT 600 HOURS. 1H71 3O3 O 5A6 E273 20020722000012002072200001CE 2002 7 22 2002FA0000837 120020625G27200400107150 CONTROL CABLE CESSNA150 152 2071835CE COPILOT PEDALS FAILED B LN3RA UNSCHED LANDING F FLT CONT AFFECTED NRNOT REPORTED 1 WP0748803518 15280973 THE PILOT COMPLAINED OF COPILOTS LEFT RUDDER PEDAL BEING LOOSE AND NOT VERY RESPONSIVE. INSPECTED PEDALS AND RUDDER CABLE SYSTEM. FOUND RIGHT RUDDER CABLE AT AFT FUSELAGE BULKHEAD HOLDING BY TWO STRANDS, FORWARD OF WHERE CABLE COMES OUT OF FUSELAGE TO ATTACH TO RUDDER ON LEFT SIDE. THE MFG IPC CALLS THE COPILOTS LEFT RUDDER CABLE THE RIGHT RUDDER CABLE. THE CABLE HAD WORN THROUGH THE PHENOIC ON THE AFT BULKHEAD WHERE CABLE COMES THROUGH AND WEARING ON THE BULKHEAD. INSTALLE NEW PIECE OF PHENOLIC TO KEEP THE CABLE FROM WEARING ON THE BULKHEAD AT FS 173.41. THIS PART WOULD HAVE FAILED WITHIN A FEW HOURS. IT APPEARS THE DAMAGE WAS CAUSED BY THE WAY THE CABLE WAS ROUTED AT LAST REPLACEMENT 518.0 HOURS AGO. 1H71 3O NT3A19 20020723000762002072300076SO 2002 7 23 2002FA0000838 120020628G812060051004 HOUSING PIPER PA34 PA34200T 7103406SO TURBOCHARGER CRACKED B YXURK NONE O OTHER ININSP/MAINT 1 WP07749LW 1381 347770416 TURBINE HOUSING HAS A 1 INCH CRACK BEYOND LIMITS DESCRIBED IN AD. 1L72 3O A7SO 20020723000782002072300078GL 2002 7 23 2002FA0000839 120020604G3222111020 SPRING AMTR CA7 CA7 05610EBGL TAIL WHEEL BROKEN G K NONE O OTHER ININSP/MAINT 1 EA17753KD119 TAIL SPRING BROKE FORWARD OF TAIL WHEEL ATTACH AREA. PREVIOUS DAMAGE NOTED AT SPRING CRACKED/BROKEN AREA. 1H71 3T NTEXPA1H71 20020723000802002072300080CE 2002 7 23 2002FA0000840 120020614G522008911077 WINDOW CESSNA310 T310R 2074246CE CONT O520 TSIO520* 17040SO EMERGENCY EXIT DEPARTED B O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CE0787RJ 310R0676 EMERGENCY WINDOW EXIT DEPARTED AIRCRAFT IN FLIGHT, IN RAIN SHOWER. ALL CABLE PINS BENT. VERY DIFFICULT TO SEE WITH INTERIOR INSTALLED. 1L72 3O3 O 3A10 E8CE 20020723000812002072300081SO 2002 7 23 2002FA0000841 120020510G57536232800 ATTACH FITTING PIPER PA34 PA34200 7103405SO RT TE FLAP FAILED G W5YSK NONE O OTHER ININSP/MAINT 1 SO151502410000 347250349 THE OUTBOARD ATTACH POINTS (2) OF THE RT FLAP FAILED IN FLIGHT. INSPECTION OF THE FLAP INTERIOR FOUND THE FAILURE WAS CAUSED BY HEAVY CORROSION AT THE STEEL TO ALUMINUM INTERFACE OF THE FLAP NOSE RIBS AND BRACKET. 1L72 3O A7SO 20020723000822002072300082 2002 7 23 2002FA0000842 420020604G611312504192 SPINNER CESSNA210 210L 2073448CE CONT O550 IO550* SO PROPELLER DEPARTED G O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 EA1159176 21060142 SPINNER DEPARTED AIRCRAFT WHILE IN FLIGHT. PARTS OF SPINNER AND HARDWARE STILL ATTACHED TO BULKHEAD. 1H71 3O3 O 3A21 E3SO 20020723000852002072300085EA 2002 7 23 2002FA0000843 220020701G8500 ENGINE PIPER PA28 PA28151 7102805SO LYC O320 O320E3D 41508EA NOSE FIRE D O OTHER F FLT CONT AFFECTED ININSP/MAINT 1 WP0733439 287515299 L40784 FIRE OCCURED IN ACCESSORY AREA OF ENGINE DURING START RESULTING IN MINOR DAMAGE. UPON POST FIRE INSPECTION, ONLY DEFECT FOUND WAS BROKEN AND SEVERLY BURNED RUBBER PRIMER HOSE ADJACENT TO EGT PROBE. 1L71 3O3 O 2A13 E274 20020723000982002072300098GL 2002 7 23 2002FA0000844 220020701G721023064640 GEARBOX BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE MISMANUFACTURED B ALGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 UPON INSPECTION BEFORE GEARBOX ASSEMBLY. SCAVENGE TUBE CUT OUT NOT WIDE ENOUGH, CAUSING TUBE TO RUB. 2 EACH STUDS NOT FULLY SEATED AT N1 PICKUP AREA. OIL PUMP INSERTS NOT CLEANED OUT. ASSURE PROPER MANUFACTURING AND INSPECTED BY QA BEFORE LEAVING FACTORY. 1G71 3U3 UO H2SW E1GL 20020723001002002072300100SO 2002 7 23 2002FA0000845 120020628G812060051004 HOUSING PIPER PA34 PA34200T 7103406SO CONT O360 LTSIO360E 17025SO TURBOCHARGER CRACKED B YXURK NONE O OTHER ININSP/MAINT 1 WP07749LW 1381 347770416 306120 TURBINE HOUSING TYPE C STAGE 1 CRACK BEYOND LIMITS DESCRIBED IN AD. 1L72 3O3 O A7SO E9CE 20020723001822002072300182EA 2002 7 23 2002FA0000847 220020715G8500 ENGINE UNIVAR108 1083 9230408NM FRNKLN6A41656A4165B3 27025EA NACELLE SHUTDOWN G A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 EA136678M 32712 ENGINE SHUT DOWN ON CLIMB OUT AT APPROX. 80 FEET, ALTITUDE. VISUAL EXAMINATION REVEALED NO OBVIOUS REASON FOR THE FAILURE. FUEL VENTING AND QUANTITY WERE COMPROMISED BY THE CRASH IMPACT AFTER RECOVERY EFFORTS WERE COMPLETE FUEL WAS PUT IN THE RIGHT WING TANK AND THE ENGINE WAS EASILY STARTED AND RAN WITH NO MALFUNCTIONS. 1H71 3O3 O A767 E238 20020724000022002072400002CE 2002 7 24 2002FA0000848 120020711G5310051313211 BRACKET CESSNA172 172I 2072426CE FUSELAGE CRACKED D DBWSK NONE O OTHER ININSP/MAINT 1 SO15356055983 17256859 DURING INSPECTION TO DETERMINE WHY INDUCTION AIR FILTER WAS RUBBING AGAINST OPENING IN LOWER ENGINE COWL. IT WAS FOUND THAT THE LT UPPER FIREWALL WAS FILLED FORWARD APPROX .2500 INCH WHERE ENGINE MOUNT ATTACHED TO FIREWALL. AFTER REMOVEING INTERIOR PANEL FORWARD OF LT ENTRANCE DOOR IT WAS DETERMINED THAT BRACKET, WHICH HAS A HOLE FOR THE UPPER LT ENGINE MOUNT BOLT. BRACKET WAS CRACKED COMPLETELY IN TO TWO PARTS. PART WITH BOLT HOLE HAD SHEARED THE TWO RIVET THAT ATTACH BRACKET TO STRINGER ASSY. ENGINE MOUNT UPPER LEFT WHEN ALLOWED ENGINE WEIGHT TO PULL FIREWALL FORWARD. SUSPECT HARD LANDING AT SOME TIME IN PAST. 1H71 3O NT3A12 20020724000032002072400003SO 2002 7 24 2002FA0000849 120020718G5313 STRINGER PIPER PA24 PA24250 7102404SO LYC O540 O540* 41532EA FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW196174P 241275 DURNING ANNUAL INSPECTION FOUND RIVETS SHEARED AND MISSING FROM HOLES ON RIGHT REAR WING SPAR ATTACH FITTING ASSY. THIS ASSEMBLY IS ATTACHED TO CENTER SECTION. CARRY THRU UNDER BAGGAGE COMPARTMENT FLOOR. ALSO ON THIS AC THE STRINGER WAS CRACKED AND BUCKLED. THIS STRINGER IS ATTACHED TO THE RIGHT FRONT WING ATTACH POINT, PREVIOUSLY THE BULKHEAD ASSY (PN 20614-11) HAD BEEN REPLACED. THIS IS ANOTHER RIGHT FRONT WING ATTACH POINT BRACKET. 1L71 3O3 O 1A15 E295 20020724000042002072400004SO 2002 7 24 2002FA0000851 120020705G2400 WIRE PIPER PA34 PA34200 7103405SO LYC O320 O320A2B 41508EA MAIN POWER SHORTED G A UNSCHED LANDING AB FLAME/FIRE SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 SO0543134 347450150 L874427 ON APPROACH TO LANDING, PILOT REPORTED ELECTRICAL FIRE UNDER INSTRUMENT PANEL. COCKPIT FILLED WITH SMOKE AND FLAMES WERE NOTED UNDER PANEL BEHIND GLOVE BOX. PILOT WAS ABLE TO LAND THE AIRCRAFT BUT THE FIRE DESTROYED THE AIRCRAFT. THE POWER WIRE FROM THE RELAY ON THE FIREWALL WAS BURNED FROM THE RELAY TO THE POINT WHERE IT GOES THROUGH THE FIREWALL. 1L72 3O3 O A7SO E274 20020724000052002072400005CE 2002 7 24 2002FA0000852 120020705G7160 DOOR CESSNA177 177RG 2073709CE ALTERNATE AIR SEPARATED G O OTHER DYJINFLIGHT SEPARATION ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 EA178200G3126 177RG0100 ALTERNATE AIR DOOR CAME LOOSE FROM PLENUM CHAMBER. DOOR WENT INTO FUEL SERVO INLET, CAUSING ENGINE TO QUIT. 1H71 3O A20CE 20020724000062002072400006EU 2002 7 24 2002FA0000853 120020723G7820 MUFFLER GROB G115 G115C 1660303EU LYC O320 O320D1A 41508EA SNSNCH74D 74DM EA EXHAUST STACK SEPARATED D A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 WP03115FN 82061C1 L1838939A A55759 RT MUFFLER/EXHAUST LITERALLY FELL APART IN FLIGHT. BEYOND REPAIR. THE INLET FLANGE/PIPE ASSEMBLY COMPLETELY BROKE LOOSE FROM THE MUFFLER BODY. THE EXHAUST HANGAR, A RUBBER STRAP, WAS THE ONLY PART SECURING THE MUFFLER BODY TO THE AIRFRAME. THIS PART WAS PREVIOUSLY REPLACED APPROXIMATELY 500 HOUR PREVIOUSLY. THIS IS A CHRONIC PROBLEM WITH THESE MAKES AND MODELS AIRCRAFT. REPLACEMENT PARTS ARE NOT READILY AVAILABLE. AIRCRAFT WAS AOG FOR THREE WEEKS. 1L71 3O3 ONTA57EU E274 5 NP88614 20020729000052002072900005SW 2002 7 29 2002FA0000854 120020708G325135021505 VALVE SWRNGNSA226 SA226T 8780122SW STEERING UNIT FAILED C W6NRK NONE L NO TEST ININSP/MAINT 1 GL25117CC T325 OVERHAULED VALVE FAILED SHOP GROUND TEST. VALVE (SN 493A), FAILED ON FIRST LANDING, CAUSING AN UNCONTROLABLE SHIMMY IN STEERING OF AIRCRAFT, VIOLANT SHAKING. 2L72 4T RTA5SW 20020729000062002072900006CE 2002 7 29 2002FA0000855 120020614G27606511711023 LINE CESSNA500 550 2076604CE SPEED BRAKE CHAFED G CNQ6K NONE O OTHER ININSP/MAINT 1 EA25316CS308 5501010 FRESH AIR DUCT IN TAILCONE FOUND CHAFING AGAINST SPEED BRAKE CONTROL LINES. 1L72 4F A22CE 20020729000072002072900007EA 2002 7 29 2002FA0000857 220020515G7414M3827 GEAR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA MAGNETO CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15412ER1286 172S8643 MAGNETO ROTOR GEAR FOUND CRACKED ON INSPECTION. 1H71 3O3 ONT3A12 1E10 20020729000082002072900008CE 2002 7 29 2002FA0000859 120020713G322099101397 ACTUATOR CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO NLG CONTAMINATED G O OTHER O OTHER TXTAXI/GRND HDL 1 GL152664T 414A0623 UPON LANDING ROLLOUT NOSE GEAR COLLAPED. INVESTIGATION INDICATED ACTUATOR CONTAMINATED BY WATER. CHEVRON SEALS WORN, AND DOWN LOCK SWITCH DETERIORATED. SUSPECT ACTUATOR FROZE IN FLIGHT FROM COLD TEMPERATURES. ACTUATOR OVERHAULED. NO FURTHER PROBLEM. 1L72 3O3 O A7CE E8CE 20020729000102002072900010SO 2002 7 29 2002FA0000861 120020626G3210AN6H14A401462 BOLT PIPER PA38 PA38112 7103812SO RT MLG FAILED B KRTRO OTHER O OTHER TXTAXI/GRND HDL 1 SO092356A619 3878A0652 RT MLG DEPARTED AIRCRAFT DURING LANDING. FORWARD CLAMP BOLT FAILED CAUSING LANDING GEAR TO ROTATE FROM ITS PROPER LOCATION. BOLT WAS FOUND WITH A SHEAR TYPE FAILURE. 1L71 3O A18SO 20020729000112002072900011EU 2002 7 29 2002FA0000862 120020625G632032030004 OIL FILTER SNIAS 350 AS350B2 8680813EU M/R GEARBOX MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SW15455AE 3509 MAIN GEAR BOX OIL FILTER USED ON CERTAIN A/C HAVE A TAB TACK WELDED TO THE FILTER CASING SO SAFETY WIRE CAN BE ATTACHED. ON 5/30/02, 3 OF THESE FILTER HAD THE SAFETY WIRE TABS FALL OFF BEFORE THE FILTERS WERE INSTALLED. MFG WAS NOTIFIED OF THIS PROBLEM. 1G71 3U H9EU 20020729000122002072900012CE 2002 7 29 2002FA0000863 120020522G322095824019 BRACE BEECH 58 58 1152740CE NLG FAILED D O OTHER O OTHER TXTAXI/GRND HDL 1 GL056577S5131 TH712 NOSE RETRACT BRACE FAILED ALLOWING NOSE GEAR TO RETRACT UPON LANDING. 1L72 3O 3A16 20020729000132002072900013SW 2002 7 29 2002FA0000864 120020702G5310 STRUCTURE MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA FUSELAGE CORRODED G K NONE O OTHER ININSP/MAINT 1 SW116363Q 670446 HEADLINER EACH LOCATION THE HEADLINER MATERIAL CAME INTO CONTACT WITH ALUMINUM ATTACH POINTS THE AREA CORRODED THE INTERIOR WAS REPLACED IN THE SUBJECT AIRCRAFT ON MAY 1, 1998 THE CORROSION WAS DISCOVERED DURING MAINTENANCE MAY 17, 2002. 1L71 3O3 O 2A3 1E10 20020729000142002072900014SO 2002 7 29 2002FA0000865 220020714G7414 SPRING BEECH 36 A36 1151604CE CONT O520 IO520BB 17032SO IMPULSE COUPLIN BROKEN B K NONE L NO TEST ININSP/MAINT 1 GL251859A1958 E1929 248569R PILOT REPORTED SMOOTH 200 RPM DROP ON LT MAGNETO DURING RUN UP. TROUBLESHOOTING FOUND LT MAGNETO TIMING 7 DEGREES RETARDED. MAGNETO WAS REMOVED AND IMPULSE COUPLING FOUND TO HAVE A BROKEN SPRING. COUPLING WAS REPLACED WITH A NEW UNIT. 1L71 3O3 O 3A15 E5CE 20020729000152002072900015SO 2002 7 29 2002FA0000866 120020702G3210AN717A401511 BOLT PIPER PA38 PA38112 7103812SO LYC O235 O235* 41505EA MLG DAMAGED B KRTRK NONE O OTHER ININSP/MAINT 1 SO092589B6684 3879A0135 MLG ATTACH BOLTS WERE REMOVED FOR INSPECTION DUE TO AN INCIDENT THAT OCCURED ON 6/17/02 WITH A SAME MODEL AIRCRAFT. FOUND THE INBOARD GEAR ATTACH BOLTS FOR BOTH MAIN LANDING GEAR BENT IN THE SHANK AREA. ONE BOLT HAD ITS SHANK DISPLACED APPROX. .012 OF AN INCH. SECOND BOLT SHANK WAS DISPLACED APPPROX. .008. 1L71 3O3 O A18SO E223 20020729000162002072900016EA 2002 7 29 2002FA0000868 220020701G732070145401 SERVO CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA FUEL INJECTION INOPERATIVE D K NONE L NO TEST ININSP/MAINT 1 GL13996RA 17280404 L2745951A AFTER RECEIVING THE ENGINE BACK FROM MFG, YELLOW TAGGED, STICKERED IN THE LOG BOOK AIRWORTHY, REINSTALLED ENGINE. GROUND RUN FOR LEAKS BUT WOULD NOT IDLE SMOOTH UNTIL IDLE/MIXTURE WAS SET AT 625 RPM. OK`D TEST FLIGHT AND IT QUIT ON LANDING. THIS AIRCRAFT DID THIS ONCE BEFORE WITH SAME PILOT, MADE SOME ADJUSTMENTS AND SENT IT UP WITH ANOTHER PILOT TELLING HIM TO WATCH FOR RECURRING RICHENED OPERATION. HE WAS ABLE TO COMPLETE TEST HOP SUCCESSFULLY WITH USE OF MIXTURE CONTROL. AFTER CALLING MFG, REMOVED SERVO PER SI. 1H71 3O3 ONT3A12 1E10 20020729000172002072900017SO 2002 7 29 2002FA0000869 120020627G812046C19839F BLADE PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA TURBOCHARGER FAILED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 EA0796PP 870 4636120 L985461A PILOT REPORTED LOSS OF POWER AT FLIGHT OF 18,000 FT. REGAINED POWER AT 9,000 FEET AND LANDED. INSPECTED, FOUND EXHAUST SIDE OF TURBO BLADE BROKEN OFF AND TURBO WAS SEIZED. 1L71 3O3 ORTA25SO E14EA 20020729000182002072900018CE 2002 7 29 2002FA0000870 120020604G7160C2945100501 AIR FILTER CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA INDUCTION SYS MISINSTALLED B H4SRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO355105U 172RG0239 INSPECTED AIRCRAFT FOLLOWING PURCHASE FOR FLIGHT SCHOOL. DISCOVERED INDUCTION AIR FILTER INSTALLED BACKWARDS. HOUSING IS EVEN LABELED FOR AIRFLOW WITH AN ARROW. HOUSING WAS IN BACKWARDS ALSO. WITH ARROW POINTING FORWARD AWAY FROM THE CARB TOWARDS THE INSIDE. 1H71 3O3 O 3A17 E286 20020729000192002072900019SW 2002 7 29 2002FA0000871 120020614G6510MS21042L4 NUT BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL T/R DRIVESHAFT UNSECURE B VE3RO OTHER EW VIBRATION/BUFFET INADEQUATE Q C NRNOT REPORTED 1 WP2383WP 4431 51359 PILOT COMPLAINED OF MEDIUM FREQUENCY VIBRATION. VIBRATION WAS ISOLATED TO THE TAIL ROTOR DRIVE SHAFT 5TH SEGMENT. THE MS21042L4 NUT THAT SECURES THE HANGER BEARING ON THE SHAFT HAD LOST TORQUE. THIS ALLOWED THE BEARING INNER RACE TO SPIN ON THE SHAFT, RUINING THE SHAFT. THE NUT HAD 5 INCH LBS. OF TORQUE. THERE HAD BEEN NO PREVIOUS MAINTENANCE IN THIS AREA EXCEPT INSPECTIONS. THE SHAFT, ADAPTER, AND THE HANGER BEARING HAD TO BE REPLACED. 1G71 3U3 U H2SW E1GL 20020729000202002072900020SO 2002 7 29 2002FA0000872 120020701G3210 BOLT PIPER PA31 PA31350 7103110SO LYC O541 TIO541* 41536EA PARK GEAR INOPERATIVE D K NONE O OTHER ININSP/MAINT 1 NM084237D9270 317305055 (PARK GEAR EXTENSION RETRACT) ACTUATOR BROKE .2500 BOLT THAT HOLDS FORK THAT RELEASES GEAR UNLOCK GEAR WOULD NOT RETRACT. 1L72 3O3 O A20SO E10EA 20020729000032002072900003SO 2002 7 29 2002FA0000873 120020726G5711 SPAR PIPER PA28 PA28235 7102810SO LYC O540 O540B4B5 41532EA WING CRACKED C K NONE O OTHER ININSP/MAINT 1 WP318536N 2811335 DURING ANNUAL INSPECTION SB1006 PERFORMED. FOUND CRACKS AND CORROSION IN AFT REAR SPAR FLANGE-APPROX 3 INCHES OUTBOARD OF LANDING GEAR ATTACH. CAUSE DUE TO STANDING WATER IN WING. FIX BY ADDING DRAIN HOLE IN THIS AREA. 1L71 3O3 O 2A13 E295 20020730000082002073000008GL 2002 7 30 2002FA0000874 320020701G6114745255 HUB CESSNA310 310R 2074245CE MCAULY3AF32C3AF32C87 GL PROPELLER CRACKED B S6PRK NONE O OTHER ININSP/MAINT 1 SO19333BS 133 310R0865 745255 PROPELLER SENT TO OUR REPAIR STATION FOR RED DYE LEAK CHECK. PROPELLER WAS DISASSEMBLED AND INSPECTED NR 1 AND NR 3 BLADE FERRULE WERE DRILLED TOO DEEP. NR 2 BLADE SOCKET WAS FILLED WITH RTV. NR 2 BLADE BEARING AND BALLS AND FERRULE WERE CONDEMNED FOR RUST FROM RTV. PROPELLER HUB WAS CRACKED. UN-AIRWORTHY PARTS RETURNED TO CUSTOMER. 1L72 3O 3A10 5 CP22EA 20020730000092002073000009GL 2002 7 30 2002FA0000875 320020509G6114777290 HUB CESSNA206 U206G 2073356CE CONT O520 IO520* 17032SO MCAULYD3A34 D3A34C404 GL PROPELLER CORRODED B S6PRK NONE O OTHER ININSP/MAINT 1 SO09756JX 187 U20604138 777290 PROPELLER CAME IN REPAIR STATION BECAUSE IT WOULD NOT CHANGE PITCH. THE PROPELLER WAS DISASSEMBLED. PROPELLER WAS FULL OF RUST, ALL STEEL PARTS WERE CONDEMNED. PROPELLER BLADES AND HUB WERE CONDEMNED FOR EXTENSIVE CORROSION. THE PROPELLER WAS FOUND TO BE UNAIRWORTHY AND RETURNED TO CUSTOMER. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020730000102002073000010GL 2002 7 30 2002FA0000876 320020702G6114D5347 HUB CESSNA206 P206C 2073312CE CONT O520 IO520* 17032SO MCAULY2A34C E2A34C73 GL PROPELLER CRACKED B S6PRK NONE O OTHER ININSP/MAINT 1 SO098630Z 1520 P2060430 737174 PROPELLER CAME IN OUR REPAIR STATION FOR RED DYE LEAK. PROPELLER WAS DISASSEMBLED AND INSPECTED. PROPELLER HUB WAS FOUND TO BE CRACKED IN THE NR 2 BLADE SOCKET. 1H71 3O3 O A4CE E5CE 5 CP3EA9 20020730000112002073000011WP 2002 7 30 2002FA0000877 220020715G723030740962 DISK GARRTTTFE731TFE731* 01518WP COMPRESSOR OUT OF TOLERANCEB UO2RK NONE W INADEQUATE Q C ININSP/MAINT 1 GL19 NEW COMPRESSOR WHEEL RECEIVED FROM HONEYWELL WITH DAMAGE GREATER THAN .001 INCHES BY FIR TREE AREA. 4 F E6WE 20020730000122002073000012WP 2002 7 30 2002FA0000878 220020715G725030723973 TURBINE WHEEL GARRTTTFE731TFE731* 01518WP 3RD LPC DISK GOUGED B UO2RK NONE O OTHER ININSP/MAINT 1 GL19 NEW TURBINE DISK RECEIVED FROM HONEYWELL WITH SCRATCHES/GOUGES ON FORWARD WEB BY CURVIC TEETH. 4 F E6WE 20020730001212002073000121NE 2002 7 30 2002FA0000881 220020427G732032448094 FUEL CONTROL CESSNA208 208 2073702CE PWA PT6 PT6A114A 52043NE THRUST BEARING FAILED B IG0RO OTHER FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 NM03 PILOT REPORTED LOSS OF ENGINE CONTROL. INVESTIGATION REVEALED A THRUST BEARING (PN 2523973) FAILURE INSIDE THE FUEL CONTROL. 1H71 3T3 TNTA37CE E4EA 20020812001302002081200130EA 2002 8 12 2002FA0000882 220020422G8530 PISTON CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 SO166376M493 15284698 L1508115 THIS ENGINE SENT BACK TO THE FACTORY FOR METAL CONTAMINATION AND REWORKED THERE. ALL NEW CYLINDERS INSTALLED. 1H71 3O3 ONT3A19 E223 20020812001312002081200131CE 2002 8 12 2002FA0000883 120020702G32461540320 SEAL BEECH 36 A36 1151604CE CONT O550 IO550* SO NLG BEARING CORRODED D K NONE O OTHER ININSP/MAINT 1 GL253243B1049 E3243 RT NOSE WHEEL BEARING, CORRODED. BEARING SEAL NOT INSTALLED ON BEARING SECURELY. THE SEAL RESTS AGAINST THE BEARING. WATER EASILY GETS INTO BEARING. BEARING CORRODES AND SPINS ON AXLE. HAD TO REPLACE AXLE. REPAIR STATION SAID THE MANUFACTURED THE SEAL TO MFG. INSTRUCTIONS AND IF THERE IS A PROBLEM IT IS A MFG PROBLEM. 1L71 3O3 O 3A15 E3SO 20020812001322002081200132CE 2002 8 12 2002FA0000884 120020723G531204120081 BULKHEAD CESSNA150 150M 2071830CE CONT O200 O200* 17020SO TAILCONE CRACKED D ET9TK NONE O OTHER ININSP/MAINT 1 NM07888082730 15076150 CRACKS THROUGH BULKHEAD. TIE DOWN PROBLEMS/ LANDINGS TAIL LOW. REPETITIVE TAIL LOW LANDINGS. 1H71 3O3 O 3A19 E252 20020812001332002081200133SO 2002 8 12 2002FA0000887 220020701G8530TSIO520VB CYLINDER CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO ENGINE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW071233T 402C0805 CRACK BETWEEN SPARK PLUG HOLE AND INJECTOR HOLE. 1L72 3O3 O A7CE E8CE 20020813000012002081300001SO 2002 8 13 2002FA0000889 220020528G7414 IMPULSE COUPLINGSLICK 6310 CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MAGNETO FAILED D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 WP271080M1749 97012222 18266034 249972R LEFT MAGNETO IMPULSE COUPLING FAILED IN FLIGHT. COUPLING PAWS BROKEN FROM BODY AND CAUSED MAGNETO CASE TO BREAK AT MOUNT PAD. MAGNETO MADE METAL INTO ENGINE BEFORE FAILING. WHEN AIRCRAFT PICKED UP AT HANGAR, NO OIL REGISTERED ON DIP STICK. 1H71 3O3 ONT3A13 E273 20020813000022002081300002SO 2002 8 13 2002FA0000890 120020715G2140A23D04475 REGULATOR PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA HEATER FUEL LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 SO05350PC42 318152006 FOUND AIRCRAFT HEATER FUEL PRESSURE REGULATOR LEAKING WHILE SERVICING AIRCRAFT HEATER. THIS UNIT INSTALLED NEW, MAY 2002, WITH 42 HOURS OF HEATER OPERATION. THIS UNIT ALSO HAD AD AND SB, COMPLIED WITH AT UNIT INSTALL (NEW TYPE FUEL PRESSURE REGULATOR). 1L72 3O3 O A20SO E14EA 20020813000032002081300003CE 2002 8 13 2002FA0000891 120020723G3250AN3H BOLT CESSNA206 TU206F 2073353CE CONT O520 IO520* 17032SO NLG STEERING SHEARED G O OTHER O OTHER LDLANDING 1 AL018763Q U20603516 ON LANDING, AIRCRAFT EXITED RUNWAY BECAUSE NOSE GEAR STEERING WAS LOST. NO DAMAGE OR INJURIES. MECHANIC FOUND STEERING COLLAR ATTACHING FORWARD BOLT SHEARED. STRUT APPEARED TO BE OVER INFLATED CAUSING BOLT TO SHEAR WHEN TOWED IN THIS CONDITION. SERVICED STRUT AND REPLACED BOLT. CHECKED OK. 1H71 3O3 O A4CE E5CE 20020813000042002081300004 2002 8 13 2002FA0000894 420020620G6113055032111 BULKHEAD CESSNA172 172S 2072439CE PROP SPINNER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL03792SP35 172S8717 DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT THE SPINNER BULKHEAD WAS CRACKED. 1H71 3O NT3A12 20020813000052002081300005NE 2002 8 13 2002FA0000895 220020724G73231528232 SPRING WOODWARD LYC LTS101LTS101600A3 41560NE O/S GOVERNOR BROKEN B OL3RO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 WP27 2122350 ENGINE WILL NOT ACCELERATE ABOVE 90 PERCENT NP. FOUND SPEEDER SPRING BROKEN IN HALF. 3 U E5NE 20020813000062002081300006CE 2002 8 13 2002FA0000897 120020712G5751512400097 ANGLE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO AILERON SEPARATED D K NONE O OTHER ININSP/MAINT 1 NE014652N 402C0011 COULD NOT MOVE AILERONS. 90 PERCENT ANGLE, USED TO PREVENT OIL CANNING, BONDED INSIDE AILERON, BROKE LOOSE AND WORKED ITS WAY DOWN TRAILING EDGE OF AILERON AND INTO FLAP TRAILING EDGE, PREVENTING AILERONS FROM MOVING. 90 PERCENT ANGLE IS 8 INCHES LONG AND .3750 WIDE, .016 THICK. AILERON WAS REPLACED. 1L72 3O3 O A7CE E8CE 20020813000072002081300007EA 2002 8 13 2002FA0000898 220020722G7532MS924530 COTTER PIN PWA PT6 PT6A27 52043EA BLEED VALVE BROKEN B UE5RK NONE O OTHER ININSP/MAINT 1 NE01 DURING TEARDOWN OF COMPONENT TO CLEAN FOR AN OVERHAUL INSPECTION, BROKEN PIECES OF COTTER PIN WERE FOUND. THE PISTON GUIDE PIN WAS LOOSE INSIDE. THE GUIDE PIN IS HELD IN THE COVER BY A PRESSFIT AND THE COTTER PIN, NORMALLY. THE COVER, GUIDE PIN AND COTTER PIN WILL BE SCRAPPED. A SERVICEABLE COVER WILL BE USED TO REPLACE THE SCRAPPED PARTS. 4 T E4EA 20020813000082002081300008CE 2002 8 13 2002FA0000899 120020723G5741MS1782612 NUT CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA WING ATTACH CRACKED B QF1RK NONE O OTHER ININSP/MAINT 1 NE03208TW1022 208B0671 FOUND RIGHT LOWER WING STRUT ATTACH HARDWARE LIGHTLY CORRODED. FURTHER INSPECTION FOUND THAT NUT WAS COMPLETELY CRACKED THROUGH. NEW NUT AND BOLT INSTALLED. PART MAY HAVE BEEN OVERTORQUED UPON INSTALLATION. 1H71 3T3 T A37CE E2NE 20020813000092002081300009CE 2002 8 13 2002FA0000900 120020708G561010138402517 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE COCKPIT FAILED G BA EMER. DESCENT UNSCHED LANDING O OTHER CRCRUISE 1 NE01525SK BB1148 IN CRUISE RIGHT WINDSHIELD SHATTERED FOLLOWED BY EMERGENCY DESCENT. UPON AFTER LANDING INSPECTION LEFT W/S OBSERVED TO HAVE A 2 X 4.7500 INCH PEEL CHIP FAILURE, UPPER LEFT CORNER. CAUSE OF PEEL CHIP FAILURE OF INNER GLASS LAMINATION WAS AN INTERNAL STRESS BUILT INTO THE WINDSHIELD AT MANUFACTURE PER TRIDENT ENGINEERING ASSOC. 1L72 4T4 T A24CE E4EA 20020813000102002081300010CE 2002 8 13 2002FA0000901 120020708G561010138402522 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE COCKPIT FAILED G O OTHER O OTHER CRCRUISE 1 NE01525SK BB1148 IN CRUISE AT WINDSHIELD SHATTERED, WINDSHIELD REMOVED AND SUBMITTED FOR EXAMINATION ( PEEL CHIP OR SPALLING FAILURES OF THE INNER LAMINATION OF BOTH WINDSHIELDS WAS AN INTERNAL STRESS BUILT INTO THE WINDSHIELDS AT MANUFACTURE. 1L72 4T4 T A24CE E4EA 20020813000112002081300011WP 2002 8 13 2002FA0000906 120020227G5246 LOCK LKHEED18 1856 5261642WP ACCESS PANEL CHAFED B K NONE O OTHER ININSP/MAINT 1 NE03669 2044 FORWARD EXT. ACCESS PANEL LOCK ASSEMBLY CHAFES DOOR LATCH WHEN PANEL IS IN THE OPEN POSITION. REMOVED MATERIAL FROM ARM OF LOCK ASSY TO PROVIDE CLEARANCE, OPS CHECK COMPLETED NO CHAFING NOTED PER B/P 1159B50000. COMPLIED WITH ENGINEERS DISPOSITION PER SR PH TEST COMPLIED WITH 7.0 2L72 4R RTA723 20020813000122002081300012WP 2002 8 13 2002FA0000907 120020227G56201159CE5000155 WINDOW LKHEED18 1856 5261642WP WRIGHTR1820 GR1820G2 67020EA CABIN CRACKED B K NONE O OTHER ININSP/MAINT 1 NE03669 2044 NR 3 RIGHT CABIN WINDOW INNER PANE IS CRACKED. REMOVED AND REPLACED CABIN WINDOW. LEAK CHECK GOOD. 2L72 4R4 RRTA723 TC157 20020813000132002081300013WP 2002 8 13 2002FA0000908 120020227G5230 CABLE LKHEED18 1856 5261642WP WRIGHTR1820 GR1820G2 67020EA CARGO DOOR MISROUTED B K NONE W INADEQUATE Q C ININSP/MAINT 1 NE03669 2044 BAGGAGE DOOR MAKES A VIBRATION NOISE WHEN DOOR IS OPENED APPROX .5000 TO .7500 OPEN POSITION. DOOR APPEARS TO BE CHAFING JUST BEFORE CLOSING. FOUND AFT CABLE NOT ROUTED PROPERLY GOING TO BAGGAGE DOOR, ROUTED CABLE OPS CHECK COMPLIED WITH, CHECKED OK. 2L72 4R4 RRTA723 TC157 20020906001982002090600198GL 2002 9 6 2002FA0000910 120020313G14301159WM5153511 SCREW AMTR WOODHSPSE1 GL LT WING INCORRECT B K NONE O OTHER ININSP/MAINT 1 NE03670 LEFT WING (D) TRACK ABOVE INBOARD EDGE 4 SCREWS TOO SHORT IN COVE PANEL. SHORT SCREWS AND INSTALLED CORRECT SCREWS PER B/P. 1M00 EXPA1M00 20020813000142002081300014SO 2002 8 13 2002FA0000911 120020717G7810LW1277885 WASTEGATE VALVE PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA LT ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 NE054045491 277305167 L482761A LT ENGINE EXHAUST BACK PRESSURE SEPARATED (PN LW 11657) WASTE GATE MALE FROM (PN LW 11656) FEMALE. (PN LW 1165) U BOLT WAS NOT LOOSE. 1L72 3O3 O 1A10 E14EA 20020813000152002081300015EA 2002 8 13 2002FA0000912 220020719G8530 RETAINER CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA NR 5 CYLINDER MISSING D K NONE O OTHER ININSP/MAINT 1 WP23300WF641 18280015 L2594348A NR 3 CYLINDER PUSH ROD BENT, REMOVED THE NR 5 CYLINDER VALVE COVER FOR FURTHER INSPECTION AND FOUND PUSH ROD RETAINING CLIP MISSING AND ASSOCIATED HARDWARE. NO DAMAGE OR PARTS FOUND 1H71 3O3 ONT3A13 1E4 20020813000162002081300016CE 2002 8 13 2002FA0000915 120020613G215073838426 ACM CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE ACM BAY DAMAGED C O OTHER O OTHER NRNOT REPORTED 1 EA074 4517 5600113 PILOT REPORTED INSUFFICIENT COOLING TO THE CABIN. UPON VISUAL INSPECTION OF THE AIR CYCLE MACHINE (ACM) IT WAS NOTICED THAT ONE OF THE THREE FAN BLADES WAS BROKEN OFF THE HUB. AFTER REMOVAL OF THE ACM IT WAS FURTHER DISCOVERED THAT THE SHAFT HAD SHEARED INTERNALLY AND THE COMPRESSOR BLADES WERE DAMAGED. 2L72 4F4 FRTA22CE E25EA 20020813000172002081300017EA 2002 8 13 2002FA0000916 220020723G7322HA6105235 CARBURETOR CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA ENGINE LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 GL256183T 772 R18201930 L2111440A PILOT BROUGHT IN AIRCRAFT WITH ROUGH RUNNING ENGINE. ENGINE WOULD SURGE BELOW 900 RPM AND MIXTURE CONTROL WOULD NOT SHUT DOWN ENGINE. FOUND FUEL DRIPPING FROM CARBURETOR THROAT. THE CARBURETOR WAS REPLACED AND OPERATION RETURNED TO NORMAL. 1H71 3O3 ORT3A13 E295 20020813000182002081300018CE 2002 8 13 2002FA0000919 120020614G3260 DOWNLOCK SWITCH BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE NLG FAILED B L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 WP03400HS594 RK314 NOSE LANDING GEAR DOWNLOCK LIGHT DID NOT COME ON AFTER DEPLOYMENT OF LANDING GEAR. GEAR CYCLED SEVERAL TIMES AND STILL NO DOWN AND LOCK LIGHT ILLUMINATION. TOWER FLY BY PERFORMED AND CONFIRMED DEPLOYMENT. AIRCRAFT LANDED SAFELY. NEW SWITCH INSTALLED. 2H72 4F4 FRTA16SW E25EA 20020813000192002081300019CE 2002 8 13 2002FA0000920 120020719G2110585550111 BRACKET BEECH 58 58 1152740CE CONT O550 IO550C SO A/C COMPRESSOR CRACKED B AWKRK NONE O OTHER ININSP/MAINT 1 WP25658DG94 TH2017 685248 DURING 100 HOUR INSPECTION FO THE LT ENGINE, THE UPPER ARM OF THE AIR CONDITION COMPRESSOR BRACKET WAS FOUND TO BE CRACKED. IT APPEARS AS IF IT WAS NOT SHIMMED CORRECTLY. DURING INITIAL INSTALATION WHICH PRELOADED THE ARM AND CRACKED. C/A: PROPERLY SHIM BRACKET TO PREVENT PRELOAD. 1L72 3O3 O 3A16 E3SO 20020813000202002081300020SO 2002 8 13 2002FA0000921 120020723G55116697500 SPAR PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA HORIZONTAL STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 GL231631913800 287305224 HORIZONTAL STAB REAR SPAR CRACKED HALF WAY ACROSS. 5 INCHES ABOVE FUSELAGE. NO SIGN OF BEING HIT OR EXTERIOR DAMAGE. 1L71 3O3 O 2A13 E286 20020813000302002081300030CE 2002 8 13 2002FA0000925 120020703G30603E20901 BRUSH BLOCK BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE PROPELLER INOPERATIVE B PIYRO OTHER O OTHER NRNOT REPORTED 1 EA0987SA 5 BB1089 PCE93030 AFTER PROPELLER OVERHAUL AND PROPELLER DE-ICE BRUSH REPLACEMENT, PILOT REPORTED DEICE SYSTEM CIRCUIT/BREAKER SWITCH TRIPPED IN FLIGHT. COULD NOT DUPLICATE PROBLEM ON GROUND WITH ENGINES RUNNING. INSPECTED SYSTEM AND FOUND IF SIDE PRESSURE WS APPLIED TO RIGHT BRUSH BLOCK STACK, THE WASHERS ON THE WIRING ATTACH SCREWS WOULD SHORT TOGETHER TRIPPING THE SWITCH. A NYLON SPACER IS USED TO RAISE ONE OF THE TERMINALS TO PREVENT THIS FROM HAPPENING, BUT THE DIFFERENCE IN HEIGHT WAS NOT SUFFICIENT IN THIS CASE. A SLIGHTLY TALLER NYLON SPACER WAS USED TO INCREASE CLEARANCE. THE AIRCRAFT WAS FLOWN AND PROPELLER DEICE SYSTEM OPERATION WAS NORMAL. 1L72 4T4 T A24CE E4EA 20020813000432002081300043EA 2002 8 13 2002FA0000927 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA CYLINDER WORN D K NONE O OTHER ININSP/MAINT 1 SO156376M400 15284698 L1508115 CYLINDER 1 AND 3 DAMAGED DUE TO PISTON PIN WEAR. ALUMINUM IF FILTER TOTAL TIME ON CYLINDERS WAS 400 HR. TSMOH FOR ENGINE 1095.3, OCCURED 9/26/01 INSTALLED CHROME CYLINDERS. 1H71 3O3 ONT3A19 E223 20020813000452002081300045EA 2002 8 13 2002FA0000928 120020510G29106047523879 LINE CNDAIRCL604 CL604 1900301EA GE CF34 CF34* NE NR 2 HYD SYS CHAFED C K NONE O OTHER ININSP/MAINT 1 NE03788SC 5391 LOST ALL NR 2 HYDRAULIC FLUID AT CRUISE FL 37 AFTER 3 HOURS IN FLIGHT. LEAK TRACED TO NR 2 EDB CASE DRAIN RETURNED LINE TUBE ASSEMBLY. REPLACED LINE, BLED AND LEAK CHECKED, NO LEAKS NOTED. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020813000462002081300046EA 2002 8 13 2002FA0000929 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA NR 1 CYLINDER WORN D K NONE O OTHER ININSP/MAINT 1 SO155416M381 15284584 L1675415 REMOVED NR 1 CLYINDER DUE TO POSTON PIN CAP WEAR INSTALLED CHROME CYLINDER ASSEMBLY OCCURED 02/15/2002. 1H71 3O3 ONT3A19 E223 20020813000482002081300048EA 2002 8 13 2002FA0000930 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA NR 1 CYLINDER WORN D K NONE O OTHER ININSP/MAINT 1 SO155416M 15284584 L1675415 REMOVED NR 1 CYLINDER. INSTALLED ANEW PISTON PIN CAPS/ WEAR WAS NOT NORMAL. THIS ENGINE FACTORY OVERHAUL 9/24. OCCURED 11/3/98 1H71 3O3 ONT3A19 E223 20020813000502002081300050EA 2002 8 13 2002FA0000931 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 SO155416M1470 15284584 L1675415 FACTORY OVERHAUL 24-9. INSTALLED ALL NEW FACTORY NEW CYLINDERS DUE TO METAL CONTAMINATION FROM PISTON PIN CAPS. OCCURRED 05/07/2001 1H71 3O3 ONT3A19 E223 20020813000512002081300051EA 2002 8 13 2002FA0000932 220020422G8530 CAP CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA NR 1 CYLINDER WORN D K NONE O OTHER ININSP/MAINT 1 SO155403H1800 15284096 L1672515 FACTORY OVERHAUL 02/28/96. OCCURRED 12/26/00. REMOVED NR 1 CYLINDER METAL IN FILTER, CAPS WORN. INSTALLED NEW FACTORY CYLINDER. 1H71 3O3 ONT3A19 E223 20020813000522002081300052EA 2002 8 13 2002FA0000933 220020422G8530 CAP CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA PISTON PIN WORN D K NONE O OTHER ININSP/MAINT 1 SO155403H1700 15284096 L1672515 FACTORY OVERHAUL ENGINE 02/28/96. RIGHT NR 2, 3 CYLINDERS HAD SOME WEAR IN PINS, NOT BAD. HAND INSTALLED NEW CAPS AND RINGS. OCCURED 10/05/00 1H71 3O3 ONT3A19 E223 20020813000542002081300054EA 2002 8 13 2002FA0000934 220020401G8530 CAP CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA PISTON PIN WORN D K NONE O OTHER ININSP/MAINT 1 SO155403H680 15284096 L1672515 FACTORY OVERHAUL 02/28/96. RIGHT NR 2 CYLINDER DUE TO PISTON PIN WEAR. INSTALLED CHROME CYLINDER. 04/01/02 1H71 3O3 ONT3A19 E223 20020813000562002081300056EA 2002 8 13 2002FA0000935 220020422G8530 CAP CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA PISTON PIN WORN D K NONE O OTHER ININSP/MAINT 1 SO155403H500 15284096 L1672515 REMOVED NR 1 CYLINDER DUE TO PISTON PIN CAP WEAR, INSTALLED CHROME CYLINDER. FACTORY OVERHAUL 02/28/90 1H71 3O3 ONT3A19 E223 20020813000582002081300058EA 2002 8 13 2002FA0000936 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 SO15946622000 15285757 FACTORY OVERHAUL 12/96. REMOVED ENGINE FOR ALUMINUM CONTAMINATION. NR 1 PISTON PIN WEAR, NR 3 PISTON PIN WEAR. 1H71 3O3 ONT3A19 E223 20020813000592002081300059EA 2002 8 13 2002FA0000937 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA ENGINE WORN D K NONE O OTHER ININSP/MAINT 1 SO15946621550 15285757 1174615 FACTORY OVERHAUL 12/96. REMOVED AND REPLACED NR 4 CYLINDER DUE TO PISTON PIN WEAR/ CYLINDER RIDGE. DATE OF OCCURANCE 01/00. 1H71 3O3 ONT3A19 E223 20020813000612002081300061EA 2002 8 13 2002FA0000938 220020412G8530 CAP CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA PISTON PIN WORN D K NONE O OTHER ININSP/MAINT 1 SO15946621000 15285757 1174615 FOUND ALUMINUM IN FILTER REMOVED AND REPLACED NR 2 CYLINDER DUE TO PISTON PIN WEAR FROM RIDGE IN CYLINDER. DATE OF OCCURANCE 11/98 1H71 3O3 ONT3A19 E223 20020813000622002081300062EA 2002 8 13 2002FA0000939 220020412G8530 CAP CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA PISTON PIN WORN D K NONE O OTHER ININSP/MAINT 1 SO1594662700 15285757 1174615 THIS ENGINE FACTORY OVERHAUL 12/96. ALUMINUM IN FILTER, NR 1 CYLINDER WEARS A RIDGE FROM RING IN FORWARD SIDE THEN THE RIDGE WEARS PISTON PIN. DATE OF OCCURANCE 03/98 1H71 3O3 ONT3A19 E223 20020813000632002081300063EA 2002 8 13 2002FA0000940 220020422G8530 PISTON PIN CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA NR 1 CYLINDER WORN D K NONE O OTHER ININSP/MAINT 1 SO1594662299 15285757 L2486615 FACTORY ENGINE OVERHAUL O1/01. ALUMINUM IN FILTER DUE TO NR 1 PISTON PIN WEAR. 1H71 3O3 ONT3A19 E223 20020813000642002081300064SO 2002 8 13 2002FA0000943 120020322G2497CM358950 SWITCH BALWKSFIREFYFIREFLY7 1050100SO AVIONICS MASTER FAILED G K NONE O OTHER ININSP/MAINT 1 NE024066A 10016 (AVIONICS BUS SWITCH) INDICATIONS SHOW A SWITCH MANUFACTURING OR LOAD PROBLEM AND SHOULD BE INVESTIGATED. 1B00 A14SO 20020813000652002081300065CE 2002 8 13 2002FA0000951 120020311G2497CM358950 SWITCH CESSNA402 402C 207590RCE AVIONICS BUS FAILED G K NONE O OTHER ININSP/MAINT 1 NE02812AN 402C0229 (AVIONICS BUS SWITCH) INDICATIONS SHOW A SWITCH MANUFACTURING OR LOAD PROBLEM AND SHOULD BE INVESTIGATED. 1L72 3O A7CE 20020813000662002081300066EA 2002 8 13 2002FA0000952 220020619G8530 CYLINDER LYC O540 TIO540J2BD 41532EA NR 3 LOOSE D K NONE O OTHER ININSP/MAINT 1 NM08 L669361A (NR 3 CYLINDER) NR 3 CYLINDER CAME LOOSE FROM CASEHALF. ROD STILL CONNECTED TO CRANKSHAFT. 3 O E14EA 20020813000672002081300067SO 2002 8 13 2002FA0000953 220020724G8530631996 RETAINER PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO ROCKER SHAFT CRACKED C BUWAK NONE O OTHER ININSP/MAINT 1 EA079712C178 347870211 306405 DURING AN ANNUAL INSPECTION, ONE ROCKER BOX COVER ON THE LEFT ENGINE WAS REMOVED IN THE PROCESS OF REPLACING PUSHROD TUBE SEALS. DISCOVERED ONE ROCKER SHAFT RETAINER CRACKED INTO TWO PIECES. DECIDED TO INSPECT REMAINDER OF CYLINDERS AND FOUND 19 OF 24 ROCKER SHAFT RETAINERS EITHER COMPLETELY CRACKED IN HALF OR ALMOST CRACKED IN HALF. ELECTED TO REPLACE ASS RETAINERS AT THIS TIME. THIS IS AN AREA THAT IS NOT NORMALLY ACCESSED DURING A NORMAL ANNUAL. SUSPECT THAT THE CAUSE MAY HAVE BEEN OVER-TORQUE ON THE NUTS HOLDING THE RETAINERS. 1L72 3O3 O A7SO E9CE 20020813000682002081300068 2002 8 13 2002FA0000954 420020625G31607011674119 SYMBOL GENERATOR RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE731* 01518WP NR 1 FAILED C O OTHER O OTHER CLCLIMB 1 GL0729B 667 258518 AFTER TAKEOFF, CAPTAINS EADI AND EHSI WENT BLANK. TROUBLESHOOTING REVEALED NR 1 SYMBOL GENERATOR HAD FAILED. UNIT (SN98071444) WAS INSTALLED.UNIT FAILED ON INSTALL. UNIT (SN 99081612) WAS INSTALLED. THIS UNIT FAILED AFTER 30 MIN OF OPERATION. UNIT (SN 91110731 WAS INSTALLED. THIS UNIT FAILED AFTER 1.5 HOURS OF OPERATION. ORIGINAL UNIT (SN 00111758) WAS INSTALLED AFTER REPAIR BY THE MANUFACTURER. THIS UNIT CONTINUES IN SERVICE. IT IS TO BE NOTED THAT ALL FAILURES HAD DIFFERENT SYMPTOMS. ALL UNITS WERE REPAIRED BY THE MANUFACTURER. THEIR SERVICE REPORTS INDICATED THAT NO DEFECTS WERE NOTED DURING BENCH TESTS AND WERE RETURNED TO SERVICE. 2L72 4F4 FRTA3EU E6WE 20020813000692002081300069GL 2002 8 13 2002FA0000955 120020724G575035128001 STOP AVIAT A1 A1A 2210405GL LYC O360 O360C1G 41514EA TE FLAPS CRACKED B EZ6RK NONE O OTHER ININSP/MAINT 1 NM11961864048 1186 L3056236A DURING FLAP HANDLE REPLACEMENT, THE FLAP SETTING STOP ASSY WAS REMOVED AND A CRACK WAS FOUND IN THE FULL FLAP NOTCH AND FAILURE OF THE ASSY WAS FORTHCOMING. THIS SAME STOP ASSY HAD BEEN REMOVED 128.7 HOURS EARLIER FOR FLAP SYSTEM INSPECTION AND NO CRACK WAS PRESENT AT THAT TIME. THIS WOULD BE THE SECOND FLAP STOP ASSY FAILURE DUE TO CRACKING FOUND BY THIS SHOP. 1H71 3O3 ONCA22NM E286 20020813000702002081300070 2002 8 13 2002FA0000956 420020627G2562 BATTERY BEECH 76 76 1153005CE ELT CONTAMINATED D K NONE O OTHER ININSP/MAINT 1 NM016701R ME281 UNDER ANNUAL INSPECTION DURING BATTERY OPS CHECK, NO READING. FURTHER INSPECTION OF BATTERY PACK REVEALED WATER INSIDE BATTERY AND ELT COMPARTMENTS. THERE WAS NO EVIDENCE OF WATER IN ELT ATTACHING TRAY. 1L72 3O A29CE 20020813000712002081300071CE 2002 8 13 2002FA0000958 120020318G2140CA14071 IGNITER CESSNA402 402B 207590PCE HEATER OVERHEATED D H DEACTIVATE SYST/CIRCUITS MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 NM01402CA 402B0842 NITE IMC HAD SUDDEN ELECTRIAL SMELL AND SMOKE IN COCKPIT. PILOT SHUT DOWN TOTAL ELECTRICAL SYSTEM SMELL AND SMOKE CLEARED. WHILE TROUBLESHOOTING FOUND INGNITION UNIT ON HEATER HAD OVERHEATED AND STARTED TO MELT DOWN CHANGED UNIT SYSTEM OPS CHECKED GOOD. 1L72 3O A7CE 20020812001222002081200122EA 2002 8 12 2002FA0000959 120020728G2823 SELECTOR VALVE PERTH BIRD BIRDCK 6840132EA COCKPIT FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CLCLIMB 1 EA2199754 4006 4545 DURING TAKE OFF, THE ENGINE SUDDENLY STOPPED RUNNING AT ALTITUDE OF 200 TO 300 FEET. ATTEMPTED TURN AROUND AND LAND WITHOUT SUCCESS. PILOT STATED THAT FUEL SELECTOR WAS IN THE ON POSITION. DURING A POST ACCIDENT ENGINE TEST RUN, IT APPEARED THAT THE FUEL SELECTOR VALVE WHEN SELECTED TO THE "ON" POSITION, DOES NOT ALLOW FULL FLOW THROUGH THE VALVE. WHEN THE FUEL SELECTOR VALVE WAS SELECTED 3/8 INCH PAST THE "ON" POSITION, THE VALVE APPARENTLY FLOWS ENOUGH FUEL TO MAINTAIN FULL ENGINE RPM. THE FUEL SELECTOR VALVE IS NOT A DETENT TYPE VALVE. IT IS NOT MARKED AS TO THE MANUFACTURER OR WITH A PART NUMBER. THIS AIRCRAFT IS AN ANTIQUE BIPLANE WHICH WAS BUILT IN 1931. 1Q71 3R ATC388 20020812001232002081200123CE 2002 8 12 2002FA0000962 120020731G304057033 MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE BLOWER FAILED G H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 EA0380AW 2991 5500186 ON DECENT, THE COPILOT DETECTED AN ODOR THAT APPEARED TO BE ELECTRICAL IN ORIGIN. THE CHECKLIST WAS EXECUTED AND THE ODOR WAS ELIMINATED. MAINTENANCE FOUND AND REPLACED THE INOP BLOWER FAN AND RETURNED THE AIRCRAFT BACK TO SERVICE. TBO FOR THIS PART IS 3500 HRS. AND THE PART REMOVED HAD 2991 HRS. THE CIRCUIT BREAKER FOR THIS CIRCUIT DID NOT TRIP IN OTHER REPORTS HAD SIMILIAR RESULTS. 1L72 4F4 F A22CE E1NE 20020812001242002081200124SO 2002 8 12 2002FA0000964 120020809G2900AN833 FITTING GULSTMG1159 G1159B 3953535SO HYD SYSTEM SCORED B A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 SW01344GW7953 7953 344 COMBINED HYDRAULIC SYSTEM INDICATED LOW QUANITY PRESSURE 330PSI TEE FITTING SCORED ON HYD LINE. 2L72 4F RTA12EA 20020816000012002081600001CE 2002 8 16 2002FA0000965 120020729G2130E45C47 SWITCH LEAR 35 36A 5170603CE CABIN PRESSURE FAILED D K NONE O OTHER ININSP/MAINT 1 SW11 ANEROID SWITCH FAIL SPECIFIC PRESSURE LIMITS. 2L72 4F A10CE 20020816000022002081600002CE 2002 8 16 2002FA0000966 120020729G2130E45C47 SWITCH LEAR 35 36A 5170603CE CABIN PRESSURE FAILED D K NONE O OTHER ININSP/MAINT 1 SW11 ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS. 2L72 4F A10CE 20020816000032002081600003CE 2002 8 16 2002FA0000967 120020729G2130E45C47 SWITCH LEAR 35 36A 5170603CE CABIN PRESSURE FAILED D K NONE O OTHER ININSP/MAINT 1 SW11 ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS. 2L72 4F A10CE 20020816000042002081600004CE 2002 8 16 2002FA0000968 120020729G2130E45C47 SWITCH LEAR 35 36A 5170603CE CABIN PRESSURE FAILED D K NONE O OTHER ININSP/MAINT 1 SW11 ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS. 2L72 4F A10CE 20020816000052002081600005CE 2002 8 16 2002FA0000969 120020729G2130E45C47 SWITCH LEAR 35 36A 5170603CE CABIN PRESSURE FAILED D K NONE O OTHER ININSP/MAINT 1 SW11 ANEROID SWITCH FAILED SPECIFIC PRESSURE LIMITS. 2L72 4F A10CE 20020816000062002081600006SO 2002 8 16 2002FA0000970 220020729G85706533608R PUMP CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO COOLING WATER FAILED D TVMRK NONE O OTHER ININSP/MAINT 1 EA05500AA 414A0313 8000652 THIS AIRCRAFT HAS RAM WATER COOLED ENGINE. LEFT ENGINE WATER PUMP FAILED. 1L72 3O3 O A7CE E8CE 20020826000082002082600008SO 2002 8 26 2002FA0000972 120020816G2497 ELECTRICAL BOX PIPER PA46 PA46500TP 7104622SO COCKPIT LOOSE B O OTHER IG FLT. ATTITUDE INST. MULTIPLE FAILURE CRCRUISE 1 SO15264B 251 4697028 ENGINE DISPLAY UNITS, PILOT'S PRIMARY FLIGHT DISPLAY, COPILOT'S PRIMARY FLIGHT DISPLAY AND COPILOT'S NAV DISPLAY DIMMED OUT OF VIEW DURING CRUISE AT FL240. PILOT REPORTED THAT DIMMING WAS AFFECTED BY OPERATION OF CABIN HEAT. FOUND TAPER BLOCK (TB4) TO HAVE LOOSE PINS. THIS IS A DISTRIBUTION BLOCK FOR AIRCRAFT LCD DIMMING. 1L71 3O RTA25SO 20020826000092002082600009SO 2002 8 26 2002FA0000973 220020606G8520 CRANKCASE CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ENGINE CRACKED B CY4RK NONE O OTHER ININSP/MAINT 1 AL036124Z4047 685 U20606150 574729 CRACK 1.3750 INCH OUT OF THE UPPER REAR CYLINDER BASE STUD, AT THE ONE OCLOCK POSITION. 1H71 3O3 O A4CE E5CE 20020826000102002082600010CE 2002 8 26 2002FA0000974 120020801G32139530489 AXLE HELIO H295 H295 4300802CE LYC O480 GO480* 41527EA RT MLG BROKEN G K NONE O OTHER ININSP/MAINT 1 AL0150718 1268 RIGHT GEAR AXLE BROKE (MAIN) ON LANDING, CAUSING SUBSTANTIAL DAMAGE TO FUSELAGE GEAR ATTACH AREA. 1H71 3O3 O 1A8 E275 20020826000112002082600011WP 2002 8 26 2002FA0000975 220020806G855021713T009 HOSE AYRES S2 S2RG10 0970217SO GARRTTTPE331TPE331* 01514WP OIL TANK VENT DETERIORATED B XR5RK NONE O OTHER ININSP/MAINT 1 EA07402611945 G10158 (HOSE) DURING ROUTINE MAINTENANCE, THE .5000 INCH OVERBOARD VENT HOSE FROM THE ENGINE OIL TANK WAS FOUND TO BE RESTRICTED. THE .5000 HOSE, WAS REDUCED TO .1250 OR LESS DIAMETER WHERE IT PASSED FROM THE OIL TANK, ALONG THE GAS GENERATOR. THE COMBINATION OF HEAT AND OIL MIST IS CAUSING THE DETERIORATION OF THE INSIDE OF THE HOSE. THIS IS NOT THE FIRST OCCURRECE OF THIS PROBLEM. RECOMMEND THAT THE MANUFACTURER INSTALL A .5000 INCH ALUMINUM TUBE IN PLACE OF THE HOSE FROM THE OIL TANK PAST THE ENGINE (APPROXIMATELY 3.5 FT), WHERE THE HOSE COULD THEN BE USED. 1L71 3T3 TNCA4SW E2WE 20020826000122002082600012 2002 8 26 2002FA0000976 420020604G6113055032111 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA PROP SPINNER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL03792SP386 172S8717 DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT THE SPINNER BULKHEAD WAS CRACKED. 1H71 3O3 ONT3A12 1E10 20020826000132002082600013 2002 8 26 2002FA0000977 420020516G6113055032111 BULKHEAD CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA PROP SPINNER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL035138731 172S9013 DURING A PRE-FLIGHT INSPECTION THE PILOT NOTED THAT SPINNER BULKHEAD WAS CRACKED. 1H71 3O3 ONT3A12 1E10 20020826000142002082600014SO 2002 8 26 2002FA0000978 220020731G8520 CRANKCASE CONT O520 IO520D 17032SO ENGINE CRACKED B O3ORK NONE O OTHER ININSP/MAINT 1 AL03 552755 DURING OVERHAUL. THE LIQUID PENETRANT INSPECTION REVEALS CRACKS IN MAIN BEARING BOSSES, CENTER ON LEFT SIDE. DOWN IN OIL CHANNEL RADIUS. THIS CRANKCASE IS PHASE III 7TH STUD STYLE. 3 O E5CE 20020826000152002082600015 2002 8 26 2002FA0000979 420020717G3421C6610550103 INDICATOR CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO COCKPIT LEAKING B MINRO OTHER O OTHER NRNOT REPORTED 1 NM0579CE 414A0263 AIRCRAFT LOST GYRO INSTRUMENTS AFTER TAKEOFF INTO IFR CONDITIONS. TROUBLESHOT PROBLEM AND FOUND CO-PILOTS ART HORIZON CASE LEAKING. CABIN PRESSURE DURING CLIMBOUT PRESSURIZED VACUUM SYSTEM CAUSING VACUUM FAILURE. 1L72 3O3 O A7CE E8CE 20020826000162002082600016SO 2002 8 26 2002FA0000980 120020802G7160 FLANGE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA AIR BOX FAILED B QE5RK NONE O OTHER ININSP/MAINT 1 NM07978WC400 4496041 4496041 THE COMPONENT AS DESCRIBED WAS BROUGHT FOR INSPECTION AND WARRANTY REPAIR DUE TO FAILURE OF MOUNTING FLANGE TO THE TUBE. THE MOUNTING FLANGE SEPARATED FROM THE TUBE IN THE HEAT AFFECTED ZONE OF THE ATTACHING WELD. ADDITIONAL CONDITIONS THAT CONTRIBUTED TO THE FAILURE IS THE TUBE IS BEADED AT THIS ATTACH POINT. THE TUBE BASE MATERIAL APPEARS TO BE STRETCHED AND STRUCTURALLY CHALLENGED DUE TO BEADING OF THE TUBE. THE AIR BOX WAS INSPECTED IAW SB AND NO PROBLEM WAS OBSERVED. AN ADDITIONAL CRACK WAS REPAIRED ON THE MOUNTING EAR OF THE FLANGE. 1L72 3O3 O A19S0 E286 20020826000172002082600017EA 2002 8 26 2002FA0000981 220020813G8520SL13521 ROD END BEARING BEECH 76 76 1153005CE LYC O360 O360A1G6D EA ENGINE SEPARATED B ZM3RK NONE O OTHER ININSP/MAINT 1 WP0766340549 ME241 L2645736A METAL CONTAMINATION FOUND IN SUCTION SCREEN AND FILTER. DISASSEMBLY OF ENGINE NOTED BABBIT SEPERATION FROM NR 1 ROD CAP BEARING SHELL. THE REMAINDER OF THE OTHER ROD BEARINGS SHOWED SIGNS OF STARTING TO SEPARATE. 1L72 3O3 O A29CE E286 20020826000222002082600022EA 2002 8 26 2002FA0000982 220020813G8520SL16711 BEARING CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE SEPARATED B ZM3RK NONE O OTHER ININSP/MAINT 1 WP07502ER974 172S8002 L2781636A CONTAMINATION FOUND IN SUCTION SCREEN. DISASSEMBLY OF ENGINE FOUND ONE OF THE CENTER MAIN BEARINGS BABBIT MATERIAL STARTED TO SEPARATE FROM SHELL. DATE CODE ON BEARING IS (07-2000). 1H71 3O3 ONT3A12 1E10 20020826000232002082600023SO 2002 8 26 2002FA0000983 120020816G29105777402 LINE PIPER PA42 PA42720 7104212SO PWA PT6 PT6* 52043EA HYD SYSTEM CHAFED B MVJRO OTHER KJ FLUID LOSS WARNING INDICATION LDLANDING 1 GL2575FL 4516 428301002 DURING LANDING THE PILOT SELECTED GEAR DOWN, WITH NO RESPONSE FROM SYSTEM. THE PILOT SUCCESSFULLY PUT GEAR DOWN WITH EMERGENCY BLOW DOWN SYSTEM AND A SAFE LANDING WAS MADE. MAINTENANCE FOUND LEFT INBOARD PORTION OF WING COVERED IN HYDRAULIC FLUID. UPON REMOVAL OF WING LEADING EDGE AND NACELLE PANELS THE LEAK WAS TRACED TO MAIN PRESSURE LINE FROM ENGINE DRIVEN PUMP. THE LINE WAS CHAFED THROUGH AT POINT WEAR IT ENTERS THE WING FROM NACELLE. THE CHAFE CAME FROM SCREW THAT WAS TO LONG IN LEADING EDGE TO NACELLE PANEL (PN 7261602) THIS PANEL SELDEM NEEDS REMOVED AND ON SOME LIKE AC IT IS RIVETED ON. THIS AREA SHOULD HAVE A CLOSE LOOK AT IT AT INSPECTION AND SCREW LENGTHS CHECKED. 1L72 4T3 T A23SO E2NE 20020826000332002082600033SO 2002 8 26 2002FA0000984 120020801G29106390170 LINE PIPER PA34 PA34200 7103405SO LYC O360 IO360A1A 41514EA NLG DETERIORATED B O0BRO OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 WP09159257209 347350109 THE AIRCRAFTS NOSE GEAR FAILED TO EXTEND DURING ROUTINE TRAINING FLIGHT. A/C MADE LANDING WITHOUT NOSE GEAR EXTENDING. PILOT WAS ABLE TO FEATHER RIGHT ENGINE BUT LEFT SUFFERED A MINOR PROP STRIKE. INSPECTION OF A/C ON THE RUNWAY REVELED THAT GEAR WAS FREE TO MOVE, HOWEVER IT WAS HELD IN UP POSITION WITH HYDRAULIC PRESSURE. ONLY AFTER PRESSURE WAS RELIEVED FROM THE NOSE GEAR ACTUATOR DID GEAR EXTEND AND LOOK. A/C WAS PLACED ON JACKS AND CONTAMINATION (RUBBER PARTICLES AND OTHER DEBRIS) WAS REMOVED FROM THE OUTLET OF THE NOSE GEAR DOWN FLEX HOSE. HOSE WAS REMOVED AND INSPECTION REVEALED INTERNAL LINING WAS DETERIORATING AND COLLAPSING. SYSTEM WAS FLUSHED, SERVICED AND OPS CHECK PERFORMED SATISFACTORILY. 1L72 3O3 O A7SO 1E10 20020826000432002082600043CE 2002 8 26 2002FA0000985 120020712G251005142132 LOCK CESSNA172 172R 2072401CE SEAT BACK WEAK B Z08RK NONE O OTHER ININSP/MAINT 1 CE079710F 17280017 THE LOCK CYLINDER RECLINE MECHANSIM BECOMES WEAK OVER TIME. SEAT BACK WOULD RECLINE ABRUPTLY WHEN PRESSURE WAS APPLIED TO THE SEAT BACK, SUCH AS TAKEOFF. THIS COULD CAUSE THE PILOT TO LOOSE CONTROL OF THE AIRCRAFT. 1H71 3O NT3A12 20020826000472002082600047SO 2002 8 26 2002FA0000986 120020805G32308360607 TRUNNION PIPER PA46 PA46350P 7104602SO NLG CRACKED B HW4RK NONE O OTHER ININSP/MAINT 1 SO159167R1913 4622032 DURING ANNUAL INSPECTION FOUND CRACK IN NOSE LANDING GEAR TRUNION WHERE ACTUATOR ATTATCHES MAY BE CAUSED FROM TOWING AIRCRAFT OR HAND LANDING. RECOMMEND CLOSE INSPECTION OF THIS AREA. 1L71 3O RTA25SO 20020826000642002082600064SO 2002 8 26 2002FA0000989 220020814G74146220 MAGNETO CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO ENGINE CORRODED B GBBRK NONE O OTHER ININSP/MAINT 1 NM1159132 21060112 517861 DURING MAINTENANCE, IT WAS NOTED THAT THE MAGNETOS WERE HAVING TROUBLE HOLDING THEIR TIMING POSITIONS. RT MAGNETO WAS DISASSEMBLED AND FOUND THAT THE DRIVE AND DRIVEN GEARS HAD ROTTED TO THE POINT OF LOSING TEETH. NOTED THAT THE CARBON BUTTON THAT RIDES ON THE COIL TAB HAD WORN THROUGH AND THE BUSHINGS THAT SUPPORT THE DISTRIBUTOR GEAR HAD BEEN SEVERELY WORN. ALL OF THE INTERNAL HARDWARE WAS SEVERELY CORRODED. BOTH POINT CAMS WERE BADLY WORN AND THE POINTS WERE WORN TO THE POINT OF BEING INOPERATIVE. DEFECTS WERE FOUND IN RT AND LT MAGNETOS. THE DRAIN FOR MAGNETO PRESSURIZATION FILTER HAD BEEN SILICONED CLOSED. 1H71 3O3 O 3A21 E8CE 20020826000652002082600065SO 2002 8 26 2002FA0000990 220020814G74146220 MAGNETO CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO ENGINE CORRODED B GBBRK NONE O OTHER ININSP/MAINT 1 NM1159132 21060112 517861 DURING MAINTENANCE, ITS WAS NOTED THAT THE MAGNETOS WERE HAVING TROUBLE HOLDING THEIR TIMING POSITIONS. RT MAGNETO WAS DISASSEMBLED AND FOUND THAT THE DRIVE AND DRIVEN GEARS HAD ROTTED TO THE POINT OF LOSING TEETH. NOTED THAT THE CARBON BUTTON THAT RIDES ON THE COIL TAB HAD WORN THROUGH AND THE BUSHINGS THAT SUPPORT THE DISTRIBUTOR GEAR HAD BEEN SEVERELY WORN. ALL OF THE INTERNAL HARDWARE WAS SEVERELY CORRODED. BOTH POINT CAMS WERE BADLY WORN AND THE POINTS WERE WORN TO THE POINT OF BEING INOPERATIVE. DEFECTS WERE FOUND IN RIGHT AND LEFT MAGNETOS. THE DRAIN FOR MAGNETO PRESSURIZATION FILTER HAD BEEN SILICONED CLOSED. 1H71 3O3 O 3A21 E8CE 20020826000662002082600066WP 2002 8 26 2002FA0000991 220020715G7532HTE49029A SEAL RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE7315R 01518WP BLEED VALVE FAILED D K NONE O OTHER ININSP/MAINT 1 WP23217AL 258177 AFTER TAKEOFF, DURING CLIMBOUT, PILOT REPORTED AFT EQUIPMENT BYA OVERHEAT LIGHT ON MASTER CAUTION WARNING PANEL ILLUMINATED. RETURNED TO PLACE OF ORIGIN. AFTER TROUBLESHOOTING, FOUND DETERIORATED BLEED VALVE SEAL AT RIGHT ENGINE BLEED AIR SHUTOFF VALVE IN AFT EQUIPMENT BAY. REPLACED DEFECTIVE SEAL WITH NEW SEAL. RAN BOTH ENGINES AT POWER AND PERFORMED OPERATIONAL AND LEAK CHECK. NO DISCREPANCIES NOTED. SUSPECT CAUSE OF DEFECT IS SHRINKAGE OF SEAL OVER PERIOD OF TIME. RECOMMEND PERIODIC BLEED AIR LEAK CHECKS AND TORQUE CHECKS OF BLEEDAIR MARMON CLAMPS. 2L72 4F4 FRTA3EU E6WE 20020826000682002082600068EA 2002 8 26 2002FA0000992 220020808G8520 PIN BEECH 60 B60 1153605CE LYC O541 TIO541E1C4 41536EA LIFTER/BORE FAILED G K NONE O OTHER ININSP/MAINT 1 SW15102SB80 P375 L61959 THE LIFTER BORES WERE ALL SLEEVED (ALL 12) NOTE: THE SLEEVES CAME LOOSE IN ALL THE HOLES (EXCEPT TWO) ROTATING AND BLOCKING OFF OIL PASSAGES. THERE WERE NO STANDARD SAFETY PINS, OR DEVICES TO HOLE THE LIFTER SLEEVE IN PLACE. THERE ARE MANY OTHER ENGINES IN SERVICE WITH THIS SAME REPAIR PRACTICE IN PLACE. 1L72 3O3 O A12CE E10EA 20020826000012002082600001NM 2002 8 26 2002FA0000993 120020706G5730P2V7 DOUBLER LKHEEDP2V P2V7 5260112NM WRIGHTR3350 R335042 EA RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 NM04139HP8782 145906 LOWER WING SKIN ACCESS PANEL CUTOUT DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE. RIGHT WING LOWER SKIN CRACKED AT AN ACCESS PANEL CWS 94. (SW) 2M72 2R4 RRTA1RM 20020826000022002082600002NM 2002 8 26 2002FA0000994 120020709G5730 DOUBLER LKHEEDP2V P2V7 5260112NM WRIGHTR3350 R335042 EA RT WING CRACKED B BZBRK NONE O OTHER ININSP/MAINT 1 NM04140HP9633 140443 LOWER WING SKIN ACCESS PANEL DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE. RIGHT WING LOWER SKIN CRACKED AT AN ACCESS PANEL AT CWS 94. (SW) 2M72 2R4 RRTA1RM 20020826000032002082600003SO 2002 8 26 2002FA0000995 120020627G5711 SPAR LKHEED282 C130A 5262502SO LT & RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 NM04133HP16959 570482 FRONT WING SPAR WEB WAS CRACKED IN THE SAME LOCATION ON BOTH WINGS JUST ABOVE THE LOWER SPAR CHORD AT THE LANDING GEAR BEAM 2H74 4T A31NM 20020826000042002082600004NM 2002 8 26 2002FA0000996 120020708G5730 DOUBLER LKHEEDP2V P2V7 5260112NM WRIGHTR3350 R335042 EA RT WING CRACKED B K NONE O OTHER ININSP/MAINT 1 NM04139HP 145906 LOWER WING SKIN ACCESS PANEL DOUBLER CRACKED IN SEVERAL PLACES CWS 90 LEFT SIDE TO CWS 90 RIGHT SIDE. RIGHT WING LOWER SKIN CRACKED AT AN ACCESS PANEL AT CWS 94. (SW) 2M72 2R4 RRTA1RM 20020826000052002082600005CE 2002 8 26 2002FA0000998 120020823G2810 SPACER CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO MCAULY3FF32 3FF32C501 GL FUEL CELL BURNED C K NONE O OTHER ININSP/MAINT 1 NM10 421C0031 608206H 891998 LT ENGINE AUX FUEL TANK ASSY HAS INCURRED HEAT RELATED DAMAGE ON THE ENGINE FIREWALL SIDE. THE FIRE SPACER SCREEN AND THE RETARDANT COATING ON THE TANK ASSY HAS SINGED AND MELTED ALONG THE FIREWALL SIDE AND UNDERSIDE OF ASSY. IN SOME AREAS THE COATING HAS RECEDED EXPOSING THE ALUMINUM LINER. THE VENT LINE FROM THE ENGINE HAS MELTED AN IMPRESSION INTO THE COATING. ADHESIVE USED TO SECURE THE TANK WAS SIMILIARLY DAMAGED. DAMAGE IS APPARENT BOTH ON THE TANK BODY AND IN THE CAVITY. 1L72 3O3 O A7CE E7CE 5 CP45GL 20020827000042002082700004EU 2002 8 27 2002FA0001000 120020808G5523115C1155 BRACKET GROB G115 G115C 1660303EU LYC O320 O320* 41508EA ELEVATOR TRIM CORRODED B GZERK NONE O OTHER ININSP/MAINT 1 GL07115SR1872 82036C SUBJECT PART IS A BRACKET MOUNTING, A TORQUE TUBE FOR THE ELEVATOR TRIM CONTROL SYSTEM TO THE REAR SPAR OF THE HORIZONTAL STABILIZER, AND WAS BEING REPLACED DURING COMPLIANCE OF MFG SB. PART WAS FOUND WITH SEVERE EXFOLIATION CORROSION OF THE ALUMINUM UNDER THE SURFACE PLATING. POSSIBLY A PROBLEM IN THE FABRICATION OF THE BASE MATERIAL OR THE PART ITSELF. CONDITION OF THIS COMPONENT SHOWS POTENTIAL FOR SAME PROBLEM TO BE FOUND ON COMPONENTS OF SIMILAR CONSTRUCTION ON THIS MODEL AIRCRAFT. 1L71 3O3 ONTA57EU E274 20020827000052002082700005EA 2002 8 27 2002FA0001001 220020808G8500 PLUG HUGHES269 269C1 8059504SW LYC O360 HO360C1A 41514EA PULLEY DRIVE MISSING E K NONE O OTHER ININSP/MAINT 1 SW05614261565 0062 L3448236A SCHEDULED INSPECTION AND MAINTENANCE, WHILE PERFORMING A COMPRESSION CHECK, IT WAS NOTED THAT THE ENGINE TURNING TOOL WENT INTO THE LOWER PULLEY DRIVE SPLINE FARTHER THAN NORMAL. FURTHER INVESTIGATION REVEALED THE ENGINE DRIVE SHAFT TO BE IMPROPERLY POSITIONED IN THE LOWER PULLEY. THE BELT DRIVE ASSEMBLY WAS REMOVED FROM THE HELICOPTER. EXAMINATION OF THE ENGINE-MOUNTED DRIVE ADAPTER REVEALED THE PN 77416 FORWARD LOWER COUPLING BUMPER PLUG WAS MISSING. THIS PLUG DETERMINES THE POSITION OF THE DRIVE SHAFT IN BOTH THE ENGINE AND THE LOWER PULLEY OF THE BELT DRIVE. 1G71 3O3 OO 4H12 E286 20020827000062002082700006CE 2002 8 27 2002FA0001002 120020729G2421 SCREW CESSNA185 A185F 2072821CE CONT O520 IO520* 17032SO ALTERNATOR MISSING D K NONE O OTHER ININSP/MAINT 1 AL03185BF 103 18503590 THIS OVERHAULED ALTERNATOR WAS INSTALLED 06/28/02 AT TACH:642.0. REMOVED 07/27/02 TACH:745.0. PILOT COMPLAINED OF LOW READING ON AMG GAUGE. UPON INSPECTION OF THE ALTERNATOR, FOUND 1 CASE SCREW MISSING AND THE OTHER 2 COMING OUT OF CASE HALF. THESE SCREWS WERE NOT SAFETY WIRED NOR DID THEY HAVE HOLES FOR WIRE. 1H71 3O3 O 3A24 E5CE 20020827000072002082700007EU 2002 8 27 2002FA0001003 120020801G24972N5684 TRANSISTOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE POWER REG UNIT INOPERATIVE C A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION NRNOT REPORTED 1 SW016088B3100 2691 9747 PILOT REPORTED AIRCRAFTS RADIOS BEGAN TO SHUT DOWN FOLLOWED BY THE INDICATORS BECOMING ERRATIC. PILOT BEGAN TO SHUT DOWN NON ESSENTIAL ELECTRICAL LOADS. ELECTRICAL SYSTEM BEGAN TO OPERATE NORMALLY. PILOT RETURNED TO MAINTENANCE FACILITY AND LANDED WITH NO FURTHER PROBLEMS NOTED. TECH. TROUBLESHOT PROBLEM ISOLATED TRANSISTOR IN POWER REGULATION UNIT. GROUND RUNS SHOWED NO DEFECT AFTER REPLACEMENT. 1G71 3U3 U H9EU E19EU 20020827000082002082700008EU 2002 8 27 2002FA0001004 120020801G2435 BRUSHES SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE STARTER GEN FAILED C A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 SW016088B2922 2691 9747 PILOT REPORTED ELECTRICAL SYSTEM FAILURE AND ACCOMPLISHED AN EMERGENCY LANDING AT AIRPORT. REMOVED STARTER/ GENERATOR, SUBSEQUEANT INSPECTION REVEALED ONE SET OF BRUSHES HAD FAILED. THE SESULT OF THIS WAS A GRADUAL DROP OF OUTPUT COMPENSATED FOR BY THE AIRCRAFT BATTERY UNTIL THE BATTERY WAS DEPLETED. 1G71 3U3 U H9EU E19EU 20020827000092002082700009CE 2002 8 27 2002FA0001005 120020813G2421 BEARING BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO ALTERNATOR FAILED G K NONE O OTHER ININSP/MAINT 1 GL21119RB1267 D8231 BEARING FAILURE IN ALTERNATOR CAUSED FAILURE OF CLUTCH ASSEMBLY. 1L71 3O3 O 3A15 E5CE 20020827000102002082700010SW 2002 8 27 2002FA0001006 120020716G6210407015001117 BLADE BELL 407 407 1182206SW ALLSN 250C 250C20 03013GL MAIN ROTOR DELAMINATED C A UNSCHED LANDING E VIBRATION/BUFFET NRNOT REPORTED 1 NM01175PA2967 53154 DURING HEAVY RAINFALL, AIRCRAFT EXPERIENCED VIBRATION ON MAIN ROTOR SYSTEM. PILOT PERFORMED A PRECAUTIONARY LANDING. MECHANIC INSPECTED THE MAIN ROTOR BLADES AFTER SHUT DOWN. MECHANIC FOUND BOTTOM SIDE OF ONE BLADE 2 INCHES AFT OF LEADING EDGE WITH METAL SKIN DELAMINATED FROM COMPOSITE BLADE. 1G71 3U3 UO H2SW E4CE 20020904000482002090400048CE 2002 9 4 2002FA0001011 120020628G2434DOFF10300JR PULLEY CESSNA172 172H 2072424CE CONT O300 O300* 17022SO ALTERNATOR LOOSE B N9VRK NONE O OTHER ININSP/MAINT 1 SO031684F 17255079 PILOT REPORTED NO ALTERNATOR OUTPUT. INSPECTION FOUND PULLEY LYING INSIDE COWLING FROM ALTERNATOR. ALTERNATOR STILL ON MOUNTS, BUT LOOSE. 1H71 3O3 ONT3A12 E253 20020904000492002090400049EA 2002 9 4 2002FA0001012 220020801G732048E21297EPAJAY CONTROLLER PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA MANIFOLD PRESS DAMAGED B N9VRK NONE O OTHER ININSP/MAINT 1 SO03944S 70211207 4636306 CONTROLLER HAD AXIAL PLAY ON SHAFT FOR CONTROL ARM. ENGINE WAS BACKING. 1L71 3O3 ORTA25SO E14EA 20020904000642002090400064SO 2002 9 4 2002FA0001016 220020816G8530646657A2 CYLINDER CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO NR 2 CRACKED C O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION LDLANDING 1 WP0758H 414A0314 UPON LANDING, PILOT REPORTED EXTREMELY ROUGH RUNNING ENGINE ON RIGHT SIDE. INSPECTED AND FOUND NR2 CYLINDER ON RIGHT SIDE TO BE CRACKED ALL THE WAY AROUND CYLINDER BETWEEN HEAD AND BARREL. PILOT ALSO REPORTED ENGINE HAD HIGH CHT JUST BEFORE CHT DROPPED TO (0). 1L72 3O3 O A7CE E8CE 20020904000662002090400066CE 2002 9 4 2002FA0001018 120020821G2434991059111 ALTERNATOR CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 SO117265Z116 17280769 THE ALTERNATORS INSTALLED ARE FAILING CONSISTENTLY. THEY USUALLY LAST BETWEEN 100 AND 500 HOURS FOR WHATEVER REASON THE RESISTANCE IN THE FIELD CIRCUIT INCREASES TO THE (MEGA OHM) RANGE, RENDERING THE ALTERNATOR TOTALLY INOPERATIVE DUE TO THE NATURE OF THE WARRANTY I AM NOT PERMITTED TO OPEN THE ALTERNATOR TO DETERMINE THE EXACT CAUSE. 1H71 3O3 ONT3A12 1E10 20020904000682002090400068CE 2002 9 4 2002FA0001026 120020821G2910 LINE CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA HYD SYSTEM FAILED D O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 EA0521PL R18201983 WHEN PILOT SELECTED GEAR DOWN AND PRESSURE WAS APPLIED TO DOWN HOSE. THE HOSE FAILED AT THE SWAGED END BLOWING ALL HYDRAULIC FLUID OVERBOARD. RECOMMEND CLOSER INSPECTION OF HOSES AND A MANDATORY TIME CHANGE OR BOTH HOSES. (PN S217840102) DOWN AND (PN S217840096) UP. 1H71 3O3 ORT3A13 E295 20020904000702002090400070NE 2002 9 4 2002FA0001027 220020729G7320 O-RING LYC LTS101LTS101750B2 41560NE ACTUATOR MISMANUFACTURED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO13 5952 12 503 WITHIN THE FIRST FEW HOURS OF OPERATION SINCE OVERHAUL/ REPAIR THE ACTUATOR WILL FAIL TO ACTUATE OR ENGINE WILL EXHIBIT TORQUE SPLITS. CAUSE: ORING/ PACKINGS USED DURING THE OVERHAUL/ REPAIR PROCESS. 3 U E5NE 20020919000122002091900012EA 2002 9 19 2002FA0001028 220020826G74146381 MAGNETO CESSNA182 T182T CE LYC O540 TIO540AK1A EA ENGINE DAMAGED B NM4RO OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 SO1524712205 T18208027 OWNER COMPAINED WHEN RT MAGNETO WAS SELECTED ENGINE WOULD QUIT. AFTER REMOVING MAGNETO FOUND MANY INTERNAL PARTS BURNED. REPLACED WITH NEW MAGNETO. 1H71 3O3 ONT3A13 20020904000442002090400044 2002 9 4 2002FA0001029 420020827G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM03789EP1801 172S8135 AIRCRAFT UNDERGOING PHASE 1 INSPECTION, MAINTENANCE FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED. A ONE INCH PIECE OF THE BULKHEAD WAS BROKEN OFF CONTAINING 1 NUTPLATE. REPLACED SPINNER BULKHEAD, REINSTALLED PROPELLER, OPERATIONAL CHECK SAT. 1H71 3O NT3A12 20020904000452002090400045SO 2002 9 4 2002FA0001030 220020829G8540653631 GEAR CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO MCAULYD3A34 D3A34C402 GL CRANKSHAFT DAMAGED D K NONE O OTHER ININSP/MAINT 1 WP235119X U20605571 818118R DURING PRE-FLIGHT INSPECTION PROPELLER WAS ROTATED BACKWARDS BY HAND TO CHECK COMPRESSION OF CYLINDERS. PROPELLER PHYSICALLY STOPPED BY SOMETHING INTERNAL IN ENGINE. AFTER INSPECTION BY REMOVING THE STARTER ADAPTER ASSEMBLY, THE CRANKSHAFT GEAR WAS FOUND TO BE MISSING ONE TOOTH FROM THE GEAR. 1H71 3O3 O A4CE E8CE 5 CP47GL 20020904000462002090400046SO 2002 9 4 2002FA0001032 220020903G8540626739 COLLAR CONT O520 IO520D 17032SO CRANKSHAFT MISMANUFACTURED B K NONE W INADEQUATE Q C ININSP/MAINT 1 WP07 282740R AT INSTALLATION OF A NEW GOVERNOR OIL TRANSFER COLLAR IT WAS DISCOVERED THAT THE ASSEMBLY HALVES WERE IRREGULAR AT THE PARTING SURFACE. THE INSIDE DIAMETER LOOKED SMOOTH AND REGULAR WHEN REMOVED FROM THE PACKAGE. ONCE DISASSEMBLED AND REASSEMBLED AND TORQUED, THE INSIDE DIAMETER AT THE PARTING SURFACE EXHIBITED A STEP AND BECAME TIGHT ON THE CRANKSHAFT JOURNAL. IT SEEMS THAT THE COLLAR WAS UNDER A STRESS THAT WAS RELIEVED AT THE FIRST DISASSEMBLY RESULTING IN THE MISALIGNMENT. ANOTHER NEW COLLAR WAS ORDERED AND IT SHOWED THE SAME PROBLEM AS WELL. 3 O E5CE 20020904000472002090400047SO 2002 9 4 2002FA0001033 220020903G8520654068 ROD BOLT CONT O520 IO520D 17032SO ENGINE STRETCHED B K NONE O OTHER ININSP/MAINT 1 WP07 566793 AT INSTALLATION OF THE NEW CONNECTING ROD BOLT AND NUT IT WAS NOTED THAT PROPER TORQUE WAS NOT ACHIEVED WITH THE SAME AMOUNT OF TURNS AS THE OTHER ROD BOLTS AND NUTS. A VISUAL INSPECTION SHOWED THAT MORE THREADS WERE SHOWING PAST THE NUT THAN OTHER BOLTS ON THE SAME CRANKSHAFT. THE BOLT MEASURED .054 INCH LONGER THAT THE ADJACENT BOLT ON THE CONNECTING ROD. UPON DISASSEMBLY A VISUAL INSPECTION SHOWED THE THREADS TO BE DEFORMED, THE SHANK NEAR THE HEAD EXHIBITED SIGNS OF STRETCHING AND THE BEARING FACE OF THE HEAD SHOWED SOME GALLING. IT IS POSSIBLE THE BOLT WAS SOFT AND NOT PROPERLY HEAT TREATED. 3 O E5CE 20020904001252002090400125CE 2002 9 4 2002FA0001034 120020823G323014141162 SPRING CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA NLG UPLOCK STRETCHED B EW0RK NONE O OTHER ININSP/MAINT 1 GL25350072867 177RG1036 DURING LANDING GEAR RETRACTION TEST, NOSE GEAR WOULD NOT FULLY RETRACT. THE BELLCRANK WAS FOUND OVERCENTER, CAUSING THE ROLLER TO MISS THE UPLOCK HOOK AND RESTRICT THE NOSE GEAR TRAVEL. THE SPRING WAS FOUND STRETCHED AND NOT PROVIDING ADEQUATE TENSION. THE SPRING WAS REPLACED AND OPERATION WAS NORMAL. THIS DEFECT CAUSED THE NOSE GEAR TO STAY PARTIALLY OUT OF THE WHEEL WELL AND THE GEAR DOORS TO REMAIN APPROXIMATELY 30 DEGREES OPEN. THIS COULD RESULT IN FAILURE OF THE DOORS AND POSSIBLE JAMMING OF THE NOSE GEAR. 1H71 3O3 O A20CE 1E10 20020904001552002090400155CE 2002 9 4 2002FA0001035 120020814G5511053200198 SPAR CESSNA172 172N 2072434CE LYC O320 O320* 41508EA HORIZONTAL STAB CRACKED D KM9SK NONE O OTHER ININSP/MAINT 1 NE016231D 17272649 CRACKS IN FORWARD OVERLAPPING SPARS FOUND AT LIGHTENING HOLE LOCATED IN CENTER OF HORIZONTAL STABILIZER. 100 HOUR INSPECTION WAS BEING PERFORMED ATH THIS TIME. UPON REMOVAL, ADDITIONAL CRACKS WER FOUND ON THE OVERLAPPING SKIN. THE ADDITIONAL CRACKS COULD NOT BE SEEN UNLESS HORIZONTAL STABILIZER IS REMOVED. PROBABLE CAUSE: HIGH STRESS IN FLIGHT OR PUSHING DON ON OUTBOARD OF TAL. POSITIVELY SURFACE CORROSION ALSO LOCATED IN THE AREA. 1H71 3O3 ONT3A12 E274 20020906001992002090600199CE 2002 9 6 2002FA0001036 120020901G2910208010015 HYDRAULIC LINE CESSNA177 177RG 2073709CE NLG SEPARATED D O OTHER K FLUID LOSS NRNOT REPORTED 1 GL052002Q 177RG0402 HOSE ASSEMBLY SEPARATED AT SWEDGED END/ AT ACTUATOR NO CHAFFING OR OTHER APPARENT WEAR ON HOSE. 1H71 3O A20CE 20020910001142002091000114 2002 9 10 2002FA0001037 420020905G3197 WIRE HARNESS CESSNA172 172R 2072401CE INSTUMENT PANEL CHAFED D K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 SO07 17280548 WHEN THE PILOTS CONTROL COLUMN WAS PULLED AFT AND ROTATED, THE AILERON CABLE TURNBUCKLES AND ASSOCIATED HARDWARE CHAFED AGAINST A WIRE BUNDLE FORWARD OF THE INSTRUMENT PANEL. THIS CAUSED TWO WIRES FROM THAT BUNDLE TO SHORT OUT AND BREAK, THUS RESULTING IN SPARKS COMING FROM UNDER THE INSTRUMENT PANEL. BOTH FUEL QUANTITY INDICATORS IMMEDIATELY LOST POWER AND WENT TO ZERO. 1H71 3O NT3A12 20020910001172002091000117NE 2002 9 10 2002FA0001038 220020905G72503040761 STATOR CESSNA500 S550 2076607CE PWA JT15 JT15D4 52112NE TURBINE SECTION CRACKED B K NONE O OTHER ININSP/MAINT 1 CE03550DS1755 1755 S5500154 PCE102316 AT HOT SECTION INSPECTION THE HT STATOR WAS FOUND TO HAVE AXIAL CRACKS IN SEVERAL PLACES IN THE INNER SHROUD RUNNING FROM THE TRAILING EDGE FORWARD TO 1/2IN. FROM INNER LUGS. AT ONE CRACK THE INNER SHROUD TRAILING EDGE LIFTED UP ENOUGH TO MAKE CONTACT WITH THE HT DISK FRONT FACE IN THE FIR TREE AREA. 1L72 4F4 FRTA22CE E1NE 20020910001222002091000122GL 2002 9 10 2002FA0001042 120020816G321010209001 GROMMET CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SO16415GE566 0067 DURING ANNUAL INSPECTION FOUND MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. SUGGEST CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS. 1L71 3O3 ONTA00009CHE3SO 20020910001232002091000123SO 2002 9 10 2002FA0001043 120020909G2913 PUMP PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCC4Y HCC4YR2 GL HYD SYSTEM FAILED D A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 GL07316GC 8152015 RL192368A THE RIGHT ENGINE HYDRAULIC PUMP FAILED SOON AFTER TAKE OFF. THE LANDING GEAR FAILED TO RETRACT FULLY. THE PILOT TRIED SEVERAL TIMES TO EXTEND THE LANDING GEAR, AND FINALLY MANAGED TO GET THEM ALL IN A SAFE DOWN AND LOCKED POSITION, TO MAKE A LANDING. UPON INVESTIGATION, IT WAS FOUND THAT THE HYDRAULIC PUMP DRIVE SHAFT SEAL WAS BROKEN. THIS WAS CAUSED BY A VALVE INSIDE THE PUMP THAT WAS STUCK IN THE OPEN POSITION, AND ALLOWED THE HYDRAULIC FLUID TO BE PUMPED OVERBOARD. PUMP MAY NOT HAVE BEEN CORRECTLY TESTED BY THE OVERHAULER. 1L72 3O3 O A20SO E14EA 5 CP52GL 20020910001242002091000124 2002 9 10 2002FA0001044 420020811G2561GA12P0201101 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 INDIVIDUAL FLOTATION DEVICE FAILED, MANUFACTURER RECOMMENDED PRESSURE TEST IAW MM. DOM: NOV 1984. 20020910001252002091000125NM 2002 9 10 2002FA0001045 120020715G5730143279 DOUBLER LKHEEDP2V P2V7 5260112NM WRIGHTR3350 972TC18DA* EA WING CRACKED B NI6RK NONE O OTHER ININSP/MAINT 1 NM051444710100 8010 DOUBLER FAILURE DUE TO IMPROPER MANUFACTURE PROCESS. DOUBLER BROKE AT MACHINE RADIUS AND CORNER OF FUEL ACCESS PANEL LOCATED IN LOWER INBOARD WING SKIN AREA. WING SKIN DEVELOPED CRACKS LOCALIZED TO CORNER OF ACCESS PANEL. REMOVED PAINT AND DYE PEN. INSPECTED ALL CORNERS OF PANELS. INSTALLED EXTERNAL DOUBLERS OVER SKIN CRACKED. (SW) 2M72 2R4 RRTA1RM 20020911000892002091100089EA 2002 9 11 2002FA0001046 220020823G853074230 VALVE GUIDE CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA EXHAUST SEIZED B VY2RK NONE O OTHER ININSP/MAINT 1 EA23926WB 18280819 L2758248 NR 2 CYLINDER EXHAUST VALVE SIEZED IN VALVE GUIDE POSSIBLY DUE TO CARBON BUILD UP. NR 2 PUSHROD AND PUSHROD SHROUD WERE BENT. NR 2 EXHAUST PLUNGER ALSO REPLACED AT MFG RECOMMENDATION. 1H71 3O3 ONT3A13 1E4 20020911000902002091100090SO 2002 9 11 2002FA0001047 220020718G8530641917 CYLINDER CONT C90 C9014F 17009SO ENGINE BROKEN D HBKAK NONE O OTHER ININSP/MAINT 1 GL21 2486 46942 THE ROCKER SHAFT ON THE EXHAUST PORT SIDE OF THE NR 1 CYLINDER FAILED. INSPECTION OF THE OTHER THREE CYLINDERS SHOWED LOOSE BUSHINGS IN THE SAME BOSS ON ALL THREE. THE VALVE SPRING SEAT (PN 24027) WAS ALSO BROKEN, APPARENTLY INCIDENTAL TO THE ROCKER SHAFT BOSS FAILURE. MORE FREQUENT DYE PENETRANT INSPECTION OF THE SUBJECT AREA IS NEEDED. 3 O E252 20020911000882002091100088GL 2002 9 11 2002FA0001048 120020910G321010209001 GROMMET CIRRUSSR SR22 2130001GL MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SW99248CG222 0092 DURING ANNUAL INSPECTION FOUND BOTH MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. SUGGEST CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS. 1L71 3O NTA00009CH 20020919000032002091900003CE 2002 9 19 2002FA0001054 120020822G323008421211 TUBE CESSNA320 320D 2074512CE CONT O520 IO520* 17032SO NLG DRIVE FAILED D O OTHER J WARNING INDICATION NRNOT REPORTED 1 WP09320F 320D0020 NOSE GEAR FAILED TO RETRACT ON CROSS COUNTRY FLIGHT. PILOT LANDED AT DESTINATION WITH MAINS LOCKED, AND HITTING THE NOSE, NOSE GEAR DOORS AND BOTH PROPS (SEVERE) UPON LANDING. 1L72 3O3 O 3A25 E5CE 20020919000042002091900004SW 2002 9 19 2002FA0001055 120020327G5511 SPAR GULSTM500 500A 0141104SW CONT O470 IO470* 17026SO HORIZONTAL STAB CRACKED D K NONE O OTHER ININSP/MAINT 1 NM05471D 4592 500A124070 FORWARD SPAR CRACKED IN RADIUS OF BEND. SB COVERS THIS CONDITION. 1H72 3O3 O 6A1 E1CE 20020919000052002091900005CE 2002 9 19 2002FA0001056 120020822G5751 HINGE BEECH 58 58 1152740CE LYC O360 O360* 41514EA AILERON MISALIGNED D K NONE O OTHER ININSP/MAINT 1 SO11793DW78 TH1421 DURING ROUTINE MAINTENANCE, TECH NOTICED LT AILERON MISALIGNED WITH TRAILING EDGE OF WING AT AILERON WELL. FOUND THAT OUTBOARD AILERON HINGE BOTTOM ATTACH SCREWS NOT IN HINGE ATTACH HOLES BUT CAUGHT BETWEEN AFT PORTION OF HINGE AND AILERON ATTACH HOLES. SCREWS HAD ENOUGH BINDING FORCE TO FEEL AS THOUGH THREADING IN HINGE ATTACH HOLES, THIS CONDITION CAUSED AILERON MISALIGNMENT. AIRCRAFT PAINTED 12/01 HAD FLIGHT CONTINUES REMOVED AND BALANCED. AIRCRAFT FLEW 78 HOURS IN THIS CONDITION. 1L72 3O3 O 3A16 E286 20020919000062002091900006CE 2002 9 19 2002FA0001059 120020827G311010238400415 PANEL BEECH 58 58P 1152744CE CONT O520 TSIO520* 17040SO COCKPIT SHORTED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW1768BB 3649 TJ317 PANEL ON SWITCH PANEL LIGHTING SHORTED WHICH MADE THE INVERTER EMITTED SMOKE INTO THE COCKPIT. BOTH PARTS WERE REPLACED WITH NEW PARTS FROM MFG. 1L72 3O3 O A23CE E8CE 20020919000072002091900007CE 2002 9 19 2002FA0001060 120020830G3230MS252534 SWITCH CESSNA CESSNA402 402B 207590PCE MLG FAULTY D O OTHER J WARNING INDICATION NRNOT REPORTED 1 WP135403M 402B0003 LANDING GEAR WILL NOT RETRACT. DURING NORMAL TAKEOFF, FAULTY SWITCH FOUND ON. SAFETY SWITCH ASSEMBLY ON LT MLG ASSEMBLY. REPLACED SWITCH AND CHECK OPS OK. AIRCRAFT RETURNED TO SERVICE. 1L72 3O A7CE 20020918000732002091800073NM 2002 9 18 2002FA0001061 120020828G8000V31001 SWITCH ROBSINR22 R22BETA 7640110NM LYC O360 O360* 41514EA ACTUATOR FAILED C K NONE L NO TEST ININSP/MAINT 1 SW177087X24 2829 ENGINE WOULD NOT CRANK, NOR WOULD CLUTCH ENGAGE (BELT TENSION MOTOR WOULD NOT ENERGIZE); ELECTRIC POWER DID NOT PASS THROUGH A NORMALLY CLOSED SWITCH IN THE ACTUATOR ASSEMBLY. REMOVED ASSEMBLY FROM AIRCRAFT; REMOVED SWITCH FROM ASSEMBLY. THE SWITCH WAS INOPERATIVE AND HAD LOOSE COMPONENTS RATTLING INSIDE ITS CASE. 1G71 3O3 O H10WE E286 20020918001052002091800105SO 2002 9 18 2002FA0001062 220020911G8550625207 TUBE CONT O520 IO520D 17032SO OIL SUMP DEFECTIVE B K NONE W INADEQUATE Q C ININSP/MAINT 1 WP07 AT ENGINE OVERHAUL, PRIOR TO INSTALLING OIL SUCTION TUBE ASSY'S IN TWO IO-520D ENGINES, BOTH WERE DISCOVERED TO BE DEFECTIVE. ONE TUBE WOULD NOT FIT PROPERLY AND APPEARED TO HAVE NOT BEEN JIGGED PROPERLY IN THE WELDING PROCESS. THE OTHER TUBE HAD SPOT WELDS BROKEN LOOSE AND THE BRAZING PROCESS WAS INCOMPLETE. 3 O E5CE 20020918001062002091800106CE 2002 9 18 2002FA0001063 120020911G324003018901 BRAKE ASSY CESSNA500 550 2076604CE MLG LOCKED B O OTHER O OTHER LDLANDING 1 SO1115JA 177 177 5500035 R/H BRAKE ASSY LOCKED UP UPON LANDING CAUSING DAMAGE TO INBOARD WHEEL HALF. 1L72 4F A22CE 20020918001092002091800109CE 2002 9 18 2002FA0001064 120020911G5347051418215 SEAT TRACK CESSNA172 172P 2072436CE COCKPIT WORN G K NONE O OTHER ININSP/MAINT 1 GL15381J 10012 17274183 AN INSPECTION OF THE SEAT FRAME REVEALED WEAR BETWEEN THE PEDESTAL FRAMES AND THE TORQUE TUBES. THIS ALLOWED THE SEAT FRAME TO "RACK" FROM SIDE TO SIDE WITH THE WEIGHT OF THE PILOT SITTING IN IT. AT TIMES THIS WOULD CAUSE ONLY ONE SEAT PIN TO PARTIALLY ENGAGE THE SEAT RAIL. WIGGLING THE SEAT AROUND WOULD ALLOW BOTH SEAT PINS TO FULLY ENGAGE THE SEAT RAILS. WITHOUT THE WEIGHT OF A PERSON IN THE SEAT THE SEAT PERFORMED SATISFACTORILY. THE AIRCRAFT WAS IN COMPLIANCE WITH AD 87-20-03 R2 AND THE SEAT RAILS HAD BEEN REPLACED 1159 HOURS AGO. THE AIRCRAFT HAD 183 HOURS SINCE ITS LAST ANNUAL INSPECTION. 1H71 3O NT3A12 20020918001102002091800110CE 2002 9 18 2002FA0001065 120020916G2822LW15473 PUMP CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA FUEL SYSTEM LOOSE B K NONE O OTHER ININSP/MAINT 1 SO032272H779 17280688 L2791051A BOLTS LOOSE IN FUEL PUMP DIAPHRAGM. 1H71 3O3 ONT3A12 1E10 20020918001112002091800111CE 2002 9 18 2002FA0001066 120020916G323228233330511 BRACKET RKWELLNA265 NA26565 7630107CE LT MLG BROKEN D K NONE O OTHER ININSP/MAINT 1 WP07670AS9263 58 DURING GEAR RETRACTION TEST, LT MLG DOOR ACTUATOR ATTACH BRACKET BROKE AT GEAR DOOR. 2L72 4J A2WE 20020918001122002091800112CE 2002 9 18 2002FA0001067 120020917G280051001101 LINE CESSNA414 414A 2075907CE FUEL VENT CHAFED D K NONE K FLUID LOSS ININSP/MAINT 1 NM10414ST6990 414A0614 FUEL RUNNING OUT OF LEFT VENT WHEN TOPPED OFF. INSPECTION REVEALED LEFT VENT TUBE HAD A HOLE CHAFED IN IT BY FUEL FILLER PORT SCREEN. THIS AIRCRAFT HAD RAM WINGLETS INSTALLED SEVERAL HOURS BEFORE THIS OCCURED. LINE MAY HAVE BEEN BENT DURING THIS INSTALLATION, CAUSING LINE TO CHAF ON FILLER PORT SCREEN. INSPECTED RIGHT SIDE WITH NO CHAFING FOUND. RECOMMEND THIS LINE TO BE INSPECTED WHEN FUEL TANKS ARE OPENED, OR VISUAL INSPECTION THRU FILLER PORT. 1L72 3O A7CE 20020920000352002092000035SO 2002 9 20 2002FA0001068 120020829G29103153600 LINE PIPER PA23 PA23250 7102308SO HYD SYSTEM BROKEN B VT3RK NONE O OTHER ININSP/MAINT 1 WP09508UU 277954001 DURING LANDING APPROACH, LANDING GEAR FAILED TO EXTEND EITHER NORMALLY OR BY USING HAND PUMP. LANDING GEAR WAS EXTENDED BY USING BLOW DOWN BOTTLE, NOSE AND RIGHT REAR DID NOT EXTEND AND AIRCRAFT WAS SUBTANTIALLY DAMAGED DURING LANDING. INSPECTION REVEALED THE RIGHT MAIN LANDING GEAR DOWN INE IN NACELLE HAD FAILED AT THE SLEEVE/FLARE AREA. 1L72 3O 1A10 20020920000362002092000036SW 2002 9 20 2002FA0001069 120020828G6220407310102101 BEARING BELL BELL 407 407 1182206SW ALLSN 250C 250C47B GL M/R HUB SEPARATED B IIFRK NONE O OTHER ININSP/MAINT 1 SW03407PR3247 A254 53232 ELASTOMERIC PORTION OF BEARING COMPLETELY DEBONDED FROM BASE. FOUND AT ROUTINE INSPECTION. THIS BEARING IS ONE OF A BATCH OF DEFECTIVE BEARINGS MANUFACTURED BEFORE 1998. RECOMMEND THAT BEARING BE BONDED WITH BETTER MATERIAL OR ADHESIVE. 1G71 3U3 UO H2SW E1GL 20020920000372002092000037SW 2002 9 20 2002FA0001070 120020806G53022060313291 FITTING BELL 206 206B 1181511SW TAILBOOM CRACKED D K NONE O OTHER ININSP/MAINT 1 WP013202X21498 3939 DURING A 100 HOUR, INSPECTION, THE LEFT UPPER TAILBOOM ATTACH FITTING WAS FOUND TO BE CRACKED. THE CRACK WAS FROM THE LOWER AFT RIVET HOLE, THRU THE UPPER AFT RIVET HOLE, AND EXTENDED TO THE UPPER EDGE OF THE FITTING. (WPO12002B6504) 1G71 3U H2SW 20020920000392002092000039CE 2002 9 20 2002FA0001072 120020902G282307161114 SHUTOFF VALVE CESSNA172 172S 2072439CE FUEL SYSTEM LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 SO053513K153 172S8917 DURING ANNUAL INSPECTION, FOUND FUEL SHUT-OFF VALVE LEAKING EXTERNALLY AT COVER. REPLACED WITH NEW PART. 1H71 3O NT3A12 20020920000402002092000040CE 2002 9 20 2002FA0001074 120020806G322208421201 TUBE CESSNA320 320 2074502CE NOSE GEAR BROKEN G K NONE O OTHER ININSP/MAINT 1 WP09 4500 320D0020 TUBE ASSEMBLY. DURING LANDING APPROACH THE NOSE GEAR DID NOT EXTEND, AND THE GEAR DOWN GREEN LIGHT DID NOT ILLUMINATE. AIRCRAFT LANDED AND NOSE GEAR COLLAPSED. INSPECTION REVEALED FAILURE OF NOSE GEAR TUBE ASSY. RECOMMEND THIS TUBE REPLACED BY ACCUMULATION OF CYCLES. 1L72 3O 3A25 20020920000412002092000041 2002 9 20 2002FA0001076 420020903G2562450017 ANTENNA ELT DEFECTIVE D K NONE W INADEQUATE Q C ININSP/MAINT 1 EA09 (ELT ANTENNA) THE ELT DID NOT TRANSMIT WHEN TESTED ON THE AIRCRAFT AT 100 HOUR INSPECTION. ELT WORKED WHEN PORTABLE ANTENNA USED. VISUAL INSPECTION FOUND MAST LOOSE. THE ANTENNA WAS MACHINED TO A DIAMETER OF .040 TO .050 AT THE BNC REDESIGN USING A FLEXIBLE MAST AND BETTER BASE CONNECTION. 20020920000422002092000042EA 2002 9 20 2002FA0001077 220020904G85301519995735 PUSHROD PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENGINE BENT D O OTHER O OTHER NRNOT REPORTED 1 SW159290P697 4496019 THE NUMBER 2 CYLINDER EXHAUST PUSH ROD BENT IN FLIGHT. 1L72 3O3 O A19S0 E286 20020920000432002092000043CE 2002 9 20 2002FA0001078 120020904G7603640791A5 THROTTLE CONTROL BEECH 58 58P 1152744CE CONT O520 TSIO520* 17040SO LEFT ENGINE BINDING D O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 NM07146Z 100 TJ426 822553 PILOT REPORTED BINDING OF LEFT ENGINE THROTTLE. INVESTIGATION REVEALED GALLING OF MIXTURE ADJUSTMENT ROD WHERE IT ATTACHES TO THE THROTTLE LEVER, WITH A SIGNIFICANT AMOUNT OF TRANSFER OF METAL FROM THE LEVER TO THE ROD, PREVENTING FULL THROTTLE MOVEMENT. THIS THROTTLE LEVER APPEARS TO BE MADE FROM A MATERIAL DIFFERENT FROM WHAT WAS PREVIOUSLY USED. 1L72 3O3 O A23CE E8CE 20020920000442002092000044CE 2002 9 20 2002FA0001079 120020905G76003012534 BOLT BEECH 90 E90 1152914CE PWA PT6 PT6A60A 52043NE GOVERNOR CONTROLCRACKED D T40RO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 NE03965LG5858 LW204 PCE24731 RIGHT ENGINE HAD NO REVERSE, FOUND FORWARD REVERSING CABLE/GOVERNOR BLEED LINK BOLT CRACKED AND SPLIT OPEN AT HOLE IN BOLT FOR REVERSING CABLE TO THREAD THROUGH. REVERSING CABLE COULD MOVE FORWARD AND AFT WITHOUT CONTROLLING GOVERNOR. POSSIBLE BOLT HAD BEEN OVERTORQUED IN THE PAST. C/A: INSTALLED NEW BOLT PN 3012534, AND RIGGED CONTROL. (NE032002B6857) 1L72 3T4 T 3A20 E4EA 20020920000302002092000030EA 2002 9 20 2002FA0001084 220020919G7310 MANIFOLD CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1A170 1A170* GL FUEL SYSTEM MALFUNCTIONED B O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 SO15428ER 17280607 L2724059A TI039 THE CREW REPORTED A MOMENTARY POWER ROUGHNESS. THE AIRCRAFT FUEL CONTROL SYSTEM AND IGNITION SYSTEM WERE INSPECTED. THE FUEL MANIFOLD WAS REPLACED ALONG WITH 2 INJECTOR NOZZLES. A GROUND OPERATIONAL CHECK WAS PERFORMED. FOLLOWING THAT A FUNCTIONAL CHECK FLIGHT WAS PERFORMED. NO DISCREPANCIES DURNING THAT FLIGHT WERE NOTED. THIS OPERATOR HAS MANY 172R AND 172S MODEL AIRCRAFT. THERE HAVE BEEN NUMEROUS MOMENTARY POWER LOSS, ROUGHNESS REPORTS AND IRREGULAR IDLE DIFFICULTIES WITH THIS MODEL AIRCRAFT. 1H71 3O3 ONT3A12 1E10 5 NP857 20020920000312002092000031CE 2002 9 20 2002FA0001085 120020722G7810NH10089740 CLAMP CESSNA310 T310Q 2074244CE CONT O520 TSIO520* 17040SO EXHAUST SYSTEM CRACKED D K NONE O OTHER ININSP/MAINT 1 GL09650PC 310Q0465 THIS CLAMP ATTACHES TAILPIPE TO TURBOCHARGER OUTLET. DURING COMPLIANCE WITH AD2000-1-16 FOUND CLAMP SPLIT AT THE APEX OF THE "V" AROUND 4.75" TO 5.0" OF CIRCUMFERENCE. PER AD2000-1-16 THIS CLAMP IS NOT LIFE-LIMITED. 1L72 3O3 O 3A10 E8CE 20020920000322002092000032SO 2002 9 20 2002FA0001086 120020919G275067201101 CONTROL CABLE PIPER PA28 PA28R201 7102816SO TE FLAPS FRAYED B K NONE F FLT CONT AFFECTED ININSP/MAINT 1 SO15492B 731 50 2844051 PILOT REPORTED AN 'UNUSUAL FEEL TO THE FLAP CONTROL. INVESTIGATION REVEALED THAT THE FLAP EXTENSION CABLE WAS SEVERELY FRAYED. IT WAS REPLACED.. 1L71 3O 2A13 20020920000342002092000034EA 2002 9 20 2002FA0001088 220020903G8500 ENGINE CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MCAULY1A170 1A170* GL NACELLE ROUGH B A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 SO15470ER 17280614 RL2931751A TI058 DURING FLIGHT, THE CREW REPORTED A ROUGH ENGINE. THE FLIGHT WAS TERMINATED AND MAINTENANCE WAS PERFORMED. THE SPARK PLUGS WERE CLEANED AND THE INJECTOR NOZZLES INSPECTED.. 1H71 3O3 ONT3A12 1E10 5 NP857 20020920001332002092000133CE 2002 9 20 2002FA0001089 120020905G321350810318 AXLE BEECH 100 A100 1152915CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 SO0618AH 1546 B118 PISTON/ AXLE ASSEMBLY HOUSING HAS AN INDICATION OF A CRACK ON BOTH SIDES AT THE CASTING LINE. ONE SIDE HAS AN INDICATION APPROXIMATELY 2 INCHES LONG. THE OTHER SIDE HAS AN INDICATION APPROXIMATELY 0.5 INCH LONG THESE INDICATIONS WERE FOUND DURING A ROUTINE 6 YEAR INSPECTION. 1L72 3T A14CE 20020920001342002092000134CE 2002 9 20 2002FA0001090 120020905G5720 BRACKET BBAVIA8 8KCAB 2110612CE LYC O360 AEIO360* EA WING ROOT MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 GL192523Z1141 33777 DURING AN ANNUAL INSPECTION, FOUND WING ROOT FAIRING BRACKET AGAINST LOWER PART OF FORWARD SPAR (LEFT WING). THE BRACKET APPEARS TO HAVE BEEN INSTALLED TOO CLOSE TO THE SPAR AT MANUFACTURE, CAUSING LOCAL MINOR DAMAGE. REPAIRED LOCAL DAMAGE. INSPECTED ENTIRE LENGTH OF FORWARD AND AFT SPARS IN BOTH WINGS AND FOUND NO OTHER DAMAGE. 1H71 3O3 O A21CE 1E10 20020920001352002092000135EA 2002 9 20 2002FA0001091 220020905G8520 LIFTER BEECH 60 B60 1153605CE LYC O541 TIO541E1C4 41536EA ENGINE SPALLED D K NONE O OTHER ININSP/MAINT 1 NM0318292 P433 L138259 SEVEN SPALLING OF LIFTERS AND CAM SHAFT WITH ONLY 130 HOURS USE. ALSO FAILED WITH 60 HOURS USE. 1L72 3O3 O A12CE E10EA 20020920001362002092000136SO 2002 9 20 2002FA0001092 120020910G322083699003 ROD PIPER PA46 PA46350P 7104602SO LYC O540 TIO540* 41532EA NLG BROKEN D K NONE O OTHER ININSP/MAINT 1 WP191AM 4622061 NOSE GEAR EMERGENCY EXTENSION DOWN SPRING ROD. BROKEN AT 71 CYCLES DUE TO INFERIOR WELD OF THE FITTING ON THE END OF THE ROD. VIOLENTLY SEPARATES FROM THE AIRCRAFT WHEN EITHER END BRAKES. 1L71 3O3 ORTA25SO E14EA 20020924000152002092400015EA 2002 9 24 2002FA0001093 220020701G741410357174 POINTS BENDIX PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA MAGNETO BURNED D K NONE L NO TEST ININSP/MAINT 1 SW15814RC195 8050704 301202 DURING ENGINE RUN AND MAGNETO CHECK, MAGNETO WOULD RUN. FOUND POINTS BURNED, PITTED AND WORN. TOTAL HOURS ON ITEM: 195.0, REPLACED BREAKER POINTS. (SW15200210915) 1L72 3O3 O A1EA 1E12 20020924000162002092400016SO 2002 9 24 2002FA0001094 120020701G1430AN175C33A BOLT PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA STABILATOR ROD CORRODED D K NONE O OTHER ININSP/MAINT 1 SW158030Y 301139 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUB AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY, TOTAL AIRFRAME APPROXIMATELY 7565.0. NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. (SW15200210914) 1L72 3O3 O A1EA 1E12 20020924000172002092400017SO 2002 9 24 2002FA0001095 120020701G1430AN175C33A BOLT PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA STAB TORQUE TUBECORRODED D K NONE O OTHER ININSP/MAINT 1 SW15814RC 301202 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY, TOTAL AIRFRAME APPROXIMATELY 5050.0 NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. FILED FAA. (SW 15200210910) 1L72 3O3 O A1EA 1E12 20020924000182002092400018SO 2002 9 24 2002FA0001096 120020325G1430AN175C33A BOLT PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA STAB TORQ TUBE CORRODED D K NONE O OTHER ININSP/MAINT 1 SW157008Y 309 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY, TOTAL AIRFRAME APPROXIMATELY 5050.0 NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. FILED WITH FAA. (SW15200208047) 1L72 3O3 O A1EA 1E12 20020924000192002092400019SO 2002 9 24 2002FA0001097 120020325G1430AN175C33A BOLT PIPER PA24 PA24250 7102404SO LYC O540 O540* 41532EA STABILATOR CORRODED D K NONE O OTHER ININSP/MAINT 1 SW157425P 242613 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBVLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY, ALSO BOLTS , TORQUE TUBE HAD CORROSION ALSO. THAT AIRFRAME, APPROXIMATELY 3073.0, NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. ALSO NOTED THAT THIS AIRPLANE WAS LOCATED IN FLA. FOR PART OF ITS LIFE. FILED WITH FAA. (SW15200208048) 1L71 3O3 O 1A15 E295 20020924000202002092400020SO 2002 9 24 2002FA0001098 120020707G1430AN175C33A BOLT PIPER PA24 PA24 7102402SO LYC O360 O360* 41514EA STABILATOR CORRODED D K NONE O OTHER ININSP/MAINT 1 SW156841P5515 241974 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMBLY,BOLTS, TOTAL AIRFRAME APPROXIMATELY 5515.0. NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. FILED WITH FAA. (SW15200210929) 1L71 3O3 O 1A15 E286 20020924000212002092400021SO 2002 9 24 2002FA0001100 120020607G1430AN175C33A BOLT PIPER PA30 PA30 7103002SO STABILATOR CORRODED D K NONE O OTHER ININSP/MAINT 1 SW15GBZRO 301923 DURING ANNUAL INSPECTION STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS (PN AN175C33A) THAT ATTACHES THE STABILARTOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERLY CORRODED. HORN ASSEMLBY, BOLTS, TOTAL AIRFRAME APPROXIMATELY UNKNOWN. AIRPLANE IS CURRENTLY LOCAKED IN UK. NO INDICATION THAT STABILATOR HAD BEEN REMOVED PREVIOUSLY. FILED WITH FAA. 1L72 3O A1EA 20020924000222002092400022CE 2002 9 24 2002FA0001101 120020822G27100523807 HINGE PIN CESSNA172 172 2072402CE CONT O300 O300* 17022SO AILERON DAMAGED D K NONE O OTHER ININSP/MAINT 1 NM076643A 28743 DURING AN ANNUAL INSPECTION IT WAS FOUND THAT THE RIGHT OUTBOARD AILERON HINGE PIN HAD COME OUT OF THE HINGE ABOUT 5 INCHES. ONE COTTER PIN WAS STILL IN PLACE AND THE OTHER COTTER PIN WAS ONLY HALF THERE. 1H71 3O3 ONT3A12 E253 20020924000232002092400023EA 2002 9 24 2002FA0001102 220020830G8520LW12440 CAMSHAFT BEECH 60 B60 1153605CE LYC O541 TIO541* 41536EA ENGINE ERODED C K NONE O OTHER ININSP/MAINT 1 NM03265D 35 P548 L179059 WITH NO PROBLEMS TO 1952 HRS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99. NOTHING BUT PROBLEMS SINCE. AT FIRST OIL CHANGE, AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER. CONTINUED FLYING. MORE FERROUS METAL AT 2ND OIL CHANGE (70 HOURS); UNACCEPTABLE AMOUNT AT 3RD (100 HOURS). OVERHAULER REPLACED CAMSHAFT AND ALL LIFTERS WITH NEW MFG PARTS. EXACTLY SAME RESULTS AT SAME TIMES AFTER REPLACEMENT, VOLUNTARILY GROUNDED AIRPLANE ON 4 FEB 2002 WAITING MODIFIED CAMSHAFT NEARING STC APPROVAL. UNDERSTAND STC IS LOW PRIORITY. PLEASE EXPEDITE. 1L72 3O3 O A12CE E10EA 20020924000242002092400024EA 2002 9 24 2002FA0001103 220020803G8520LW15861 LIFTER BEECH 60 B60 1153605CE LYC O541 TIO541* 41536EA ENGINE ERODED C K NONE O OTHER ININSP/MAINT 1 NM03265D 35 P548 L164859 WITH NO PROBLEMS TO 1952 HOURS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99. NOTHING BUT PROBLEMS SINCE. AT FIRST OIL CHANGE AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER. CONTINUED FLYING. MOR FEROUS METAL AT 2ND OIL CHANGE(70 HOURS); UNACCEPTABLE AMOUNT AT 3RD (100 HOURS). OVERHAULER REPLACED CAMSHAFT AND ALL LIFTERS WITH NEW MFG. PARTS. EXACTLY SAME RESULTS AT SAME TIMES AFTER REPLACEMENT, VOLUNTARILY GROUNDED AIRPLANE (DUKE B60) ON 4 FEB 02 WAITING MODIFIED CAMSHAFT NEARING STC APPROVAL. UNDERSTAND STC IS LOW PRIORITY. PLEASE EXPEDITE. (HAVE PHOTOS) 1L72 3O3 O A12CE E10EA 20020924000252002092400025SO 2002 9 24 2002FA0001104 120020827G57305102299902 PANEL AMRGENAA5 AA5 0631410SO LYC O320 O320* 41508EA WING DELAMINATED D K NONE O OTHER ININSP/MAINT 1 NM011317R AA50717 HONEYCOMB SIDEPANELS HAVE BECOME DELAMINATED IN NUMEROUS AREAS, EVEN IN THE AREA THAT THE CARRY THROUGH SPAR IS BOLTED TO. THE DELAMINATION OF THE HONEYCOMB PANELS IN THIS AREA REDUCE THE STRUCTURAL INTEGRITY AND MAY ALLOW POSSIBLE SPAR SLIPPAGE AFFECTING THE ANGLE OF INCIDENCE OF THE WINGS WHICH WILL DIRECTLY AFFECT THE FLIGHT CONTROLS BY BINDING THE FLAP AND AILERON TORQUE TUBES. LARGE AMOUNT OF MFG AIRCRAFT WERE BUILT USING A PURPLE GLUE. THIS GLUE WAS WIDELY USED IN THE MID 1970`S AND WAS SUSCEPTIBLE TO BONDED SKIN SECTIONS AND REFERS TO DELAMINATION. (200206996) 1L71 3O3 O A16EA E274 20020924000142002092400014SO 2002 9 24 2002FA0001105 120020906G2810UNKNOWN FUEL CAP PIPER PA22 PA22150 7102210SO LYC O320 O320A2A 41508EA RT TANK BLOCKED G A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 EA012626P 222963 384827 AIRCRAFT WAS AT A CRUISE ALTITUDE OF 1800 FT WHEN ENGINE QUIT RUNNING. MADE AN EMERGENCY LANDING IN A HAY FIELD. FUEL SELECTOR WAS SELECTED ON RT TANK. POST INSPECTION FOUND ORIGINAL TYPE FUEL CAP VENTING WAS BLOCKED (RT TANK). INSPECTION OF FUEL AND OIL SCREENS WERE NORMAL. ENGINE SUBSEQUENTLY STARTED AND RAN NORMALLY. CAUSE OF BLOCKAGE IN FUEL CAP IS UNKNOWN. 1H71 3O3 O 1A6 E274 20020925000022002092500002NM 2002 9 25 2002FA0001110 120020912G5102RX83242 SPRING AROSTRRX8 RX8 7487008NM VALVE HANDLE HUNG UP B OG2RO OTHER O OTHER NRNOT REPORTED 1 CE077146J RX83242 MALFUNCTION OF GLOW BURNER, VALVE HANDLE HANGING UP ON SPRING, CAUSING IT TO CONTINIOUSLY DISCHARGE PROPANE. VALVE COULD NOT RETURN TO CLOSED POSITION. TO PREVENT RECURRENCE, REPLACE WITH METAL HANDLE IN PLACE OF PLASTIC. (SW) 1B00 A15CE 20020927000192002092700019GL 2002 9 27 2002FA0001111 120020925G321110209001 GROMMET CIRRUSSR SR22 2130001GL MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SO15929R 141 0133 DURING A SCHEDULED INSPECTION FOUND BOTH MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. SUGGEST CLOSE ATTENTION TO THESE PARTS DURING SCHEDULED INSPECTIONS AND AFTER HARD LANDINGS. 1L71 3O NTA00009CH 20020927000012002092700001GL 2002 9 27 2002FA0001113 320020920G6110F7666A2 BLADE HARTZL AMTR STEEN STEENSKYBOLT GL LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YR1 GL PROPELLER DAMAGED B FR6RK NONE O OTHER ININSP/MAINT 1 NM03302JS3455 135 CH13880 100163 CH13880 PROP WAS REMOVED WITH 135.0 HOURS SINCE OVERHAUL. REASON FOR REMOVAL WAS TO EVALUATE PROP FOR POSSIBLE TRADE IN. DURING PRELIMINARY INSPECTION OF BLADE WIDTH AND THICKNESS FOR VALUE ASSESSMENT, BOTH BLADES WERE FOUND TO BE BELOW MFG MINIMUM SPECS AT 34 INCH STATION. ONE BLADE MEASURED 3.656 INCHES. VISUAL CONDITION OF PROPELLER BLADES ARE NEARLY AS IF THEY WERE JUST OUT OF OVERHAUL, MEANING NO FILING HAS BEEN DONE ON LEADING EDGES OF BLADES AND THERE IS VERY LITTLE IF ANY PITTING FROM STONE DAMAGE. PAINT ALSO LOOKS ORIGINAL FROM OVERHAUL AND HAS NOT BEEN REPAINTED. 1Q71 3O3 ONCEXPA1Q711E10 5 CP920 20020927000022002092700002CE 2002 9 27 2002FA0001114 120020730G28217560097 FILTER CESSNA188 A188B 2073005CE CONT O520 IO520D 17032SO FUEL SYSTEM CONTAMINATED D K NONE O OTHER ININSP/MAINT 1 CE079639G 18801575 563319 THE FUEL FILTER SUFFERED CONTAMINATION TO THE POINT OF ENGINE LEANING, REDUCING POWER TO LOW TO MAINTAIN FLIGHT WHILE IN AERIAL APPLICATION WORK. THE ALTITUDE WAS APPROXIMATELY .5000 FT AGL THE SPEED OVER THE CROP WAS 115 MPH. REPOSITIONING THE FUEL FILTER STRAINER DRAIN SO ONE COULD SEE THE CONDITION OF THE FUEL BEING DRAINED WOULD UNDOUBTLY HELP TO DETERMINE IF CONTAMINATION IS PRESENT IF AT ALL IN THE FUEL. 1L71 3O3 O A9CE E5CE 20020927000032002092700003CE 2002 9 27 2002FA0001115 120020913G3233AN6227B9 O-RING CESSNA CESSNA210 210E 2073416CE CONT O520 IO520* 17032SO ACTUATOR LEAKING B OF1RK NONE O OTHER ININSP/MAINT 1 EA172398F3708 21058598 AIRCRAFT LANDED WITH MAIN LANDING GEAR UP AND NOSE GEAR DOWN. CAUSE OF INCIDENT WAS A FAILED ORING IN NOSE LANDING GEAR ACTUATOR. LEAK RATE DEPLETED RESEVOIR AND WAS TOO GREAT FOR HAND PUMP VOLUME. MM HAS NO REPLACEMENT SCHEDULE FOR THESE ORINGS. 1H71 3O3 O 3A21 E5CE 20020927000042002092700004EA 2002 9 27 2002FA0001116 220020916G8530 INTAKE VALVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA CYLINDER BROKEN B K NONE O OTHER ININSP/MAINT 1 EA134074F577 318052164 L708261 INTAKE VALVE BROKEN AT CLIP END, UNDER CRUISE POWER, VALVE REMAINED IN CYLINDER. 1L72 3O3 O A20SO E14EA 20020927000162002092700016GL 2002 9 27 2002FA0001117 120020925G575110332002 FITTING CIRRUSSR SR22 2130001GL AILERON HINGE LOOSE D K NONE O OTHER ININSP/MAINT 1 SO15929R 141 0133 DURING INSPECTION FOUND LT INBOARD AILERON HINGE LOOSE. CONDITION FOUND BY FEELING A CLUNK WHILE MOVING TRAILING EDGE OF AILERON UP AND DOWN SLOWLY. TRAILING EDGE OF AILERON HINGE ABLE TO BE MOVED 1/8" UP AND DOWN. FOUND EVIDENCE OF "TORQUE-SEAL" ON ATTACH BOLT NUTS AND THREADS. CONTINUED MOVEMENT OF AILERON HINGE COULD POTENTIALLY DAMAGE ATTACH HARDWARE AND CAUSE SEPARATION OF AILERON FROM WING. 1L71 3O NTA00009CH 20020927000172002092700017GL 2002 9 27 2002FA0001118 320020926G6110S90AT8 BLADE CESSNA185 A185F 2072821CE MCAULY2A34C D2A34C58 GL PROPELLER CRACKED B K NONE O OTHER ININSP/MAINT 1 NM081056F1855 18502712 747226 RECEIVED PROPELLER FOR ROUTINE OVERHAUL. NO OVERHAUL OR INSPECTION SINCE 1982 (START OF LOG BOOK). PENETRANT INSPECTION OF PARTS REVEALED CRACK IN 1ST THREAD OF NR 1 BLADE. CONFIRMED WITH EDDY CURRENT. PROP WAS OIL FILLED IN 1982. NO INSPECTIONS PERFORMED ON BLADES AS WAS NOT A REQUIREMENT AT THAT TIME. 1H71 3O 3A24 5 CP3EA 20021011000602002101100060EA 2002 10 11 2002FA0001123 220020919G741410382585 POINTS BENDIX BEECH 80 65B80 1152812CE LYC O720 IO720* 41546EA MAGNETO MELTED B KZ5RK NONE O OTHER ININSP/MAINT 1 GL15103BA B003505 LD435 L132654A MELTING OF NYLON WHERE IT CONTACTS POINT ARM DURING OPENING AND CLOSING OF POINTS DURING OPERATION. INFERIOR NYLON USED, NOT RESISTANT TO WEAR OR HEAT. 1L72 3O3 O 3A20 1E15 20021011000612002101100061EA 2002 10 11 2002FA0001124 220020920G7322 FLOAT PRECISION CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA CARBURETOR DAMAGED B KC2RK NONE O OTHER ININSP/MAINT 1 GL03 CK611523 CARBURETOR SEAT IN FOR REPAIR BECAUSE IT WAS LEAKING. AFTER DISASSEMBLY ONE PONTOON OF (AP) FLOAT WAS FILLED WITH FUEL. OPPOSITE PONTOON HAD MARK FROM RUBBING HOUSING. 1H71 3O3 ONT3A12 E274 20021011000622002101100062CE 2002 10 11 2002FA0001125 120020914G321112414231 SADDLE CESSNA210 210E 2073416CE CONT O520 IO520* 17032SO MLG CRACKED B OF1RK NONE O OTHER ININSP/MAINT 1 EA172398F2441 21058598 BOTH MLG SADDLES WERE FOUND TO BE CRACKED IAW AD. PREVIOUS INSPECTION WAS 132 HOURS BEFORE THIS INSPECTION. 1H71 3O3 O 3A21 E5CE 20021011000632002101100063WP 2002 10 11 2002FA0001126 120020903G79103406220602 OIL TANK CVAC 340 340CVAC 242270AWP PWA R2800 R2800* 52026NE ENG NACELLE RUPTURED C K NONE O OTHER ININSP/MAINT 1 SO21153JR 117 THE OIL TANK WAS OVERFILLED ON LEFT ENGINE. ON TAKE OFF ROLL, THE PRESSURE FROM THE OVERFILL CAUSED THE TANK TO RUPTURE. OIL THEN BEGAN TO SPRAY ONTO THE EXHAUST SYSTEM. THIS OIL IGNITED AND THE SUBSEQUENT FLAMES DAMAGED THE NACELLE IN THE AREA AFT OF THE OIL TANK, PRIMARILY ABOVE AND OUTBOARD. 2L72 4R4 R 6A6 5E8 20021011000642002101100064CE 2002 10 11 2002FA0001128 120020911G2730SAR21534 CABLE BBAVIA7 7KCAB 21101P3CE LYC O320 IO320E2A 41508EA DOWN ELEV CABLE BROKEN G K NONE O OTHER ININSP/MAINT 1 GL151843G 78 L358555A THE DOWN ELEVATOR CONTROL CABLE FAILED AT THE REAR PULLEY BELOW BATTERY BOX. THE PULLEY HAD STOPPED TURNING THUS CUTTING OR WEARING CONTROL CABLE TO A CONDITION IT WHERE IT FAILED WITH HARD FORWARD STICK. METER SHOWED .5 AND GS. 1H71 3O3 O A759 1E12 20021011000732002101100073EA 2002 10 11 2002FA0001130 220020909G7322MA4SPA CARBURETOR PIPER PA28 PA28151 7102805SO LYC O320 O320E3D 41508EA ENGINE INOPERATIVE B K NONE O OTHER ININSP/MAINT 1 SW13434734000 287415504 L3757427A (CARBURETOR) AN ALUMINUM SLIVER, .188 LONG, .018 THICK, .023 WIDE WAS FOUND BETWEEN THE NEEDLE VALVE AND SEAT. PREVENTING OPERATION OF NEEDLE VALVE. THE SLIVER APPEARS OF THE THROTTLE BODY ASSEMBLY, WHERE THE FUEL INLET AND STRAINER ASSEMBLY IS INSTALLED. 1L71 3O3 O 2A13 E274 20021011000742002101100074SO 2002 10 11 2002FA0001131 120020905G3211 BOLT PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA LT MLG SHEARED D K NONE O OTHER ININSP/MAINT 1 WP092171D12250 287916146 LT GEAR ASSEMBLY SHEARED UPPER AND LOWER RETAINING BOLTS. UPON LANDING, AIRCRAFT USED FOR STUDENT TRAINING AND HAS OVER 12200.0 HOLES, SUSPECT HARD LANDINGS WAS CAUSE. REPLACE BOLTS AND INSPECT MOUNTING AREA AT 5000 HOURS. 1L71 3O3 O 2A13 E274 20021011000752002101100075CE 2002 10 11 2002FA0001133 120020531G2820AN91220 FITTING CESSNA CESSNA172 172RG 2072438CE FUEL SYSTEM CRACKED B LW5RK NONE O OTHER ININSP/MAINT 1 GL179515B 172RG0846 THE FUEL STRAINER ON THIS PARTICULAR AIRCRAFT IS NOT MOUNTED RIGIDLY TO THE AIRFRAME. THEREFORE IT IS SUPPORTED BY THE FUEL LINES ATTACHED TO IT. THE VIBRATIONS CAUSED THIS FITTING TO CRACK. MFG MM LATER MODELS USE BRACKET FOR MOUNTING. 1H71 3O 3A17 20021011000772002101100077EU 2002 10 11 2002FA0001134 120020910G215020388022 BLADE BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE731* 01518WP COOLING TURBINE FAILED G K NONE O OTHER ININSP/MAINT 1 GL05799S 1790 258019 FAILURE OF TURBINE BLADE IN COOLING TURBINE RESULTING IN VIOLENT VIBRATION CAUSING CRACKING TO THE HEAT EXCHANGER ASSEMBLY. THE CURRENT INTERVAL ON THIS COMPONENT IS O/C. 2L72 4F4 FRTA3EU E6WE 20021011000802002101100080GL 2002 10 11 2002FA0001135 320020830G6110E697711D BRACKET BEECH 200 200BEECH 1152920CE PWA PT6 PT6* 52043EA HARTZLHCA3V HCA3V* GL PROP BLADE CUFF CRACKED C K NONE O OTHER ININSP/MAINT 1 SO1144US 400 BB56 PCE80109 BUA22847 THE BRACKETS (PN E6977-11D) THAT SUPPORT THE QUICK DISCONNECT PLUG ASSEMBLY FOR THE PROP DEICE BOOT DUG INTO THE PROPELLER BACKPLATE. THIS WAS DONE TO VARYING DEGREES AT EACH BLADE POSITION ON THE BACKPLATE. THIS OCCURRED ON BOTH PROPS ALTHOUGH IT WAS WORSE ON THE RIGHT PROP. THIS IS THE PROP REFERENCED ON THE FORM. THE HITTING OF THE BACKPLATE BY THE DEICE BRACKET ONLY OCCURS WHEN THE PROP GOES TO MAX REVERSE. THE PROPS ARE NOW AT THE PROP SHOP FOR INVESTIGATION. 1L72 4T3 T A24CE E2NE 5 CP6EA 20021011000812002101100081CE 2002 10 11 2002FA0001136 120020815G5542 SKIN BEECH 200 B200 1152922CE RUDDER CRACKED D K NONE O OTHER ININSP/MAINT 1 GL11942CE595 B1731 FOUND A 3.5 INCH CRACK APPROXIMATELY 6 INCHES DOWN AND .0200 INCH ON THE RIGHT SIDE TRAILING EDGE OF THE RUDDER. 1L72 4T A24CE 20021011000952002101100095GL 2002 10 11 2002FA0001139 320020826G611172R3BD BLADE AMTR GLASTRGLASTAR 05605M8GL LYC O320 O320* 41508EA AMTR T6801 WRAPDRIVE GL PROPELLER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM0399DF 37 5221 T8021 PROPELLER BLADE SHANK CRACKED RADIALLY AT THE JUNCTION OF THE SHANK AND THE BLADE. SLIGHT FORE AND AFT BLADE MOVEMENT DETECTABLE. ALL 3 BLADES CRACKED. INSTALLATION LOOKED PROPER WITH CORRECT TORQUE ON HUB AT BLADE ATTACH POINT. 1H71 3O3 ONCEXPA1H71E274 5 CEXPA5C 20021011000972002101100097CE 2002 10 11 2002FA0001140 120020918G5521 SPAR BEECH 55 95C55 1152708CE CONT O520 IO520* 17032SO LT ELEVATOR CRACKED B LC1RK NONE O OTHER ININSP/MAINT 1 EA077952M3500 TE192 REMOVED LT ELEVATOR AND FOUND REAR SPAR CRACKED AT TRIM TAB ACTUATOR. TECH SUPPORT AND CONSENSUS IS TO REPLACE REAR SPAR. 1L72 3O3 O 3A16 E5CE 20021011001052002101100105CE 2002 10 11 2002FA0001142 120020911G552350340091 STRUCTURE CESSNA414 414 2075908CE CONT O520 TSIO520* 17040SO ELEVATOR TAB BROKEN D K NONE O OTHER ININSP/MAINT 1 WP25616RM5800 4140375 DURING 100 HOUR INSPECTION, ELEVATOR TRIM BEARINGS WERE SUSPECTED TO BE LOOSE AND REQUIRE REPLACEMENT. TO REPLACE THESE BEARINGS, ELEVATOR TRIM TAB HORN WAS REMOVED. WHEN FORCE WAS APPLIED TO TWO OF FOUR ATTACHING NUTS TO EFFECT THEIR REMOVAL FROM THE MATING SCREW, THEY SEPARATED, BROKE OFF INSIDE OF TRIM TAB. WHEN FULL REMOVAL OF TWO OF SCREWS WAS EFFECTED IT WAS NOTED THAT ONE HAD RUST CORRODED OVER 90 PERCENT OF ORIGINAL DIAMETER AND SECOND SCREW HAD A FULL 100 PERCENT LOSS. ONLY ATTACHMENT OF THESE SCREWS WERE FROM THE COATING OF PAINT APPLICATION. 1L72 3O3 ORTA7CE E8CE 20021011001082002101100108SO 2002 10 11 2002FA0001143 220020925G7414 DISTRIBUTOR BLK PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360* 17025SO MAGNETO BURNED D GMZ2K NONE L NO TEST ININSP/MAINT 1 SW015227K200 3449205 322103 DURING MAGNETO PERFORMANCE, CHECK PRIOR TO FLIGHT, PILOT NOTED ENGINE WANTED TO QUIT RUNNING WITH RIGHT MAGNETO SELECTED TO OFF. EXTERNAL INSPECTION OF MAGNETO LEFT CHECKED GOOD. REMOVED LEFT MAGNETO AND INSPECTED INTERNALLY. INSPECTION REVEALED .5000 INCH SECTION OF DISTRIBUTOR BLOCK BURNED AWAY. UNKNOWN CAUSE AND NO RECOMMENDATION AT THIS TIME. 1L72 3O3 O A7SO E9CE 20021011001092002101100109NM 2002 10 11 2002FA0001144 120020925G27416355B000103 MOTOR BOEING737 737* NM STAB TRIM INOPERATIVE B VK6RK NONE L NO TEST ININSP/MAINT 1 GL09 THE UNIT PASSED ALL TESTS AND WAS READY TO BE SHIPPED BACK TO THE CUSTOMER. WHEN THE TECHNICIAN NOTICED A RATTLE INSIDE THE UNIT. THE UNIT WAS OPENED AND A WASHER WAS FOUND LOOSE INSIDE. THE WASHER WAS NOT A PART OF THE ASSEMBLY AND ITS ORIGIN WAS UNKNOWN. THE WASHER WAS REMOVED AND THE UNIT WAS RETESTED, TESTED GOOD AND WAS RETURNED. 2L72 4F RTA16WE 20021011001112002101100111 2002 10 11 2002FA0001145 420020906G25624520130 BATTERY ARTEX BEECH 36 A36 1151604CE CONT O550 IO550* SO ELT CRACKED B AKGRK NONE K FLUID LOSS ININSP/MAINT 1 CE05128JG 64155 E3332 IN COMPLETING 14 CFR ON THIS ELT, IT WAS NOTED THAT MOUNTING TRY HAS SOME KIND OF WHITE RESIDUE IN IT, INSPECTION OF THE ELT FOUND A CRACK IN THE BATTERY HALF OF THRU ELT CASE. OPENED UP ELT AND INSPECTION OF BATTERY ASSEMBLY SOUND THAT ONE OF THE CELLS HAD RUPTURED. 1L71 3O3 O 3A15 E3SO 20021011001132002101100113CE 2002 10 11 2002FA0001146 120020919G5740351150581 FITTING BEECH 45 A45 1152006CE CONT O470 O470* 17026SO RT WING DAMAGED B K NONE O OTHER ININSP/MAINT 1 GL03421NM G720 REMOVED WING LOWER ATTACH FITTING COVERS IN PREPARATION FOR EDDY-CURRENT INSPECTION IAW T34 REPORT. BEFORE BEGINNING EDDY-CURRENT INSPECTION NOTED DEEP TOOL MARKS/GOUGES IN RIGHT WING LOWER AFT BATHTUB FITTING INTERIOR. ALSO NOTED SIMILAR MARKS IN LEFT WING LOWER FORWARD FITTING DAMAGE APPEARS TO HAVE BEEN CAUSED BY ROUGH, IMPROPER WING ATTACH BOLT REMOVAL/ INSTALLATION TECHNIQUES DURING PREVIOUS MAINTENANCE. NO FURTHER ACTION TAKEN. 1L71 3O3 O 5A3 E273 20021010000122002101000012GL 2002 10 10 2002FA0001147 220020722G725023071311 SHAFT BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE CORRODED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03 ON VISUAL INSPECTION OF SHAFT, FOUND EXCESSIVE PITTING ON INNER RACE AREA. EXCESSIVE CORROSION ON INNER RACE SURFACE. PROTECTIVE GREASE WAS ON SURFACE OF INNER RACE. 1G71 3U3 U H2SW E1GL 20021010000112002101000011SW 2002 10 10 2002FA0001149 120020809G630077416 BUMPER BLOCK HUGHES269 269C1 8059504SW LYC O360 HIO360C1A 41514EA ENGINE MISSING D K NONE O OTHER ININSP/MAINT 1 SW0561426 0062 L3448236A DURING A SCHEDULED INSPECTION, THE LOWER PULLEY DRIVESHAFT WAS FOUND TO HAVE AN ABNORMAL AMOUNT OF MOVEMANT. UPON REMOVING THE SHAFT, THE CRANKSHAFT BUMPER BLOCK WAS FOUND TO BE MISSING. IT SHOULD BE NOTED THAT THIS PART IS NOT IN EITHER THE AIRFRAME OR THE ENGINE MANUFACTURERS PUBLICATIONS. THERE IS NO STEP TO INSTALL OR INSPECT FOR INSTALLATION OF THIS BUMPER IN THE ENGINE INSTALLATION PROCEDURES. 1G71 3O3 OO 4H12 1E10 20021010001172002101000117CE 2002 10 10 2002FA0001151 120020927G2140551130101 ELEMENT LEAR 35 31A 5170531CE HEATER BLISTERED B K NONE O OTHER ININSP/MAINT 1 CE0977PY 089 UPON DISASSEMBLY AND INSPECTION OF EMERGENCY POWER SUPPLY, FOUND THE HEATER BLANKET ELEMENT TO HAVE BECOME HEAT DAMAGED SEVERELY ENOUGH TO SEPERATE THE LAMINATION SURROUNDING THE CONDUCTIVE ELEMENT. 2L72 4F RTA10CE 20021010001342002101000134EA 2002 10 10 2002FA0001152 220020927G853072057 VALVE SEAT PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA CYLINDER MISREPAIRED B K NONE O OTHER ININSP/MAINT 1 WP07571ER129 4496147 L74171A DURING ROUTINE COMPRESSION TEST FOUND NR 3 CYL COMPRESSION LOW. REMOVED CYLINDER AND FOUND THE INTAKE VALVE SEAT HAD BEEN INSTALLED AND GROUND CROOKED AT THE FACTORY. SEAT WAS REINSTALLED AND GROUND CORRECTLY AND CYL REINSTALLED ON ENGINE. 1L72 3O3 O A19S0 E286 20021011001152002101100115SO 2002 10 11 2002FA0001153 220020822G8550640926 DRIVE SHAFT PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO OIL PUMP FAILED B K NONE O OTHER ININSP/MAINT 1 GL158385C1700 347670134 233882H RT ENGINE LOST OIL PRESSURE AFTER TAKEOFF DISASSEMBLY REVEALED BROKEN OIL PUMP DRIVE SHAFT/GEAR. SHAFT IS THE WEAK LINK. 1L72 3O3 O A7SO E9CE 20021010001362002101000136EA 2002 10 10 2002FA0001154 220020927G853072057 VALVE SEAT PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA ENGINE MISREPAIRED B K NONE W INADEQUATE Q C ININSP/MAINT 1 WP07575ER 4496151 L3873736A DURING ROUTING COMPRESSION TEST FOUND NR 4 CYLINDER COMPRESSION LOW. REMOVED CYLINDER AND FOUND THE INTAKE VALVE SEAT HAD BEEN INSTALLED AND GROUND CROOKED AT THE FACTORY. SEAT REINSTALLED AND GROUND CORRECTLY AND REINSTALLED ON THE ENGINE. 1L72 3O3 O A19S0 E286 20021010001372002101000137EU 2002 10 10 2002FA0001155 120020927G24976141H82 CIRCUIT BREAKER ISRAEL1124 1124 4500102EU AFT BAY BURNED B O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SW0930GF 5050 401 INVESTIGATION HAS REVEALED A FAILURE OF THE LT MAIN FUEL BOOST PUMP. THE NATURE OF THE FAILURE HAS RESULTED IN CATASTROPHIC DAMAGE TO THE WIRING AND POWER DISTRIBUTION SYSTEMS. IN REVIEWING THE ELECTRICAL DISTRIBUTION SYSTEM IT APPEARS THAT THE CIRCUIT PROTECTION DEVICES FAILED TO PROTECT THE SYSTEM. HAVE UNCOVERED THAT THE PUMP WIRING TO THE AFT JUNCTION BOX IS BURNED BEYOND RECOGNITION AND PRELIMINARY CHECKS HAVE CONFIRMED EXTENSIVE DAMAGE TO THE LT CONTACTOR BOX. WE SUSPECT THAT THE LT MAIN BOOST PUMP FAILED AND THE REMOTE CIRCUIT BREAKER DID NOT OPEN CAUSING THE WIRES TO OVERHEAT TO TH JOINT THAT THE INSULATION MELTED OFF WHICH CAUSED EXPOSED WIRES TO BURN INTO THE WIRING TO THE LT ALTERNATE FUEL PUMP. 2M72 4F A2SW 20021010001382002101000138 2002 10 10 2002FA0001156 420020930G6113D7582 BULKHEAD MCAULY MOONEYM20 M20R 5870225SW CONT O550 IO550G 17042SO MCAULY2A34C 2A34C* GL SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 GL19101DX42 42 290221 679463 992954 THE SPINNER BULKHEAD WAS FOUND CRACKED COMPLETELY AROUND THE CIRCUMFERENCE OF THE MOUNTING FLANGE. THE TOTAL TIME ON THE SPINNER ASSEMBLY IS 315.5 HOURS. THIS IS THE THIRD CRACKED BULKHEAD FOUND ON THIS AIRCRAFT. THE TIME IN SERVICE OF THIS BULKHEAD IS 42.8 HOURS. THE FIRST BULKHEAD WAS FOUND CRACKED (SEPARATED FROM PROP HUB) AT 104.6 HOURS TIS. THE SECOND WAS FOUND CRACKED AT 168.1 HOURS TIS. MCCAULEY SERVICE BULLETIN 237 WAS COMPLIED WITH AT THE FIRST REPLACEMENT. SB 237A WAS COMPLIED WITH AT THE SECOND REPLACEMENT. 1L71 3O3 ORT2A3 E3SO 5 CP3EA 20021010001392002101000139EA 2002 10 10 2002FA0001157 220020921G855076617 LINE MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA ENG OIL FAILED G A UNSCHED LANDING BKRSMOKE/FUMES/ODORS/SPARKS FLUID LOSS PARTIAL RPM/PWR LOSS CRCRUISE 1 GL116231U 2070 L510036 DURING FLT,SHORTLY AFTER DEPARTURE FROM LAF, IN CRUISE AT 3,000 FT, PILOT HEARD A POP FROM THE ENGINE. SMOKE FROM FRONT COWLING, AND IN THE COCKPIT. CONTACTED TOWER TO ADVISE OF SITUATION AND BEGAN 180 DEGREE TURN TO RETURN TO LAF. HEARD TWO MORE POPS FROM ENGINE AND BEGAN LOSING POWER. COULD NOT MAINTAIN ALTITUDE. ADVISED TOWER OF PUTTING AIRCRAFT DOWN IN A FIELD. AIRCRAFT LANDED IN FIELD APPROXIMATELY 12 MILES NW OF LAF. NO DAMAGE TO AIRCRAFT DURING THE EMERGENCY LANDING. INSPECTION OF THE AIRCRAFT REVEALED THE PROP GOVERNOR EXTERNAL OIL LINE FRACTURED AT THE B-NUT CAUSING LOSS OF OIL. THE NR 2 CYLINDER AFT PUSH ROD FAILED DUE TO LACK OF OIL AND CREATED A HOLE IN THE ENGINE CASE. 1L71 3O3 O 2A3 E286 20021011001182002101100118SO 2002 10 11 2002FA0001159 220021002G7421RHB32E SPARK PLUG CESSNA421 421C 2076016CE CONT O520 GTSIO520* 17032SO ENGINE FOULED D O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 EA23421G 125 421C0664 ROUGH MAGNETO ON RT ENGINE DURING RUN UP. PULLED SPARK PLUGS ON LT MAGNETO SIDE. FOUND ONE SPARK PLUG SHORTED OUT (OUTSIDE ELECTRODE TOUCHING CENTER ELECTRODE). WHEN THE OUTER ELECTRODES WERE TOUCHED THEY WERE FOUND TO BE VERY LOOSE AND FLOATING. SUSPECT THAT SPARK PLUG WAS MANUFACTURED POORLY. 1L72 3O3 O A7CE E7CE 20021011001192002101100119CE 2002 10 11 2002FA0001160 120020929G56105111604202 WINDSHIELD CESSNA421 421B 2076014CE COCKPIT FAILED C B EMER. DESCENT D INFLIGHT SEPARATION CRCRUISE 1 NM04421DK 421B0825 DURING CRUISE FLIGHT NEAR SHR AT 25000 FT., RT WINDSHEILD SUSTAINED AN EXPLOSIVE DECOMPRESSION. PILOT PERFORMED EMERGENCY PROCEDURES AND LANDED WITHOUT FURTHER INCIDENT. 1L72 3O A7CE 20021011001202002101100120CE 2002 10 11 2002FA0001161 120020905G2910572700258 LINE CESSNA441 441 2076020CE GARRTTTPE331TPE331* 01514WP HYD SYSTEM CRACKED G K NONE O OTHER ININSP/MAINT 1 GL25308323750 4410342 HYDRAULIC LINE FAILED DURING FLIGHT AND AIRCRAFT LOST ALL HYDRAULIC PRESSURE. LANDING GEAR WAS EXTENDED BY EMERGENCY BLOW DOWN BOTTLE. LINE IS ON LEFT SIDE, AFT OF FIREWALL BETWEEN FILTER AND FLOW VALVE. FAILURE APPEARS TO BE MANUFACTURER DEFECT. 1L72 3T3 TRTA28CE E2WE 20021011000012002101100001EA 2002 10 11 2002FA0001162 120020925G2420756654A ADG CNDAIRCL600 CL6002B16 1900305EA ELECTRICAL FAILED C K NONE W INADEQUATE Q C ININSP/MAINT 1 SW05371CL 5371 INSTALLED A LOANER AIR DRIVEN GENERATOR (ADG) DUE TO SURFACE CORROSION ON THE GENERATOR SHAFT AND NUT THAT WAS FOUND ON AN INSPECTION. COMPLETED AN IN-FLIGHT CHECK TO OPERATE THE ADG AND FOUND THE ADG INOPERATIVE AT THAT TIME. RETURNED TO HANGAR AND REINSTALLED THE PREVIOUSLY REMOVED ADG. TROUBLESHOOTING REVEALED THAT THE LOANER ADG HAD DAMAGED TWO OTHER COMPONENTS IN THE SYSTEM DURING THE OPERATIONAL CHECK. THE ADG AUTO CONTROL UNIT AND THE ADG GENERATOR CONTROL UNIT. INSTALLED NEW PARTS AND THEN COMPLETED A SATISFACTORY IN FLIGHT OPERATIONAL CHECK OF THE ADG SYSTEM. 2L72 4F RTA21EA 20021011000022002101100002SO 2002 10 11 2002FA0001163 220021008G8530 CYLINDER HEAD CONT O520 TSIO520NB 17040SO ENGINE SEPARATED C K NONE O OTHER ININSP/MAINT 1 SW17 650 ENGINE CYLINDER HEAD AND BARREL SEPERATED DURING ENGINE RUN. 3 O E8CE 20021011000032002101100003SO 2002 10 11 2002FA0001164 220021008G8530 CYLINDER HEAD CONT O520 TSIO520NB 17040SO ENGINE SEPARATED C K NONE O OTHER ININSP/MAINT 1 SW17 650 ENGINE CYLINDER HEAD AND BARREL SEPERATED. 3 O E8CE 20021011000042002101100004CE 2002 10 11 2002FA0001165 120021009G321122411001 FITTING CESSNA182 TR182 2072735CE MLG CRACKED C K NONE O OTHER ININSP/MAINT 1 EA216584S9500 R18201692 MLG AXLE ATTACHMENT FITTING, FOUND CRACKED AT TOP OUTBOARD EDGE. CRACK IS VISIBLE WITHOUT ADDITIONAL AIDS. CRACK ORIGINATES AT THIN EDGE WHERE FITTING WAS MACHINED DURING MANUFACTURE. CRACK IS ALSO IN ALIGNMENT WITH FORGING LINE. 1H71 3O 3A13 20021011000052002101100005GL 2002 10 11 2002FA0001166 120021001G321110209001 GROMMET CIRRUSSR SR22 2130001GL MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SO1525MV 124 0095 DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. 1L71 3O NTA00009CH 20021011000062002101100006GL 2002 10 11 2002FA0001167 320021009G6114 HUB MCAULY 3AF32C505B CESSNA402 402CESSNA 207590KCE MCAULY3AF32C3AF32C505 GL PROPELLER MAKING METAL C K NONE K FLUID LOSS ININSP/MAINT 1 WP23TZAMS 374 841637 402C0517 841637 OIL WAS DETERMINED TO BE LEAKING FROM THE PACKING AROUND THE BLADE AND NOT FROM THE CRANKSHAFT SEAL. PROPELLER WAS REMOVED FROM ENGINE AND DISASSEMBLED. HUB WAS CONFIRMED TO BE FILLED WITH ENGINE OIL. UPON FURTHER EXAMINATION, AN EXCESSIVE AMOUNT OF SCORING WAS FOUND ON THE PISTON ROD ASSEMBLY AND THE HUB AND THE PACKING WAS DAMAGED. IN ADDITION, METAL SHAVINGS WERE FOUND IN THE CYLINDER ASSEMBLY AND THE PISTON ASSEMBLY COULD NOT BE REMOVED FROM THE PISTON ROD ASSEMBLY. THIS IS THE SECOND PROPELLER FAILURE OF THIS KIND IN THE PAST YEAR. 1L72 3O A7CE 5 CP22EA 20021011001222002101100122SO 2002 10 11 2002FA0001168 220020813G8500 ENGINE CESSNA150 150M 2071830CE CONT O200 O200A 17020SO NACELLE MALFUNCTIONED G A UNSCHED LANDING EMJVIBRATION/BUFFET OVER TEMP WARNING INDICATION LDLANDING 1 SO17704TJ 15078858 23480A AIRCRAFT LANDED ON THE ROADWAY BECAUSE PILOT STATED HE COULD NOT AMINTAIN ALTITUDE AT 1200 FT, THE ENGINE STARTED BACKFIRING AND SOUNDED LIKE IT WAS MISSING. ALL OTHER INSTRUMENTS APPEARED NORMAL, AND THE WEATHER WAS CLEAR AND 85 DEGREES. THIS WAS NOT THE FIRST TIME FOR THIS AIRCRAFT. OTHER PILOTS HAVE STATED THAT THEY HAVE HAD THE SAME PROBLEM. 1H71 3O3 O 3A19 E252 20021011001232002101100123CE 2002 10 11 2002FA0001169 120020904G3246300257 WHEEL BEECH 90 C90A 1152911CE PWA PT6 PT6A6 52043EA MLG CRACKED B K NONE O OTHER ININSP/MAINT 1 SO133195Q375 LJ1595 FOUND WHEEL HALF CRACKED FROM BOLT HOLE CAUSING LEAK DOWN OF TIRE. THERE WERE NO SIGNS OF OVER TORQUE OR EXCESSIVE WEAR. TT 375 HOURS. CASTING OR MANUFACTURE DEFECT. PART WAS SENT TO MFG FOR EVALUATION. 1L72 3T3 TRT3A20 E4EA 20021011001242002101100124CE 2002 10 11 2002FA0001170 120020926G3211504100112 BELLCRANK CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO RT MLG WHEEL WELBROKEN D K NONE O OTHER ININSP/MAINT 1 GL19340FS 340A0801 RIGHT MAIN LANDING GEAR COLLAPSED ON ROLLOUT AFTER TOUCHDOWN. INITIAL INSPECTION REVEALED OUTBOARD MAIN LANDING GEAR RETRACTION LINK (PN 504100112) SEPARATED FROM RIGHT MAIN LANDING GEAR STRUT AT ITS TWO ATTACH POINTS. BOTH BREAKS APPEAR TO BE INSTANTANEOUS AND UPPER STRUT ATTACH LUG AND BOLT WERE SHEARED. NO OBVIOUS CAUSE FOR THE BREAKS WERE APPARENT. 1L72 3O3 O 3A25 E8CE 20021011001252002101100125CE 2002 10 11 2002FA0001171 120020924G53203634031015 CHANNEL BEECH 36 A36 1151604CE CONT O550 IO550B SO FUSELAGE CRACKED B YWBRK NONE O OTHER ININSP/MAINT 1 WP17801NH5697 E2692 686008 DURING ROUTINE INSPECTION AFT RADIO (AVIONICS) SHELF ATTACH BRACKET WAS FOUND CRACKED AT AFT END IN BEND RADIUS. BRACKET IS LOCATED ON RIGHT SIDE BETWEEN BS 179.00 TO 207.00. VIBRATION AND TIME IN SERVICE IS PROBABLE CAUSE. AVIONICS SHELF ASSEMBLY ALSO FOUND CRACKED IN BEND RADIUS. 1L71 3O3 O 3A15 E3SO 20021011001262002101100126EA 2002 10 11 2002FA0001173 220021001G8500 ENGINE CESSNA172 172R 2072401CE LYC O360 IO360C1A 41514EA NACELLE MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 EA219878F 17280438 L2749551A ENGINE SHUT DOWN IN FLIGHT. ABLE TO RESTART ON GROUND RUNUP INDICATES NO PROBLEMS. REMOVED FUEL SERVO FOR BACK/FLOW CHECK FOUND OIL IN SERVO NOT DETERMINED IF CAUSE OF SHUTDOWN. FLOW DIVIDER OVERHAULED. IGNITION SWITCH DISASSEMBLED/REPAIRED. FUEL VENT SYSTEM CHECKED, OK. CAUSE OF SHUTDOWN UNKNOWN. NOT ABLE TO DUPLICATE. 1H71 3O3 ONT3A12 1E10 20021015000042002101500004SO 2002 10 15 2002FA0001174 120020929G5711 SPAR LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO LT & RT WINGS CORRODED D K NONE O OTHER ININSP/MAINT 1 WP071291B 5918 INTERGRANULAR CORROSION, FOUND IN THE FOLLOWING WING COMPONENTS DURING A REPAIR/REBUILD PROCESS. LT AND RT MAIN SPAR BEAMS, REAR, LEFT MAIN SPAR BEAM, FRONT. 1H71 3O3 O A694 E205 20021015000052002101500005CE 2002 10 15 2002FA0001175 120020820G143010161000013 RIVET BEECH 200 A200 1152921CE TRIM TAB MISSING D K NONE O OTHER ININSP/MAINT 1 SW151554 10 BC21 ELEVATOR TRIM TABS ON AIRCRAFT WERE INSPECTED FOR RIVETS. FOUND LT ELEVATOR TRIM TAB THAT WAS INSTALLED 10 HOURS PRIOR, TO BE MISSING ALL RIVETS. THE SKINS WERE BONDED BUT RIVETS WERE NEVER INSTALLED. THE TRIM TAB HAD BEEN SITTING ON OUR SHELF FOR 2 YEARS BEFORE INSTALLATION. THOUGH INSPECTION OF TRIM TABS BEFORE INSTALLATION TO VERIFY RIVET INSTALLATION. 1L72 4T A24CE 20021015000062002101500006SW 2002 10 15 2002FA0001177 120020407G323071461 LEG ASSY BBAVIA8 8GCBC 1220803SW LYC O360 O360* 41514EA MLG BROKEN G O OTHER O OTHER NRNOT REPORTED 1 WP012693Z 26878 LEFT MAIN GEAR LEG BROKE AT ATTACHING CLAMP ON LANDING. EVIDENCE OF CHAFING AT FORWARD LOWER SURFACE WHERE UNDETECTED FLAW IS NOTED. NO INJURIES TO PILOT, OUTBOARD RIB BENT, PROP STRIKE. 1H71 3O3 O A21CE E286 20021015000072002101500007WP 2002 10 15 2002FA0001179 120020717G6420369D2172121 BEARING HUGHES369 369D 4470706WP TAIL ROTOR LOOSE B EOORO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 AL03CGLNQ 2006620 AIRCRAFT WAS EXPERIENCING INCREASED TAIL ROTOR VIBRATIONS IN THE TAIL ROTOR FORK, UPON REMOVAL, ONE BEARING POPPED OUT. IT APPEARS THAT IT HAD ALREADY BEEN LOOSE AND ROTATING WITHIN THE FORK. 1G71 3U H3WE 20021015000012002101500001SW 2002 10 15 2002FA0001180 120021012G7603660017003 CLAMP MOONEYM20 M20R 5870225SW CONT O550 IO550G 17042SO THROTTLE BODY WORN D O OTHER O OTHER LDLANDING 1 GL19101DX320 290221 679463 OWNER COMPLAINED THAT HE WAS UNABLE TO CLOSE THROTTLE TO LAND. THE MIXTURE HAD TO BE MOVED TO CUT-OFF TO LAND. INVESTIGATION REVEALED THAT THE THROTTLE CABLE HOUSING WAS MOVING IN THE CLAMP LOCATED AT THE THROTTLE BODY PREVENTING THE THROTTLE FROM CLOSING ALL THE WAY. THE CLAMP HALVES WERE WORN INTERNALLY TO THE POINT THAT THEY NO LONGER WERE TIGHT. THE INTERNAL RIDGE IN THE CLAMP HALVES THAT CONTACTS A GROOVE IN THE THROTTLE CABLE HOUSING WAS WORN AWAY. THE WEAR APPEARS TO HAVE BEEN CAUSED BY VIBRATION. THE CLAMP IS MADE OF ALUMINUM. IT WOULD SEEM THAT A HARDER MATERIAL WOULD BE APPROPRIATE. AT THE SAME TIME THE MIXTURE CABLE CLAMP WAS FOUND WORN AND CLOSE TO FAILURE. THIS IS THE SAME CLAMP USED ON 1L71 3O3 ORT2A3 E3SO 20021015000022002101500002CE 2002 10 15 2002FA0001181 120021013G325266082788 COMPUTER LEAR 35 35A 5170602CE NLG STEERING MALFUNCTIONED D D RETURN TO BLOCK L NO TEST TXTAXI/GRND HDL 1 WP2810AH 657 NOSE WHEEL STEERING WILL NOT ARM. FOUND NO OUTPUT VOLTAGE ON P224 PIN A. 1.0 VAC REQUIRED FROM THIS PIN. 2L72 4F A10CE 20021015000032002101500003 2002 10 15 2002FA0001183 420021014G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM03789EP82 34 172S8135 FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED AT ONE FLANGE AT PROPELLER BLADE CUT OUT. EDGE WITH NUTPLATE AND SCREW STILL ATTACHED TO PROPELLER SPINNER. CESSNA SERVICE BULLETIN SB02-61-01 WAS ACCOMPLISHED 34.0 HOURS PREVIOUSLY AND THE AFT SPINNER BULKHEAD REPLACED AT 82.2 HOURS WITH. THIS IS AN ONGOING PROBLEM AND HAS NOT BEEN RESOLVED WITH THE NEW -11 BULKHEAD NOR CESSNA SERVICE BULLETIN SB02-61-01. 1H71 3O NT3A12 20021015000082002101500008SO 2002 10 15 2002FA0001184 220021014G8550626739 COLLAR CONT O520 IO520D 17032SO ENGINE DISTORTED B K NONE O OTHER ININSP/MAINT 1 WP07 566793 IN ASSEMBLING A NEW STANDARD GOVERNOR OIL TRANSFER COLLAR TO THE CRANKSHAFT IT WAS FOUND TO BIND ON THE JOURNAL. PRIOR TO DIASSEMBLING THE COLLAR HALVES THE INSIDE DIAMETER WAS NOTED TO BE SMOOTH AND COLLAR TO JOURNAL CLEARANCE WITHIN NEW LIMITS. ONCE THE COLLAR HAD BEEN DISASSEMBLED AND REASSEMBLED A STEP OF APPROXIMATELY .001 INCH WAS FOUND AT THE PARTING SURFACES. INSTALLING THE COLLAR ON THE CRANKSHAFT AND TORQUING IT IN PLACE CAUSED IT TO BIND IN AN INTERFERENCE FIT. IT APPEARS THE TWO HALVES ARE UNDER SOME TORSIONAL STRESS WHICH IS RELIEVED UPON TAKING THEM APART. THIS IS NOW THE FOURTH CONSECUTIVE COLLAR ORDERED FROM OUR AVIALL DISTRIBUTOR TO EXHIBIT THESE CHARACTERISTICS. CALLS HAVE BEEN MADE TO TELE 3 O E5CE 20021022000112002102200011CE 2002 10 22 2002FA0001186 120021008G2915HE151854SN1 PRESSURE SWITCH RAYTHNDH125 HAWKER800XP 7150012CE GARRTTTFE731TFE731* 01518WP NR 2 HYD SYSTEM LEAKING D O OTHER K FLUID LOSS NRNOT REPORTED 1 SO111630 428 258557 HYD FLUID SQUIRTING FROM UPPER PART OF PRESSURE SWITCH. 2L72 4F4 FRTA3EU E6WE 20021022000122002102200012EA 2002 10 22 2002FA0001187 220020923G7414LW15416 ADAPTER CESSNA150 150H 2071818CE LYC O360 O360A4A 41514EA MAGNETO MISSING C K NONE O OTHER ININSP/MAINT 1 GL0522159392 15068106 L2554236A PULLED THE MAGNETOS FOR INSPECTION, AND FOUND THAT THE RT MAGNETO DRIVE ADAPTER HAS SOME DAMAGED BEARINGS. PULLED THE DRIVE ADAPTER, AND FOUND THAT PIECES OF THE BEARING CAGE WERE MISSING, AND THE BEARINGS WEREN`T SPACED PROPERLY. PULLED THE OIL FILTER, SCREEN, AND OIL SUMP IAW, AND FOUND 6 PIECES OF STEEL. REASSEMBLED THE ENGINE, AND RETURNED TO SERVICE. INFORMATION FROM THE MAGNETO DRIVE ADAPTER ASSEMBLY WERE AS FOLLOWS. 1H71 3O3 O 3A19 E286 20021022000132002102200013EA 2002 10 22 2002FA0001188 220020823G8500LW13885M06 BEARING LYC O540 TIO540* 41532EA NR 2 DELAMINATED B VD3RK NONE O OTHER ININSP/MAINT 1 WP01 11 L2177248A BEARING FAILURE OF FRONT MAIN BEARING IN THE NR 2 POSITION. FLAKING, BENT, AND DELAMINATED OVER ENTIRE WIDTH OF NR 2 POSITION. MOST OF BEARING SURFACE STILL CONNECTED TO SHELL. DELAMINATION OF BEARING CRANKSHAFT AND CRANKCASE NOT SERVICEABLE AFTER DAMAGE. C/A: CHANGE BACK TO TRIMETAL BEARINGS FROM THESE ALUMINUM/STEEL BACKED TYPE. 3 O E14EA 20021022000142002102200014GL 2002 10 22 2002FA0001189 320020925G611483410 COLLAR BEECH 35 G35 1151516CE CONT E225 E2258 17015SO HARTZLHCA2V HCA2V* GL PROPELLER CRACKED B LU4RK NONE O OTHER ININSP/MAINT 1 SO1734TT D4737 GUIDE COLLAR CRACKED DUE TO VIBRATION FROM PROPELLER. BOTH BLADES SLIPPED IN CLAMP CREATING A SPLIT IN ANGLES. THIS CAUSED VIBRATION. 1L71 3O3 O A777 E267 5 CP24EA 20021022000152002102200015GL 2002 10 22 2002FA0001190 320020925G6114B4460 PIN BEECH 36 A36 1151604CE CONT O520 IO520BB 17032SO MCAULY3A32C 3A32C76 GL PROPELLER BROKEN B LU4RK NONE O OTHER ININSP/MAINT 1 SO172061A 750 E1425 ACTUATING PIN BROKE AT BASE OF THREADS DUE TO IMPROPERLY DRILLED HOLE TO ACCEPT PIN. SHALLOW DEPTH NOT TAPPED TO THE BOTTOM OF THE HOLE. 1L71 3O3 O 3A15 E5CE 5 CP21EA 20021022000162002102200016EA 2002 10 22 2002FA0001191 220021003G852061156 LOCK BEECH 23 C23 1151242CE LYC O360 O360A4K 41514EA CRANKSHAFT OVERTORQUED C KKCSK NONE W INADEQUATE Q C ININSP/MAINT 1 CE07837KS M2076 L3022436A LOCKPLATE FOR CRANKSHAFT GEAR RETAINING BOLT NOT SUFFICIENTLY BENT ALLOWING CRANKSHAFT GEAR BOLT TO LOOSEN. CRANKSHAFT GEAR DOWEL PIN SHEARED. RECOMMENDATION TO PREVENT RECURRENCE: CRANKSHAFT GEAR BOLT TORQUE SHOULD BE VERIFIED AT 204IN/LBS AND LOCKPLATE INSPECTED TO ENSURE PROPER LOCKING OF THE PLATE AGAINST THE BOLT HEAD. 1L71 3O3 O A1CE E286 20021022000172002102200017SW 2002 10 22 2002FA0001192 120021003G3710211CC PUMP GULSTM112 112TC 7630306SW LYC O360 IO360A1A 41514EA VACUUM SYS FAILED D O OTHER O OTHER NRNOT REPORTED 1 CE074613W 13103 L22109A VACUUM PUMP FAILED IN NIGHT IFR CONDITIONS. 1L71 3O3 O A12SO 1E10 20021022000182002102200018EA 2002 10 22 2002FA0001193 220021001G7414ES10682054 DISTRIBUTOR BLK BENDIX MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MAGNETO CRACKED D K NONE O OTHER ININSP/MAINT 1 NM03 4081110 DISTRIBUTOR GEAR TOOTH DAMAGE. SEVERAL GEAR TEETH BROKEN ON BOTH GEARS. NEW GEARS WERE FOUND TO BIND ON ROTOR PINION GEAR EVERY 90 DEGREES. NO ROTOR TO HOUSING INTERFERENCE INDICATED. VISUAL INSPECTION REVEALED NO CRACKS OTHER THAN ACCEPTABLE STRESS CRACK AT BEARING BORE IN BLOCK. GEAR AXLE BUSHINGS APPEAR SECURE, MAY BE MISALIGNED FROM WARPAGE OR MANUFACTURE DEFECT. SCREW THREAD INSERTS FOR CONTACT ASSY. PULL OUT BEFORE REACHING MINIMUM TORQUE. BLOCK HAS A 94 DATE CODE. REPLACED BLOCK, MAGNETO FUNCTIONS PROPERLY. 1L71 3O3 O 2A3 1E10 20021021000012002102100001CE 2002 10 21 2002FA0001194 120020920G14308178610 BOLT BEECH 100 B100 1152919CE WING CRACKED W D7FFK NONE O OTHER ININSP/MAINT 1 NM01 2716 BE15 LEFT AFT UPPER WINGBOLT CRACK FOUND WHERE SHAFT CONNECTS TO BOLT HEAD. WINGBOLT INSPECTION CARRIED OUT IAW AD. BOLT WAS INSPECTED 1 YEAR/ 324 HOURS, PRIOR. BOLT, TT 2716.5 HOURS, 2544 A/C CYCLES. INSTALLED APRIL 1991. 1L72 4T A14CE 20021022000192002102200019NE 2002 10 22 2002FA0001195 220020819G7250 RIVET BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE TURBINE WHEEL ERODED D K NONE O OTHER ININSP/MAINT 1 GL25457CW2505 RK57 PCE100294 HIGH TURBINE BLADE RETAINING RIVETS AND COLLARS APPEAR TO BE SUFFERING EROSION, CAUSING RIVET TAILS TO FALL BELOW THE .050 INCH PROTRUSION AS OUTLINED IN MFG MM. IF LEFT IN SERVICE THIS SITUATION COULD CAUSE THE HIGH TURBINE BLADES TO SHIFT AND/OR FAIL, CAUSING ENGINE FAILURE. ALL 71 RIVETS AND 71 COLLARS ARE BEING REPLACED WITH NEW. 2H72 4F4 FRTA16SW E25EA 20021023000632002102300063SO 2002 10 23 2002FA0001196 220021015G8530655469A7 CYLINDER CONT O520 IO520D 17032SO ENGINE CRACKED B K NONE O OTHER ININSP/MAINT 1 WP07 282740R A CRACKED CYLINDER HEAD FIN WAS DISCOVERED ON NR 1 CYLINDER FOLLOWING THE ACCEPTANCE RUN AFTER THE ENGINE HAD BEEN OVERHAULED. AN ATTEMPT TO DRESS IT OUT INDICATED THAT THE CRACK EXTENDED ON TO THE BASE OF THE FIN AND POSSIBLY CYLINDER HEAD. CYLINDER WAS REMOVED AND REPLACED UNDER FACTORY WARRANTY. 3 O E5CE 20021022000202002102200020CE 2002 10 22 2002FA0001197 120020913G2752 SHAFT BEECH 90 C90A 1152911CE PWA PT6 PT6A6 52043EA FLAP ACTUATOR CRACKED D K NONE O OTHER ININSP/MAINT 1 EA13394B LJ1553 DURING A ROUTINE PHASE 1 AND 2 INSPECTION ON THIS AIRCRAFT, LUBRICANT WAS FOUND ACCUMULATING AT ACTUATOR HOUSING. FURTHER INSPECTION REVEALED A CRACK IN THE CHROMED SHAFT RUNNING PARALLEL WITH THE SHAFT STARTING AT THE ROD-END. THIS CRACK WAS APPROXIMATELY 2.75 INCHES IN LENGTH. THE ACTUATOR WAS REPLACED WITH A NEW ASSEMBLY. NO RECOMMENDATIONS CAN BE MADE TO PREVENT THIS OCCURANCE. 1L72 3T3 TRT3A20 E4EA 20021023000642002102300064EU 2002 10 23 2002FA0001198 120021017G2520T700A251000710 SEAT BELT SOCATATBM TBM700 8682000EU CABIN FAILED B BNGRK NONE L NO TEST ININSP/MAINT 1 GL19700SP1333 98 SEAT BELT BUCKLE CAME APART WITH A SIMPLE JERK TEST. WITH A STEADY PULL ON THE SEAT BELTS THE BELTS HOLD OK. ALL BELTS IN THE AIRCRAFT DID THE SAME THING. SEAT BELTS ARE MANUFACTURED BY ANJOU AERONAUTIQUE, THERE IS A SOCATA SERVICE LETTER SL70-027 THAT INFORMS USERS ABOUT POSSIBILITY OF REPLACEMENTS AND MENTIONS FRENCH AD 2002-104 & 2002-105, BUT DOES NOT INDICATE THE SERIOUSNESS OF THE PROBLEM. THE SUBMITTER BELIEVES THAT THIS IS A SERIOUS SAFETY ISSUE AS THEY HAVE FOUND ALL LIKE BELTS IN ANOTHER AIRCRAFT WILL FAIL TO HOLD IN THE SAME MANOR AND RECOMMENDS IMMEDIATE INSPECTION AND REPLACEMENT OF THE EFFECTED SEAT BELTS. THIS ORGINALY SUBMITED TO GL-19 BY PAT BEATY @ IMAGE AIR, INC. (BNGR) 1L71 3T RTA60EU 20021023000602002102300060CE 2002 10 23 2002FA0001199 120021022G2842S33311 TRANSMITTER CESSNA172 172S 2072439CE RT FUEL TANK FAILED D A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 NM03789EP1893 172S8135 RT FUEL QUANTITY WENT TO "0" IN FLIGHT, AIRCRAFT RETURNED TO HOME STATION. MAINTENANCE FOUND FUEL QUANTITY TRANSMITTER FLOAT SEPERATED FROM THE TRANSMITTER. THE FLOAT ATTACH ARM BROKE OUTBOARD OF THE FLOAT WHERE IT WAS CRIMPED AND THE END PIECE, WASHER AND FLOAT SEPERATED. THE PIECES WERE FOUND INSIDE THE FUEL CELL. REPLACED THE TRANSMITTER, RESEALED THE TANK ACCESS COVER, RESERVICED, RECALIBRATED AND LEAK CHECKED SATISFACTORY. 1H71 3O NT3A12 20021024000022002102400002CE 2002 10 24 2002FA0001204 120021023G32348857K44 SELECTOR SWITCH CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA MLG MISINSTALLED D O OTHER W INADEQUATE Q C LDLANDING 1 CE078971M2319 177RG0371 PILOT INEVERTANTLY BUMPED MLG SWITCH ON SHORT FINAL WHILE MOVING THE TRIM WHEEL, CAUSING A GEAR-UP LANDING. THE SAFETY FAILED TO WORK ON MLG SWITCH. UPON INVESTIGATION FOUND THAT THE SWITCH KNOB WHEN SCREWED COMPLETLY ONTO SWITCH CAUSED THE SPRING LOADED SAFETY TO COME OFF THE SWITCH. THIS CAUSED THE SAFETY NOT TO WORK AND MADE IT EASY TO MOVE THE SWITCH WITHOUT PULLING OUT ON THE KNOB TO MOVE SWITCH INTO THE UP POSITION OR DOWN POSITION. INSTALLED A NEW SWITCH AND KNOB AND CHECKED THE OPERATION AND WAS FOUND TO WORK PROPERLY. 1H71 3O3 O A20CE 1E10 20021025000062002102500006EA 2002 10 25 2002FA0001205 220021017G852005K19987 BOLT CESSNA182 182S 2072701CE LYC O540 IO540* 41532EA CRANKSHAFT DEFECTIVE B DPORK NONE W INADEQUATE Q C ININSP/MAINT 1 NM079562D 18280239 FINAL TORQUE OF CRANKSHAFT BOLT COULD NOT BE REACHED, AFTER REMOVAL OF BOLT, IT WAS FOUND TO BE DEFFECTIVE, AND TAPPERED TOWARDS THE CENTER OF THE SHANK. 1H71 3O3 ONT3A13 1E4 20021025000072002102500007 2002 10 25 2002FA0001206 420021009G2561KD9P0101 LIFE VEST FAILED B KQ1RK NONE O OTHER ININSP/MAINT 1 EA07 LIFE PRESERVER FAILED, MFG RECOMMEDNED CELL PRESSURE TEST IAW MM. DOM JANUARY 1983 20021025000082002102500008 2002 10 25 2002FA0001208 420021016G3452411230027 TRANSISTOR CESSNA150 150L 2071826CE CONT O200 O200* 17020SO TRANSPONDER UNAPPROVED PART B BIERK NONE O OTHER ININSP/MAINT 1 EA2119255 15074278 TRANSPONDER FAILURE: IDENT PULSE PRESENT AND REPLY LAMP LIT WHEN UNIT HOT. (NOT COMMANDED) FOUND Q22 AND ASSORTED CIRCUIT VERY TEMPERATURE SENSITIVE. REPLACED COMPONENTS AND FOUND Q22 NOT STANDARD PART. PART INSTALLED AN ECG TPE 123. PART REPLACED WITH ARC PART RENDERING UNIT SERVICEABLE. 1H71 3O3 O 3A19 E252 20021025000092002102500009SW 2002 10 25 2002FA0001209 120020909G2730740009007 UNIVERSAL JOINT MOONEYM20 M20K 5870220SW CONT O360 TSIO360* 17025SO PITCH TRIM INOPERATIVE B MGORK NONE O OTHER ININSP/MAINT 1 CE09231GE 250233 DURING INVESTIGATION OF AUTO PILOT PITCH OSOLATIONS. FOUND UNIVERSAL JOINT AT PITCH TRIM JACK SCREW SQUARE DRIVE ISSING ONE OF THE FOUR STAKED IN ROLL PINS. 1L71 3O3 O 2A3 E9CE 20021025000012002102500001SO 2002 10 25 2002FA0001210 120021024G7160950618283 SPACER PIPER PA44 PA44180 7104402SO CARB HEAT MISSING B O OTHER O OTHER LDLANDING 1 WP28571ER160 4496147 DURING LANDING ROLLOUT THE RIGHT ENGINE QUIT. ENGINE WAS RESTARTED AND RUNUP NORMAL EXCEPT FOR CARB HEAT OPERATION. MAINTENANCE FOUND BOTH LT & RT CARB HEAT CONTROLS NOT RIGGED RIGHT. MECHANIC OPENED CONSOLE AND FOUND THE SPACERS FOR BOTH CARB HEAT LEVERS HAD NOT BEEN INSTALLED AT THE FACTORY AND THIS ALLOWED THE CARB HEAT CONTROL LEVERS TO HANG UP ON THE CONSOLE FRAME 1L72 3O A19S0 20021025000022002102500002SO 2002 10 25 2002FA0001211 120021024G3233 SEAL PIPER PA44 PA44180 7104402SO MLG ACTUATOR LEAKING B K NONE K FLUID LOSS ININSP/MAINT 1 WP28574ER49 4496150 RIGHT MAIN GEAR ACTUATOR LEAKING AT SHAFT SEAL. ACTUATOR REPLACED. ACTUATOR PREVIOUSLY REPLACED AT 32.3 HOURS AFTT. THIS IS AN ONGOING PROBLEM WITH PIPER ACTUATOR. SO FAR ON A FLEET OF ONLY 7 PA-44 AIRCRAFT WE HAVE REPLACED 18 ACTUATORS SINCE AUGUST 2002. PIPER FACTORY HAS BEEN AWARE OF THE PROBLEM AND ARE WORKING WITH ON A NEW SEAL. WE FIND THE ACTUATOR SHAFTS HAVE BEEN LEFT WITH VERY SHARP EDGES ON THE OUTER END WHERE IT IS MACHINED. WE HAVE ALSO FOUND THE WITNESS HOLE FOR THE ROD END NOT CHAMFERED TO GET RID OF BURRS. THESE ARE TEARING UP THE SEALS. IT IS ALSO NOTED THAT THE SEALS SEEM TO BE VERY SOFT. AN ALTERNATE SEAL (O-RING) IS LISTED IN THE PARTS CATALOG. 1L72 3O A19S0 20021025000032002102500003EU 2002 10 25 2002FA0001212 120021024G2842522304010 TRANSMITTER AVIONSR2160 R2160 0960101EU FUEL QTY DAMAGED G A UNSCHED LANDING N FALSE WARNING ABAEROBATIC 1 WP05216RN7011 NR200 FUEL QUANTITY TRANSMITTER, HAS INTERNAL DAMAGE CAUSING THE RHEOSTAT TO STICK. CONDITION ALLOWED THE TRANSMITTER TO SEND AN ERRONEOUS SIGNAL TO THE FUEL QUANTITY INDICATOR. 1L71 3O RTA48EU 20021025000042002102500004 2002 10 25 2002FA0001213 420021024G25624520130 BATTERY PACK ARTEX ELT1104 ELT CRACKED C K NONE K FLUID LOSS ININSP/MAINT 1 GL19 61297 ON ANNUAL INSPECTION DISCOVERS BATTERY PACK ON ELT1104 CRACKED AND BATTERY ACID LEAK. FOUND ON TWO SEPARATE UNITS, SAME LOCATION AND SAME FAILURE. BATTERY PACKS PURCHASED IN OCT-2000 DUE FOR REPLACEMENT NEXT MONTH. DAMAGE WAS NOT PRESENT AT PREVIOUS ANNUAL IN OCT-2001. 20021028000042002102800004GL 2002 10 28 2002FA0001214 320021010G6114D5044 HUB MCAULY CESSNA177 177 2073704CE MCAULY2D34C B2D34C207 GL PROPELLER CORRODED C L2PRK NONE O OTHER ININSP/MAINT 1 SW13 742422 RETIRED HUB DUE TO SURFACE CORROSION ON EXTERIOR, HUB NOT PAINTED. 1H71 3O NTA13CE 5 CP7EA 20021028000052002102800005GL 2002 10 28 2002FA0001215 320020919G6114698500 HUB CESSNA401 401A 207590DCE CONT O520 TSIO520* 17040SO MCAULY3AF32C3AF32C87 GL PROPELLER MISMANUFACTURED B L2PRK NONE O OTHER ININSP/MAINT 1 SW136221Q 401A0021 756476 BLADE RETENTION NUT TO HUB LOCK PLUG HOLE MACHINED IN WRONG LOCATION AT LAST OVERHAUL OR LAST ASSEMBLY. HUB RETIRED FROM SERVICE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021028000062002102800006GL 2002 10 28 2002FA0001216 320020919G6114D5892C87 HUB CESSNA401 401A 207590DCE MCAULY3AF32C3AF32C87 GL PROPELLER MISMANUFACTURED B L2PRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW136221Q 401A0021 791238 BLADE FERRULE ACTUATING PIN HOLE DRILLED IN WRONG LOCATION IAW MM. (MIN. EDGE DISTANCE BETWEEN HOLE 1 INCH) HUB RETIRED FROM SERVICE. 1L72 3O A7CE 5 CP22EA 20021028000072002102800007GL 2002 10 28 2002FA0001217 320020919G6114D5892C87 HUB CESSNA401 401A 207590DCE MCAULY3AF32C3AF32C87 GL PROPELLER MISMANUFACTURED B L2PRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW136221Q 401A0021 791238 BLADE RETENTION NUT TO HUB LOCK PLUG HOLE DRILLED TO IMPROPER DEPTH. HUB RETIRED FROM SERVICE. 1L72 3O A7CE 5 CP22EA 20021028000082002102800008CE 2002 10 28 2002FA0001218 120021016G2435300SGL129Q STARTER GEN CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE RIGHT INOPERATIVE C K NONE O OTHER ININSP/MAINT 1 EA19400LX950 5600453 GENERATOR DROPPED OFF LINE DURING FLIGHT AND WAS ABLE TO BE RESET. AFTER LOADS WERE SHED. AFTER LANDING AND SHUTDOWN STARTER WOULD NOT ROTATE FOR NEXT START. REPLACED RIGHT STARTER GENERATOR. CHECKED OK. 2L72 4F4 FRTA22CE E25EA 20021028000092002102800009CE 2002 10 28 2002FA0001219 120021011G571117107036 SPAR CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA WING CORRODED D K NONE O OTHER ININSP/MAINT 1 GL132692V3040 177RG0659 OBSERVED THE CARRY THRU SPAR CORROSION WHEN LOOKING AT THE AIRCRAFT. THIS ITEM HAD SURFACE CORROSION THAT HAS BLISTERING THAT COULD BE PICKED AT AND MOST OF THE SURFACE AREA HAD WHITE DUSTING AND DISCOLORATION INDICATING CORROSION THAT REQUIRES TREATMENT. CAUSE IS PROBABLY FROM EXPOSURE TO OUTSIDE STORAGE. 1H71 3O3 O A20CE 1E10 20021028000102002102800010EA 2002 10 28 2002FA0001220 220020809G8530 BOLT PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA NR 3 CYLINDER BROKEN D K NONE O OTHER ININSP/MAINT 1 WP0732481722 28R7535061 NR 3 CYLINDER CONNECTING ROD BOLT BROKE. ENGINE WAS DESTROYED. PROBABLE CAUSE, POSSIBLE OVER-TORQUED. 1L71 3O3 O 2A13 1E10 20021028000112002102800011SW 2002 10 28 2002FA0001222 120020930G7722580505 INDICATOR GULSTM690TP 690B 7630516SW GARRTTTPE331TPE331* 01514WP EGT DEFECTIVE B MV5RK NONE O OTHER ININSP/MAINT 1 GL25690HT214 11467 NON-LINEAR ERROR GAGE READS COOLER THAN INPUT 5 DEGREE AT 400, 6 DEGREE C 500, 7 DEGREES C 600 AS HIGH AS 10 DEGREE AT TIMES ZERO ERROR AT 200 DEGREE. DEFECT FOUND DURING CALIBRATION OF EGT DUE TO TEMP SPLITS. 1H72 3T3 T 2A4 E2WE 20021030002202002103000220 2002 10 30 2002FA0001223 420021008G2210SVO8513 SERVO ISRAELGALAXYGALAXY 4500307EU AUTOPILOT FAILED G O OTHER J WARNING INDICATION NRNOT REPORTED 1 GL2583EJ 344 009 SERVO CAUSED AUTOPILOT MISTRIM CONDITION AND EVENTUALLY DID NOT PERMIT AUTOPILOT TO ENGAGE. 2L72 4F RTA53NM 20021030002222002103000222 2002 10 30 2002FA0001224 420021009G6122 SETSCREW RHNFLUEXT300EA300L 70218DGEU LYC O540 AEIO540L1B5 41532NE MUHBR MTV MTV9* EU PROP GOVERNOR BACKED OUT D K NONE O OTHER ININSP/MAINT 1 WP28162FC 135 L2790648A 01088 PROPELLER GOVERNOR SET SCREW INSIDE CASE HALVES, BACKED OUT CAUSING A CHAIN REACTION OF ENGINE DAMAGE. ALL MAJOR ENGINE COMPONENTS BROKEN (NON-REPAIRABLE), RESULTING IN AN ENGINE FAILURE AND A FORCED LANDING. 1M71 3O3 ONCEA67U 1E4 5 CP24NE 20021030002232002103000223SO 2002 10 30 2002FA0001225 220021012G74146320 MAGNETO PIPER PA34 PA34220T 7103420SO CONT O360 LTSIO360RB SO ENGINE INOPERATIVE D O OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 CE075034U173 3449200 322096 WHILE TRAINING, A/C SIMULATED ZERO THRUST SINGLE ENGINE APPROACH. WHEN POWER WAS REAPPLIED, ENGINE WAS FOUND DEAD AND WOULD NOT RESPOND TO ANY INPUTS FOUND IN EMERGENCY PROCEDURES CHECKLIST. A SINGLE ENGINE LANDING WAS MADE WITHOUT INCIDENT. FOUND BOTH MAGNETOS FAILED FROM SEVERE INTERNAL CORROSION AND BOTH COILS WERE SHORTED AND BURNED THROUGH IN THE SAME LOCATION. REMOVED AND INSP BOTH MAGS ON THE OTHER ENG AND FOUND THE LEFT MAG WITH SEVERE CORROSION AND PRESSURIZED AND FILTERS APPEARED IN GOOD CONDITION. THESE MAGS HAVE VERY SMALL VENT HOLES THAT WERE ALL PLUGGED. THE MAG THAT WAS IN GREAT SHAPE HAD A DISTORTED HSG SEAL THAT OBVIOUSLY ALLOWED THE NEEDED VENTILATION THAT THE OTHER MAGS DID NOT GET. 1L72 3O3 O A7SO E9CE 20021030002242002103000224CE 2002 10 30 2002FA0001226 120021002G8011C12ST1 STARTER CESSNA182 182 2072702CE CONT O470 O470R 17026SO ENGINE INOPERATIVE B DD2RK NONE O OTHER ININSP/MAINT 1 SW155711B 33711 STARTER DOES NOT ALLOW THE STARTER ADAPTER TO DISENGAGE WHEN THE ENGINE STARTS. THE RESULT IS EXCESSIVE HEAT AND WEAR WHICH RAPIDLY DESTROYS THE EFFECTIVENESS OF THE ADAPTER. WITHIN 30-60 HOURS THE ADAPTER MUST BE REPLACED. 1H71 3O3 ONT3A13 E273 20021030002292002103000229SO 2002 10 30 2002FA0001227 120021022G5712356171 RIB PIPER PA28 PA28161 7102803SO LYC O320 O320* 41508EA RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 NM02515MS148 2842157 DURING INSPECTION NOTED CRACK AROUND STIFFENER BEAD. CRACK APPEARED TO BE PRESENT AT MFG. CONTACT WITH MFG MADE AND A REPAIR SCHEME DONE IAW SB. 1L71 3O3 O 2A13 E274 20021030002302002103000230SO 2002 10 30 2002FA0001229 120021015G282098044072 LINE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA FUEL SYSTEM CORRODED D K NONE O OTHER ININSP/MAINT 1 NE03214114150 287990044 FUEL LINE CORRODED UNDER CUSHION CLAMP TO A POINT OF LEAKING INSIDE CABIN. OTHER AREAS OK. SUSPECT REPEATED EXPOSURE TO MOISTURE AROUND DOOR OPENING AND CARPET AND INSULATION CONTRIBUTED TO CONDITION. THE SEVERITY OF THE CORROSION COULD NOT BE SEEN UNTIL CLAMP WAS REMOVED. 1L71 3O3 O 2A13 E286 20021030002322002103000232 2002 10 30 2002FA0001230 420021010G2561AV8AS2100 LIFE VEST CABIN FAILED B KQ1RK NONE L NO TEST ININSP/MAINT 1 EA07 INDIVIDUAL FLOATATION DEVICE FAILED, MFG RECOMMENDED CELL PRESSURE TEST. 20021030002142002103000214CE 2002 10 30 2002FA0001231 120021025G5210 LINE CESSNA650 650 2076802CE GARRTTTFE731TFE7314R 01518WP DOOR SEAL CHAFED C O OTHER O OTHER TXTAXI/GRND HDL 1 GL23 3525 2462 7046 PILOT CLOSED MAIN CABIN DOOR. UPON LOCKING DOOR CREW HEARD HISSING NOISE FROM DOOR AND DOOR SEAL WOULD NOT INFLATE. INSPECTION BY MAINTENANCE DISCOVERED LINE HAD BEEN CHAFED THROUGH BY A FLIGHT CONTROL CABLE. LINE IS FOR MAIN ENTRANCE DOOR SEAL INFLATION. HOWEVER OPENING AND CLOSING OF DOOR STILL PUSHES THE LINE IN AND OUT ALLOWING IT TO CHAFED. THIS AREA IS INSPECTED EVERY PHASE 5 WHICH IS 1200 HOURS OR 36 MONTHS WHICH EVER OCCURS FIRST. SUGGEST THIS AREA BE INSPECTED DURING ONE THE PHASE ONE THROUGH FOURS. 2L72 4F4 F A9NM E6WE 20021030002152002103000215 2002 10 30 2002FA0001232 420021028G6113055032111 BULKHEAD CESSNA172 172S 2072439CE PROP SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM03949SP1756 172S8145 DURING PHASE 1 INSPECTION, MAINTENANCE FOUND AFT PROPELLER SPINNER BULKHEAD CRACKED AT ONE FLANGE BY THE PROPELLER BLADE CUT OUT ON ONE SIDE. REPLACED PROPELLER AFT SPINNER BULKHEAD & REINSTALLED PROPELLER. 1H71 3O NT3A12 20021030002162002103000216EU 2002 10 30 2002FA0001233 120021028G7910 VALVE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA OIL DRAIN ERODED D K NONE K FLUID LOSS ININSP/MAINT 1 EA23242MC 0671 L2624051A OIL DRAIN VALVE WAS REMOVED BECAUSE OF LEAK, UPON REMOVAL IT WAS DISCOVERED THAT SMALL NUT HOLDING SLUDGE VALVE ASSY TOGETHER WAS WORE TO MIN AMOUNT AND MISSING ONE HALF, IF NUT HAD COME OFF VALVE ASSY WOULD OPEN CAUSING ENGINE OIL TO COMPLETLY DRAIN. 1L71 3O3 O0 A76EU 1E10 20021030002172002103000217CE 2002 10 30 2002FA0001234 120021028G27204555400001V3800 RUDDER LEAR 45 45LEAR 5170805CE EMPENNAGE OUT OF RIG B K NONE O OTHER ININSP/MAINT 1 CE09882CA601 155 UPON RE-INSTALLATION OF RUDDER AFTER INSTALLATION OF S/B 45-55-6, FOUND THAT THE RUDDER TRAVEL WAS APPROXIMATELY 25 DEGREES IN LIEU OF 30 +/-1 DEGREES AS PER LEARJET AMM 27-20-00. WHEN TRAVEL WAS CORRECTED, DISCOVERED THAT THE BOTTOM SKIN OF RUDDER WAS CONTACTING THE SKIN PRIOR TO ACHIEVING FULL TRAVEL.. THE RUDDER WAS REPLACED WITH SAME P/N (S/N 0155). NO OTHER ACTION WAS REQUIRED AT THAT TIME. 2L72 4F RTT00008WI 20021030002182002103000218CE 2002 10 30 2002FA0001235 120021029G270124600352 GUIDE CESSNA172 172S 2072439CE CONTROL COLUMN DAMAGED B K NONE L NO TEST ININSP/MAINT 1 WP28528ER1055 172S8926 PILOT'S YOKE BINDS WHEN PULLED FULL AFT WITH LEFT HAND CREATING A SIDE LOAD ON COLUMN (IE. FLYING SINGLE HANDED). MAINTENANCE FOUND THE YOKE ROLLER NOT FULLY ENGAGING IN GUIDE. YOKE CLEARANCE IS WITHIN SPECIFIED .100 INCH CALLED OUT IN SB99-53-03, HOWEVER, THE ROLLER RIDES TOO LOW IN THE GUIDE AND WILL POP OUT OF THE GUIDE IF ANY SIDE PRESSURE IS APPLIED. PER SB99-53-03 A AN970-3 SPACER WASHER WAS INSTALLED ALLOWING THE ROLLER DEEPER ENGAGEMENT IN THE GUIDE WITHOUT THE ROLLER BOLT HEAD SCRAPING THE TOP OF THE GUIDE. 1H71 3O NT3A12 20021030002192002103000219SO 2002 10 30 2002FA0001236 120021029G2497455151 CONTACTOR PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA SNSNCH76E 76EM8S5 EA COCKPIT BURNED G BA EMER. DESCENT UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 NE015675V300 287790493 L2321536A 15426K A/C DIVERTED DUE TO THE SEVERE CHOKING SMOKE. PILOT DECLARED AN EMERGENCY AND SQUAWKED 7700 STATING THAT DUE TO THE SMOKE HE WOULD HAVE TO DITCH IN THE OCEAN. HE SAW THE BLOCK ISLAND AIRPORT AND LANDED LONG AND FAST RUNNING OFF THE END OF THE RUNWAY INTO A PERIMETER FENCE. PILOT STATED HE HAD A HARD TIME STARTING THE ENGINE AND CRANKED THE ENGINE CONTINUOUSLY UNTIL THE BATTERY WENT DEAD. HE GOT A JUMP-START FROM A VEHICLE USING THE CORRECT PLUGS AND 12 VOLT BATTERY. IT APPEARS THAT THE POWER RELAY CONTACTOR PIPER FAILED, PERHAPS SHORTED INTERNALLY. STARTER, ALTERNATOR, REGULATOR, START SWITCH, STARTER SOLENOID ALL CHECKED GOOD. THIS CONTACTOR WAS CHANGED TWO MONTHS PRIOR TO THIS FAILURE. 1L71 3O3 O 2A13 E286 5 NP4EA 20021101000012002110100001CE 2002 11 1 2002FA0001237 120021015G282305160194 SHAFT CESSNA172 172P 2072436CE LYC O320 O320* 41508EA FUEL SELECTOR MISMANUFACTURED B K NONE O OTHER ININSP/MAINT 1 WP2554661 17275028 TOP FUEL SELECTOR SHAFT AT SELECTOR HANDLE ATTACH AREA NOT MANUFACTURED CORRECTLY CAUSING INADVERTENT MISCLOCKING OF SELECTOR HANDLE. OLD SHAFT AND NEW SHAFT BOTH HAVE GLOB OF ALUMINUM WELDED ON TOP OF SHAFT TO PREVENT THIS, BUT THE WELD GLOB NEEDS TO EXTEND TO TOP OF SHAFT, AND THEN SHAPED TO EXCEPT HANDLE IN ONE DIRECTION ONLY. 1H71 3O3 ONT3A12 E274 20021101000022002110100002GL 2002 11 1 2002FA0001238 120020913G55402055450000WIP HINGE DIAMONDA20 DA20C1 2990001GL CONT O200 O200* 17020SO RUDDER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM07986CT1497 C0086 DURING 100 HOUR INSPECTION MECHANIC DISCOVER THAT THE LOWER LEFT CORNER OF THE LOWER RUDDER HINGE SUPPORT TOWER HAD A CRACK. EVIDENCED BY LINE OF BROWN RUST RESIDUE VISIBLE AGAINST THE BLACK PAINT, AND ADJACENT TO THE WELD. PART WAS REPLACED. 1L71 3O3 ONTTA4CH E252 20021101000032002110100003GL 2002 11 1 2002FA0001239 120020913G55402055450000WIP HINGE DIAMONDA20 DA20C1 2990001GL CONT O240 IO240A SO RUDDER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM07978CT1126 C0078 DURING 100 HOUR INSPECTION MECHANIC FOUND CRACK ON LOWER RIGHT CORNER OF LOWER RUDDER HINGE SUPPORT TOWER NEXT TO THE WELD LINE. PART WAS REPLACED WITH NEW PART. 1L71 3O3 ONTTA4CH E7SO 20021101000042002110100004 2002 11 1 2002FA0001240 420021014G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM03789EP82 172S8135 FOUND AFT PROPELLER SPINNER BULKHEAD, CRACKED AT ONE FLANGE AT PROPELLER BLADE CUT OUT. EDGE WITH NUTPLATE AND SCREW STILL ATTACHED TO PROPELLER SPINNER. AFT SPINNER BULKHEAD REPLACED AT 82.2 HOURS . 1H71 3O NT3A12 20021101000982002110100098CE 2002 11 1 2002FA0001241 120021031G323397343 SPRING RAYTHN BEECH 23 C24R 1151254CE LYC O360 IO360A1B6 41514EA LT UPLOCK DISTORTED D K NONE O OTHER ININSP/MAINT 1 SO2526TM A13084 MC638 L1977151A LT MLG UPLOCK ACTUATOR WOULD NOT RELEASE THE LANDING GEAR DURING 'FREE FALL' TEST. DISSAMBLY OF ACTUATOR REVEALED A NON APPROVED SPRING THAT WAS 0.125 INCHES SHORTER THAN THE ORIGINAL MANUFACTURER. THE SCARCITY OF REPLACEMENT PARTS FOR THIS UNIT MAY HAVE CAUSED A PREVIOUS REPAIRER TO USE UNAPPROVED PARTS. 1L71 3O3 O A1CE 1E10 20021101001012002110100101CE 2002 11 1 2002FA0001242 120021031G3211 SUPPORT BEECH 23 C24R 1151254CE LT & RT MLG LOOSE D K NONE O OTHER ININSP/MAINT 1 SO2526TM 3138 MC638 LT AND RT MLG FORWARD PIVOT SUPPORT ATTACHMENT 'JO-BOLTS' WERE FOUND LOOSE AND COULD BE ROTATED BY HAND. MORE THAN HALF OF THE 26 TOTAL FASTENERS HAD TO BE REPLACED. 1L71 3O A1CE 20021101001062002110100106CE 2002 11 1 2002FA0001243 120021031G561051116041 WINDSHIELD CESSNA421 421B 2076014CE COCKPIT MISINSTALLED G BA EMER. DESCENT UNSCHED LANDING WD INADEQUATE Q C INFLIGHT SEPARATION CRCRUISE 1 SO07333CJ4550 43 421B0313 ON 27 JUNE 2002 WHILE AT CRUISE ALT FL240, PILOTS FRONT WINDSHIELD DEPARTED THE AIRCRAFT ALONG WITH PART OF THE INSTRUMENT GLARE SHIELD AND PILOTS SUN VISOR. LABORATORY EXAMINATION OF THE WINDSHIELD DID NOT REVEAL THE POINT OF FAILURE BUT DID STATE NUMEROUS INSTALLATION DISCREPANCIES ISSUES AT THE TIME OF MANUFACTURE/INSTALLATION AT THE MANUFACTURER. RECORDS REVIEW DID NOT SHOW THAT THIS WINDSHIELD HAD EVER BEEN REPLACED SINCE MANFACTURE. MAINTENANCE RECORD DID SHOW A REPAIR WAS ACCOMPLISHED TO CORRECT A PRESSURIZATION LEAK AT THE 7 O' CLOCK POSITION ON THE WINDSHIELD. SIX PLASTIC INSERTS WERE INSTALLED. DISCREPANCIES PERTAINING TO REPAIRS TO THE WINDSHIELD HAVE BEEN REPORTED TO THE FAA PMI OF THE RESPONS1L72 3O A7CE 20021101001082002110100108CE 2002 11 1 2002FA0001244 120021031G551066312024 CLIP CESSNA560 560XL 2076702CE VERTICAL STAB CRACKED B K NONE O OTHER ININSP/MAINT 1 CE03 1195 5605081 CRACKS AT TWO FASTENER HOLES ATTACHING NOTED CLIP TO THE VERTICAL STABILIZER AFT SPAR. 2L72 4F RTA22CE 20021101001112002110100111SO 2002 11 1 2002FA0001245 120021025G56101159SCB51023 WINDSHIELD GULSTMG1159 GIV 3980115SO COCKPIT CRACKED C B EMER. DESCENT O OTHER CRCRUISE 1 GL031990C3831 1276 OUTER PANE ON CO-PILOT WINDSHIELD CRACKED 2L72 4F RTA12EA 20021101001122002110100112SO 2002 11 1 2002FA0001246 220021031G8550535810 BOLT CONT O520 IO520D 17032SO CRANKCASE MISMANUFACTURED B K NONE W INADEQUATE Q C ININSP/MAINT 1 WP07 566793 CRANKCASE UPPER TIE BOLT THREADS WERE NOT CUT PROPERLY. THEY HAD A FLAT PROFILE LIKE THE THREADS WERE NOT CUT DEEP ENOUGH. CONDITION DISCOVERED WHEN ATTEMPTING TO INSTALL NUTS ON THE BOLT. 3 O E5CE 20021106000622002110600062CE 2002 11 6 2002FA0001248 120021004G55110532001202 SPAR CESSNA172 172N 2072434CE HORIZONTAL STAB BROKEN B GSZRK NONE O OTHER ININSP/MAINT 1 SW19172GK8134 17271968 HORIZONTAL STABILIZER, SPAR BROKEN THRU LIGHTENING HOLE AS MARKED. SPAR AND REINFORCEMENT ARE BOTH BROKEN. UPPER CRACK EXTENDS INTO TOP OF REINFORCEMENT. BOTH CRACKS ARE INBOARD OF STABILIZER ATTACH HOLES. 1H71 3O NT3A12 20021106000632002110600063SO 2002 11 6 2002FA0001249 220021005G8530CCST712 CYLINDER CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO ENGINE CRACKED B CY4RA UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 AL038300Q U20603161 PILOT NOTED ROUGH RUNNING ENGINE AND MADE PRECAUTIONARY LANDING. LATER INSPECTION REVEALED NR 1 CYLINDER CRACKED AND A HOLE BLOWN THROUGH THE EXHAUST SIDE. 1H71 3O3 O A4CE E5CE 20021114000102002111400010SO 2002 11 14 2002FA0001250 220021009G7310646207 TUBE MOONEYM20 M20R 5870225SW CONT O550 IO550* SO FUEL INTAKE CRACKED B CQNRK NONE K FLUID LOSS ININSP/MAINT 1 SW1522166150 290225 INSPECTED AIRCRAFT ENGINE DURING ROUTINE OIL CHANGE AND NOTICED FUEL STAIN ON NR 6 INTAKE TUBE. REMOVED TUBE AND FOUND TO BE CRACKED AT FLANGE PART HAD BEEN REPLACED 2 MONTHS EARLIER FOR SAME REASON. COULD BE CAUSED BY ABNORMAL VIBRATIONS OR SHOCK COOLING OF TUBE. 1L71 3O3 ORT2A3 E3SO 20021107000662002110700066CE 2002 11 7 2002FA0001251 120020927G1430 BOLT CESSNA185 A185E 2072818CE TRUNNION LOOSE B ZKGRK NONE O OTHER ININSP/MAINT 1 NE054546F 1851039 FOUND BOTH MAIN GEAR FORWARD TRUNNION BOLTS LOOSE IN SPAR. THIS WAS FOUND ON AN 100 HOUR INSPECTION. 1H71 3O 3A24 20021107000672002110700067EA 2002 11 7 2002FA0001252 220021002G853075874 CYLINDER PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA ENGINE WORN B ZKGRO OTHER O OTHER NRNOT REPORTED 1 NE057991W 133 282048 REMOVED 2 CYLINDER ASSEMBLY FROM ENGINE BECAUSE OF LOW COMPRESSION. CYLINDER WERE REPAIRED AND INSTALLED AT OVERHAUL. 1L71 3O3 O 2A13 E286 20021114000112002111400011 2002 11 14 2002FA0001253 420020924G3414 INDICATOR CHRIS HUSKY A1 221020XNM LYC O360 O360* 41514EA COCKPIT CONTAMINATED B ZKGRK NONE O OTHER ININSP/MAINT 1 NE052950Q 1046 AFTER RAIN STORM, FOUND WATER IN THE AIRSPEED INDICATOR AND THE ALTERNATOR POSSIBLE CAUSE IS COMING THROUGH THE STATIC PORTS ON THE PITOT TUBE. 1H71 3O3 ONCA22NM E286 20021107000682002110700068CE 2002 11 7 2002FA0001254 120020822G7921627392 OIL COOLER CESSNA182 182P 2075816CE CONT O470 O470* 17026SO ENGINE LEAKING B XYERK NONE K FLUID LOSS ININSP/MAINT 1 NE0552509 18262652 FACTORY REBUILT ENGINE, INITIAL START UP OIL COOLER LEAKS, REMOVED COOLER AND BASE PLATE AND CHECKED SURFACES, SURFACES FOUND NOT TO BE FLAT. 1H71 3O3 ONTTA13 E273 20021107000692002110700069CE 2002 11 7 2002FA0001255 120021001G7921G02188528 OIL COOLER CESSNA206 TU206F 2073353CE CONT O520 TSIO520M 17040SO ENGINE LEAKING B XYERK NONE K FLUID LOSS ININSP/MAINT 1 NE05603ET U20602230 UPON INITIAL RUN UP OF FACTORY REBUILT ENGINE, COOLER LEAK NOTED. REMOVED COOLER AND CHECK BASE PLATE AND COOLER BASE FOR SURFACE VARIATIONS. BOTH PIECES DID NOT HAVE SURFACES THAT SHOWED TO BE TRUE AND FLAT. 1H71 3O3 O A4CE E8CE 20021114000122002111400012SO 2002 11 14 2002FA0001256 220021002G7322 FLOAT CESSNA182 182P 2075816CE CONT O470 O470S 17026SO CARBURETOR SEPARATED B XYERK NONE O OTHER ININSP/MAINT 1 NE056582M400 CL01030 18263764 CARBURETOR, LEAKING ON AIRCRAFT. SUSPECT FLOAT OR FLOAT NEEDLE STUCK. REMOVED CARBURETOR, REMOVED BOWL. HALF OF FLOAT PONTOON COMPLETELY SEPARATED FROM FLOAT ASSY. SOLDER JOINT HOLDING FLOAT TO ARM SEPARATED. 1H71 3O3 ONTTA13 E273 20021114000132002111400013GL 2002 11 14 2002FA0001257 120021022G2434 NUT AMTR LANCARLANCAIR 05616TSGL CONT O550 IO550G 17042SO ALTERNATOR SHAFTSEPARATED G K NONE O OTHER ININSP/MAINT 1 WP2141MF 141 679313 NUT SECURING ALTERNATOR DRIVE GEAR CAME OFF. GEAR SUBSEQUENTLY FELL OFF OF ALTERNATOR SHAFT DAMAGING INTERNAL ENGINE GEARS. 1L71 3O3 ORTEXPA1L71E3SO 20021114000142002111400014GL 2002 11 14 2002FA0001258 320021010G6114B24573 FORK CESSNA175 175 2072502CE LYC O360 O360* 41514EA HARTZLHCC2Y HCC2YK1 GL PROPELLER CRACKED B W59RK NONE O OTHER ININSP/MAINT 1 WP079391B 55191 CH18963 OVERHAUL WAS BEING ACCOMPLISHED DUE TO HIGH CALENDER TIME, LOW HOURS SINCE NEW. DURING MAGNETIC PARTICAL INSPECTION, MULTIPLE LARGE CRACKS WERE DISCOVERED IN PITCH CHANGE FORK. FORK APPEARS TO BE MANUFACTURING DEFECTS, POSSIBLY HEAT TREAT CRACKS. 1H71 3O3 ONT3A17 E286 5 CP920 20021114000152002111400015CE 2002 11 14 2002FA0001259 120021021G32221018200741 FORK BEECH 200 B200 1152922CE PWA PT6 PT6A11 52043NE MLG CRACKED B FCPRK NONE O OTHER ININSP/MAINT 1 NM094PT 6798 2113 BB879 FOUND HOLE FORK CRACKED, INSTALLED KIT. 1L72 4T3 T A24CE E4EA 20021107000702002110700070CE 2002 11 7 2002FA0001260 120021029G5753122010024 SKIN CESSNA206 T206H 2073303CE T/E FLAP CRACKED B HLFRK NONE O OTHER ININSP/MAINT 1 SW17XBASV 08271 RIGHT SIDE FLAP CRACKED SKIN AROUND RIVETS IN INBOARD LEADING EDGE BOTTOM SKIN. 1H71 3O RTA4CE 20021107000712002110700071CE 2002 11 7 2002FA0001261 120021029G5753122010024 SKIN CESSNA206 T206H 2073303CE LYC O540 TIO540* 41532EA T/E FLAP CRACKED B HLFRK NONE O OTHER ININSP/MAINT 1 SW177277R T20608073 FLAP HAS SEVERAL CRACKS ON SKIN AROUND RIVETS ON INBOARD LEADING EDGE. 1H71 3O3 ORTA4CE E14EA 20021107000722002110700072SO 2002 11 7 2002FA0001262 120021031G27204004009 TORQUE TUBE PIPER PA31 PA31325 7103105SO LYC O540 TIO540* 41532EA RUDDER CORRODED B VQ1RK NONE O OTHER ININSP/MAINT 1 SW17596L 2614 317712036 WHILE COMPLYING WITH SB, WE FOUND EXCESSIVE CORROSION ON RUDDER TORQUE TUBE, RUDDER BUTT RIB AND RUDDER MAIN RIB. 1L72 3O3 O A20SO E14EA 20021114000162002111400016CE 2002 11 14 2002FA0001263 120021021G554407436062 FITTING CESSNA182 182Q 2072732CE RUDDER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW15977844085 18267191 FOUND RUDDER TO BE OUT OF RIG FOR 2ND TIME IN 17 HRS INSPECTED AND FOUND LOWER STRUT FITTING TO BE CRACKED WERE STRUT FITTING TO BE CRACKED WERE STRUT ATTACHES TO FITTING. 1H71 3O NT3A13 20021107000732002110700073CE 2002 11 7 2002FA0001264 120021021G5521043200121 SPAR CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA ELEVATOR CRACKED D K NONE O OTHER ININSP/MAINT 1 SW159426814155 15285632 L2343615 FOUND CRACK EXTENDING ABOUT.5 INCH FROM OUTBOARD HINGE POINT TO SPAR ATTACHMENT. 1H71 3O3 ONT3A19 E223 20021114000172002111400017SO 2002 11 14 2002FA0001265 120021017G2823 SHUTOFF VALVE PIPER J3 J3C65 7100510SO FUEL SYSTEM FAILED G K NONE O OTHER ININSP/MAINT 1 NE0317171 19970 DURING AN INVESTIGATION OF AN AIRCRAFT INCIDENT IN WHICH THE AIRCRAFT CRASHED INTO A POND DUE TO FUEL STARVATION. IT WAS DETERMINED THAT AN ALTERATION TO FUEL SHUT OFF VALVE HAD BEEN PERFORMED AND WAS NOT APPROVED. AN EXTENSION TO THE VALVE WAS INSTALLED AND THE EXTENSION SWIVELLED ON THE FUEL SHUT OFF VALVE HANDLE CAUSING A FALSE INDICATION IN THE COCKPIT SHOWING THE VALVE TO BE OPEN BUT IN REALITY THE VALVE WAS CLOSED. THE SHUT OFF VALVE WAS PROBABLY PARTIALLY OPEN BUT THE EXTENSION WAS 90 DEGREES TO THE HANDLE AND WAS BUMPED DURING FLIGHT WHILE PICTURES WERE BEING TAKEN CAUSING THE FUEL SHUT OFF VALVE TO CLOSE AND ENGINE TO QUIT. 1H71 3O A691 20021114000182002111400018EA 2002 11 14 2002FA0001267 220021015G7414 P-LEAD CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA LT MAGNETO FAILED D K NONE O OTHER ININSP/MAINT 1 NE03113PF1636 17280401 REPORTS OF INTERMITTENT LT MAG FAILURE. TROUBLESHOT AND REMOVED ENTIRE P-LEAD ASSEMBLY. FOUND SHIELDING SOLDER / CRIMP AT SWITCH END CUT INTO CENTER CORE VERY SLIGHTLY. REPLACED P-LEAD ASSEMBLY. NO ADDITIONAL REPORTS OF MAG FAILURE. 1H71 3O3 ONT3A12 1E10 20021114000192002111400019SO 2002 11 14 2002FA0001268 120021004G324640142 BOLT PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A11 52043NE MLG WHEEL CORRODED B FTURK NONE O OTHER ININSP/MAINT 1 NE055335R299 4697100 DURING A TIRE REPLACEMENT ON THE RT MAIN WHEEL ASSEMBLY, ALL WHEEL THRU BOLTS FOUND WORN AND CORRODED. THERE WAS NO TYPE OF ANTI-SEIZE LUBRICANT ON THE BOLTS. PIPER MAINTENANCE MANUAL DOES NOT REQUIRE ANY ANTI-SEIZE LUBRICAN ON THE THRU BOLTS. 1L71 3O3 TRTA25SO E4EA 20021114000202002111400020SO 2002 11 14 2002FA0001269 120021021G7160570473 SCREEN PIPER PA42 PA42 7104202SO PWA PT6 PT6A41 52043EA AIRSCOOP CRACKED B FTURK NONE O OTHER ININSP/MAINT 1 NE05444SC 428001034 DURING A SCHEDULED EVENT INSPECTION, BOTH ENGINE AIR INLET SCOOP SCREENS WERE FOUND CRACKED IN BOTH FORWARD CORNERS FOR EACH ENGINE. REPAIR WAS NOT FEASABLE DUE TO THE LOCATION DAMAGE. BOTH INLET SCREEN HAD TO BE REPLACED WITH NEW PARTS. 1L72 4T4 T A23SO E4EA 20021114000212002111400021SO 2002 11 14 2002FA0001270 220021023G8530539487 CLAMP BEECH 36 B36TC 1151609CE CONT O520 TSIO520* 17040SO CROSSOVER TUBE DISCONNECTED B BONRK NONE O OTHER ININSP/MAINT 1 GL197SA EA427 249089R PILOT REPORTED HEARING A POP AT 11,000 FT AND IMMEDIATELY LOST MANIFOLD PRESSURE. PILOT MAKE PRECAUTIONARY LANDING WITHOUT INCIDENT. INSPECTION OF ENGINE REVEALED FORWARD CYLINDER INDUCTION MANIFOLD CROSSOVER TUBE HAD BECOME DISCONNECTED FROM NR 5 CYLINDER INTERCONNECT HOSE. IT APPEARS SECURITY CLAMP MAY BE TOO NARROW TO ADEQUATELY SECURE CROSSOVER TUBE TO NR 5 CYLINDER MANIFOLD ASSEMBLY AND INTERCONNECT HOSE. ORDERED AND INSTALLED CLAMP IAW IPC. REPLACEMENT CLAMP IS WIDER THAN CLAMP REMOVED AND WILL PROVIDE IMPROVED INTEGRITY. 1L71 3O3 O 3A15 E8CE 20021114000222002111400022CE 2002 11 14 2002FA0001271 120021031G304051116041 WINDSHIELD CESSNA421 421B 2076014CE CONT O520 GTSIO520C 17032SO COCKPIT FAILED G A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 SO07333CJ 421B0313 WHILE AT CRUISE ALT FL240, PILOTS FRONT WINDSHIELD DEPARTED THE AIRCRAFT ALONG WITH PART OF THE INSTRUMENT GLARE SHIELD AND PILOTS SUN VISOR. LAB EXAM OF WINDSHIELD DID NOT REVEAL POINT OF FAILURE BUT DID STATE NUMEROUS INSTALLATION DISCREPANCIES. MAINTENANCE RECORD DID SHOW A REPAIR WAS ACCOMPLISHED TO CORRECT A PRESSURIZATION LEAK AT THE 7 O`CLOCK POSITION ON THE WINDSHIELD. SIX PLASTIC INSERTS WERE INSTALLED. 1L72 3O3 O A7CE E7CE 20021114000232002111400023EA 2002 11 14 2002FA0001272 220021028G8530 LIFTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA NR 2 CYLINDER BROKEN D K NONE O OTHER ININSP/MAINT 1 GL25405SP1636 172S8298 WHILE DRAINING OIL, FOUND A PIECE OF STEEL WITH A ROUNDED EDGE. ALSO FOUND METAL IN THE OIL FILTER. REMOVED NR 2 CYLINDER AND FOUND THE INTAKE VALVE LIFTER HAD PIECES FRACTURED OFF OF THE EDGE. THE CAM WAS SPALLED AND THE NR1 CYLINDER INTAKE VALVE LIFTER WAS ALSO SPALLED. THE SKIRT ON THE NR 2 PISTON HAD SCRATCH MARKS FROM SHIPS OF THE LIFTER. I COULD FIND NO OBVIOUS CAUSE TO THE DAMAGED. SUSPECT MANUFACTURING FLAW IN THE LIFTER BODY. 1H71 3O3 ONT3A12 1E10 20021114000242002111400024SO 2002 11 14 2002FA0001274 120020831G282366945000 SELECTOR VALVE PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA FUEL SYSTEM FAILED G K NONE O OTHER ININSP/MAINT 1 SW053961K 2823841 L1987927A FUEL PLACARD, UPSIDE DOWN, FUEL SELECTOR LEVER WOULD TURN ONLY 180 DEGREES, AREA OF TRAVEL, COULD NOT SELECT OTHER 180 DEGREES. 1L71 3O3 O 2A13 E274 20021114000252002111400025CE 2002 11 14 2002FA0001275 120021018G561010138402516 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT CRACKED D K NONE O OTHER ININSP/MAINT 1 GL03366EA BB841 WINDSHIELD SHATTERED IN FLIGHT, FROM UNKNOWN CAUSES. 1L72 4T4 T A24CE E4EA 20021114000422002111400042CE 2002 11 14 2002FA0001276 120021004G3340 CURRENT LIMITER RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE731* 01518WP PULSELIGHT FAILED B K NONE L NO TEST ININSP/MAINT 1 GL192426 258272 ON A/C WITH BUS-TIE OPEN, LEFT MAIN BUS (PS1) AND RIGHT MAIN BUS (PS2) SHOULD BE SEPARATED. COULD NOT SEPARATE PS1 AND PS2. THEY WERE INADVERTENTLY LINKED TOGETHER THROUGH A PULSELIGHT INSTALLATION. HAD A PULSELIGHT SYSTEM INSTALLED, A COMPONENT OF THE PULSELIGHT SYSTEM WAS INCORRECTLY INSTALLED. IT IS THE CURRENT LIMITER. 2L72 4F4 FRTA3EU E6WE 20021114000432002111400043CE 2002 11 14 2002FA0001277 120021004G3340 CURRENT LIMITER RAYTHNDH125 HAWKER800 7450004CE GARRTTTFE731TFE731* 01518WP PULSELIGHT FAILED B K NONE O OTHER ININSP/MAINT 1 GL192428 258274 ON A/C WITH BUS-TIE OPEN, LEFT MAIN BUS (PS1) AND RIGHT MAIN BUS (PS2) SHOULD BE SEPARATED. COULD NOT SEPARATE PS1 AND PS2. THEY WERE INADVERTENTLY LINKED TOGETHER THROUGH A PLUSELIGHT INSTALLATION. HAD A PULSELIGHT SYSTEM INSTALLED, A COMPONENT OF THE PULSELIGHT SYSTEM WAS INCORRECTLY INSTALLED. IT IS THE CURRENT LIMITER. 2L72 4F4 FRTA3EU E6WE 20021114000382002111400038EU 2002 11 14 2002FA0001278 120021025G2820200001040 LINE REIMS 177 F177RG 7530211EU LYC O360 IO360A1B6 41514EA FUEL SYSTEM CORRODED B RH6RK NONE O OTHER ININSP/MAINT 1 NE01274LH1650 0056 FUEL VENT LINES ABOVE HEADLINER CORRODED FROM CLAMPS AND SEAT TUBING TOUCHING LINES CAUSING RAW FUEL AND FUMES TO ENTER UPPER CABIN AREA. 1H71 3O3 O A26EU 1E10 20021114000392002111400039CE 2002 11 14 2002FA0001279 120021028G2434 NUT CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO ALTERNATOR LOOSE B RH6RK NONE O OTHER ININSP/MAINT 1 NE014690N 18267289 467413 ALTERNATOR CHARGE, FAILURE DUE TO LOOSE PULLEY FAN AND SHROUD ASSEMBLY. UNDER ANY LOAD SLIPPAGE OCCRUED . HEATED NUT AND LOOSENED ASSEMBLY. KEYWAY INSTALLATION WOULD SOLVE POSSIBLE PROBLEM AND PULLEY SLIPAGE. AIRCRAFT WAS REPORTING INTO IMC PREFLIGHT RUN UP, CHARGING FAILED. 1H71 3O3 ONT3A13 E273 20021114000402002111400040CE 2002 11 14 2002FA0001280 120021029G5753 SKIN CESSNA206 T206H 2073303CE TE FLAP CRACKED B HLFRK NONE O OTHER ININSP/MAINT 1 SW17XBRRV114 08247 RT SIDE FLAP CRACKED SKIN AROUND RIVETS ON LEADING EDGE BOTTOM SECTION. 1H71 3O RTA4CE 20021114000412002111400041GL 2002 11 14 2002FA0001281 120021017G270011898002 CARTRIDGE CIRRUSSR SR22 2130001GL CONT O550 IO550* SO YAW TRIM DEFECTIVE B V9MRK NONE O OTHER ININSP/MAINT 1 SW0518DN 0096 DURING COMPLIANCE WITH SB, REPLACEMENT OF TRIM CARTRIDGE NUT THE YAW TRIM CARTRIDGE FAILED TORQUE CHECK. THE ROD FOR THE TRIM CARTRIDGE APPEARS TO BE UNDERSIZE THEREFORE THE NUT WILL ONLY HOLD AT 1 INCH POUND OF TORQUE RATHER THAN 3 INCH POUNDS AS REQUIRED IN SB. 1L71 3O3 ONTA00009CHE3SO 20021114000442002111400044GL 2002 11 14 2002FA0001283 220021106G72506895801 TURBINE WHEEL ALLSN 250C 250C28 03013GL TURBINE SECTION MISMANUFACTURED B K NONE W INADEQUATE Q C ININSP/MAINT 1 SW05A9UR CAT70139 AREA OF WHEEL EXCEEDS MAXIMUM LIMITS. AREA MIN. 4.60, AREA MAX 4.78. AREA OF THIS WHEEL IS 4.80. 3 U E1GL 20021114000552002111400055EU 2002 11 14 2002FA0001284 120021105G5500 SPAR SPHRTHCIRRUSCIRRUSSTD 38019VEEU STABILATOR CRACKED B L1MRK NONE O OTHER ININSP/MAINT 1 WP1144FV 1683 V1 MAIN SPAR OF TAILPLANE (STABILATOR) WAS FOUND TO CONTAIN MULTIPLE CRACKS IN WOOD STRUCTURE AFT MOUNTING HOLES. PLYWOOD FACE PLATES WERE DELAMINATED AND HIDING CRACKS. ALL ATTACHMENT HARDWARE WERE RUSTED. TAILPLANE WAS LOOSE WITH EXCESSIVE PLAY AFTER HARD LANDING, PILOT INDICATED IT WAS ALWAYS LOOSE. 1K00 G23EU 20021114000722002111400072SW 2002 11 14 2002FA0001285 120021101G322045291401 TORQUE TUBE GULSTM112 112 0144701SW LYC O360 IO360A1A 41514EA NLG CRACKED B GF4RK NONE O OTHER ININSP/MAINT 1 WP151169J2023 169 DURING INSPECTION OF THIS LANDING GEAR TORQUE TUBE THE PART WAS CLEANED OFF WITH A RAG AND VISUALLY INSPECTED AS USUAL. PAINT WAS SMOOTH AND UNBROKEN AROUND ENTIRE PART OTHER THAN NORMAL SMALL CHIPS IN PAINT FROM NORMAL USAGE. THEN SERVICED WITH A HAND OPERATED GREASE GUN ON THE FORWARD ZERK FITTING THE PAINT ON AFT SIDE OF PART SPLIT ALONG APPROXIMATELY FOUR INCH LENGTH AND GREASE EXITED FROM CRACK. THIS DEFECT WOULD NOT HAVE BEEN DETECTED DURING THE ANNUAL INSPECTION UNLESS THE SERVICE WORK HAD BEEN DONE CONCURRENTLY WITH THE INSPECTION. 1L71 3O3 O A12SO 1E10 20021114000732002111400073NE 2002 11 14 2002FA0001286 220021029G72402A3537 SEAL IAE V2500 V2500A1 NE ENGINE CRACKED B KB1RK NONE O OTHER ININSP/MAINT 1 WP01 SEAL REJECTED FOR CRACK AT 1 PLACE ON BACK WALL OF THE PILOT GROOVE SEAL AS MARKED ON THE PART. 4 F E311NE 20021114000742002111400074NE 2002 11 14 2002FA0001287 220021024G72402A3537 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1RK NONE O OTHER ININSP/MAINT 1 NE03 SEAL REJECTED AT FPI FOR VOID WITH LINEAR INDICATION ON SEAL LAND EXCEEDING 3X1 LIMIT. 4 F E311NE 20021114000752002111400075CE 2002 11 14 2002FA0001288 120021021G2497128364231601 WIRE HARNESS BEECH MU300 400A 1155402CE PWA JT15 JT15* 52060NE MAIN BATTERY BURNED D K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 SO13134CM910 RK144 WHILE MOTORING ENGINE FOR OTHER MAINTENANCE, FOUND BURNING ODOR AND SMOKE IN AREA OF MAIN BATTERY. ON VISUAL INSPECTION, FOUND POSITIVE TERMINAL AND WIRE LEADS OF CONNECTOR BURNED. ALSO FOUND DAMAGE TO BATTERY TERMINAL. 2H72 4F4 TRTA16SW E1NE 20021114000762002111400076CE 2002 11 14 2002FA0001289 120021031G321310581002367 FRAME BEECH 76 76 1153005CE LYC O360 O360* 41514EA MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 NM02516MS6561 ME166 THE LEFT FRAME WAS NOTED TO HAVE CORROSION PREVENTATIVE OOZING IN THE EXACT AREA OF THE INSPECTION, IN A LINE THAT APPEARED AS A CRACK. THE AREA WAS CLEANED AND A CRACK WAS APPARENT BY USING A GOOD LIGHT AND 10 POWER GLASS. A DYE CHECK OF THE AREA FAILED TO REVEALED THE CRACK. SUSPECT THE CORROSION PREVENTATIVE FILLS THE CRACK AND IS NOT CLEANED OUT BY THE PENETRANT CLEANER SO THE PENETRANT IS NOT ALLOWED TO WORK AS IT IS MEANT TO. 1L72 3O3 O A29CE E286 20021114000062002111400006GL 2002 11 14 2002FA0001290 120021101G321010209001 GROMMET CIRRUSSR SR22 2130001GL MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SO15101CD224 0101 DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. 1L71 3O NTA00009CH 20021114000072002111400007GL 2002 11 14 2002FA0001291 120021108G321010209001 GROMMET CIRRUSSR SR22 2130001GL MLG DEFORMED D K NONE O OTHER ININSP/MAINT 1 SO15806CD192 0106 DURING A SCHEDULED INSPECTION FOUND BOTH MLG LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMMET WILL RESULT IN DAMAGE TO THE LAMINATED MAIN GEAR LEG THAT WILL RENDER IT UNSERVICEABLE. 1L71 3O NTA00009CH 20021114000082002111400008EU 2002 11 14 2002FA0001293 220021113G8520 CRANKCASE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912S3 EU ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA2187HA 659 10086 4922711 AIRCRAFT WAS SQUAWKED FOR OIL LEAKING FROM COWL. UPON INSPECTION THE LEAK WAS DETERMINED TO BE COMMING FROM A CRACK ON TOP OF ENGINE UNDER COOLING SHROUD. (COOLING SHROUD HAS TO BE REMOVED TO INSPECT THIS AREA) THE CRACK WAS APPROXIMATLY 3 INCHES AND IS ORINTATED FORE AND AFT BETWEEN CYLINDERS 1 AND 3. 1L71 3O3 ONTTA4CH E00051EN 20021114000092002111400009EA 2002 11 14 2002FA0001294 220021113G7310 LINE AVIAT A1 A1B 2210406GL LYC O360 O360* 41514EA ENGINE FUEL SYS SEPARATED B K NONE O OTHER ININSP/MAINT 1 NE0584HY 259 2184 L3851036A CENTER SUPPLY PRIMER LINE SEPARATED FROM TEE FITTING AT BACK OF ENGINE. DISCOVERED DURING ATTEMPT AT COLD ENGINE STARTING. NOTICED DIFFICULTY IN STARTING AND FUEL SMELL. OPENED COWLING TO DISCOVER PRIMER LINE SEPARATED. 1H71 3O3 ONCA22NM E286 20021115000012002111500001 2002 11 15 2002FA0001297 420021114G3422 WIRE HARNESS CESSNA500 550 2076604CE DIRECTIONAL GYROCHAFED B K NONE O OTHER ININSP/MAINT 1 GL231258B20 5501037 OPERATOR NOTED NR 2 DIRECTIONAL GYRO CIRCUIT BREAKER POPPING. MAINTENANCE DETERMINED A WIRE BUNDLE ROUTED AROUND THE DATA TRANSFER UNIT (DTU) WAS CHAFING AGAINST THE OUTBOARD CONNECTOR PLUG ON THE DTU. ONE WIRE IN THE BUNDLE WAS FOUND SHORTED AGAINST THE CONNECTOR PLUG. THE WIRE WAS REPAIRED BY INSTALLING AN ENVIRONMENTAL SPLICE IN THE DAMAGED AREA. SPIRAL WRAP WAS INSTALLED AROUND THE WIRE BUNDLE AND THE WIRE BUNDLE WAS RELOCATED AS MUCH AS POSSIBLE TO PREVENT A RECURRENCE OF THE PROBLEM. FUNCTION TEST REVEALED NO FURTHER DEFECTS. 1L72 4F A22CE 20021120000222002112000022CE 2002 11 20 2002FA0001298 120021106G2750AN460A BOLT CESSNA172 172P 2072436CE LYC O320 O320* 41508EA RT FLAP PULLEY LACK OF LUBE B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO06529648911 17274645 LACK OF LUBRICATION CAUSED BOLT TO SEIZE IN FLAP DRIVE PULLEY RIGHT BUSHING. OVER PERIOD OF TIME, WITH EVERY CYCLE OF FLAPS THIS BOLT ROTATING ELONGATED TOP AND LOWER BRACKETS . ON PREFLIGHT PILOT NOTED SOMETHING STREAKING FROM LOWER SKIN. REPLACEMENT OF BRACKETS, BOLT, BUSHING WERE NECESSARY. 1H71 3O3 ONT3A12 E274 20021120000232002112000023SO 2002 11 20 2002FA0001299 220021014G8520652832 CRANKSHAFT CONT O520 GTSIO520* 17032SO ENGINE CRACKED B VA1RK NONE O OTHER ININSP/MAINT 1 SW19 2916 241235R CRANKSHAFT CRACKED BETWEEN FRONT TWO COUNTERWEIGHTS AND A PIECE MISSING FROM THAT AREA. 3 O E7CE 20021120000242002112000024SO 2002 11 20 2002FA0001300 120021106G3252 BOLT PIPER PA24 PA24250 7102404SO LYC O540 O540* 41532EA SHIMMY DAMPENER MISINSTALLED B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO056292H 243189 BOLT WAS INSTALLED BACKWARDS ON SHIMMY DAMPNER. GEAR WAS LOWERED IN FLIGHT AND HUNG UP ON COWL LT V CHANNEL. SUBSEQUENT DAMAGE WAS CAUSE TO CHANNEL AND REAR SUPPORT. TIME SINCE LAST WORK TO SHIMMY DAMPENER MOUNT CLAMP UNKNOWN. 1L71 3O3 O 1A15 E295 20021120000252002112000025CE 2002 11 20 2002FA0001301 120021106G3246D30321 HUB CESSNA421 421C 2076016CE CONT O520 GTSIO520* 17032SO NOSEWHEEL CRACKED D K NONE O OTHER ININSP/MAINT 1 SO065491G5422 421C0238 DURING NOSE TIRE CHANGE, DEGREASING OF WHEEL AND HUB, THREE CRACKS WERE FOUND ON CENTER HUB WHERE END PLATES BOLT TO HUB. WHEEL ASSEMBLY WAS PREVIOUSLY PAINTED MAKING VISUAL INSPECTION IMPOSSIBLE. AT TIME OF CHANGE, PAINT FLAKING ALLOWED CRACKS TO SHOW UP. LAST NOSE TIRE CHANGE WAS 2/97 AT TT 4952.4. 1L72 3O3 O A7CE E7CE 20021120000272002112000027CE 2002 11 20 2002FA0001303 120021116G3010671440238 TUBE CESSNA750 750 2076810CE DEICE SYSTEM FAILED D H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION CLCLIMB 1 NM09551AM670 220 7500155 PILOTS COMPLAINT OF RT ANTI-ICE HOT MESSAGE WHEN SYSTEM TURNED ON. VERIFIED SENSOR AND LOGIC CARD OPERATION OK. REMOVED RT LEADING EDGE AND FOUND MAIN TUBE HAD BURST WITH A 2.5 X .375 INCH HOLE, BLOWING AWAY INSULATION AROUND ASSEMBLY. THIS WAS JUST INBOARD OF THE SLAT ANTI-ICE VALVE. TUBE ASSEMBLY TO BE RETURNED TO MFG FOR EVALUATION. NEW ASSEMBLY INSTALLED. 2L72 4J RTT00007WI 20021120000282002112000028CE 2002 11 20 2002FA0001304 120021107G2510MM201057 ACTUATOR CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA SEAT RECLINE INOPERATIVE C K NONE O OTHER ININSP/MAINT 1 CE03142ME250 172S8425 PILOT SEAT RECLINE MECHANISM FAILED. SEAT RECLINED FULLY AFT, WAS REPEATABLE. 1H71 3O3 ONT3A12 1E10 20021120000292002112000029SO 2002 11 20 2002FA0001307 120020914G3213 BOLT MAULE M5 M5235C 5460135SO LYC O540 O540* 41532EA MLG STRUT FAILED D K NONE O OTHER ININSP/MAINT 1 NM085636D 7305C BOLT (NR 32) IS ONE OF FOUR. THREE APPARENTLY WERE PROBABLY SHEARED FROM PAST ACCIDENT. SAFETY WIRE HELD 211 BOLTS FROM ROTATING. REMAINING BOLT TORE OUT END OF UPPER TUBE, CAUSING COMPLETE DISASSEMBLY OF UPPER PART OF STRUT. UPPER ATTACH BOLT (NR 17) AND LOWER ATTACH BOLT (NR 16) WERE BENT SLIGHTLY, ALSO. 1H71 3O3 O 3A23 E295 20021120000202002112000020EU 2002 11 20 2002FA0001308 120021119G5311A102006L FRAME LET L13 L13BLANIK 1360306EU FUSELAGE AFT DETACHED B K NONE O OTHER ININSP/MAINT 1 NM03421BA 028902 DURING ACCEPTANCE INSPECTION UPON DELIVERY FROM THE CZECH REPUBLIC, EXTERNAL DAMAGE WAS NOTED WHERE THE AFT FUSELAGE RESTS IN THE TRAILER TAIL DOLLY. INTERNAL INSPECTION OF THE FUSELAGE REVEALED DEFORMED AND TORN FUSELAGE FRAME MEMBERS NR 11, 12, AND 13. SUBSEQUENT INSPECTION OF THREE OTHER RECENTLY ACQUIRED AIRCRAFT REVEALED SIMILAR DAMAGE. THE SUBMITTER SUGGESTS TWO POSSIBLE CAUSES FOR THIS DAMAGE. FIRST, THAT THIS DAMAGE OCCURRED DUE TO LACK OF LOAD DISTRIBUTION ON THE AFT FUSELAGE WHILE BEING TRANSPORTED IN THE TRAILER. SECOND, THAT THE DAMAGE OCCURRED DURING THE MANUFACTURING PROCESS. PART NUMBERS OF AFFECTED FRAMES: FRAME NR 11- A102006L (LT), A102006P (RT) FRAME NR 12- A102007L, A102007P FRAME N1K00 G24EU 20021120000212002112000021EU 2002 11 20 2002FA0001309 120021119G5311A102006P FRAME LET L13 L13BLANIK 1360306EU FUSELAGE AFT DETACHED B K NONE O OTHER ININSP/MAINT 1 NM03422BA80 028903 DURING ACCEPTANCE INSPECTION UPON DELIVERY FROM THE CZECHOSLOVAKIA SOCIALIST REPUBLIC, EXTERNAL DAMAGE WAS NOTED WHERE THE AFT FUSELAGE RESTS IN THE TRAILER TAIL DOLLY. INTERNAL INSPECTION OF THE FUSELAGE REVEALED DEFORMED AND TORN FUSELAGE FRAME MEMBERS NR 11, 12, AND 13. SUBSEQUENT INSPECTION OF THREE OTHER RECENTLY ACQUIRED AIRCRAFT REVEALED SIMILAR DAMAGE. THE SUBMITTER SUGGESTS TWO POSSIBLE CAUSES FOR THIS DAMAGE. FIRST, THAT THIS DAMAGE OCCURRED DUE TO LACK OF LOAD DISTRIBUTION ON THE AFT FUSELAGE WHILE BEING TRANSPORTED IN THE TRAILER. SECOND, THAT THE DAMAGE OCCURRED DURING THE MANUFACTURING PROCESS. PART NUMBERS OF AFFECTED FRAMES: FRAME NR 11- A102006L (LT), A102006P (RT) FRAME NR 12- A102007L1K00 G24EU 20021120000502002112000050CE 2002 11 20 2002FA0001313 120021111G271050452133 TUBE CESSNA414 414 2075908CE CONT O520 TSIO520* 17040SO AILERON FAILED B NT2RK NONE O OTHER ININSP/MAINT 1 CE07105GB 4140644 AT ANNUAL INSPECTION, A CLICKING NOISE WAS NOTED WHEN LANDING GEAR WAS RETRACTED. UPON INVESTIGATION, IT WAS DETERMINED THAT THE END FITTINGS RIVETED IN THE TUBE ASSEMBLY WERE WORKING. CATASTROPHIC FAILURE WAS PROBABLY NOT IMMINENT, HOWEVER IF LEFT UNATTENDED THE RIVETS WOULD HAVE EVENTUALLY SHEARED ALLOWING THE END FITTING TO SEPARATE FROM TUBE. 1L72 3O3 ORTA7CE E8CE 20021125000152002112500015EU 2002 11 25 2002FA0001314 120021107G243051509006C GCU BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE731* 01518WP NR 1 GENERATOR INOPERATIVE C A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 EA03332WE556 257186 PILOTS REPORTED LOSS OF NR 1 GENERATOR INFLIGHT, PROCEEDED TO DESTINATION. WITHOUT INCIDENT, TROUBLESHOT AND FOUND NR1. GCU GENERATOR CONTROL UNIT INOPERATIVE ALSO FUSE F1 ON PANEL ZX OPEN REPLACED GCU AND FUSE OPS CHECKED OK. 2L72 4F4 F A3EU E6WE 20021125000162002112500016SO 2002 11 25 2002FA0001315 120021101G27204004007 TUBE PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A60A 52043NE RUDDER CORRODED G K NONE O OTHER ININSP/MAINT 1 GL03804C 5113 31T1166006 RUDDER TUBE ASSY HAS SEVERE CORROSION AND EXFOLIATION, WHICH HAS CAUSED STRUCTURAL DETERIORATION OF THE COMPONENT. 1L72 3T4 TRTA8EA E4EA 20021125000172002112500017 2002 11 25 2002FA0001316 420021101G2562AK450 ELT BEECH 35 V35A 1151544CE CONT O520 TSIO520D 17040SO CABIN WILL NOT TEST B K NONE L NO TEST ININSP/MAINT 1 NM03222S D9008 180081 ELT NOT TRANSMITTING ON AM RADIO OR 121.5 VHF FREQUENCIES. DOES NOT PASS CFR PART 91.207D TEST. ELT WAS INSTALLED DEC, 2001 (NEW) AND TESTED PROPERLY AT THAT TIME UNIT HAS BEEN SENT FOR REPAIR. 1L71 3O3 O 3A15 E8CE 20021125000182002112500018EA 2002 11 25 2002FA0001317 220021017G852013S19646 GEAR LYC O320 O320D3G 41508EA CRANKSHAFT MISMARKED D K NONE W INADEQUATE Q C ININSP/MAINT 1 EA13 THE CRANK GEAR WAS INSTALLED NEW IN A FRESHLY OVERHAULD ENGINE. THE ENGINE WAS HARD STARTING AND WOULD NOT GIVE A SATISFACTORY STATIC POWER CHECK. TROUBLESHOOTING REVEALED THE OVERHAULER ASSEMBLED THE ENGINE WITH THE TIMING MARKS ALIGNED. THE TIMING MARK WAS NOT INDEXED TO THE PROPER TOOTH ON THE GEAR FROM THE FACTORY. 3 O E274 20021125000192002112500019CE 2002 11 25 2002FA0001318 120021016G7810 FLANGE CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO EXHAUST WYE BROKEN D K NONE O OTHER ININSP/MAINT 1 WP0928RG 1241 340A0347 THE ATTACHING FLANGES BETWEEN THE EXHAUST WYE AND WASTE GATE ELBOW CRACKED ON BOTH PARTS. 1L72 3O3 O 3A25 E8CE 20021125000202002112500020CE 2002 11 25 2002FA0001319 120021016G7810 FLANGE CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO EXAHAUST WYE CRACKED D K NONE O OTHER ININSP/MAINT 1 WP0928RG 1241 340A0347 THE ATTACHING FLANGES BETWEEN THE EXHAUST WYE AND WASTE GATE ELBOW CRACKED ON BOTH PARTS. 1L72 3O3 O 3A25 E8CE 20021125000212002112500021CE 2002 11 25 2002FA0001320 120021016G7920S112980310 HOSE CESSNA172 172RG 2072438CE LYC O360 O360* 41514EA OIL COOLER LOOSE D K NONE K FLUID LOSS ININSP/MAINT 1 WP096303V200 172RG0615 THE OIL RETURN HOSE FROM THE OIL COOLER WORKED ITSELF LOOSE AT THE OIL COOLER FITTING. 1H71 3O3 O 3A17 E286 20021125000222002112500022CE 2002 11 25 2002FA0001321 120021105G7603 SWITCH RAYTHN390 390 CE THROTTLE INOPERATIVE B K NONE O OTHER ININSP/MAINT 1 NE02719L 99 RB25 HIGH RESISTANCE (8 OHMS) IN RIGHT LOW NR THROTTLE LEVER SWITCH. 6 OHMS MAX PER SPEC SHEET. SPOILER CONTROL UNIT RECEIVES ELECTRICAL SIGNAL FROM LOW N1 THROTTLE SWITCH AS A SUBSYSTEM TO SATISFY LIFT DUMP EXTEND AND RETRACT LOGIC. SCU WILL NOT EXTEND OR RETRACT WITHOUT SIGNAL AND AIRCRAFT WILL NOT HAVE DESIGNED BRAKING. 17 2 3F RTA00010WI 20021125000232002112500023SO 2002 11 25 2002FA0001322 120021114G3020 ANTI-ICE VALVE LKHEED1329 1329* SO GARRTTTFE731TFE7313 01518WP NACELLE INOPERATIVE B QQGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW09 ANTI-ICE VALVE RECEIVED FROM OVERHAUL AGENCY WITH A FRESH OVERHAUL, SOLENOID VALVE WAS CLOCKED 90 DEGREE FROM WHERE THE PRODUCTION PRINT SHOWED WHERE IT SHOULD BE. WE WOULD NOT BE ABLE TO INSTALL IT IN THE AIRCRAFT. THIS HAS BEEN REPORTED TO THIS OVERHAUL AGENCY IN THE PAST AND THE PROBLEM HAS NOT BEEN CORRECTED. 2L74 4J4 F 2A15 E6WE 20021125000242002112500024SO 2002 11 25 2002FA0001323 120021114G3020JC007A ANTI-ICE VALVE LKHEED1329 1329 5263102SO GARRTTTFE731TFE7313 01518WP NACELLE INOPERATIVE B QQGRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW09 ANTI-ICE VALVE RECEIVED FROM OVERHAUL AGENCY WITH A FRESH OVERHAUL, SOLENOID VALVE WAS CLOCKED 90 DEGREE FROM WHERE THE PRODUCTION PRINT SHOWED WHERE IT SHOULD BE. WE WOULD NOT BE ABLE TO INSTALL IT IN THE AIRCRAFT. THIS HAS BEEN REPORTED TO THIS OVERHAUL AGENCY IN THE PAST AND THE PROBLEM HAS NOT BEEN CORRECTED. 2L74 4J4 F 2A15 E6WE 20021125000252002112500025SO 2002 11 25 2002FA0001324 120021023G3233757833 COUPLING PIPER PA24 PA24250 7102404SO LYC O540 O540* 41532EA MLG ACTUATOR BROKEN D O OTHER J WARNING INDICATION NRNOT REPORTED 1 WP097141P 242306 COUPLING FAILED ON GEAR RETRACTION. COUPLING FROM MOTOR TO GEAR BOX CAUSING COUPLING TAB TO SLIDE OUT OF SLOTS CAUSING GEAR TO LOCK HALF-WAY UP, WOULD NOT EXTEND OR RETRACT. USED EMERGENCY PROCEDURE TO EXTEND GEAR. GEAR CIRCUIT BREAKER POPPED. EMERGENCY SPRING WAS BROKEN ON THE JACKSCREW ASSEMBLY, NOT ALLOWING THE JACKSCREW TO DISCONNECT, HAD TO BE MANUALLY LIFTED. 1L71 3O3 O 1A15 E295 20021125000122002112500012 2002 11 25 2002FA0001325 420021121G3197 WIRE HARNESS CESSNA172 172S 2072439CE INSTRUMENT PANELCHAFED D K NONE O OTHER ININSP/MAINT 1 SO19484SP 172S8030 INVESTIGATING AN INOPERATIVE GLARE SHIELD LIGHT, FOUND THAT THE WIRING BUNDLE HAD CHAFED AGAINST THE THROTTLE HOUSING BEHIND THE INSTRUMENT PANEL, SHORTING THE CIRCUIT. SEVERAL WIRES WERE DAMAGED. THERE IS NOTHING TO PROTECT THE WIRES IN THIS AREA SINCE THEY ARE LEFT LYING LOOSELY ON TOP OF THE THROTTLE HOUSING. 1H71 3O NT3A12 20021125000132002112500013SO 2002 11 25 2002FA0001327 220021122G74146310 MAGNETO BEECH 58 58 1152740CE CONT O550 IO550C SO ENGINE FAILED C K NONE O OTHER ININSP/MAINT 1 SO06316RB590 TH1947 684363 MAGNETO APPARENTLY SUFFERED A STOPPAGE CONDITION DUE TO UNKNOWN FAILURE OF IMPULSE COUPLING. DISINTEGRATED INTO SEVERAL PIECES. PARTS FOUND IN FILTER AND PRESSURE RELIEF VALVE. PROBLEM NOTED AT OIL CHANGE AND PILOT REPORTED GRIP OF LOW OIL PRESSURE. MAGNETO HAD BEEN CHANGED PREVIOUSLY AT DIFFERENT LOCATION. 1L72 3O3 O 3A16 E3SO 20021125000142002112500014EA 2002 11 25 2002FA0001328 220021122G7414MS3333 IMPULSE COUPLINGSLICK PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA MAGNETO FAILED C K NONE O OTHER ININSP/MAINT 1 SO054241R 01050291 3240606 L1298248 "ALERT" MAGNETO IMPULSE COUPLING PAWL RIVET (RIVET ATTACHES PAWL TO IMPULSE HUB ASSEMBLY) FAILED ALLOWING PAWL TO WEDGE IN MAGNETO DRIVE GEAR CAUSING FAILURE OF DOWEL ON CRAKKSHAFT DRIVE GEAR RESULTING IN COMPLETE STOPPAGE OF ENGINE. IN ADDITION, THE MAGNETO FLANGE BROKE AWAY AT THE HOLD DOWN BRACKET. 1L71 3O3 O A3SO 1E4 20021126000332002112600033GL 2002 11 26 2002FA0001329 120021007G5540205540000WIP SUPPORT DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO RUDDER CRACKED D K NONE O OTHER ININSP/MAINT 1 NM07974CT2568 C0074 THE SUPPORT BRACKET HAS BEEN FOUND CRACKED AT THE WELD ON THE LOWER LEFT SUPPORT LEG. AIRCRAFT TOTAL TIME 2568. THE SUPPORT IS VERY LIGHT AND IS MOUNTED TO THE COMPOSIT VERTICAL SPAR. THE AREA UNDER THE TOWER IS NOT FLAT AND CAUSES THE TOWER TO CRACK DUE TO THE UNEVEN FORCE APPLIED WHEN THE MOUNTING BOLTS ARE TORQUED TO THERE PORPER TORQUE. THE AREA UNDER THE TOWER NEEDS TO BE FLAT. THE TOWER NEEDS TO BE MADE STRONGER WHERE IT IS WELDED TO BASE. 1L71 3O3 ONTTA4CH E7SO 20021126000342002112600034NM 2002 11 26 2002FA0001330 120021114G243503600923 BEARING DHAV DHC8 DHC8* NM STARTER GEN FAILED B OL3RK NONE O OTHER ININSP/MAINT 1 WP27 1877 1809 STARTER GENERATOR HAD BEARING FAILURE. 2H72 4T RTA13NM 20021127000352002112700035EU 2002 11 27 2002FA0001332 220021107G8530854381 ROCKER ROTAX 912 ROTAX912S4 EU ENGINE CYLINDER WORN B FCPRK NONE O OTHER ININSP/MAINT 1 NM09124XS336 WHEN COMPLYING WITH AD, FOUND ROCKER ARMS WORN AT VALVE FACE AREA, AND GALLING AT PUSHROD SOCKETS. ROTAX SB ADDRESSES THIS PROBLEM, HOWEVER IT DOES NOT INCLUDE THIS SN OF ENGINE. 3 O E00051EN 20021127000442002112700044SO 2002 11 27 2002FA0001335 120021112G2720767350 TORQUE TUBE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A11 52043NE RUDDER CORRODED D K NONE O OTHER ININSP/MAINT 1 GL03195AA3794 31T7904001 FLIGHT CONTROLS, RUDDER TORQUE TUBE/ RIBS CORROSION PRESENT, REPAIRABLE. 1L72 3T3 T A8EA E4EA 20021127000452002112700045SO 2002 11 27 2002FA0001336 120021112G2720767350 TORQUE TUBE PIPER PA31T PA31T1 7103126SO PWA PT6 PT6A11 52043NE RUDDER CORRODED D K NONE O OTHER ININSP/MAINT 1 GL03855JL3234 31T8104045 DURING COMPLIANCE OF SB (RUDDER FLIGHT CONTROLS) TORQUE TUBE ASSEMBLY AND ASSOCIATED RIBS WERE NOTED TO BE NON-REPAIRABLE. CORROSION PRESENT. 1L72 3T3 T A8EA E4EA 20021127000462002112700046 2002 11 27 2002FA0001337 420021113G22100105R2 ROLL SERVO BEECH 36 A36 1151604CE CONT O520 IO520* 17032SO AUTOPILOT DEFECTIVE B DDNRK NONE O OTHER ININSP/MAINT 1 GL2736VG 21 E309 SERVO DRIVE MOTOR SEPARATED FROM REDUCTION GEAR ASSEMBLY. OCCURRED IN NORMAL FLIGHT OPERATIONS. SECOND OCCURRENCE IN THIS AIRCRAFT, IDENTICAL FAILURE. WARRANTY SERVO INSTALLED 9/27/2002, FAILED 11/12/2002. 1L71 3O3 O 3A15 E5CE 20021127000472002112700047GL 2002 11 27 2002FA0001338 220021121G731323055438 NOZZLE ALLSN 250C 250C30S 03013GL ENGINE FAILED B YKERK NONE O OTHER ININSP/MAINT 1 EA17 CAE890553 ENGINE FAILED WHILE AC WAS ON GROUND. UPON DISASSEMBLY OF ENGINE, FOUND GAS PRODUCER ROTOR TIE BOLT BROKEN IN HALF. FURTHER EXAMINATION FOUND THAT NR 2 NOZZLE, WHICH HAD BEEN OVERHAULED 1751 HOURS PRIOR, WAS MISSING 3 OF 5 KEYS THAT HOLD DIAPHRAGM IN PLACE. INSPECTION OF WELDS ON THE 2 REMAINING KEYS FOUND THAT THEY WERE NOT WELDED ON 3 SIDES, AS IS REQUIRED. THE WELDS APPEARED TO LACK PENETRATION. THE AREAS WHERE THE MISSING 3 KEYS WERE ATTACHED ALSO HAD EVIDENCE OF WELDS THAT DID NOT MEET THE REQUIREMENTS. IT IS BELIEVED THAT THE FAILURE OF THE WELDS AND THE SUBSEQUENT LOSS OF THE KEYS AND SHIFTING OF THE DIAPHRAGM RESULTED IN CONTACT OF THE DIAPHRAGM WITH THE ROTOR AND EVENTUALLY FAILURE OF TIE BOLT. 3 U E1GL 20021127000482002112700048CE 2002 11 27 2002FA0001339 120021120G3340 SWITCH CESSNA172 172M 2072418CE LYC O320 O320* 41508EA LANDING LIGHT MELTED D K NONE L NO TEST ININSP/MAINT 1 NE0120402 17261261 INOPERATIVE LANDING LIGHT TRACED TO A MELTED SWITCH AND BURNED WIRES AT THE SWITCH. PROBLEM TRACED TO FLIGHT SCHOOL USING LANDING LIGHT FULL TIME AS A RECOGNITION LIGHT. SWITCH AND WIRING CANNOT STAND A CONTINUOUS 20 AMP LOAD OF THE 250 WATT LAMP. 1H71 3O3 ONT3A12 E274 20021127000512002112700051SO 2002 11 27 2002FA0001340 120021119G71106520200 LATCH PIPER PA32 PA32260 7103206SO LYC O540 O540* 41532EA ENGINE COWL CRACKED D K NONE O OTHER ININSP/MAINT 1 NE01671802 32121 COWL LATCHES ON RIGHT SIDE OF COWL FAILED DURING IFR FLIGHT AND EMERGENCY LANDING MADE SUCCESSFULLY. LATCHES HAD BEEN REPLACED BEFORE THE TRIP. THIS IS THE THIRD SET OF HINGES INSTALLED AND ALL FAILED AFTER A FEW HOURS. THE COWL NOW HAS A SET OF OLD SERVICEABLE HINGES WHICH SEEM TO BE HOLDING UP OK. 1L71 3O3 O A3SO E295 20021127000532002112700053CE 2002 11 27 2002FA0001342 120021029G5753122010024 SKIN CESSNA206 T206H 2073303CE RT TE FLAP CRACKED B HLFRK NONE O OTHER ININSP/MAINT 1 SW17XBACL171 08210 RIGHT FLAP SKIN CRACKED AROUND LEADING EDGE INBOARD. 1H71 3O RTA4CE 20021127000582002112700058GL 2002 11 27 2002FA0001343 120021119G325088341602 CONTROL CABLE NAMER T6 T6G 6400432GL PWA R1340 R1340* 52016NE NLG STEERING BROKEN G O OTHER O OTHER TXTAXI/GRND HDL 1 NM037197C 492897 AFTER NORMAL LANDING AND ROLLOUT AIRCRAFT SUDDENLY VERIED RT. PILOT BRAKED BUT AIRCRAFT NOSED OVER AND CAME TO REST UPSIDE DOWN. DURING INVESTIGATION FOUND BROKEN STEERING CONTROL CABLE (LEFT). 1L71 3R3 R A2575 5E2 20021127000652002112700065GL 2002 11 27 2002FA0001344 120021107G270135283001 INDICATOR AVIAT A1 A1B 2210406GL LYC O360 O360* 41514EA TRIM SEPARATED B S1FRO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 SO23367SA24 2197 TRIM ARM INDICATOR CAME OFF ACTUATOR STUD AND JAMMED TRIM WHEEL. CAUSE DUE TO NO RETAINING NUT ON ACTUATOR STUD SCREW. INSTALL RETAINING NUT ON ACTURATOR STUD SCREW. 1H71 3O3 ONCA22NM E286 20021127000662002112700066EA 2002 11 27 2002FA0001345 220021107G855062817 SCREEN AVIAT A1 A1B 2210406GL LYC O360 O360* 41514EA OIL SYSTEM MISSING B S1FRK NONE O OTHER ININSP/MAINT 1 SO33367SA24 2197 OIL SCREEN MISSING FROM HOUSING. MISSING INSPECTORS. 1H71 3O3 ONCA22NM E286 20021127000682002112700068CE 2002 11 27 2002FA0001346 120021114G282005160167 FITTING CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA FUEL VENT LINE CORRODED G O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 EA11737HV2668 17269438 L222326 FUEL ODOR IN CABIN, INSPECTED AND FOUND FUEL LINE COUPLERS UNDER HEAD LINER DRY ROTTED. ON THE LT SIDE, MFG ROUTED THE AIR VENT DUCT (SCAT HOSE) ON TOP OF THE FUEL VENT LINE CORROSION CREATED A HOLE FROM DAMPNESS AND AGE, FUEL SEEPS THROUGH THE HOLE. 1H71 3O3 ONT3A12 E274 20021127000692002112700069CE 2002 11 27 2002FA0001347 120021114G282005560203 FUEL LINE CESSNA172 172M 2072418CE LYC O320 O320* 41508EA FUSELAGE CORRODED G O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 EA119223H1717 17266024 L4310627A FUEL ODOR IN CABIN, INSPECTED AND FOUND FUEL COUPLERS UNDER HEAD LINER DRY ROTTED. ON THE LEFT SIDE MFG ROUTED THE AIR VENT DUCT (SCAT HOSE) ON TOP OF THE FUEL VENT LINE, CORROSION CREATED A HOLE FROM DAMPNESS AND AGE. FUEL SEEPS THROUGH THE HOLE. 1H71 3O3 ONT3A12 E274 20021127000152002112700015SO 2002 11 27 2002FA0001348 220021126G7414ES10391586 MAGNETO BEECH 58 58P 1152744CE CONT O520 TSIO520WB 17040SO LEFT LACK OF LUBE D C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CE05112RS10 10 ELECTROSYSTEMS DISTRIBUTOR BLOCK FAILED ON TAKEOFF ROLL APPROXIMATELY 10 HOURS AFTER INSTALLATION. IT APPEARS THAT THE OIL LIGHT BEARING THAT THE ROTOR SHAFT RIDES IN WAS NOT PROPERLY OIL BEFORE INSTALLATION. THE PART WAS INSTALLED IN THE LEFT MAGNETO ON THE LEFT ENGINE. 1L72 3O3 O A23CE E8CE 20021127000182002112700018EA 2002 11 27 2002FA0001349 220021126G74141038255511 MAGNETO CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA ENGINE DETACHED G A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 GL057510V 61 177RG0808 ON OCT 12, 2002 AT APPROX. 2030, AIRCRAFT WAS SUBSTANTIALLY DAMAGED WHILE EXECUTING AN ENGINE OUT, GEAR UP, FORCED LANDING, NEAR SOUTH VIENNA, OHIO. PILOT AND PASSENGER WERE SERIOUSLY INJURED. ACCORDING TO THE PILOT, HE WAS CRUISING AT 2500 FT, WHEN HE NOTICED AN UNUSUAL ODOR AND SHORTLY AFTER THAT, THE ENGINE QUIT. AFTER ATTEMPT TO RESTART THE ENGINE, MADE A FORCED LANDING. AIRCRAFT TOUCHED DOWN HARD, BREAKING THE LT WING SPAR AND WRINKLING THE FUSELAGE, EMPENNAGE, FIREWALL AND DAMAGING THE PROPELLER. EXAMINATION BY AN FAA SAFETY INSPECTOR, REVEALED THAT THE MOUNTING HARDWARE FOR THE SINGLE MOUNTED, DUAL MAGNETO WAS MISSING AND THE MAGNETO HAD WORKED LOOSE AND WAS LAYING IN THE ACCESSORY SECTION. 1H71 3O3 O A20CE 1E10 20021203000292002120300029EA 2002 12 3 2002FA0001350 120021118G3230AN676AC13700 WIRE SCWZERG164 G164B 3952802EA PWA R1340 R1340* 52016NE MLG FAILED G GMMGA UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 NM137502A3679 797B LANDING WIRE SEPARATED IN FLIGHT ON RT WING. AIRCRAFT RETURNED FOR LANDING. RT WING SETTLED TO RUNWAY AS AIRCRAFT SLOWED. WIRE APPEARS TO HAVE SMALL ELECTRICAL ARC AT FAILURE POINT THAT COULD HAVE CREATED AS STRESS RISER OCCURRENCE ON 8/28/2002. 1Q71 3R3 R 1A16 5E2 20021203000302002120300030EA 2002 12 3 2002FA0001351 120020616G273050893 PULLEY WACO YMF YMF 9600412EA ELEVATOR WORN D K NONE O OTHER ININSP/MAINT 1 WP0753WC 2861 F5C074 THE INCIDENT OCCURRED ON TAKEOFF ROLL, FORWARD PRESSURE WAS APPLIED TO BRING THE TAIL UP, AT THAT POINT THE CONTROL CABLE BROKE. FURTHER INSPECTION SHOWED THAT THE OTHER CONTROL CABLE WAS 50 PERCENT WORN. IT APPEARED THAT THE PULLEYS COULD BE CAUSING THE PROBLEM THROUGH MISALIGNMENT. 1Q71 3R ATC542 20021203000312002120300031EA 2002 12 3 2002FA0001352 120020901G273050893 PULLEY WACO YMF YMF 9600412EA JACOBPR755 R755B2 35007SW ELEVATOR WORN D K NONE O OTHER ININSP/MAINT 1 WP0796T 1613 F5C052 17859 ELEVATOR PULLEYS WORN. 1Q71 3R3 R ATC542 E237 20021203000322002120300032EA 2002 12 3 2002FA0001353 120021101G273050893 PULLEY WACO YMF YMF 9600412EA JACOBPR755 R755B2 35007SW ELEVATOR WORN D K NONE O OTHER ININSP/MAINT 1 WP07430641873 F5C062 15886 ELEVATOR PULLEYS 20 PERCENT WORN. 1Q71 3R3 R ATC542 E237 20021204000022002120400002SO 2002 12 4 2002FA0001354 120021127G7603455322 THROTTLE CABLE PIPER PA28 PA28R200 7102811SO FUEL CONTROL BROKEN C K NONE O OTHER ININSP/MAINT 1 CE093982X 28R7535382 UPON INVESTIGATION FOUND THROTTLE CABLE BROKEN JUST AFT OF FULL CONTROL. 1L71 3O 2A13 20021204000032002120400003CE 2002 12 4 2002FA0001355 120021120G5412 FIREWALL CESSNA172 172N 2072434CE ENGINE BAY CRACKED C K NONE O OTHER ININSP/MAINT 1 NM034675G11166 17273301 DURING ROUTINE INSPECTION FOUND CRACK IN FIREWALL EXT POWER PLUG BEHIND AND RADIATING OUT TO COWL SHOCK MOUNT DOUBLER AND TOWARD UPPER LT. ALSO TOWARD LOWER RIGHT. THIS COULD BE FROM YEARS OF CONNECTING AND DISCONNECTING EXTERNAL POWER FIREWALL NEEDS TO BE CHECK CLOSELY THIS IS NOT ALWAYS AN EASY CRACK TO SEE. 1H71 3O NT3A12 20021204000042002120400004EA 2002 12 4 2002FA0001356 220021118G741403000 DISTRIBUTOR BLK PIPER PA28 PA28236 7102815SO LYC O540 O540J3A5 41532EA LT MAGNETO CONTAMINATED G K NONE O OTHER ININSP/MAINT 1 EA034295R 288311014 AIRCRAFT MADE OFF-AIRPORT LANDING JUST AFTER TAKE-OFF, DUE TO LOSS OF POWER. DURING INVESTIGATION, MAGNETO WAS DISASSEMBLED AND INSPECTED. LEFT DIDTRIBUTOR TOWER HAD NR 5 TOWER SPRING MISSING AND CORROSION AT CONTACT, GREASE CONTAMINATION WAS NOTED INSIDE DIRTRIBUTOR BLAOCKS AND UNDERNEATH DISTRIBUTOR GEARS MIGRATED FROM CENTER AFT BEARING, SIGNS OF ARCING AND FLASH-OVER OBSERVED. 1L71 3O3 O 2A13 E295 20021211000342002121100034 2002 12 11 2002FA0001358 420021112G2561AV8AS2100 BOTTLE LIFE VEST BROKEN B K NONE O OTHER ININSP/MAINT 1 EA07 CARBON DIOXIDE BOTTLE HOUSING WAS BROKEN DUE TO BLUNT IMPACT FORCE APPLIED. 20021211000352002121100035SO 2002 12 11 2002FA0001360 120021202G5520710563 SPRING PIPER PA31 PA31325 7103105SO ELEVATOR BROKEN D K NONE O OTHER ININSP/MAINT 1 GL2713ES 965 317812046 THE ELEVATOR BUNGE SPRING PART NUMBER 710563 WAS FOUND BROKEN. THIS SPRING IS LIFE LIMITED TO 1000 HOURS PER AD 98-08-18. THIS SPRING WAS LAST INSPECTED AT 964 HOURS OF SERVICE. 1L72 3O A20SO 20021211000362002121100036CE 2002 12 11 2002FA0001363 120021101G5330071378775 SKIN CESSNA182 182R 2072731CE CONT O470 O470* 17026SO FUSELAGE CRACKED C K NONE O OTHER ININSP/MAINT 1 NM039669X 18268584 DURING A 100 HOUR INSPECTION, A CRACK WAS FOUND IN THE FUSELAGE SKIN JUST BEHIND THE STEP THAT IS ATTACHED TO THE FUSELAGE TO AID THE PILOT FOR FUEL CAP INSPECTION OR REFUELING. THIS STEP IS LOCATED ON BOTH SIDES OF THE AIRCRAFT AT STATION 17.0 AND IS ATTACHED TO BULKHEADS, LEFT AND RIGHT, THE BULKHEADS HAVE FOUND TO BE CRACKED. 1L71 3O3 ONT3A13 E273 20021211000242002121100024CE 2002 12 11 2002FA0001367 120021203G552412346603 SKIN CESSNA210 210J 2073439CE LT ELEVATOR WILL NOT BALANCED K NONE W INADEQUATE Q C ININSP/MAINT 1 SO253368S 21059168 AIRCRAFT REPORTED AS NOT HAVING ENOUGH NOSE DOWN TRIM IN CRUISE FLIGHT. AFTER INSPECTION IT WAS NOTED THAT THE TRAILING EDGE OF THE LT ELEVATOR WAS CONTOURED DOWN AND A CHECK OF THE BALANCE SHOWED IT TO BE 'UNDERBALANCED' BY ALMOST TWO INCH POUNDS. THE TRAILING EDGE SKIN WAS REMOVED AND FOUND TO BE A REPLACEMENT SKIN THAT HAD BEEN INSTALLED WITH SOME TYPE OF EXPANDING FOAM TO FILL THE INTERIOR. THIS REPLACEMENT WAS DESIGNED NOT TO HAVE ANY FILLING DUE TO CORROSION PROBLEMS WITH THE ORIGINAL. NO RECORD OF THE REPAIR WAS FOUND IN THE AIRCRAFT RECORDS. A NEW SKIN WAS INSTALLED, THE ELEVATOR CHECKED FOR BALANCE, AND THE AIRCRAFT WAS TEST FLOWN SATISFACTORILY. 1H71 3O 3A21 20021211000252002121100025CE 2002 12 11 2002FA0001368 120021204G5711 SPAR CAP CESSNA210 2105A 2073406CE WING CORRODED D K NONE O OTHER ININSP/MAINT 1 EA258418Z2800 418 INSPECTION MADE DURING INSTALLATION OF SHOULDER HARNESSES REVEALED EXFOLIATION OF AFT CARRY THRU SPAR AND ADJACENT SKINS. CENTER RUDDER ATTACHMENT POINT WAS CORRODED TO SUCH AN EXTENT THAT THE AIRFRAME SUCH THAT REMOVAL OF RUDDER WAS POSSIBLE WITHOUT REMOVING THE CENTER BOLT. MISSING RIVET HEADS AND BULGING SKIN ALONG THE MAIN WING SPAR UNDER BOTH LEFT AND RIGHT FUEL TANKS. EXFOLIATED SKIN ON HORIZONTAL STABILIZER. AIRCRAFT SPENT MOST OF ITS LIFE IN COASTAL FLORIDA. AIRCRAFT RECEIVED AN ANNUAL INSPECTION 1 MONTH PRIOR TO BEING SOLD AND 2 MONTHS PRIOR TO THE INSPECTION LEADING TO THE DISCOVERY OF THESE DISCREPANCIES. AIRCRAFT DISASSEMBLED AND RETURNED TO OWNER AS SCRAP. 1H71 3O 3A21 20021212000012002121200001SO 2002 12 12 2002FA0001369 220021104G7321 LINKAGE BEECH 33 3533 1151402CE CONT O470 IO470* 17026SO THROTTLE BODY WORN B QC4RK NONE O OTHER ININSP/MAINT 1 SO01808ZA 3057R CD202 WHILE TROUBLESHOOTING A ROUGH RUNNING ENGINE, FOLLOWING PROBLEMS WERE FOUND WITH THROTTLE BODY. LINKAGE FROM THROTTLE ATTACH ARM TO FUEL CONTROL UNIT WAS EXCESSIVELY WORN. PIN ON THROTTLE BODY SIDE OF LINKAGE HAS SEVERELY WORN, AND AREA AROUND HOLE FOR COTTER PIN WAS VERY THIN. HOLE IN THROTTLE BODY ARM (THAT RECEIVES THE PIN MENTIONED ABOVE) WAS ALSO WORN EXCESSIVELY. BRASS BUSHING WAS INSERTED BY PREVIOUS REPAIR. PIN HAD WORN THROUGH BUSHING AND WAS STARTING TO CUT INTO ARM. WHILE REMOVING THROTTLE BODY, FOUND MIXTURE CONTROL ATTACHED TO FUEL CONTROL UNIT WITH INCORRECT HARDWARE. IT WAS ATTACHED WITH A PLAIN NUT. THERE WAS NO SAFETY OF ANY KIND, AND NUT WAS LOOSE. MECH SPUN NUT OFF BY HAND. 1L71 3O3 O 3A15 E1CE 20021211000262002121100026CE 2002 12 11 2002FA0001370 120021204G32201058200155 PIN BEECH 76 76 1153005CE NOSE GEAR LOOSE D K NONE O OTHER ININSP/MAINT 1 SO15663636397 ME254 AIRCRAFT TAXIED TO A PARKING SPOT AFTER LANDING. THE NOSE GEAR PIN ROTATED IN THE GEAR LEG CAUSING AN INTERFERENCE WITH THE DOWN LOCK HOOK TO ENGAGE WITH THE PIN, NOT ALLOWING THE NOSE GEAR TO BE DOWN AND LOCKED. THE DOWN LOCK HOOK ENGAGES TO THE FLAT OF THE DOWN LOCK PIN, BUT SINCE IT ROTATED THE RADIUS OF THE PIN STOPPED THE HOOK FROM LOCKING INTO PLACE. THE NOSE GEAR COLLAPSED CAUSING DAMAGE TO THE NOSE GEAR DOORS AND NOSE OF THE AIRCRAFT. WHEN THE GEAR WAS CYCLED DOWN, THERE WERE THREE GREEN INDICATED IN THE COCKPIT AND I VERIFIED THAT THE NOSE GEAR WAS NOT DOWN AND LOCKED LIKE IT SHOULD OF BEEN. 1L72 3O A29CE 20021211000272002121100027SO 2002 12 11 2002FA0001371 220021204G8530654967 CYLINDER CESSNA180 180 2072602CE CONT O470 O470J 17026SO MCAULY2A34C 2A34C66 GL ENGINE SEPARATED D K NONE O OTHER ININSP/MAINT 1 EA172922C383 383 30822 469818JR 681575 SIX CYLINDER SET INSTALLED ON ABOVE ENGINE AT ENGINE TOTAL TIME OF 3605.0 (TSO 381.5). AT ENGINE TOTAL TIME OF 3989.0 HEAD OF CYLINDER NR 4 SEPERATED FROM BARREL. CYLINDER SENT TCM. TCM REPLACING ALL 6 CYLINDERS. 1H71 3O3 ONC5A6 E273 5 CP3EA 20021211000282002121100028SW 2002 12 11 2002FA0001374 120021206G274010699 PEDESTAL AIRTRCAT500 AT502B 0390307SW HORIZONTAL STAB CRACKED B O OTHER O OTHER AGAGRICULTURE 1 SW07605183246 502B0346 PEDESTAL WAS FOUND TO BE CRACKED DURING INSPECTION. 1L71 3T NCA17SW 20021211000292002121100029NE 2002 12 11 2002FA0001375 320021206G611454507 NUT AIRTRCAT400 AT401 0390204SW PWA R1340 R1340* 52016NE HAMSTD23D 23D40 NE PROP HUB CRACKED G K NONE O OTHER ININSP/MAINT 1 GL191008Q280 280 4010702 U23037 A NEWLY OVERHAULED "0" TIME PROPELLER WAS INSTALLED 05/31/01. DURING MAINTENANCE JULY 5, 2002 THE PROPELLER HAD TO BE REMOVED TO FACILITATE OTHER WORK. DURING THE REMOVAL IT WAS DISCOVERED THAT THE PROPELLER RETAINING NUT WAS CRACKED THE FULL HEIGHT OF THE NUT AND IT HAD EXPANDER TO THE EXTENT THE SPECIAL SPLINE WRENCH WOULD NOT FIT OVER THE NUT. THIS CONDITION COULD LEAD TO THE LOSS OF THE PROPELLER AND WOULD NOT HAVE BEEN DETECTED UNTIL COMPLETE FAILURE OF THE RETAINING NUT. THE NUT WAS NEW AT THE TIME OF INSTALLATION. 1L71 3R3 R A17SW 5E2 6 CP719 20021211000302002121100030NE 2002 12 11 2002FA0001376 320021206G611454507 NUT AIRTRCAT400 AT401 0390204SW PWA R1340 R1340* 52016NE HAMSTD23D 23D40 NE PROP HUB CRACKED G K NONE O OTHER ININSP/MAINT 1 GL191008Q280 280 4010702 U23037 A NEWLY OVERHAULED "0" TIME PROPELLER WAS INSTALLED 05/31/01. DURING MAINTENANCE JULY 5, 2002 THE PROPELLER HAD TO BE REMOVED TO FACILITATE OTHER WORK. DURING THE REMOVAL IT WAS DISCOVERED THAT THE PROPELLER RETAINING NUT WAS CRACKED THE FULL HEIGHT OF THE NUT AND IT HAD EXPANDER TO THE EXTENT THE SPECIAL SPLINE WRENCH WOULD NOT FIT OVER THE NUT. THIS CONDITION COULD LEAD TO THE LOSS OF THE PROPELLER AND WOULD NOT HAVE BEEN DETECTED UNTILL COMPLETE FAILURE OF THE RETAINING NUT. THE NUT WAS NEW AT THE TIME OF INSTALLATION. PICTURES OF THE NUT ARE AVAILABLE. 1L71 3R3 R A17SW 5E2 6 CP719 20021211000312002121100031CE 2002 12 11 2002FA0001377 120021209G5711 SPAR BBAVIA7 7KCAB 21101P3CE LYC O320 IO320E2A 41508EA SNSNCH74D 74DM EA WING CRACKED B K NONE O OTHER ININSP/MAINT 1 WP0311687 31372 L482655A K33815 WHILE COMPLYING WITH AD 2000-25-02 R1 (WING SPAR INSPECTION) FOUND BOTH FORWARD SPARS CRACKED AT SPAR ROOT. EACH SPAR HAD TWO CRACKS RUNNING THE LENGTH OF THE WOOD GRAIN AND ADJACENT TO UPPER AND LOWER ATTACH BOLT HOLES. PAINT FROM THE AREA HAD TO BE REMOVED PRIOR TO EXPOSING CRACKS. UPPER CRACKS WERE UNDETECTABLE UNTIL WING REMOVAL. 1H71 3O3 O A759 1E12 5 NP88614 20021212000022002121200002SO 2002 12 12 2002FA0001378 120021104G2434 BEARING PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA ALTERNATOR DAMAGED B PNRGK NONE O OTHER ININSP/MAINT 1 NM0956887 346 A116232 287425059 THE FRONT BEARING ON THE ALTERNATOR HOUSING FAILED CAUSING THE HOUSING THERE TO BE DAMAGED, THE BELT TENSIONING STRAP TO THE ENGINE CASE TO CRACK AND THE ROTOR TO FALL LOOSE ENOUGH INSIDE THE HOUSING TO DESTROY THE ELECTRICAL GENERATING CAPABILITIES OF THE ALTERNATOR. THE CAUSE OF FAILURE WAS NOT CLEAR, ENGINE/PROPELLER VIBRATION WAS DETERMINED TO NOT BE A SIGNIFICANT FACTOR. 1L71 3O3 O 2A13 E274 20021212000032002121200003SO 2002 12 12 2002FA0001379 120021120G1430680660 COLLAR PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520* 17040SO FASTENER LOOSE G K NONE O OTHER ININSP/MAINT 1 NM139130N 4608075 LEFT WING REAR ATTACH FITTING COLLAR FOUND IN RECESS BELOW FITTING. RIVET LOOSE IN HOLE. REPLACED WITH OVERSIZE FASTENER AND TORQUED COLLAR. DISCOVERED DURING ALTERATION FOR ENGINE INSTALLATION. 1L71 3O3 ORTA25SO E8CE 20021212000042002121200004 2002 12 12 2002FA0001380 420021125G25621104 BATTERY CESSNA525 525 2076601CE ELT CORRODED B FCPRK NONE K FLUID LOSS ININSP/MAINT 1 NM09523BT 5250311 ELT BATTERY, BATTERY CASE CORRODED AND CRACKED. ELECTROLYTE LEAK. 1L72 4F RTA1WI 20021212000052002121200005GL 2002 12 12 2002FA0001381 320021127G6111FC76634 BLADE BBAVIA8 8KCAB 2110612CE LYC O320 IO320E1A 41508EA HARTZLHCC2Y HCC2YL1 GL PROPELLER CRACKED B W59RK NONE O OTHER ININSP/MAINT 1 WP0776KF 2934 15374 L514555A DURING INSPECTION, MAINTENANCE WAS UNABLE TO DETERMINE COMPLIANCE WITH AD. DUE TO INADEQUATE RECORDS, PROPELLER WAS SUBMITTED FOR OVERHAUL AND ALSO TO REPLACE THE HUB IAW AD. AT DISASSEMBLY, PROP WAS FOUND TO HAVE COLD COMPRESSION ROLLED SHANKS. HOWEVER, DURING PENETRANT INSPECTION OF THE BLADES AS REQUIRED BY O/H MANUAL, BLADE WAS FOUND CRACKED IN THE COMPRESSION ROLLED RADIUS. BLADE WAS SUBMITTED TO MFG FOR EVALUATION. BLADE IS CRACKED. 1H71 3O3 O A21CE 1E12 5 CP920 20021212000062002121200006CE 2002 12 12 2002FA0001382 120021121G2613115611 OVERHEAT SENSOR CESSNA525 525 2076601CE MAIN BATTERY DEFECTIVE B A UNSCHED LANDING N FALSE WARNING NRNOT REPORTED 1 GL19525RA 5250167 PILOT REPORTED MAIN BATTERY OVER HEAT LIGHT CAME ON IN FLIGHT. BATTERY WAS CHECKED AFTER LANDING AND WAS NOT WARM. BATTERY CELLS CHECKED GOOD ND WERE ALL EVEN VOLTAGE. THE BATTERY OVERHEATED SENSOR WAS FOUND TO BE DEFECTIVE. PURCHASED NEW BATTERY AND SENSOR. 1L72 4F RTA1WI 20021217000012002121700001SO 2002 12 17 2002FA0001383 120021203G3110 SWITCH PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6* 52043EA DISPLAY DIMMER FAILED B LF1RO OTHER O OTHER NRNOT REPORTED 1 EA0717LH 4697007 PILOT EXPERIENCED FAILURE OF ALL DISPLAYS IN AIRCRAFT. AUTOPILOT AND RADIOS APPEARED TO BE OPERATING, BUT NO DISPLAY AVAILABLE. COULD NOT DUPLICATE ON GROUND. CHECKED WIRING AND DIMMING UNIT. FOUND EVIDENCE OF ARCING ON RING TERMINAL AT LOAD CONNECTION. REPLACED DIMMER UNIT AND RING TERMINAL ON WIRE. OPS CHECK GOOD. IT APPEARS THAT RING TERMINAL BECAME LOOSE. THERE WAS NO PLAIN WASHER INSTALLED UNDER THE LOCK WASHER ON SCREW. 1L71 3O3 TRTA25SO E2NE 20021217000192002121700019EA 2002 12 17 2002FA0001384 220021212G7230 BEARING SOCATATBM TBM700 8682000EU PWA PT6 PT6A6 52043EA NR 1 FAILED G O OTHER YGJENGINE STOPPAGE MULTIPLE FAILURE WARNING INDICATION DEDESCENT 1 GL1912WY 1979 112 PCE111098 A/C EXPERIENCED SUDDEN POWER LOSS & ENG STOPPAGE, AND A EMERGENCY LANDING FROM FL245. NO EXTERNAL OIL LEAKS, AND OIL LEVEL WAS DOWN 3 QUARTS FROM FULL. INSPECT OF THE POWER TURBINE SHOWED FOD AND A SMALL AMOUNT OF MELTED METAL IN THE DUCT. PROP SHAFT COULD NOT BE ROTATED. OIL SCREEN PULLED, FERROUS METAL AND BRONZE LIKE FILINGS WERE NOTED. ENG WAS SPLIT. COMPRESSOR HAD DAMAGED BLADES AND ONE MISSING. COMPRESSOR HAD FORE/AFT AND SIDE TO SIDE PLAY, AND RUBBED WHEN TURNED. INSPECT OF THE POWER TURBINE INLET DUCT SHOWED FOD AND SEVERAL TEMP PROBES BROKEN AND MISSING. INDICATIONS WERE THAT THE ENG EXPERIENCED A NR 1 BEARING FAILURE, RESULTING IN FAILURE OF THE COMPRESSOR AND POWER TURBINE WHEELS. 1L71 3T3 TRTA60EU E4EA 20021217000202002121700020CE 2002 12 17 2002FA0001385 120020814G323008421022 BELLCRANK CESSNA310 310Q 2074242CE NLG BROKEN B L ABORTED APPROACH J WARNING INDICATION LDLANDING 1 SO11120SA4298 310Q1041 UPON GEAR EXTENSION, BELLCRANK FAILED. ALL ATTEMPTS TO EXTEND NOSE GEAR FAILED. AIRCRAFT LANDED WITH NOSE GEAR AT 45 DEGREE ANGLE. DAMAGE TO NOSE GEAR AREA. 1L72 3O 3A10 20030106000112003010600011GL 2003 1 6 2002FA0001386 120021215G2821 FUEL TANK AMTR NUWACOT10 GL JACOBSR755 R7559 35003EA MAIN BLOCKED P A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 SW99 163 20 ENGINE FAILURE DURING CRUISE FLIGHT. FAILURE DUE TO RIVETS FROM MAIN FUEL TANK CONSTRUCTION BLOCKING FUEL LINE DOWNSTREAM OF TANK. NO FINGER SCREEN INSTALLED AT TANK OUTLET. RECOMMEND CHECKING OTHER TANKS FOR FINGER SCREENS AND DEBRIS IN TANK. 1B71 3R3 RNCEXPA1B71TC121 20030106000132003010600013CE 2003 1 6 2002FA0001388 120020922G3233R3582517213 ACTUATOR BEECH 36 A36 1151604CE LYC O540 TIO540J2B NE NLG FAILED G O OTHER J WARNING INDICATION APAPPROACH 1 SW17711AM3150 E1487 NLG ACTUATOR ARM FAILED DURING GEAR EXTENSION. NOSE LANDING GEAR WOULD NOT EXTEND. AIRCRAFT LANDED. CAUSING DAMAGE TO PROP, GEAR DOORS, SKIN. 1L71 3O3 O 3A15 E14EA 20030106000142003010600014 2003 1 6 2002FA0001389 420021204G611305503671 SPINNER CESSNA172 172S 2072439CE MCAULY1A170 1A170E GL PROPELLER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL0335339445 172S8891 DURING PREFLIGHT INSPECTION, THE PILOT NOTED THE PROPELLER SPINNER WAS CRACKED. 1H71 3O NT3A12 5 NP857 20030106000152003010600015GL 2003 1 6 2002FA0001390 320021107G6114747621 HUB MCAULY2A34C D2A34C98 GL PROPELLER CRACKED B L2PRK NONE O OTHER ININSP/MAINT 1 SW13 747621 CLEANED HUB, PLASTIC MEDIA BLASTED THREADED AREAS, AND EDDY CURRENT INSPECTED. EDDY CURRENT REVEALED CRACK INDICATION IN THREADED AREA NR 2 BLADE SOCKET 3RD THREAD INBOARD AFT SECTION, NO FURTHER ACTION TAKEN. 5 CP3EA 20030106000162003010600016SO 2003 1 6 2002FA0001391 220021211G8530643766 VALVE GUIDE CONT O200 O200A 17020SO CYLINDER HEAD MISINSTALLED G K NONE O OTHER ININSP/MAINT 1 WP11 EXHAUST VALVE GUIDE IS A REPLACEMENT GUIDE FOR EXHAUST VALVE GUIDE. IN THE ENGINE CYLINDER ASSEMBLY. WHEN THE EXHAUST VALVE GUIDE IS INSTALLED, THE EXHAUST VALVE SPRING RETAINER WILL NOT SEAT PROPERLY OVER THE INSTALLED VALVE GUIDE. THERE IS NO IDENTIFIED EXHAUST VALVE SPRING RETAINER THAT WILL CORRECT THIS PROBLEM. CONTACTED MFG, NO ANSWER OR SOLUTION. 3 O E252 20030106000172003010600017CE 2003 1 6 2002FA0001392 120021204G3397M227591618 WIRE CESSNA402 402B 207590PCE CONT O520 IO520* 17032SO LIGHT SOCKET BROKEN D A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 WP135403M 402B0003 ON TAKEOFF PILOT OBSERVED SMOKE AND SPARK FROM BEHIND INSTRUMENT PANEL. BROKEN WIRE WAS FOUND FROM POST LIGHT SOCKET CONNECTOR. REPLACED CONNECTOR. OPS CHECK OF DASHBOARD LIGHTING FOUND, OK. 1L72 3O3 O A7CE E5CE 20030106000182003010600018SO 2003 1 6 2002FA0001393 120021023G7160554294 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA LT ALT AIR DOOR BROKEN D DF2SK NONE O OTHER ININSP/MAINT 1 SW159290P2874 4496019 DURING 100 HOUR INSPECTION FOUND THAT THE FOLLOWING CONTROL CABLE WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SHROUD OF SWAGED TOGETHER. PROBABLE CAUSE MAY BE DUE TO THE WAY THE CABLES ARE ROUTED. 1L72 3O3 O A19S0 E286 20030106000192003010600019SO 2003 1 6 2002FA0001394 120021023G7160554545 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA ALT AIR DOOR BROKEN D DF2SK NONE O OTHER ININSP/MAINT 1 SW159290P2874 4496019 DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLES WERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SHROUD OF SWAGED TOGETHER. 1L72 3O3 O A19S0 E286 20030106000202003010600020SO 2003 1 6 2002FA0001395 120021023G7602554544 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA ENG MIXTURE BROKEN D DF2SK NONE O OTHER ININSP/MAINT 1 SW159290P2874 4496019 DURING 100 HOUR INSPECTION FOUND THAT THE FOLLOWING CONTROL CABLES WERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SHROUD OF SWAGED TOGETHER. 1L72 3O3 O A19S0 E286 20030106000212003010600021SO 2003 1 6 2002FA0001396 120021023G7602 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA MIXTURE CONTROL BROKEN D DF2SK NONE O OTHER ININSP/MAINT 1 SW159290P 4496019 DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLES WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SHROUD OF SWAGED TOGETHER. 1L72 3O3 O A19S0 E286 20030106000222003010600022SO 2003 1 6 2002FA0001397 120021023G7603554546 CONTROL CABLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA THROTTLE CONTROLBROKEN D DF2SK NONE O OTHER ININSP/MAINT 1 SW159290P2874 4496019 DURING 100 HOUR INSPECTION, FOUND THAT THE FOLLOWING CONTROL CABLE WHERE BROKEN ON THE ENGINE SIDE WHERE TWO PIECES OF SHROUD OF SWAGED TOGETHER. 1L72 3O3 O A19S0 E286 20030106000232003010600023EA 2003 1 6 2002FA0001398 220020112G8530 PUSHROD LYC O540 IO540K1A5 41532EA ENGINE DESTROYED B O3ORK NONE O OTHER ININSP/MAINT 1 AL03 5927 1395 L2078848A ENGINE DISMANTLED DUE TO ENGINE FAILURE, FOUND NR 6 PUSHROD FAILED OR BEARING FAILED. PUSHROD COME OFF NR 6 CRANK JOURNAL AND DESTROYED ENGINE. 3 O 1E4 20030106000242003010600024SO 2003 1 6 2002FA0001399 220021204G8550 NUT CESSNA210 210E 2073416CE CONT O520 IO520A 17032SO OIL FILTER ADAPTLOOSE D K NONE O OTHER ININSP/MAINT 1 CE0195PY 21058514 1120787AR LARGE LOCKNUT ON OIL FILTER ADAPTER CAME LOOSE AND OIL WENT OVERBOARD AND THE ENGINE SEIZED. THE AIRCRAFT LANDED IN A FIELD. THE SAFETY WIRE WAS STILL ATTACHED. 1H71 3O3 O 3A21 E5CE 20020128000502002012800050CE 2002 1 28 2002TU65 120020107G2722556545071 ACTUATOR CESSNA500 550 2076604CE RUDDER DAMAGED B R8RRK NONE O OTHER ININSP/MAINT 1 WP071200N 5500681 ON PREINSTALLATION INSPECTION, THE MECHANIC NOTICED DAMAGE IN THE ATTACH THREADS ON THE ACTUATOR. THE BOLT WOULD NOT THREAD IN EVEN ONE TURN WITH OUT BINDING. AFTER FURTHER INVESTIGATING IT WAS FOUND TO HAVE PART OF A BROKEN BOLT STILL INSIDE THE HOUSING.THIS ACTUATOR WAS JUST OVERHAULED BY THE AVIATION GROUP INC. 231 TIGER WAY PEACHTREE CITY GA 30269 CERTIFICAT NO. VGOR728L W/O 13614. 1L72 4F A22CE 20030320000712003032000071CE 2003 3 20 2003F00143 120021030G3710 LINE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312B WP EJECTOR PUMP CLOGGED D O OTHER O OTHER NRNOT REPORTED 1 CE0310R 042 DEBRIS WAS DISCOVERED IN THE PRESSURE LINE TO THE EJECTOR PUMP. THIS CAUSED A LACK OF VACUUM TO THE OUTFLOW VALVES AND ALLOWED THE CABIN TO PRESSURIZE ON THE GROUND. 2L72 4F4 FRTT00008WIE6WE 20030326000162003032600016CE 2003 3 26 2003F00144 120021111G275026111441 BRACKET CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA FLAP MOTOR CRACKED W O OTHER O OTHER NRNOT REPORTED 1 SO2190HL 4291 208B0693 PRIMARY FLAP MOTOR CB POPPED WHEN SELECTING FULL FLAPS IN FLT. ON GROUND PROBLEM COULD NOT BE DUPLICATED, RIGGING CHECKED. FURTHER MAINT INSP REVEALED FORE AND AFT SUPPORT BRACKET, OF FLAP MOTOR, BUCKLING AND COMPLETE TRANSVERSE CRACKS OF THE AFT SUPPORT BRACKET, WAS CRACKED OUTBOARD AT ATTACHMENT POINT. ASSY HAD ACCUMULATED 9559 LDGS. MATERIAL OF FWD AND AFT SUPPORT BRACKETS, ARE MADE OF .032 T2024. THIS MATERIAL WAS SHOWN TO HAD GIVE WHEN HAND PRESSURE WAS APPLIED AFTER NEW PART WAS INSTALLED. DEPLOYMENT OF FLAPS TO FULL AT HIGH AIRSPEEDS, IAW AFM, SHOWED SIGNIFICANT SLOW MOVEMENT OF FLAPS TO FULL DOWN IN FLT. THESE HIGH AERODYNAMIC LOADS PUT UNUSUAL STRESS ON LIGHTER MATERIAL. 1H71 3T3 T A37CE E2NE 20030106000272003010600027CE 2003 1 6 2003FA0000000 120021126G242199105921 ALTERNATOR CESSNA210 T210L 2073449CE ENGINE SEIZED B SL4RK NONE O OTHER ININSP/MAINT 1 SO072317G3389 21061485 PILOT REPORTED THAT THE LOW VOLTAGE LIGHT ILLUMINATED ON TAXI. MECHANIC FOUND THAT THE ALTERNATOR HAD SEIZED AND THE BELT HAD BROKEN. WHEN THE ALTERNATOR WAS REMOVED, THE MECHANIC NOTED THAT THERE WAS A NOTICEABLE CATCH WHILE ROTATION THE PULLEY. ADDITIONALLY ONE OF THE CASE HALF THROUGH BOLTS HAD BACKED OUT SLIGHTLY AND WAS LOOSE. 1H71 3O 3A21 20030106000282003010600028CE 2003 1 6 2003FA0000001 120021126G2421MDW100211 THRU BOLT CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ALTERNATOR UNDERTORQUED B SL4RK NONE O OTHER ININSP/MAINT 1 SO079815Z U20606678 245523 THE ALTERNATOR THROUGH BOLTS SECURING THE FRONT CASE HALF TO THE REAR CASE HALF WERE FOUND TO HAVE BACKED OUT, ALLOWING THE CASE HALVES TO SEPARATE APPROXIMATELY .1250 INCH. THE THROUGH BOLT RETAINERS AND SAFETY WIRE WERE STILL IN PLACE. THE ALTERNATOR HAD A MANUFACTURING DATE OF 02/00. THIS IS ONE OF TWO CONDITION REPORTS FILED FROM THIS REPAIR STATION WITH THE SAME DEFICIENCY AND MANUFACTURING DATE. IT IS SUSPECTED THAT THE CASE HALF THROUGH BOLTS WERE NOT TORQUED TO THE PROPER SPECIFICATION. 1H71 3O3 O A4CE E5CE 20030106000292003010600029CE 2003 1 6 2003FA0000002 120021126G2421MDW100211 THRU BOLT CESSNA206 TU206F 2073353CE CONT O520 TSIO520C 17040SO ALTERNATOR UNDERTORQUED B SL4RK NONE O OTHER ININSP/MAINT 1 SO073160L U20602815 THE ALTERNATOR THROUGH BOLTS SECURING THE FRONT CASE HALF TO THE REAR CASE HALF WERE FOUND TO HAVE BACKED OUT ALLOWING THE CASE HALVES TO SEPARATE APPROXIMATELY .1250 INCH. THE THROUGH BOLT RETAINERS AND SAFETY WIRE WERE STILL IN PLACE. THE ALTERNATOR HAD MFG DATE OF 02/00. THIS IS ONE OF TWO CONDITION REPORTS FILED FROM THIS REPAIR STATION WITH THE DEFICIENCY AND MFG DATE. THE CASE HALF THROUGH BOLTS WERE NOT TORQUED TO THE PROPER SPECIFICATIONS. 1H71 3O3 O A4CE E8CE 20030106000302003010600030CE 2003 1 6 2003FA0000003 120021126G242199105921 ALTERNATOR CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO ENGINE SEIZED B SL4RK NONE O OTHER ININSP/MAINT 1 SO079815Z98 U20606678 PILOT REPORTED THAT THE AMMETER WAS SHOWING A DISCHARGE UPON ENGINE STARTUP. IT WAS DISCOVERED THAT THE ALTERNATOR HAD SEIZED AND THE BELT HAD BROKEN. 1H71 3O3 O A4CE E5CE 20030106000012003010600001SO 2003 1 6 2003FA0000004 220021220G8550CH48109 OIL FILTER BEECH 35 G35 1151516CE CONT E225 E2258 17015SO ENGINE BURST D E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 SO134575D21 D4727 36300D98 AFTER STARTING ENGINE AND PERFORMING A ROUTINE WARM UP. PILOT NOTICED OIL PRESSURE DROPPING. AFTER SHUTDOWN, THE OIL FILTER WAS SHOWN TO HAVE PARTIALITY BLOWN OPEN AT THE BASE WHERE IT IS CRIMPED. ALSO THE PRESSURE RELIEF VALVE WAS FOUND TO HAVE 14 WASHERS UNDER THE SPRING. THIS ENGINE IS NOT ALLOWED TO HAVE ANY WASHERS. THE OIL FILTER HAD 21 HRS SINCE INSTALLATION AND WAS NOT OVER TORQUED. THE ENGINE HAS 1044 HRS. SMOH. 1L71 3O3 O A777 E267 20030106000032003010600003CE 2003 1 6 2003FA0000007 120021112G3220C1630050201 WHEEL CESSNA172 172RG 2072438CE MLG CRACKED D K NONE O OTHER ININSP/MAINT 1 CE07471KP6473 172RG0798 DISCOVERED CRACK IN THE SEAT FOR THE WHEEL BEARING RACE IN THE NOSE WHEEL HALF DURING ANNUAL INSPECTION. DEFECT APPEARS TO HAVE BEEN CAUSED BY REPEATED INSTALLATION OF THE RACE OVER THE LIFE OF THE WHEEL 1H71 3O 3A17 20030106000042003010600004SO 2003 1 6 2003FA0000008 120021231G632116420 DISK MAULE M5 M5210C 5460134SO BRAKE ASSY MISINSTALLED D C ABORTED TAKEOFF W INADEQUATE Q C TOTAKEOFF 1 GL27901SP 6180C PILOT GROUND LOOPED A/C FOR THE SECOND TIME, FIRST FLIGHT AFTER REPAIRS FROM 1ST GROUND LOOP. PILOT REPORTED IT FELT LIKE BRAKE WAS LOCKING UP. DISASSEMBLED BOTH WHEEL AND BRAKE ASSY AND FOUND INCORRECT DISCS NR 164020 HAD BEEN INSTALLED BY PERSONS UNKNOWN.THIS DISC THICKNESS IS .187 INCH. INSTALLED CORRECT DISC 164-02601 WHICH HAS A THICKNESS OF .250 INCH. THE DIFFERENCE IN DIMENSION WAS ALLOWING THE PISTON TO EXTEND TO FAR OUT AND BINDING THE CALIPER. VISUAL INSPECTION ALSO SHOWED FLUID SEEPAGE AROUND BOTH PISTONS. NEW SEALS HAD BEEN INSTALLED AT LAST ANNUAL/15 HOURS PRIOR. 1H71 3O 3A23 20030110000472003011000047SO 2003 1 10 2003FA0000009 120021209G32321159L41000145 ACTUATOR GULSTMG1159 GIV 3980115SO RROYCETAY TAY6118 EU MLG LEAKING D K NONE KL FLUID LOSS NO TEST ININSP/MAINT 1 EA25464QS7264 1264 CREW REPORTED COMBINED HYDRAULIC QUANTITY LOW, LIGHT ILLUMINATED. JACKED AIRCRAFT AND PERFORMED GEAR SWING. FOUND RT MLG SIDEBRACE ACTUATOR LEAKING. REMOVED LEAKING ACTUATOR, INSTALLED OVERHAULED ACTUATOR OF SAME P/N, PERFORMED GEAR SWINGS, OPERATIONAL AND LEAK CHECKS GOOD. SERVICED AND BLED HYDRAULIC RESERVOIRS. ALL WORK PERFECTLY IAW GAC G IV MSG-3 MM. OLD ACTUATOR SENT TO MFG FOR EVALUATION. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA12EA E25NE 20030110000482003011000048EA 2003 1 10 2003FA0000010 220021209G8520LW13884 BEARING CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FWD MAIN DELAMINATED D K NONE O OTHER ININSP/MAINT 1 GL07914MA1241 172S8257 L2843351A BEARING DELAMINATED PART DEFECT REQUEST PART BE ANALYSED BY MANUFACTURER OR FAA. 1H71 3O3 ONT3A12 1E10 20030110000492003011000049CE 2003 1 10 2003FA0000011 120021203G3710 PUMP CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO VACUUM SYS LEAKING G K NONE O OTHER ININSP/MAINT 1 CE01356D 340A0745 LOSS OF OIL AND OIL PRESSURE ON RT ENGINE. TROUBLESHOT FOUND LEAKING FROM VACUUM PUMP BASE. REMOVED VACUUM PUMP. FOUND PIECES OF OLD GASKET STILL ATTACHED TO MOUNTING PAD WITH A NEW GASKET INSTALLED. CLEANED MOUNTING BASE, INSTALLED NEW VACUUM PUMP GASKET AND REINSTALLED VACUUM PUMP. INSPECTED OIL FILTER, NO METAL NOTED. INSTALLED NEW OIL FILTER, SERVICED ENGINE WITH OIL. RAN ENGINE. OPS AND LEAK CHECKED, OK. PILOT SAID VACUUM PUMP WAS CHANGED THAT DAY. 1L72 3O3 O 3A25 E8CE 20030110000502003011000050CE 2003 1 10 2003FA0000013 120021218G2910228000113 LINE CESSNA182 TR182 2072735CE LYC O540 O540L3C5 41532EA HYD POWERPACK LEAKING G K NONE O OTHER ININSP/MAINT 1 NM07757PD R18201251 L21618 THE POWERPACK CONTROL LINE WAS LEAKING HYDRAULIC FLUID, CAUSED BY AN IMPROPER SECURITY AND/OR ROUTING OF THE HYDRAULIC POWERPACK CONTROL LINE IN PROXIMITY TO THE MIXTURE CONTROL CABLE. AREA AROUND THE HYDRAULIC POWERPACK CONTROL LINE SHOULD BE INSPECTED UNDER THE PANEL DURING ROUTINE AND ANNUAL INSPECTIONS. 1H71 3O3 O 3A13 E295 20030110000532003011000053CE 2003 1 10 2003FA0000015 120020930G1430 BOLT CESSNA206 U206B 2073322CE CONT O520 IO520* 17032SO VERTICAL STAB LOOSE B WWKRK NONE O OTHER ININSP/MAINT 1 AL034994F U2060694 INSPECTION IAW AD AND FOUND LOOSE BOLT HOLES FOR VERTICAL STABILIZER ATTACH. INSTALLED OVERSIZE BOLTS AND DYE CHECK, NO CRACKS FOUND, RETORQUED BOLTS DYE PENETRANT INSPECTION ITEMS. 1H71 3O3 O A4CE E5CE 20030110000542003011000054EA 2003 1 10 2003FA0000018 220021219G8520SL13885M03 MAIN BEARING LYC O720 IO720A1B 41546EA ENGINE FAILED B BG4RK NONE O OTHER ININSP/MAINT 1 WP17 3 L25254 AFTER TEST CELL RUN, ENGINE OIL WAS DRAINED AND THE SUCTION SCREEN AND FILTER WAS CHECKED. A ABNORMAL AMOUNT OF ALUMINUM WAS FOUND. UPON DISASSEMBLY, IT WAS FOUND THAT THE FRONT BEARING HAD FAILED AT THE NR 2 JOURNAL. THE METAL APPEARED TO HAVE DELAMINATED AND TRANSFERRED TO THE CRANKSHAFT THRUST AREA AND CRANKCASE THRUST FACE. 3 O 1E15 20030204002312003020400231SO 2003 2 4 2003FA0000024 120021130G5740 ATTACH FITTING GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY50614 54519EU WING MISINSTALLED B N3DRK NONE W INADEQUATE Q C ININSP/MAINT 1 GL09200AB 71 DURING ROUTINE 24-MONTH ULTRASONIC EXAMINATION NOTED ASC-426 (3 PIECE WING ATTACH FITTING) MODIFICATION WAS IMPROPERLY INSTALLED. NOTED THAT DOUBLER WAS TRIMMED TO FIT WING PLANK CUT OUT INSTEAD OF WING PIN DIAMETER. RECOMMEND ALL OPERATORS VISUALLY INSPECT FOR PROPER INSTALLATION AND CONTACT MFG. 2L72 4F4 FRTA12EA E2EU 20030204002372003020400237EU 2003 2 4 2003FA0000026 120021209G793130723742 LINE AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP 2 ENGINE CRACKED C EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 EA25833AV1237 181 P101345 DURING CRUISE FLIGHT, NR 2 OIL LIGHT ON MASTER WARNING PANEL CAME ON. POWER LEVER WAS REDUCED TO IDLE, OIL PRESSURE INDICATION CONTINUED TO FALL TO LESS THAN 25 PSI, THIS TOOK APPROXIMATELY 15-20 SECONDS. CHECKLIST WAS CALLED, NR 2 ENGINE WAS SHUT DOWN. CREW DEIVERTED FOR LONGER RUNWAY AND MAINTENANCE SERVICES. NO OTHER ABNOMALIES WERE ENCOUNTERED AND EMERGENCY WAS NOT DECLARED. UNEVENTFUL LANDING WAS MADE. AIRCRAFT WAS TAXIED TO MAINTENANCE BASE. OIL WAS FOUND DRIPPING OUT OF NR 2 ENGINE COWLING. FURTHER EXAMINATIONS OF ENGINE DISCOVERED CRACK ON OIL PRESSURE SUPPLY LINE TO THE AFT BEARING AREA. THE PART WAS REPLACED AND RUN AND LEAK CHECKS COMPLIED WITH. NO LEAKS NOTED AND AIRCRAFT WAS RETURNED TO SERVICE.2L73 4F4 FRTA46EU E6WE 20030110000552003011000055CE 2003 1 10 2003FA0000027 120021219G2820 LINE CESSNA172 172N 2072434CE LYC O320 O320* 41508EA FUEL SYSTEM LEAKING B K NONE K FLUID LOSS ININSP/MAINT 1 SO06739LC3930 17270619 FUEL LEAK NOTED CENTER TOP EDGE OF LT DOOR FROM HEADLINER. FOUND OUTSIDE AIR DUCT CHAFING ON FUEL VENT LINE, CORRODED HOLE IN LINE. BOTH LINE AND DUCT REPLACED. SPIRAL PLASTIC WRAP ADDED TO NEW LINE DUE TO TIGHT AREA ON LT SIDE. RT SIDE INSPECTED, NO PROBLEMS, AS CLEARANCE IS ADEQUATE. INSPECTION AT LEAST DURING ANNUAL INSPECTIONS SHOULD BE ACCOMPLISHED. REQUIRES OPENING HEADLINER TO VIEW DUCT, LINES AND RUBBER HOSE CONNECTIONS. 1H71 3O3 ONT3A12 E274 20030110000562003011000056CE 2003 1 10 2003FA0000028 120021025G3260363800501 SWITCH BEECH 36 A36 1151604CE CONT O550 IO550* SO CAM LOOSE D C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 SO152324A528 E3124 LANDING GEAR WARNING HORN WAS SOUNDING IN COCKPIT AS A/C WAS TAXIED. DURING TAKEOFF, LANDING GEAR RETRACTED AS SOON AS A/C BROKE GROUND, EVEN THOUGH LANDING GEAR CONTROL SWITCH WAS IN LANDING GEAR (DOWN). ELECTRICAL T/S ESTABLISHED THAT LANDING GEAR CONTROL SWITCH COMMANDING GEAR RETRACTION EVEN THOUGH SWITCH WAS IN DOWN POSITION. SWITCH WAS REMOVED FROM PANEL AND INSPECTED. CAM, WHICH ACTUATES SWITCH TO RAISE AND LWR LANDING GEAR, INSIDE OF LANDING GEAR CONTROL SWITCH WAS LOOSE. CAM IS HELD IN PLACE WITH TWO SET SCREWS WHICH LOCK CAM TO GEAR SELECTOR HANDLE SHAFT. ONE OF SET SCREWS WAS NOT MAKING CONTACT WITH THE GEAR HANDLE SHAFT. THE OTHER SET SCREW WAS MAKING LIGHT CONTACT. RIGGED CAM IAW MM. 1L71 3O3 O 3A15 E3SO 20030203000942003020300094CE 2003 2 3 2003FA0000032 120021231G54141213401 COWLING CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO ENGINE WORN G K NONE O OTHER ININSP/MAINT 1 GL0311KR 21061249 IT IS POSSIBLE THAT DUE TO NORMAL WEAR OF THE ENGINE COWL CAUSED CONTACT WITH THE NLG DOOR EDGE PREVENTING THE NLG FROM FULLY EXTENDING. IN ADDITION IT IS POSSIBLE THAT DUE TO THE INCORPORATION OF STC SA 5934SW, REMOVING HYDRAULIC POWER FROM THE NLG, ACTUATION PREVENTED FORCING THE DOOR ALL THE WAY OPEN WHICH WOULD ALLOW THE GEAR TO FULLY EXTEND. 1H71 3O3 O 3A21 E8CE 20030203000952003020300095CE 2003 2 3 2003FA0000037 120021209G2913105932E COMMUTATOR CESSNA177 177RG 2073709CE LYC O360 IO360A1A 41514EA HYD PUMP MOTOR WORN D O OTHER O OTHER NRNOT REPORTED 1 CE058971M2321 177RG0371 PUMP OPERATED SLOWLY. SENT FOR OVERHAUL WHICH SHOWED THAT MOTOR BRUSHES WERE WORN AND THE COMMUTATOR WAS WORN IRREGULARLY. LED TO SLOW OPERATION OF THE LANDING GEAR. 1H71 3O3 O A20CE 1E10 20030203000962003020300096CE 2003 2 3 2003FA0000038 120021209G326020700174 DOWNLOCK SWITCH CESSNA177 177RG 2073709CE LYC O360 IO360A1A 41514EA MLG SHORTED D O OTHER O OTHER NRNOT REPORTED 1 CE058971M2321 177RG0371 FOUND THAT RT MLG DOWNLOCK SWITCH TO BE STUCK IN THE CLOSED POSITION WHICH, WHEN COMBINED WITH THE LT MLG DOWNLOCK SWITCH OPERATING IMPROPERLY, LED TO A LANDING WHERE THE MAIN GEAR COLLAPSED WITH A GREEN DOWN AND LOCKED LIGHT. 1H71 3O3 O A20CE 1E10 20030203001032003020300103EU 2003 2 3 2003FA0000063 120021209G2910120A9491105AV RELAY GROB 120 G120A 1660208EU HYD SYSTEM SHORTED B VJ3RK NONE O OTHER ININSP/MAINT 1 WP07 DURING PROGRESSIVE INSPECTION AND CYCLE OF THE LANDING GEAR WE HAD A FAILURE OCCURED. FOUND A BAD HYDRAULIC CONTROL RELAY THAT SHORTED. BECAUSE OF THAT SHORT, IT ALLOW TO MUCH CURRENT TO FLOW TO PC BOARD AND SHORT OUT BOARD BETWEEN RELAY K13 PIN 13 AND 16 TO BOARD PIN 6, RECOMMEND THAT SOME TYPE OF CIRCUIT PROTECTION BE PLACED BEFORE BOARD TO PROTECT FROM POWER SPIKES. PART NEW OUT OF STOCK. 1L71 3O RTA49CE 20030203001142003020300114SW 2003 2 3 2003FA0000072 120021212G6410471201353 GRIP BELL 47 47G3B1 1181028SW ALLSN 250C 250C20 03013GL T/R BLADE CRACKED B E5WRK NONE O OTHER ININSP/MAINT 1 GL218548F 6507 CRACK LIKE INDICATION ON 9TH THREAD INBOARD WHICH EXCEEDS 15 PERCENT. IAW AD. PART REJECTED AND RED TAGGED BY REPAIR STATION. OPERATOR STATED PART WAS PURCHASED AS SPARE PRIOR TO AD. PART DESTROYED BY OPERATOR. 1G71 3O3 U 2H3 E4CE 20030203001212003020300121CE 2003 2 3 2003FA0000076 120021216G3710442CW PUMP BEECH 80 65B80 1152812CE LYC O720 IO720* 41546EA LT ENGINE VACUUMFAILED D O OTHER O OTHER NRNOT REPORTED 1 WP1346MA 283 LD413 PUMP FAILED UNDER NORMAL OPERATING CONDITIONS. 1L72 3O3 O 3A20 1E15 20030203001232003020300123SO 2003 2 3 2003FA0000078 120021227G323016667000 LINK PIPER PA23 PA23160 7102304SO LYC O360 O360A1D 41514EA NLG BROKEN D K NONE O OTHER ININSP/MAINT 1 NE034188P4298 231676 L3041736A PILOT REPORTED HEARING A BANG WHEN GEAR RETRACTED. NO NOSE GEAR INDICATION ON GEAR EXTENSION. UPON LANDING, NOSE GEAR DOWN AND LOCKED WITH GREEN LIGHT. LANDED WITHOUT INCIDENT. ON INSPECTION, FOUND HYDRAULIC ACTUATOR CONNECTOR LINKS BROKEN IN HALF WHICH ALSO RIPPED OPEN BOLT HOLES FOR LOCKING LINK. REPLACED PART, OPS CHECK GOOD. SUSPECT FATIGUE FAILURE. 1L72 3O3 O 1A10 E286 20030203001302003020300130EU 2003 2 3 2003FA0000083 120021201G2121M3348A1 MOTOR SAAB SF340 SF340A 7850100EU FAN FAILED D K NONE O OTHER ININSP/MAINT 1 SW99ZKNLP FAN RETURNED TO MFG FOR OVERHAUL. WHEN FAN WAS TESTED, IT FAILED THE MINIMUM RPM REQUIREMENTS, WHEN IT WAS DISASSEMBLED, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED IAW THE MM. THE ARMATURE IS NOT OF DAE DESIGN. OVERHAUL MANUAL DOES NOT ALLOW FOR THE REWINDING OF THE ARMATURE OR THE REPLACEMENT OF PARTS OTHER THAN LISTED. 2L72 4T RTA52EU 20030203001362003020300136SO 2003 2 3 2003FA0000087 120020806G29103153601 LINE PIPER PA23 PA23250 7102308SO HYD SYSTEM FAILED C K NONE O OTHER ININSP/MAINT 1 EA07508UU2774 277954001 LANDING GEAR HYDRAULIC FLUID HARD LINE FAILED DUE TO CRACKED FLARE UNDER (B) NUT CAUSING HYDRAULIC FLUID TO BE PUMPED OVERBOARD. RIGHT MLG AND NLG FAILED TO DOWN AND LOCK WITH EMERGENCY CO2 BOTTLE DEPLOYMENT. AIRCRAFT LANDED WITH THE RT MLG AND NLG UNLOCKED. VERY HARD TO INSPECT THIS LINE DURING A ANNUAL INSPECTION DUE TO ITS LOCATION. SHOULD HAVE A HIGH PRESSURE HYDRAULIC HOSE INSTALLED IN THIS POSITION AND MANDATORY REPLACEMENT EVERY TEN YEARS. 1L72 3O 1A10 20030203001412003020300141NM 2003 2 3 2003FA0000092 120021204G2822568126713005 PUMP BOEING737 737* NM FUEL BOOST INOPERATIVE B IU6RO OTHER O OTHER NRNOT REPORTED 1 NM01 666 BOOST PUMP IS INOPERATIVE. STATOR HAS THREE BLOWN FUSES. INTERNALLY CORRODED ROTOR CAUSED UNIT TO OVERHEAT AND BLOW FUSES. ADDRESS ROTOR CORROSION PROBLEMS WITH MFG. (JOB NR 172794) 2L72 4F RTA16WE 20030218000742003021800074 2003 2 18 2003FA0000116 420020103G2561GA1ZP0201101 LIFE VEST CABIN FAILED B KO1RK NONE L NO TEST ININSP/MAINT 1 EA07 INDIVIDUAL FLOAT DEVICE FAILED. MFG RECOMMENDED CELL PRESSURE TEST IAW 25-60-13. DOM NOV 1984. 20030218000752003021800075 2003 2 18 2003FA0000118 420020412G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA273537B241 172S8827 SPINNER BULKHEAD CRACKED. 1H71 3O NT3A12 20030218000762003021800076 2003 2 18 2003FA0000119 420020524G611305503671 SPINNER CESSNA172 172S 2072439CE PROPELLER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA273537B55 172S8827 PROPELLER SPINNER CRACKED. 1H71 3O NT3A12 20030218000772003021800077 2003 2 18 2003FA0000120 420020524G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA273537B55 172S8827 SPINNER BULKHEAD CRACKED 1H71 3O NT3A12 20030218000802003021800080 2003 2 18 2003FA0000123 420020206G611305503671 SPINNER CESSNA172 172S 2072439CE PROPELLER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27393SP950 172S8290 PROPELLER SPINNER CRACKED. 1H71 3O NT3A12 20030218001082003021800108 2003 2 18 2003FA0000126 420020307G611305503671 SPINNER CESSNA172 172S 2072439CE PROPELLER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27740SP466 172S8671 PROPELLER SPINNER CRACKED. 1H71 3O NT3A12 20030218001102003021800110 2003 2 18 2003FA0000127 420020307G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27740SP 172S8671 SPINNER BULKHEAD, CRACKED. 1H71 3O NT3A12 20030218001122003021800112 2003 2 18 2003FA0000128 420020411G611305503671 SPINNER CESSNA172 172S 2072439CE PROPELLER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27740SP 172S8671 PROPELLER SPINNER, CRACKED. 1H71 3O NT3A12 20030218001132003021800113 2003 2 18 2003FA0000129 420020411G6113055032111 BULKHEAD CESSNA172 172S 2072439CE SPINNER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27740SP43 172S8671 SPINNER BULKHEAD, CRACKED. 1H71 3O NT3A12 20030218001142003021800114 2003 2 18 2003FA0000130 420020820G611305503671 SPINNER CESSNA172 172S 2072439CE PROPELLER CRACKED B IBIRO OTHER O OTHER NRNOT REPORTED 1 EA27740SP187 172S8671 PROPELLER SPINNER, CRACKED. 1H71 3O NT3A12 20030218001212003021800121CE 2003 2 18 2003FA0000133 120021227G3220HSBG5S BEARING CESSNA310 310D 2074212CE CONT O470 IO470* 17026SO NLG SEIZED C O OTHER O OTHER NRNOT REPORTED 1 SW016738T 39038 FORWARD ROD END BEARING (ON INTERMEDIATE ROD FROM LANDING GEAR GEARBOX TO NOSE GEAR) SEIZED, CAUSING ROD END TO SHEAR IT`S ATTACH RIVETS, ALLOWING ROD END TO PARTIALLY SEPARATE FROM ROD, EFFECTIVELY JAMMING NOSE GEAR. THIS RESULTED IN A NOSE GEAR-UP LANDING. ROD END APPARENTLY SNAPPED DURING LANDING. 1L72 3O3 O 3A10 E1CE 20030214000162003021400016SO 2003 2 14 2003FA0000139 220020927G85203979 GEAR CONT R670 W6706A 17016SO CAMSHAFT WRONG PART B RAQRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW15 14090 ENGINE STOPPED RUNNING DUE TO A FAILED INTERMEDIATE CAM DRIVE GEAR. UPON DISASSEMBLY IT WAS FOUND THAT A PN 3979 GEAR FROM A TANK ENGINE HAD BEEN SUBSTITUTED FOR THE PN A3062. AIRCRAFT ENGINE GEAR WHICH SHOULD HAVE BEEN USED. TANK IGNITION DRIVE GEARS HAD BEEN USED AS WELL IN PLACE OF THEIR AIRCRAFT COUNTERPARTS. THE TEETH HAD SHEARED FROM THE INTERMEDIATE CAM DRIVE GEAR CAUSING THE CAM TO STOP TURNING AND ENGINE QUIT RUNNING. 3 R E162 20030220000022003022000002EA 2003 2 20 2003FA0000166 120021108G3210C6UM111010 STRUCTURE DHAV DHC6 DHC6 2802606EA MLG CRACKED B A7RRO OTHER O OTHER NRNOT REPORTED 1 SW19 MAIN LANDING GEAR, CRACKED AT TAC OF WELD. UNKNOWN. NO OTER APPARENT DAMAGE. 1H72 3T RTA9EA 20030220000052003022000005SO 2003 2 20 2003FA0000170 120021230G301014565200402 PICCOLO TUBE EMB 145 EMB145 3260210SO WING BENT B A7RRO OTHER O OTHER NRNOT REPORTED 1 SW19 PICCOLO TUBE BENT AND CRUSHED. 2L72 4F RTT00011AT 20030311000742003031100074SO 2003 3 11 2003FA0000171 120021121G3230AN313A BOLT PIPER PA44 PA44180 7104402SO LYC O360 O360* 41514EA NLG DOWNLOCK MISSING G O OTHER O OTHER NRNOT REPORTED 1 WP05205ER 447995320 THE NOSE LANDING GEAR DOWNLOCK BOLT WAS MISSING, FOUND BROKEN OFF AT NUTPLATE. THIS CONTRIBUTED TO AN INADVERTENT NOSE GEAR RETRACTION. BOLT COULD POSSIBLY HAVE BEEN BENT PREVIOUSLY OR LOOSE. 1L72 3O3 O A19S0 E286 20030311000792003031100079EA 2003 3 11 2003FA0000179 120020926G5230C6FSM373027 LATCH DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A11 52043NE CARGO DOOR UNSECURE C O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 EA17204SA 402 CARGO DOOR DEPARTED AIRCRAFT. AFTER INSPECTION OF THE REAR CARGO DOOR UPON ITS RECOVERY, IT WAS NOTED THAT AN ATTEMPT MAY HAVE BEEN TRIED TO OPEN THE DOOR ON THE AIRCRAFT AND THE DOOR WAS NOT FULLY SECURED WHEN THE AIRCRAFT DEPARTED. TESTING ON THE GROUND SHOWED THAT THE DOOR COULD ONLY BE PARTIALLY SECURED, THE LATCHING PINS WERE PARTIALLY ENGAGED IN THE DOOR FRAME. IT WAS FOUND THAT PRIOR TO THE COMPLETE LATCHING OF THE DOOR, THE LATCHING MECHANISM BECAME HARDER TO TURN, GIVING THE IMPRESSION THAT THE DOOR WAS FULLY LATCHED AND SECURED. 1H72 3T3 TRTA9EA E4EA 20030313000092003031300009CE 2003 3 13 2003FA0000215 120020514G2422MD2628 INVERTER CESSNA208 208B 2073701CE PWA PT6 PT6* 52043EA DIRECTIONAL GYROFAILED D O OTHER W INADEQUATE Q C NRNOT REPORTED 1 SO212222C200 47416 208B0921 DIRECTIONAL GYRO FAILED DUE TO UNACCEPTABLE INSTALLATION OF A MD26-28 INVERTER WITH ITS 26V AC OUTPUT IN PARALLEL WITH THE KG102A 26V AC OUTPUT. THIS WAS DONE IN ERRO TO BOOST THE CURRENT CAPACITY ON THE 26V AC LINE. CANNOT PARALLED INVERTER OUTPUT UNLESS THE CAN BE SYNCHRONIZED, WHICH IS NOT POSSIBLE ON THESE TWO UNITS. IN THIS INSTALLATION, THE ADDITIONAL CURRENT WAS NOT REQUIRED SINCE THE TWO UNITS DRIVEN BY THE BOOTSTRAP ARE NOT MECHANICAL SYNCHROS BUT HIGH IMP ELECTRONIC CIRCUITS. THE GYRO WAS REPLACED AND THE MD26-28 ELIMINATED. 1H71 3T3 T A37CE E2NE 20030313000132003031300013CE 2003 3 13 2003FA0000219 120020314G781020179110 EXHAUST PIPE ZINAIRCH2000CH2000 9950100CE LYC O235 O235* 41505EA ENGINE CRACKED B QE5RO OTHER O OTHER NRNOT REPORTED 1 NM078500Z 201003 ASSEMBLIES ARE CRACKING WITH LESS THAN 100 HOURS IN SERVICE SINCE NEW. THE CRACKS ARE UNDER THE CABIN HEAT SHROUD AND CAN NOT BE SEEN UNLESS THE SHROUD IS REMOVED. NUMEROUS CRACKS HAVE ALSO BEEN FOUND IN OTHER AREAS OF THESE ASSEMBLIES. IT IS SUGGESTED THAT THE MANUFACTURER BE CONTACTED IMMEDIATELY WITH THE ABOVE INFORMATION AND RECOMMEND CORRECTIVE ACTION. UNTIL THE ABOVE IS CORRECTED BY THE MANUFACTURER, IT IS SUGGESTED BY THIS REPAIR STATION THAT THE EXHAUST SYSTEM BE PRESSURE CHECKED EVERY TWENTY FIVE (25) HOURS. 1L71 3O3 ONTTA5CH E223 20030409000612003040900061CE 2003 4 9 2003FA0000322 120020125G781012509921 SLIP JOINT CESSNA206 T206H 2073303CE LYC O540 TIO540AJ1A EA EXHAUST STACK WORN D JZYRO OTHER O OTHER NRNOT REPORTED 1 NM0925AK 445 T20608010 L10106HA THERE IS AN EXHAUST ELBOW THAT COMES OFF THE WASTEGATE AND RETURNS TO THE TAILPIPE. THIS PIPE HAD WORN NEARLY THROUGH AT THE SLIP JOINT BETWEEN IT AND THE TAIL PIPE. THE TAIL PIPE WAS WORN TO A SHARP EDGE WHERE THE ELBOW ENTERS THE SLIP JOINT. THIS CONDITION WAS NOT VISIBLE UNTIL THE TAILPIPE WAS REMOVED. PROBABLE CAUSE IT THE VIBRATION BETWEEN THE TWO PIPES. THE TAILPIPE NEEDS TO BE REMOVED EVERY 200 HOURS TO INSPECT THIS JOINT FOR DAMAGE. UNDETECTED, THIS EXHAUST PIPE WOULD HAVE FAILED IN A FEW MORE HOURS. THIS FAILURE COULD HAVE CAUSED AN INFLIGHT FIRE AND POSSIBLE LOSS OF LIFE. 1H71 3O3 ORTA4CE E14EA 20030409000622003040900062SO 2003 4 9 2003FA0000323 220020315G8520A50446 CRANKSHAFT CONT A75 A75* 17005SO ENGINE BROKEN B JZYRO OTHER O OTHER NRNOT REPORTED 1 NM09 5641703 OWNER COMPLAINED ABOUT THE ENGINE KNOCKING. BROUGHT ENGINE TO US FOR INSPECTION. UPON DISASSEMBLY WE FOUND THE CRANKSHAFT IN TWO PIECES. THE CRANKSHAFT WAS BROKEN BETWEEN THE FRONT MAIN JOURNAL AND THE NR 4 ROD BEARING JOURNAL. ENGINE WAS OPERATING ON AUTO FUEL. ENGINE HAD BEEN DISASSEMBLED FOR REPAIR WORK APPROXIMATELY 20 HOURS BEFORE. 3 O E213 20030409000102003040900010SW 2003 4 9 2003FA0000325 120020305G74006891969 CONTROL UNIT BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL AUTO RELIGHT INTERMITTENT D O OTHER O OTHER NRNOT REPORTED 1 NM099984K 45054 CAE832197R AUTO-RELIGHT SYSTEM ACTIVATES INTERMEDIATELY DURING NORMAL ENGINE OPERATION. 1G71 3U3 U H2SW E4CE 20030409000742003040900074SW 2003 4 9 2003FA0000338 120020621G5320206033110239 STIFFENER BELL 206 206L4 1182110SW ALLSN 250C 250C30 03013GL FUSELAGE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NM092064S2587 52002 FOUND SUBJECT STIFFENER AND WEB CRACKED DURING MAINTENANCE EVENT. GAINED ACCESS AND FOUND RIGHT HAND BEAM ALSO CRACKED. BEAM AREA WAS HIDDEN UNTIL DISASSEMBLY SHOWED FURTHER DAMAGE. SUGGEST THAT BETTER ATTENTION IS PAID TO THIS AREA ON INSPECTIONS, ESPECIALLY IF HELICOPTER IS SUBJECTED TO A HARD LANDING OR IS USED FOR EXTERNAL LOAD OPERATIONS. MANUFACTURER COULD MODIFY STIFFENER IN THE CURVED AREA TO STRENGTHEN THE ASSEMBLY. 1G71 3U3 UNCH2SW E1GL 20030410000052003041000005GL 2003 4 10 2003FA0000350 120020104G2820281210081 LINE ENSTRMF28 280C 3300505GL LYC O360 HIO360E1AD 41514EA FUEL SYSTEM BROKEN D PNRGO OTHER O OTHER NRNOT REPORTED 1 NM09646H 1099 THE TUBE FAILED INSIDE THE FERRULE ON THE ENGINE DRIVEN FUEL PUMP FITTING DUE TO RUBBING AND VIBRATION. FAILURE WAS FOUND AFTER PILOT COMPLAINED OF LOW M.A.P., ABOUT 2 IN HG, AT MAXIMUM OPERATING PERIMETERS, AND FUEL CONSUMPTION LOW. 1G71 3O3 O H1CE 1E10 20030410000062003041000006GL 2003 4 10 2003FA0000351 120020104G2820281210081 LINE ENSTRMF28 F28F 3300412GL LYC O360 HIO360F1AD 41514EA FUEL PUMP BROKEN D PNRGO OTHER O OTHER NRNOT REPORTED 1 NM098626A1650 783 THE TUBE FAILED ADJACENT TO FERRULE ON THE ENGINE DRIVEN FUEL PUMP FITTING. FAILURE WAS FOUND UPON REMOVAL OF THE PART FROM THE AIRCRAFT TO PERFORM OTHER MAINTENANCE. RECOMMEND CHANGING THIS RIDGED LINE TO A FLEXIBLE LINE; 1G71 3O3 O H1CE 1E10 20030410000092003041000009EA 2003 4 10 2003FA0000355 220021024G8530LW19001 EXHAUST VALVE PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA NR 3 CYL INDER FAILED D A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 GL1595118 2825812 L2470327A A/C EXPERIENCED SUDDEN LOSS OF POWER, LANDED SAFELY ON COUNTRY ROAD. INVESTIGATION FOUND NR 3 CYLINDER LOST 75 PERCENT OF EXHAUST VALVE FACE THAT SUBSEQUENTLY TRAVELED THROUGH THE INDUCTION SYSTEM TO REMAINING CYLINDERS. BROKEN VALVE PARTS FORCED SPARK PLUG TIPS TO CRUSH TO A NO GAP CONDITION. NR 1 CYLINDER HAD BOTH PLUGS CRUSHED, NR 2 HAD ONE PLUG CRUSHED, ENGINE BASICALLY RAN ON 2 CYLINDERS. PN OF VALVE LW OR SL19001. ENGINE REPLACED, TEST RUN OPS REVEALED INADEQUATE COOLING TO THE NR 3 CYL WITH SAME BAFFLING AS FAILED ENG. CHT IND REVEALED TEMPS TO BE ABOVE 420 DEGREE TEMPERATURE DROP IN OPERATION. SUSPECT HIGH CHT TEMP CAUSED SHORT LIFE SPAN OF VALVE. 1L71 3O3 O 2A13 E274 20030410000102003041000010CE 2003 4 10 2003FA0000356 120020917G282051001101 VENT LINE CESSNA414 414A 2075907CE CONT O520 TSIO520* 17040SO LT WING CHAFED D O OTHER K FLUID LOSS NRNOT REPORTED 1 NM09414ST 414A0614 FUEL RUNNING OUT OF LT VENT WHEN TOPPED OFF. INSP REVEALED LEFT VENT TUBE HAD A HOLE CHAFED IN IT BY FUEL FILLER PORT SCREEN. THIS AIRCRAFT HAD RAM WINGLETS INSTALLED SEVERAL HOURS BEFORE THIS OCCURRED. LINE MAY HAVE BEEN BENT DURING THIS INSTALLATION, CAUSING LINE TO CHAFF ON FILLER PORT SCREEN. INSPECTED RIGHT SIDE WITH NO CHAFING FOUND. RECOMMEND THIS LINE TO BE INSPECTED WHEN FUEL TANKS ARE OPENED, OR VISUAL INSPECTION THRU FILLER PORT. 1L72 3O3 O A7CE E8CE 20030410000112003041000011CE 2003 4 10 2003FA0000357 120021031G561010138402517 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE COCKPIT CRACKED B CGORO OTHER O OTHER NRNOT REPORTED 1 GL03363CA2067 BB1250 LEFT WINDSHIELD INNER PLY FAILED INFLIGHT, SPIDER WEB, CRACKED OVER ENTIRE INNER PLY. FLIGHT CONDITIONS AT TIME, NOT REPORTED. NO OBVIOUS EXTERIOR DEFECTS OR FOD OBSERVED. 1L72 4T4 T A24CE E4EA 20030423000522003042300052SW 2003 4 23 2003FA0000394 120021122G32331057005G ACTUATOR MOONEYM20 M20J 5870219SW MLG FAILED D FR8SO OTHER J WARNING INDICATION NRNOT REPORTED 1 EA23747CF4284 349 240196 AIRCRAFT LANDING GEAR WOULD NOT FULLY EXTEND WITH MOTOR OR HAND CRANK. AIRCRAFT LANDED FOLLOWED BY GEAR COLLAPSE, CAUSING DAMAGE TO BELLY, STEP, PROP AND GEAR DOORS. EXAMINATION REVEALED SEVERAL TEETH GROUND FLAT. ALL LIMIT SWITCHES APPEARS TO FUNCTION NORMAL. 1L71 3O 2A3 20030507001572003050700157CE 2003 5 7 2003FA0000397 120021126G323012416307 BUMPER BLOCK CESSNA210 P210N 2073454CE CONT O520 TSIO520* 17040SO MLG DEBONDED B SMTRO OTHER O OTHER NRNOT REPORTED 1 EA175555S183 P21000417 LT AND RT MAIN LANDING GEAR SHELL BUMPER DEBONDS, THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FULL DOWN TRAVEL. THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, THEREFORE AN UNSAFE CONDITION. IT APPEARS THAT MFG MAY HAVE CHANGED THE COMPOSITION OF THE SHELL BUMPER MATERIAL WHICH DOES NOT HAVE GOOD BONDING QUALITIES. (PHOTO) 1H71 3O3 O 3A21 E8CE 20030509000902003050900090SO 2003 5 9 2003FA0000434 220021011G8530SA631475 PISTON CONT O520 IO520F 17032SO ENGINE CONTAMINATED B O3ORO OTHER O OTHER NRNOT REPORTED 1 AL03 941 901094H ENGINE DISMANTELED DUE TO METAL CONTAMINATION, FOUND NR 2 PISTON BROKEN AT RING LAND ON LOWER SIDE OF ENGINE. 3 O E5CE 20030508000602003050800060SO 2003 5 8 2003FA0000435 220021010G8520SA631475 PISTON CONT O520 IO520F 17032SO ENGINE CONTAMINATED B O3ORO OTHER O OTHER NRNOT REPORTED 1 AL03 700 1684688F ENGINE DISMANTLED DUE TO METAL CONTAMINATION. FOUND NR 2 PISTON BROKEN AT TOP SCRAPER RING LAND. 3 O E5CE 20030514002302003051400230SW 2003 5 14 2003FA0000467 120021207G3897304316 HEAT TAPE GULSTM111 111RKWELL 0144601SW GALLEY MELTED C RO3RO OTHER O OTHER NRNOT REPORTED 1 CE03 460 DURING INSPECTION, TECHNICIANS DISCOVERED MELTED GALLEY DRAIN HEAT TAPE. WHEN THE TAPE OVERHEATED, IT APPEARS TO HAVE CAUSED THE INSULATION TO HAVE MELTED. THIS TAPE WAS INSTALLED IN 1996. 1L71 3O A11SO 20030606000372003060600037CE 2003 6 6 2003FA0000513 120021202G531207126151 BULKHEAD CESSNA182 182P 2075816CE CONT O470 O470* 17026SO FUSELAGE CRACKED D O OTHER O OTHER NRNOT REPORTED 1 CE077446Q 18261086 WHEN PERFORMING A FULL STALL LANDING THE TAIL TIE DOWN STRUCK THE GROUND (RATHER HARD). INSPECTION FOUND NO DAMAGE OTHER THAN SCUFFING OF THE TIE DOWN RING. FOUND ALL FIVE NUTS AND BOLTS TO BE TIGHT TO BOTH FINGER PRESSURE AND WRENCH, COMPLIENCE WITH AD. WHILE CLEANING AREA AROUND RT RUDDER CABLE HOLE, A POSSIBLE CRACK WAS NOTED AND CONFIRMED. CRACK ORIGINATED AT APPROX 11 OCLOCK ON THE HOLE, RADIATING OUTWARD AND UPWARD APPROX .3125 INCH, TO A POINT APPROX .1875 INCH FROM UPPER CURVE AT BULKHEAD FLANGE. STRIKE ON TIE DOWN RING WAS A DIRECT CONTRIBUTOR TO THE DAMAGE FOUND. 1H71 3O3 ONTTA13 E273 20030606000532003060600053SW 2003 6 6 2003FA0000516 120021101G5542420030507 CAP GULSTM690TP 690B 7630516SW GARRTTTPE331TPE331* 01514WP RUDDER SEPARATED G O OTHER O OTHER NRNOT REPORTED 1 SW1777UA 10450635 11422 SHORTLY AFTER LEVELING OFF AT A CRUISE ALTITUDE OF 16,000 FT, THE AIRCRAFT MADE A HARD UNCOMMANDED TURN TO THE LEFT AND LOST APPROX 1000 FT ALTITUDE BEFORE THE PILOT WAS ABLE TO REGAIN CONTROL. POST FLIGHT INSPECTION REVEALED THAT THE TOP PORTION OF THE RUDDER, RED BEACON, LEAD BALANCE WEIGHT, AND APPROXIMATELY SIX INCHES OF THE RUDDER SKIN WERE MISSING. MAINTENANCE RECORDS REVEALED PREVIOUS DAMAGE HISTORY IN THIS AREA WHICH MAY HAVE CONTRIBUTED TO THE SEPARATION. 1H72 3T3 T 2A4 E2WE 20030625000302003062500030EA 2003 6 25 2003FA0000566 120021218G2823TC173007 SELECTOR VALVE DHAV DHC2 DHC2* 2800108EA PWA R985 R985* 52008NE FUEL SYSTEM LEAKING C O OTHER K FLUID LOSS NRNOT REPORTED 1 NM01233N 269 976 WITH FUEL SELECTOR VALVE IN OFF POSITION FUEL LEAKS BY VALVE, SLIGHT PRESSURE ON CABLE DRUM ON VALVE MAKES IT WORSE. (SIDE LOAD) THIS VALVE MUST BE CHECKED DURING AND ANNUAL, IN THE OFF POSITION AND PUTTING PRESSURE ON DRUM TO SEE IF FUEL FLOWS THROUGH VALVE IN THE OFF POSITION. 1H71 3R3 R A806 5E1 20030918000692003091800069SO 2003 9 18 2003FA0000764 120021031G3230487312 SPRING PIPER PA23 PA23250 7102308SO LYC O540 TIO540* 41532EA MLG DOWNLOCK BROKEN D O OTHER O OTHER NRNOT REPORTED 1 EA2513878 274513 THERE ARE 4 DOWNLOCK HOOK SPRINGS ON EACH GEAR 2 WERE FOUND BROKEN AFTER A RIGHT GEAR COLLAPSED ON ROLLOUT, IT IS UNKNOWN IF A HARD LANDING WAS MADE PRIOR TO COLLAPSE THERE ARE NO REPLACEMENT TIMES FOR THESE SPRINGS, BUT PROBABLY 1000 HOURS, WHOULD BE A GOOD IDEA. 1L72 3O3 O 1A10 E14EA 20030922000042003092200004EU 2003 9 22 2003FA0000833 120021210G5302 SKIN AGUSTAA109 A109A2 0260120EU TAIL BOOM CORRODED C O OTHER O OTHER NRNOT REPORTED 1 NE03500WK3485 7341 EXTENSIVE CORROSION IN SEVERAL AREAS OF THE TAIL BOOM. CORROSION UNDER THE LT AND RIGHT SIDES OF THE HORIZONTAL STABILIZER THROUTH THE SHEET ALUMINUM. CORROSION UNDER THE AIRCRAFT, BELOW THE BAGGAGE AREA THROUGH THE SHEET ALUMINUM AND CORROSION ON THE ANGLED FITTING IN THE FORWARD VERTICAL STABILIZER. THE CORROSION WAS FOUND DURING AN ANNUAL INSPECTION OF THE AIRCRAFT. 1G72 3U H7EU 20030915000252003091500025 2003 9 15 2003FA0000889 420021120G61224508042 GOVERNOR RKWELL700 700 7630520SW LYC O540 TIO540R2AD 41532EA HARTZLHCE3Y HCE3YR2A GL PROPELLER MALFUNCTIONED F E ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 GL03 PN 4508-042 WAS OF A LOWER THAN SPECIFIED HARDNESS WHEN INSPECTED. THIS LOWER HARDNESS ALLOWED THE PART TO WEAR AT A FASTER RATE THAN EXPECTED. THIS WEAR ALLOWED THE DRIVE SPRING TO DISENGAGE FROM THE DRIVER IN THE PROPELLER GOVERNOR AND PERMITTED THE PROPELLER TO OPERATE AT A SPEED FASTER THAN SPECIFIED. THE PART HAS BEEN IN SERVICE SINCE 1977. 1L72 3O3 O A12SW E14EA 5 CP33EA 20031027000432003102700043EA 2003 10 27 2003FA0000980 220020502G7230311211703 BEARING BEECH 200 200BEECH 1152920CE PWA PT6 PT6* 52043EA COMPRESSOR DELAMINATED C K NONE O OTHER ININSP/MAINT 1 SO03283KA806 BB83 BEARING RACE SILVER PLATING DELAMINATED. FOUND SILVER IN MAIN OIL FILTER CHECK AT ROUTINE MFG INSPECTION. BEARING WAS REMOVED FROM SERVICE BY STANDARD AERO AND WARRANTED BY MFG. ALSO COPPER FLASHING FOR SILVER PLATING WAS ALSO PEELING FROM RACE. MFG SIL ADDRESSED THIS PROBLEM ON THE NR 2 AND NR 3 BEARINGS IN A CERTAIN BATCH THAT THE COPPER FLASHING WAS OMITTED IN MANUFACTURING. THIS WAS A NR 1 BEARING AND THE COPPER FLASHING WAS PRESENT BUT DELAMINATING. 1L72 4T3 T A24CE E2NE 20031030000972003103000097EA 2003 10 30 2003FA0000996 220021007G8520LW13884M10 MAIN BEARING PIPER PA32 PA32260 7103206SO LYC O540 O540E4B5 41532EA HARTZLHCC2Y HCC2YK1 GL CRANKSHAFT FAILED D O OTHER O OTHER NRNOT REPORTED 1 WP013450W503 32317 L1002040 CH6746E NEW FRONT MAIN BEARING PN LW13884M010 (6-99 ML-KS) INSTALLED AT ENGINE MAJOR OVERHAUL ON 5/15/00. ENGINE REMOVED THIS DATE FOR METAL CONTAMINATION DV SCREEN AND FILTER. METAL SOURCE IS FROM MAIN BEARING DELAMINATION. THIS IS A MANUFACTURING PROBLEM. FURTHER INVESTIGATION IS NEEDED TO DETERMINE MANUFACTURING ERROR. ENGINE WAS MOMENTS AWAY FROM A CATASTROPHIC FAILURE. (WP01200304903) 1L71 3O3 O A3SO E295 5 CP920 20031113000632003111300063NE 2003 11 13 2003FA0001141 220020731G8530 ROCKER BOSS WSK M18 PZLM18 9180102EU WSK ASZ62 ASZ62IRM18 NE NR 9 CYLINDER CRACKED G O OTHER RB PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW116236M IZ012308 KAD848870 AIRCRAFT COLLIDED WITH THE GROUND WHILE MANEUVERING FOR AERIAL APPLICATION. (FAR 137) EYE WITNESS OBSERVED WHITE SMOKE COMING FROM AIRCRAFT BEFORE ACCIDENT. NR 9 CYLINDER(JNG) EXHAUST ROCKER BOX HAD DEVELOPED A CRACK AND EXHAUST AND OIL BURNING FURTHERED BURNED OUT THE CRACK TO APPROX. 1 INCH IN WIDTH. POLISH PRODUCED ENGINE. FAA TC-EIONE.(K) 1L71 3R3 R E10NE 20031230000732003123000073NE 2003 12 30 2003FA0001212 120020717G612026305 CONTROL HANDLE CONAERLA4 LA4 5110302NE LYC O360 O360* 41514EA COCKPIT BROKEN D O OTHER O OTHER NRNOT REPORTED 1 AL037604L 377 PILOT REPORTED THAT ON APPROACH TO LANDING THAT HE ADVANCED PROP TO FULL RPM AND THE PROP CONTROL LEVER BROKE OFF IN HIS HAND, INSTALLED A NEW PROP CONTROL LEVER. OLD PART SHOWS EVIDENCE THAT IT WAS CRACKED FOR SOME TIME PRIOR TO THIS, BUT WENT UNDETECTED DUE TO A PLASTIC COATING ON THE LEVER. RECOMMEND A CLOSER INSPECTION THAT WOULD INCLUDE THE REMOVAL OF THIS PLASTIC COATING IF A CRACK IS SUSPECTED. 1H71 3O3 O 1A13 E286 20031230000582003123000058 2003 12 30 2003FA0001213 420020322G6113055032111 BULKHEAD CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA MCAULY1A170 1A170* GL PROP SPINNER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL03792SP60 172S8717 DURING A PREFLIGHT INSPECTION THE PILOT NOTED AN .7500 INCH CRACK IN THE CORNER OF SPINNER BULKHEAD. 1H71 3O3 ONT3A12 1E10 5 NP857 20040304000452004030400045 2004 3 4 2004FA0000228 420021217G2562AK450 ELT CESSNA310 310N 2074234CE CABIN FAILED D K NONE L NO TEST ININSP/MAINT 1 CE53310VD60 50035 310N0123 EMERGENCY LOCATOR BEACON FAILED PRIOR TO FIRST ANNUAL CHECK. BATTERIES WERE FINE, BUT UNIT FAILED TO FUNCTION- IT WAS DEAD ONLY ONE YEAR AFTER INITIAL INSTALLATION. 1L72 3O 3A10 20040908001702004090800170SO 2004 9 8 2004FA0000609 120021115G1430AN175C33A BOLT PIPER PA30 PA39 7103902SO LYC O320 IO320* 41508EA STABILATOR CORRODED D Q76EO OTHER O OTHER NRNOT REPORTED 1 SW158943Y3004 39104 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA 30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERLY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE. TT3004. 1L72 3O3 O A1EA 1E12 20040908001682004090800168SO 2004 9 8 2004FA0000610 120021025G1430AN175C33A BOLT PIPER PA24 PA24 7102402SO LYC O360 O360* 41514EA STABILATOR CORRODED D Q76EO OTHER O OTHER NRNOT REPORTED 1 SW156613P 241734 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILIATOR HORN ASSEMBLY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). THE TORQUE TUBE. 1L71 3O3 O 1A15 E286 20040908001712004090800171SO 2004 9 8 2004FA0000615 120020919G1430AN175C33A BOLT PIPER PA30 PA30 7103002SO LYC O320 IO320* 41508EA STABILATOR CORRODED D Q76EO OTHER O OTHER NRNOT REPORTED 1 SW157672Y3342 30750 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE. TT 3342. 1L72 3O3 O A1EA 1E12 20040908001652004090800165CE 2004 9 8 2004FA0000618 120021025G1430AN175C33A BOLT PIPER PA24 PA24180 7102402CE LYC O360 O360* 41514EA STABILATOR CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SW15487NM 24835 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE. 1L71 3O3 ONT1A15 E286 20040908001782004090800178SO 2004 9 8 2004FA0000620 120021010G1430AN175C33A BOLT PIPER PA24 PA24260 7102406SO LYC O540 TIO540* 41532EA STABILATOR CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SW159073P6132 244542 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321). AND THE TORQUE TUBE. TT 6132. 1L71 3O3 O 1A15 E14EA 20040908001792004090800179SO 2004 9 8 2004FA0000622 120020707G1430AN175C33A BOLT PIPER PA24 PA24260 7102406SO LYC O540 TIO540* 41532EA STABILATOR CORRODED D O OTHER O OTHER NRNOT REPORTED 1 SW158700P3842 244146 DURING ANNUAL INSPECTION THE STABILATOR WAS REMOVED FOR FURTHER INSPECTION. THIS IS DUE TO PREVIOUS PROBLEMS ON OTHER PA24 AND PA30/39 AIRCRAFT WITH STABILATOR TORQUE TUBE AND ATTACHMENT BOLTS WITH EXCESSIVE CORROSION. BOTH BOLTS AN175C33A THAT ATTACHES THE STABILATOR HORN ASSY TO THE TORQUE TUBE WERE SEVERELY CORRODED. ALSO CORRODED WERE THE FOLLOWING BOLTS: AN24-46A (400-932), AN174-22A (402-321) AND THE TORQUE TUBE. TT 3842. 1L71 3O3 O 1A15 E14EA 20040831000412004083100041SO 2004 8 31 2004FA0000625 120020220G27402020302 TORQUE TUBE PIPER PA24 PA24250 7102404SO LYC O540 O540* 41532EA STABILATOR CORRODED D K NONE O OTHER ININSP/MAINT 1 SW155947P 241037 PRIOR TO ANNUAL INSPECTION. THE RT STABILATOR TIP WAS OBSERVED TO OSCILLATE SEVERAL INCHES. DURING THE ANNUAL INSPECTING THE RT STABILATOR BEARING, PN 4250383 WAS FOUND TO BE LOOSE. THIS PROCESS TOOK THREE PEOPLE SEVERAL HOURS TO COMPLETE. TO ASSIST IN THE REMOVAL, MAKE-SHIFT LEVER WAS CONSTRUCTED TO HELP IN THE TWISTING OF THE STABILATOR ON THE TORQUE TUBE. CORROSION WAS FOUND ON THE STABILATOR TORQUE TUBE AND THE BOLTS, AN175-33A, THAT ATTACH THE STABILATOR TORQUE TUBE TO THE HORN ASSY, 20397. AFTER CORROSION WAS REMOVED FROM BOLTS, OVER .45 MATERIAL WAS REMOVED. NO RECORD WAS FOUND TO SUGGEST THAT THE STABILATOR WAS REMOVED PRIOR TO THIS DATE. 1L71 3O3 O 1A15 E295 20040831000252004083100025SO 2004 8 31 2004FA0000626 220020116G8520 CRANKCASE PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO RIGHT CRACKED D K NONE O OTHER ININSP/MAINT 1 SW0535597519 348070063 807616R THE TURBOCHARGER ATTACHES TO THE ENGINE RT CRANKCASE, THROUGH A 21 INCH MOUNTING BRACKET, WHICH ATTACHES TO THE RT AFT ENGINE MOUNT. DURING A ROUTINE 100 HR INSPECTION, A 1.75 INCH CRACK WAS FOUND ON THE RT CRANKCASE HALF, RT AFT ENGINE MOUNT ATTACH. IT APPEARS THAT OVER TIME, THE FLEXING OF THE TURBOCHARGER INSTALLATION PRODUCES A STRESS CRACK ON THE CASE HALF AROUND THE FWD STUD. IT IS POSSIBLE THAT THIS PROBLEM IS DUE TO HIGH TIME CRANKCASE HALVES AND THE DESIGN OF THE TURBOCHARGER MOUNTING. ENGINE HAS 519.2 HRS SINCE FACTORY REMAN. 1L72 3O3 O A7SO E9CE 20040923000912004092300091SO 2004 9 23 2004FA0000627 220020116G8520 CRANKCASE PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO ENGINE CRACKED D O OTHER K FLUID LOSS NRNOT REPORTED 1 SW0535597146 348070063 818407R THE TURBOCHARGER ATTACHES TO THE ENGINE RT CRANKCASE, THROUGH A 21 INCH MOUNTING BRACKET, WHICH ATTACHES TO THE RT AFT ENGINE MOUNT. DURING A ROUTINE 100 HR INSPECTION, A .75 INCH CRACK WAS FOUND ON THE RT CRANKCASE HALF, RT AFT ENGINE MOUNT ATTACH. IT APPEARS THAT OVER TIME, THE FLEXING OF THE TURBOCHARGER INSTALLATION PRODUCES A STRESS CRACK ON THE CASE HALF AROUND THE FWD STUD. IT IS POSSIBLE THAT THIS PROBLEM IS DUE TO HIGH TIME CRANKCASE HALVES AND THE DESIGN OF THE TURBOCHARGER MOUNTING. IT APPEARS AS THOUGH THIS CRACK HAS BEEN PREVIOUSLY WELDED. ENGINE HAS 146.6 HRS SINCE FACTORY REMAN. 1L72 3O3 O A7SO E9CE 20051228000742005122800074EA 2005 12 28 2005FA0001607 120021218G2823TC173007 SELECTOR VALVE DHAV DHC2 DHC2* 2800108EA PWA R985 R985* 52008NE FUEL SYSTEM LEAKING C O OTHER K FLUID LOSS NRNOT REPORTED 1 NM01233N 269 976 WITH FUEL SELECTOR VALVE IN OFF POSITION FUEL LEAKS BY VALVE, SLIGHT PRESSURE ON CABLE DRUM ON VALVE MAKES IT WORSE. (SIDE LOAD) THIS VALVE MUST BE CHECKED DURING AN ANNUAL IN THE OFF POSITION AND PUTTING PRESSURE ON DRUM TO SEE IF FUEL FLOWS THROUGH VALVE IN THE OFF POSITION. (K) 1H71 3R3 R A806 5E1 20021011001272002101100127CE 2002 10 11 3399 220021008G73106544453 LINE CONT TSIO360RB1B PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360RB 17025CE ENGINE FUEL CHAFED B K NONE O OTHER ININSP/MAINT 1 NE036TZ 553 322262 3449125 322262 FUEL INJECTION LINE TO NR 3 CYLINDER CHAFED BY CLAMP SECURING RUBBER INDUCTION COUPLING FROM INDUCTION SPIDER TO NR 5 CYLINDER INTAKE TUBE. 1L72 3O3 O A7SO E9CE 20021120000302002112000030CE 2002 11 20 3739 120021118G2701102933D5ZM2452 SPACER BEECH 36 A36TC 1151603CE CONTROL COLUMN MISSING D K NONE W INADEQUATE Q C ININSP/MAINT 1 WP0966885 EA48 THESE BUSHINGS ARE LOCATED BETWEEN THE CONTROL COLUMN TORQUE KNEES, LOCATED BEHIND THE INSTRUMENT PANEL. THE SPACERS WERE FOUND MISSING WHILE INVESTIGATING EXCESSIVE PLAY IN THE TORQUE KNEES. 1L71 3O 3A15 20020313001222002031300122CE 2002 3 13 441M 120020313G2822 WIRE HARNESS CESSNA441 441 2076020CE BOOST PUMP CHAFED B K NONE O OTHER ININSP/MAINT 1 CE03441M 6735 4410032 FOUND CHAFED WIRE THAT HAD BEEN ARCING ON THE BOX THAT SURROUNDS THE BOOST PUMPS TO KEEP THE FUEL IN THE FUEL HOPPER. ABOUT SIX INCHES FROM WHERE THE BOOST PUMP, CONNECTOR PLUG ENTERS THE INBOARD RIB OF THE WET WING AREA, A WIRE (THE RED WIRE) HAD BEEN CHAFING ON THE BOX AND CHAFED THROUGH THE INSULATION. A PIN HOLE WAS CREATED IN THE CAN FROM THE ELECTRICAL ARCING. 1L72 3T RTA28CE 20020327001512002032700151CE 2002 3 27 441M032002 120020320G2897 WIRE CESSNA441 441 2076020CE BOOST PUMP CHAFED B K NONE O OTHER ININSP/MAINT 1 CE03441M 6735 4410032 WIRING FOR FUEL BOOST PUMPS IN EACH WING WERE CHAFED THROUGH TO CONDUCTOR. WIRING HARNESS HAS TWO CONNECTOR PLUGS, ONE TO EACH BOOST PUMP. CONNECTOR PLUGS ARE WIRED TO A THIRD, LARGER PLUG THAT CONNECTS TO BULKHEAD PLUG THAT FEEDS THROUGH INBOARD MOST RIB IN WET WING AREA. BOOST PUMPS ARE MOUNTED TO PLATE AND SURROUNDED BY METAL BOX SHAPED CAN WHICH WHEN INSTALLED, GETS INSERTED THROUGH HORIZONTAL PANEL WITH NEOPRENE SEALS, TO CREATE THE FUEL HOPPER. BOX LIKE ENCLOSURE FOR BOOST PUMPS IS VERY CLOSE TO WHERE THE WIRES EXIT LARGER OF THREE CONNECTOR PLUGS, SO WIRES ARE PUSHING FIRMLY AGAINST THE BOOST PUMP BOX LIKE COVER AND ARE CHAFING ON IT. FOUND AT LEAST ONE WIRE IN EACH WING THAT WAS CHAFED THROUGH. 1L72 3T RTA28CE 20020425000972002042500097SW 2002 4 25 474 120020424G57115146 SPAR BBAVIA7 7EC 2110120SW CONT C90 C9012F 17009SO MCAULY1A90 1A90* GL RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 WP034351C5500 500 7EC370 46334812 53617 C/W AD 00-25-02R1 FOUND CRACK AT BUTT OF MAIN SPAR JUST UNDER ATTACH FITTING TO FUSELAGE ON R/H WING TRAVELING SEVERAL INCHES LONGITUDINALLY AND PARALLEL- SEVERAL RIB NAILS LOOSE ON BOTH WINGS- AIRCRAFT HANGARED FOR SEVERAL YEARS (20)VERY LOW USEAGE- CAUSE UNKOWN- REPAIR OF WINGS REQUIRED. 1H71 3O3 O A759 E252 5 NP842 20020402000262002040200026SO 2002 4 2 5124 120020401G552283515002 PLATE PIPER PA46 PA46350P 7104602SO RT ELEVATOR SHEARED B K NONE O OTHER ININSP/MAINT 1 GL17775RD990 4622174 ELEVATOR CONTROL PLATE ASSEMBLY HAD 4 OUT OF 7 AN4 RIVETS SHEARED. NO PREVIOUS DAMAGE HISTORY WAS NOTED IN THE LOGBOOK. 1L71 3O RTA25SO 20020904000712002090400071EU 2002 9 4 5211 120020826G3233 SETSCREW AMD FALC20FALCON200 2730150EU MLG STRUT LOOSE B GQRRK NONE O OTHER ININSP/MAINT 1 SW05VH-EC 493 A SMALL SET SCREW BACKED OUT OF THE THREADED RING CAUSING THE THREADED RING TO BACK OFF AND LEAVE A SPACE BETWEEN THE THREADED RING AND THE PISTON. THIS CONDITION CAN BE NOTED WITH THE AIRCRAFT ON JACKS AND PULLING BACK AND FORTH ON THE COMBO STRUT. A SLUNKING SOUND WILL BE HEARD AND FELT IF A LOOSE CONDITION IS PRESENT. THE SET SCREW HAD NOT BEEN INSTALLED PROPERLY NOR STACKED ENOUGH TO PREVENT BACKING OUT. IF THE THREADED RING CONTINUES TO BACK OFF OR UNSCREW FROM THE PISTON THE LANDIN GEAR COULD COLLAPSE. 2L72 4F RTA7EU 20020506001502002050600150CE 2002 5 6 53550 120020305G3210 STIFFENER CESSNA650 650 2076802CE NLG CRACKED D K NONE O OTHER ININSP/MAINT 1 EA23397CW 6500107 LT AND RT OUTBOARD NOSE GEAR TRUNNION SUPPORT STIFFENERS ARE CRACKED 4 INCHES AFT OF FS 94.0 REPAIRED BY REPLACING DOUBLERS 6213011-139 AND 6213011-140. POSSIBLY CAUSED BY INCORRECT TOWING PROCEDURES. 2L72 4F A9NM 20030106000312003010600031SO 2003 1 6 56724 120021219G5740ASC426 FITTING GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY50614 54519EU WING MISMANUFACTURED B K NONE W INADEQUATE Q C ININSP/MAINT 1 GL25200AB 71 WHILE PERFORMING AND NDT INSPECTION IT WAS BROUGHT TO OUR ATTENTION THAT THERE APPEARED TO BE MORE THAN NORMAL SPACING BETWEEN THE WING CLOTHESPIN FITTING AND THE DOUBLER PLATE THAT WERE MODIFIED IAW ASC. UPON INSPECTION WE DETERMINED THAT THERE WAS A GAP BETWEEN THE PARTS THAT SHOULD NOT BE THERE. WE HAVE CONTACTED THE MANUFACTURER AND HAVE RECEIVED AN ENGINEERING ORDER ADVISING THAT THE INSTALLATION OF THE ASC 426 WAS IN FACT, NOT DONE CORRECTLY. WE ARE IN THE PROCESS OF DISASSEMBLING THE AREA IAW THE MANUFACTURERS INSTRUCTIONS FOR THE PURPOSE OF REQUESTED NDT TESTING AND INSPECTION AND INTEND TO CORRECT THE DEFECTS AS ADVISED BY THE AIRCRAFT MANUFACTURER. 2L72 4F4 FRTA12EA E2EU 20020506001132002050600113CE 2002 5 6 609170 120020501G7910M832481117 O-RING CESSNA650 650 2076802CE GARRTTTFE731TFE731* 01518WP OIL CAP SPLIT B E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 SO15717JH 0138 87397 LEFT ENGINE WAS SHUTDOWN IN FLIGHT AFTER LOW OIL PRESSURE ANNUNCIATION ILLUMINATED. FOUND O-RING ON OIL FILLER CAP SPLIT. 2L72 4F4 F A9NM E6WE 20021120000892002112000089WP 2002 11 20 778 220021117G73207221493 CONTROL CABLE LKHEED1329 132925 5263125SO ALIDSGTFE731TFE7313AR WP FUEL CONTROL BROKEN C O OTHER P NO WARNING INDICATION DEDESCENT 1 WP0795BD 7963 7963 5208 78121 NR 1 ENGINE TELEFLEX CABLE BROKE INSIDE ITS HOUSING MAKING IT IMPOSSIBLE FOR THE PILOTS TO HAVE CONTROL OF THE ENGINE AS FAR AS MAKING CHANGES TO THE SPEED AND FOR SHUTTING THE ENGINE DOWN IN THE NORMAL MANNER. THE PILOTS SHUT THE ENGINE DOWN USING THE FIREWALL SHUTOFF AND LANDED WITHOUT INCIDENT. 2L74 4F4 F 2A1SO E6WE 20020911000912002091100091CE 2002 9 11 A152 120020909G2897 WIRE BEECH 90 E90 1152914CE FUEL PANEL CORRODED B K NONE L NO TEST ININSP/MAINT 1 SW155462G LW69 DURING INSPECTION OF FUEL PANEL DIODES: FOUND FUEL PANEL DIODES AND WIRING CONNECTION CORRODED: CLEANED , TREATED AND REINSTALLED PANEL. 1L72 3T 3A20 20020123000472002012300047SW 2002 1 23 AC2A077546 120020107G6410206310105101 BEARING 206016201131BELL 206 206B3 1181506SW T/R BLADES WORN H AC2AK NONE O OTHER ININSP/MAINT 1 FS0171319788 CS7008 4112 TAIL ROTOR BLADE BEARINGS WERE WORN BEYOND LIMIT. REPLACED WITH NEW BEARINGS. 1G71 3U H2SW 20020123000482002012300048SW 2002 1 23 AC2A077548 120020107G6410206010733003 SLEEVE 206016201131BELL 206 206B3 1181506SW TAIL ROTOR BLADEWORN H AC2AK NONE O OTHER ININSP/MAINT 1 FS0171319788 CS7008 4112 SLEEVES WERE WORN IN TAIL ROTOR ASSY. REPLACED WITH NEW SLEEVES. 1G71 3U H2SW 20021011001302002101100130 2002 10 11 AC2A081089 420020401G3140430375002107 DISPLAY BELL 430 430 1182150SW COCKPIT FAILED H AC2AK NONE O OTHER ININSP/MAINT 1 FS01430CH46 49037 EHSI SCREEN FAILED TO ILLUMINATE REPLACED WITH SERVICEABLE EFIS TUBE. 1G72 3U RTH9SW 20021011001352002101100135NE 2002 10 11 AC2A081090 220020401G7320430360055101 SOLENOID BELL 430 430 1182150SW ALLSN 250C 250C40B 03032NE NR 1 ENGINE DEFECTIVE H AC2AK NONE O OTHER ININSP/MAINT 1 FS01430CM26 49090 SOLENOID IS DEFECTIVE. SNAP RING ON SHAFT UNDER THE SPRING DOES NOT STAY IN GROOVE. REPLACED SOLENOID. 1G72 3U3 URTH9SW E1GL 20021011001372002101100137SW 2002 10 11 AC2A081107 120021001G3211601025015 CLAMP BELL 206 206L3 1182108SW MLG BROKEN H AC2AK NONE O OTHER ININSP/MAINT 1 FS017159J 51408 DURING RETORQUE OF LANDING GEAR SADDLE CLAMP, THE "T" BOLT BROKE IN TWO. UPON EXAMINATION IT WAS EVIDENT THAT THE CLAMP WAS CRACKED PRIOR TO BREAKING. REPLACED CLAMP WITH NEW PART. 1G71 3U H2SW 20021023000682002102300068NE 2002 10 23 AC2A081172 220021013G726123063372 SEAL SKRSKYS76 S76A 8143006NE TMECA ARRIELARRIEL1D NE ENGINE LEAKING H AC2AK NONE K FLUID LOSS ININSP/MAINT 1 FS015447C 760180 ENGINE STARTED LEAKING OIL AFTER OIL FLOW CHECK. REPLACED SEAL 1G72 3U3 U H1NE E19EU 20021211000392002121100039SW 2002 12 11 AC2A081580 120021130G3340729144501283 CONTROLLER BELL 430 430 1182150SW SEARCH LIGHT FAILED H AC2AK NONE L NO TEST ININSP/MAINT 1 FS01430CV211 49072 SEARCH LIGHT WILL NOT STOW. REPLACED WITH SERVICEABLE SEARCH LIGHT ASSEMBLY. 1G72 3U RTH9SW 20030103000032003010300003SW 2003 1 3 AC2A082140 120021210G3350214175140101 POWER SUPPLY BELL 430 430 1182150SW CABIN MALFUNCTIONED H AC2AK NONE L NO TEST ININSP/MAINT 1 FS01430CT866 49089 POWER SUPPLY WILL NOT CHARGE BATTERIES. REPLACED POWER SUPPLY. 1G72 3U RTH9SW 20020621000132002062100013EA 2002 6 21 AG2R04230201 220020423G8520SL738190 BUSHING LYC O720 IO720D1C 41546EA COUNTER WEIGHT FAILED B AG2RK NONE O OTHER ININSP/MAINT 1 SW17 250 COUNTER WEIGHT BUSHINGS (PN LS73810) HAVE FAILED AT 2 TO 250 HOURS. IT APPEARS THAT THE MATERIAL MAY BE TOO SOFT. BUSHINGS WERE REMOVED BY OPERATOR AND SENT BACK FOR EVALUATION. 3 O 1E15 20020625000042002062500004GL 2002 6 25 ALGA079296 220020528G72106895007 BEARING 23063393 BELL 407 407 1182206SW ALLSN 250C 250C47B GL GEARBOX GALLED H ALGAK NONE O OTHER ININSP/MAINT 1 FS01577AL683 CAG47062 53247 T/M JOURNAL AND INNER RACE FOUND EXCESSIVE GALLING, CAUSING METAL CONTAMINATION. 1G71 3U3 UO H2SW E1GL 20020722001662002072200166SW 2002 7 22 ALGA080392 120020718G2840206063656001 TRANSMITTER BELL 206 206L1 1182107SW FUEL INDICATOR DEFECTIVE H ALGAK NONE O OTHER ININSP/MAINT 1 FS013185P 45775 FUEL GAUGE FLUCTUATING DUE TO TRANSMITTER BEING DEFECTIVE. 1G71 3U H2SW 20021217000212002121700021GL 2002 12 17 ALGA081610 220021210G725023066744 WHEEL CLARK 1000 1000CLARK 2230102SW ALLSN 250C 250C30 03013GL TURBINE SECTION MISMANUFACTURED H ALGAK NONE W INADEQUATE Q C ININSP/MAINT 1 FS01PARTO THIS IS A NEW PART. PART CAN NOT BE DYNAMIC BALANCED, DUE TO BEING TOO HIGH OUT OF BALANCE AND OFF SCALE ON THE X10 SCALE AND ON UPPER SCALE. 1Q71 3R3 U 2A6 E1GL 20021217000262002121700026SW 2002 12 17 ALGA081621 120021211G6230204010904001 SLEEVE 412010402109BELL 412 412 1182202SW SWASHPLATE WORN H ALGAK NONE O OTHER ININSP/MAINT 1 FS01XAAAR1753 RE741 36255 SLEEVE BORE INNER DIAMETER MEASURES 0.011 INCH OVER MAXIMUM ALLOWED WITH ONLY 1753.2 HRS. (ORIGINAL EQUIPMENT) THIS PART HAS A 9000 HR. RETIREMENT LIFE. 1G72 4U H4SW 20021217000292002121700029SW 2002 12 17 ALGA081624 120021211G6300406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN H ALGAK NONE O OTHER ININSP/MAINT 1 FS01409AL1175 53494 FOUND BEARINGS WORN. BEARING HAS A 5000 HR. RETIREMENT LIFE. 1G71 3U O H2SW 20021217000342002121700034SW 2002 12 17 ALGA081630 120021211G6320407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER WORN H ALGAK NONE O OTHER ININSP/MAINT 1 FS01577AL825 53247 COOLER BLOWER BEARING IS ROUGH IN ROTATION. 1G71 3U O H2SW 20020205001922002020500192CE 2002 2 5 AUS20020002 120020102G571105230142 SPAR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD SPAR ASSEMBLY CONTAINED SEVERE EXFOLIATION CORROSIONBETWEEN THE SPAR PNO 0523014-2 AND THE ATTACHMENT PLATE PNO 0523016-1. THE THICKNESS OF THE ASSEMBLY WAS REDUCED BY APPROXIMATELY 50% DUE TO THE CORROSION. THE RIVETS HOLDING THEASSEMBLY TOGETHER WERE ALSO CORRODED (18OF22). CORROSION WAS ALSO FOUND AT RIB TO SKIN INTERFACES. INVESTIGATION OF OTHER SIMILAR WINGS HELD IN STORAGE FOUND THEM TO BE IN A SIMILAR CONDITION. 1H71 3O3 ONT3A12 E274 5 NP910 20020206000602002020600060CE 2002 2 6 AUS20020003 120020102G5220 DOOR CESSNA310 310L 2074230CE CONT O470 IO470U 17026SO MCAULY2AF34CD2AF34C81 GL EMERGENCY EXIT MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EMERGENCY EXIT INCORRECTLY INSTALLED. ONLY TWO OF THREE LATCHING PINS ENGAGED. EMERGENCY RELEASE CABLE LOOPED AND THE TWO LATCHING PINS WERE FITTED BACKWARDS. IT WOULD HAVE BEEN IMPOSSIBLE FOR THE EMERGENCY EXIT TO BE RELEASED. 1L72 3O3 O 3A10 3E1 5 CP5EA 20020205001962002020500196EA 2002 2 5 AUS20020008 220020103G8520AS13884M03 BEARING LYC IO540E1B5 GULSTM500 500U 0141108SW LYC O540 IO540E1B5 41532EA HARTZLHCA3X HCA3XK2 GL RECIPROCATING ENDELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE NO1 MAIN BEARING DELAMINATED. METAL CONTAMINATION OF OIL FILTERS. 1H72 3O3 O 6A1 1E4 5 CP913 20020206000842002020600084SO 2002 2 6 AUS20020012 120020102G55109735500 BOLT PIPER LIFTSTRUT PIPER PA36 PA36285 7103610SO PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAILPLANE LIFT STRUT CLEVIS BOLT CRACKED IN AREA OF FIRST THREAD ON THE HEAD END OF THE BOLT. 1L71 3O3 T A10SO E4EA 6 CP15EA 20020206000862002020600086SO 2002 2 6 AUS20020015 220020109G741410349367 IMPULSE COUPLINGBENDIX 10349505 CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 AUS L039021F (AUS) MAGNETO IMPULSE COUPLING FLYWEIGHTS WORN BEYOND LIMITS. 1H71 3O3 ONT3A13 E273 20020205001982002020500198GL 2002 2 5 AUS20020017 320020107G61101949 PROPELLER HARTZL HCE2YK2RB PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL PROPELLER ASSEMBFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 267 1949 (AUS) PROPELLER BLADE CLAMP BOLTS NOT IN SAFETY. NO SPACERS BETWEEN SPINNER BACKPLATE AND PROPELLER HUB. PROPELLER BLADES CONTACTINGBACKPLATE WHEN BLADE IS IN THE FEATHER POSITION.PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 1A10 1E4 5 CP9EA 20020206000962002020600096EA 2002 2 6 AUS20020018 220020107G8530LW12425 CYLINDER PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL ENGINE FAULTY W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT ENGINE NR 2 CYLINDER OUT OF ROUND. NR 5 CYLINDER BORE STEPPED AND BLUE MARKING ON FINS. NR 1 CYLINDER IS MARKED AS NITRIDED BUT IS ACTUALLY A CHROMED CYLINDER. RT ENGINE NR 4 CYLINDER NOT ENTERED ON RELEASE NOTE. NR 2 CYLINDER IS NOT MARKED ORANGE FOR CHROMED. CYLINDER SN A3104 DOES NOT EXIST IN THE PAPERWORK. 1L72 3O3 O 1A10 1E4 5 CP9EA 20020214000042002021400004NE 2002 2 14 AUS20020019 220020111G731030J228501 LINE CESSNA500 550 2076604CE PWA 530 PW530A NE FUEL SYS RUPTURED W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) ENGINE HEAT EXCHANGER FUEL TUBE LEAKING. FUEL SPRAYING INSIDE COWLS AND ENTERING ENGINE THROUGH INTAKE. 1L72 4F4 F A22CE E00053EN 20020205001992002020500199NE 2002 2 5 AUS20020020 120020107G2560 FLOAT SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE EMERGENCY EQUIPMFAULTY W K NONE O OTHER DEDESCENT 1 AUS (AUS) AIRCRAFT SUFFERED AN UNCOMMANDED INFLATION OF THE REAR CELLS OF THE NOSE FLOATATION BAGS. THE FLOAT SYSTEM WAS NOT ARMED AT THE TIME. 1G72 3U3 UNCH1NE E19EU 20020205002002002020500200NE 2002 2 5 AUS20020022 220020111G73203031829 PIPE PWA PT6A65AG AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A65AG 52043NE HARTZLHCB5M HCB5MP3 GL FUEL CONTROLLINGCRACKED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS PCE32620 (AUS) P3 PIPE TO FUEL CONTROL UNIT CRACKED. 1L71 3T4 TNCA19SW E4EA 6 CP44GL 20020205002012002020500201EU 2002 2 5 AUS20020023 120020107G5743 FITTING MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU WING, LANDING GECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 990 (AUS) LH AND RH FORWARD LANDING GEAR ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPECTION IAW AD/CAP10/3. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020206000992002020600099SO 2002 2 6 AUS20020024 220020107G7310630626 BALANCE TUBE CESSNA182 182K 2072724CE CONT O470 O470R 17026SO FUEL DIST FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 AUS 940 (AUS) ENGINE BALANCE TUBE FRACTURED AT WELD JOINT. NR 3 CYLINDER INOPERATIVE AND PROPELLER BLADE LOOSE. 1H71 3O3 ONT3A13 E273 20020205002022002020500202SO 2002 2 5 AUS20020025 220020103G74141051675 CONDENSER BENDIX S6RN25 CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL MAGNETO/DISTRIBUFAULTY W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) MAGNETO CONDENSER FAULTY. A TOTAL OF FIVE CONDENSERS FAILED INAPPROXIMATELY 500 HOURS OF OPERATION. INVESTIGATION FOUND THATTHE FAILURE OCCURRED IN THE SMALL ATTACHMENT BRACKET HOLDING THECONDENSER IN THE POINTS CAVITY. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020206001002002020600100CE 2002 2 6 AUS20020026 120020110G2430 LIMITER CESSNA441 441 2076020CE ELECTRICAL FAILED W O OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 AUS (AUS) DURING ENGINE EMERGENCY SHUTDOWN THE NR 2 ELECTRICAL SYSTEM BUS LIMITERS (225A) FAILED. 1L72 3T RTA28CE 20020206001012002020600101CE 2002 2 6 AUS20020027 120020110G7920124F0018CR0194 HOSE CESSNA441 441 2076020CE GARRTTTPE331TPE3318 01514WP HARTZLHCB3T HCB3TN5 GL RT ENGINE OIL RESTRICTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT ENGINE OIL COOLER SCAVENGE HOSE INTERNALLY RESTRICTED. SUSPECT HOSE COULD HAVE BEEN KINKED DURING ENGINE INSTALLATION. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20020206001022002020600102CE 2002 2 6 AUS20020028 120020114G52809981003034 DOOR BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE MLG SEPARATED W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 AUS (AUS) RT MAIN LANDING GEAR DOOR SEPARATED FROM AIRCRAFT DUE TO FAILURE OF THE HINGE PIN. 1L72 4T4 T A24CE E4EA 20020206001222002020600122SO 2002 2 6 AUS20020033 120020116G534197101301 FITTING PIPER PA36 PA36375 7103620SO LYC O720 IO720D1C 41546EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT FRONT SPAR ATTACHMENT FITTING ON FUSELAGE LOCATED AT RT STN 124.250 CRACKED IN REAR LAMINATE. CRACK LENGTH 10MM (0.39IN). 1L71 3O3 O A10SO 1E15 20020306000072002030600007SO 2002 3 6 AUS20020037 220020117G8500810533R BEARING CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL ENGINE MAKING METAL W K NONE O OTHER ININSP/MAINT 1 AUS 449 (AUS) ENGINE MAKING METAL. SUSPECT DEFECTIVE BEARINGS. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020304001262002030400126EU 2002 3 4 AUS20020041 120020118G21502676C010 DUCT BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE CABIN COOLING SYCRACKED W K NONE J WARNING INDICATION TOTAKEOFF 1 AUS (AUS) NO2 AIR CYCLE MACHINE INLET PIPE CRACKED. 2H74 4F4 F A49EU E6NE 20020304001272002030400127EU 2002 3 4 AUS20020044 120020121G8000S1991A1 RELAY LYC AEIO360B2F MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU ENGINE STARTING FAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS (AUS) STARTER RELAY FAULTY. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020304001282002030400128SO 2002 3 4 AUS20020046 120020118G27316270142 CABLE PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK1 GL ELEVATOR TAB CONFAILED W K NONE F FLT CONT AFFECTED CLCLIMB 1 AUS (AUS) STABILATOR TRIM CABLE SEPARATED AT ELECTRIC TRIM SERVO ACTUATOR. 1L71 3O3 O A3SO 1E4 5 CP920 20020306000312002030600031SO 2002 3 6 AUS20020047 120020122G3260 BRACKET PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL MLG OUT OF ADJUST W O OTHER N FALSE WARNING DEDESCENT 1 AUS (AUS) RT MAIN LANDING GEAR MICROSWITCH MOUNT BRACKET MOVED. MICROSWITCH OUT OF ADJUSTMENT. BRACKET HAD BEEN REMOVED DURING DRAG BRACE REPLACEMENT. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001292002030400129SO 2002 3 4 AUS20020048 220020116G8520 CONNECTING ROD CONT TSIO520E CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C87 GL RECIPROCATING ENFAILED W K NONE EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS (AUS) RH ENGINE INTERNAL FAILURE. INSPECTION FOUND HOLES IN THE FORWARD END OF THE CRANKCASE IN THE AREA OF NO5 AND NO6 CYLINDERS. ON DISASSEMBLY MASSIVE INTERNAL DAMAGE FOUND. CONNECTING ROD FOUND IN SUMP. CAMSHAFT BROKEN. SUSPECT CONNECTING ROD OR CONNECTINGROD BOLT FAILURE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020304001302002030400130CE 2002 3 4 AUS20020049 120020118G3233JRA4582 ACTUATOR CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULY3A32C D3A32C88 GL LANDING GEAR ACTFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS BATCH2 (AUS) MAIN LANDING GEAR ACTUATOR HAS NO PROVISION FOR SEPARATION WASHER AND FELT. 1H71 3O3 O 3A21 E5CE 5 CP21EA 20020304001312002030400131NM 2002 3 4 AUS20020050 120020123G2824BACC63CE14S5S PLUG BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUEL TRANSFER VAFAULTY W K NONE J WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) FUEL CROSSFEED VALVE CONNECTOR PLUG AND WIRING FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001322002030400132CE 2002 3 4 AUS20020051 120020122G2430S19432 CABLE CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL DC GENERATING SYWORN W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 AUS (AUS) ALTERNATOR OUTPUT CABLE ARCING ON ALTERNATOR GROUND CABLE. CABLEHAD BEEN REMANUFACTURED FROM MIL-W-22759/16-4 MATERIAL. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020306000332002030600033WP 2002 3 6 AUS20020052 220020116G73218977801A FUEL CONTROL SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE ENGINE FAULTY W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 AUS 3673 (AUS) FUEL CONTROL UNIT FAULTY. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020306000362002030600036NE 2002 3 6 AUS20020054 220020126G720012680 ENGINE BOEING747 747338 NM RROYCERB211 RB211524G19 NE NR 2 VIBRATES W EA ENGINE SHUTDOWN UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS 7039 (AUS) NR 2 ENGINE VIBRATION EXCESSIVE. 2L72 4F4 FRTA20WE E30NE 20020306000452002030600045NM 2002 3 6 AUS20020059 120020119G24349110813 BEARING ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA DC ALTERNATOR LACK OF LUBE W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 AUS 340 (AUS) ALTERNATOR BEARING SEIZED. SUSPECT CAUSED BY LACK OF LUBRICATION. 1G71 3O3 O H10WE E274 20020304001332002030400133EU 2002 3 4 AUS20020060 120020125G6320350A32106321 GASKET AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL MAIN ROTOR GEARBFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN ROTOR TRANSMISSION EPICYCLIC RING GEAR GASKET FAULTY. GASKET WAS EXTRUDING FROM BETWEEN THE UPPER AND LOWER CASES AND BREAKING INTO PIECES AND CAUSING AN OIL LEAK WHICH WAS PROGRESSIVELY WORSENING. ON DISASSEMBLY THE MATING CASE FLANGES SHOWEDSIGNS OF FRETTING. 1G72 3U3 U H11EU E4CE 20020304001342002030400134CE 2002 3 4 AUS20020061 120020121G323399101363 ACTUATOR CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL LANDING GEAR ACTFAULTY W K NONE O OTHER LDLANDING 1 AUS (AUS) RH MAIN LANDING GEAR RETRACTION RAM INTERNAL FAULT CAUSING RAM TO BE UNLOCKED. RH MLG COLLAPSED ON LANDING. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020306000472002030600047CE 2002 3 6 AUS20020062 120020109G5511123262224 SPAR CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HORIZONTAL STABILISER MAIN SPAR CRACKED. CRACKS WENT THROUGH SPAR, SPLICE AND CHANNEL. CRACKS RADIATED FROM THE TOP AND BOTTOM OF THE CENTRAL LIGHTENING HOLE. REAR ATTACHMENT FITTING ALSO CRACKED AT THE TAILPLANE TO FUSELAGE ATTACHMENT POINT. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020306000692002030600069NM 2002 3 6 AUS20020064 120020129G2781189929 SENSOR BOEING737 737400 138449ANM CFMINTCFM56 CFM563C 13802EU SLATS FAULTY W D RETURN TO BLOCK N FALSE WARNING TXTAXI/GRND HDL 1 AUS (AUS) NR 2 LEADING EDGE FLAP EXTEND SENSOR FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001352002030400135NM 2002 3 4 AUS20020065 120020117G5270A42006992302 SOLENOID BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU DOOR WARNING SYSFAULTY W K NONE N FALSE WARNING TOTAKEOFF 1 AUS (AUS) RH OVERWING EXIT FLIGHT LOCK RELAY AND SOLENOID FAULTY. 2L72 4F4 FRTA16WE E21EU 20020306000712002030600071NM 2002 3 6 AUS20020066 120020128G4920737M49503011 APU BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU APU BAY LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) APU LEAKING FUEL FROM DRAIN MAST. 2L72 4F4 FRTA16WE E21EU 20020306000752002030600075SW 2002 3 6 AUS20020070 120020124G324376C76612501 ROD END 76C76612501 SWRNGNSA227 SA227* SW MCAULY4HFR344HFR34C652 NE MASTER CYLINDER SHEARED W O OTHER O OTHER LDLANDING 1 AUS 14749 RH0112 (AUS) PILOTS LT BRAKE MASTER CYLINDER ROD END SHEARED. 2L72 4T RTA5SW 6 C3PNE 20020306000762002030600076CE 2002 3 6 AUS20020071 120020131G5711 SPAR CAP CESSNA441 441 2076020CE HARTZLHCB3T HCB3TN5 GL WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7560 (AUS) WING SPAR CAP CONTAINED EXFOLIATION CORROSION. 1L72 3T RTA28CE 6 CP15EA 20020304001362002030400136 2002 3 4 AUS20020075 420020115G2564733M2537011 LIFE RAFT BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU LIFERAFT FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 11208487 (AUS) LIFERAFT FAULTY. LH BOTTLE PRESSURE READING ZERO. 2L72 4F4 FRTA16WE E21EU 20020307000022002030700002CE 2002 3 7 AUS20020076 120020116G2842 SENSOR BEECH 76 76 1153005CE LYC O360 IO360A1G6 41514EA FUEL QUANTITY STUCK W O OTHER ERNVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FALSE WARNING CLCLIMB 1 AUS (AUS) RT FUEL SENSOR JAMMED IN HALF FULL POSITION. ERRONEOUS FUEL INDICATIONS ALLOWED RT FUEL TANK TO BE LOW ON FUEL RESULTING IN RT ENGINE POWER LOSS. 1L72 3O3 O A29CE 1E10 20020304001372002030400137NM 2002 3 4 AUS20020079 120020204G215065771 COOLING FAN BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU CABIN COOLING SYFAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 AUS 10430 (AUS) NORMAL EXHAUST FAN FAILED. 2L72 4F4 FRTA16WE E21EU 20020307000062002030700006NE 2002 3 7 AUS20020081 220020125G8500R183092 ENGINE DOUG DC3 DC3CS1C3G 3021458WP PWA R1830 R183092 52020NE HAMSTD23E 23E50 NE LEFT MAKING METAL W O OTHER EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS 974 (AUS) LT ENGINE OIL FILTER CONTAMINATED WITH METAL. 2L72 4R4 R A669 5E4 6 CP603 20020307000072002030700007GL 2002 3 7 AUS20020083 320020201G6111BU9606 BLADE BEECH 200 B200C 1152924CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 2932 (AUS) LT PROPELLER NR 2 BLADE CRACKED. CRACK LENGTH APPROXIMATELY 40MM (1.57IN) RUNNING CHORDWISE ACROSS THE BLADE FROM THE TRAILING EDGE. CRACK IS LOCATED APPROXIMATELY 150MM (5.9IN) FROM THE BLADE TIP. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020304001382002030400138CE 2002 3 4 AUS20020084 120020125G2460S123230 CIRCUIT BREAKER CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL DC POWER DISTRIBFAILED W K NONE H ELECT. POWER LOSS-50 PC DEDESCENT 1 AUS (AUS) CIRCUIT BREAKER FAILED. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020307000082002030700008CE 2002 3 7 AUS20020085 120020204G5751512400021 BALANCE WEIGHT CESSNA402 402C 207590RCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C93 GL AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH AILERON INTERNAL BALANCE WEIGHT LOOSE. INVESTIGATION FOUND THE MIDDLE SECTION OF THE BALANCE WEIGHT WAS BROKEN OFF. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020304001392002030400139SO 2002 3 4 AUS20020086 220020130G741436066AA GEAR BENDIX 105005147 EAGLE XTS EAGLEXTS150 05607BZGL CONT O240 IO240A SO MCAULY1A135 1A135BRM GL MAGNETO/DISTRIBUWORN W K NONE O OTHER ININSP/MAINT 1 AUS 498 LHE3194060RH (AUS) LH AND RH MAGNETO GEARS WORN. 1H71 3I3 ONCA00005LAE7SO 5 NP842 20020307000092002030700009GL 2002 3 7 AUS20020087 320020121G611190A8 BLADE CESSNA182 182B 2072706CE CONT O470 O470* 17026SO MCAULY2A34C 2A34C50 GL PROPELLER MISREPAIRED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) INSPECTION OF PROPELLER WHEN RECEIVED FOR REPAIR FOUND THAT THE BLADE THREADS HAD BEEN TRUNCATED TO COMPLY WITH AD/PMC/24/3 BUT HAD NOT BEEN SHOT PEENED. THE RETENTION NUTS DID NOT HAVE THE O-RING GROOVE WIDENED AS LISTED IN SL 1990-2. AD/PMC/41HAD NOT BEEN INCORPORATED AT THE LAST OVERHAUL. THE SERIAL NUMBER OF ONEBLADE WAS INCORRECT IN THE LOGBOOK. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020307000102002030700010EA 2002 3 7 AUS20020088 220020125G7414AO9815 SCREW GIPPLDGA200 GA200 EU LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YR1 GL MAGNETO LOOSE W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS (AUS) LT MAGNETO SEPARATED FROM ENGINE. INVESTIGATION FOUND THAT THE MAGNETO BASE FLANGE RETAINING SCREWS (3OFF) FELL OUT AND WERE FOUND INSIDE THE ENGINE. SUSPECT CAUSED BY LACK OF TORQUE ON THESCREWS. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 ONCA00001LA1E4 5 CP920 20020304001402002030400140CE 2002 3 4 AUS20020090 120020206G28200800400261 PIPE CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL AIRCRAFT FUEL DICORRODED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) RH INBOARD FUEL TRANSFER PIPE CORRODED AND LEAKING. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20020307000592002030700059CE 2002 3 7 AUS20020091 120020203G5313 STRINGER BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STRINGER NR 9 LT LOCATED BEHIND FRONT PRESSURE BULKHEAD CRACKED AT THE END OF THE ATTACHMENT GUSSETT. 1L72 4T4 T A24CE E4EA 20020307000642002030700064CE 2002 3 7 AUS20020095 120020208G6120 CABLE BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF34C3AF34C502 GL PROP CONTROL WRONG PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT PROPELLER CONTROL CABLE DIAMETER WAS FOUND TO BE LESS THAN THE DIAMETER OF THE RH SIDE CABLE. LT CABLE WAS4.762MM (0.1875IN) INDIAMETER AND THE RT CABLE WAS 6.350MM (0.25IN). UNAPPROVED PART. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20020304001412002030400141EU 2002 3 4 AUS20020096 120020209G3230HP848430621 VALVE SAAB SF340 SF340A 7850100EU GE CT7TP CT75A 30030NE ROTOL R354 R3544123F13 NE LANDING GEAR RETFAULTY W K NONE O OTHER LDLANDING 1 AUS 18217 (AUS) LANDING GEAR CONTROL VALVE FAULTY. INVESTIGATION FOUND THAT THE DOWN SOLENOID HAD A RESISTANCE PROBLEM. 2L72 4T4 TRTA52EU E8NE 6 CP61GL 20020307000682002030700068NE 2002 3 7 AUS20020098 220020122G7420311983301 IGNITION LEAD BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE IGNITION SYSTEM MISMANUFACTURED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE IGNITER LEADS CAUSING IGNITER PIN EROSION. LEADS ARE A NEW ITEM WITH SHORTER INSULATORS. 1L72 4T4 T A24CE E4EA 20020304001422002030400142EU 2002 3 4 AUS20020100 220020131G73218063215 MEC GE CFM563C1 BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU FUEL CONTROL/TURFAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 857543 (AUS) NO2 ENGINE MAIN ENGINE CONTROL (MEC) FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001432002030400143NM 2002 3 4 AUS20020104 120020212G3230A42000028305 SOLENOID BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU LANDING GEAR RETFAULTY W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) LANDING GEAR LOCK SOLENOID FAULTY. AIR/GROUND SWITCH S106 OUT OFADJUSTMENT. 2L72 4F4 FRTA16WE E21EU 20020307000922002030700092EU 2002 3 7 AUS20020106 120020214G2520MS220441P00501 HOOK AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL CABIN FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) SAFETY HARNESS USED BY CAMERAMAN FAULTY. SNAP HOOK ON HARNESS MAY UNDER SOME CIRCUMSTANCES HAVE THE SPRING LOADED SAFETY CATCH FORCED OPEN ALLOWING THE SNAP HOOK TO SEPARATE FROM THE AIRCRAFT ATTACHMENT POINT. 1G72 3U3 U H11EU E4CE 20020304001442002030400144NM 2002 3 4 AUS20020110 120020105G5101 STRUCTURE BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE AIRCRAFT STRUCTUCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EXFOLIATION CORROSION FOUND AT NO3 CARGO DOOR UPPER FORWARD SIDEAT STN 1090, STRINGER 20R. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20020307000962002030700096CE 2002 3 7 AUS20020111 120020207G716012507043 FILTER CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL AIR INTAKE BURNED W O OTHER EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) ENGINE AIR FILTER BURNT. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020304001452002030400145NM 2002 3 4 AUS20020117 120020218G792128E997 OIL COOLER PWA PW120A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE OIL COOLELEAKING W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 428 REF75980 (AUS) NO2 ENGINE OIL COOLER LEAKING. LOSS OF ENGINE OIL. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020307001022002030700102CE 2002 3 7 AUS20020120 120020211G2823HE7805 SELECTOR SWITCH BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AMTR C8289 C8289 GL FUEL SYSTEM CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 197 (AUS) LT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 NEXPP5N 20020307001032002030700103CE 2002 3 7 AUS20020121 120020211G2823HE7803 SELECTOR SWITCH BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AMTR C8289 C8289 GL FUEL SYSTEM CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 197 (AUS) RT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 NEXPP5N 20020304001462002030400146NM 2002 3 4 AUS20020122 120020218G7712311694201 SENSOR PWA PW120A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE BMEP/TORQFAULTY W KE NONE ENGINE SHUTDOWN E VIBRATION/BUFFET TOTAKEOFF 1 AUS 6362 120683 (AUS) ENGINE TORQUE SENSOR FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020307001042002030700104EU 2002 3 7 AUS20020123 120020211G2434ALV2045BS BRUSH BLOCK BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL DC ALTERNATOR SHORTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ALTERNATOR BRUSHES SHORTING BETWEEN THE SLIP RINGS AND ALTERNATOR SLIP RING END BEARING. 1H72 3O3 O A17EU E295 5 CP920 20020307001052002030700105SO 2002 3 7 AUS20020124 120020220G2140461731 REGULATOR VALVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL HEATING SYSTEM FAULTY W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) RT HEATER FUEL PRESSURE REGULATOR FAULTY. REGULATOR LEAKING FUELFROM DRAIN. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001472002030400147CE 2002 3 4 AUS20020125 120020126G7810 EXHAUST PIPE CONT GTSIO520H CESSNA421 421B 2076014CE CONT O520 GTSIO520H 17032SO MCAULY3AF34C3AF34C92 GL ENGINE COLLECTORLEAKING W K NONE EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 AUS (AUS) RH ENGINE FIRE. ENGINE COMPARTMENT DAMAGED. FIRE WAS EXTINGUISHED USING CABIN FIRE EXTINGUISHER. INVESTIGATION FOUND THE FIRE WAS CAUSED BY MISALIGNMENT OF THE EXHAUST SWIVEL JOINT WHICH ALLOWEDEXHAUST GAS TO LEAK INTO THE ENGINE BAY. A LIST OF DAMAGE IS AS FOLLOWS:- 1.OUTBOARD ENGINE MOUNT BEAM HEAT DAMAGED 2.STARTER HEAT DAMAGED3.OUTBOARD REAR ENGINE MOUNT HEAT AFFECTED4.INTERCOOLER INDUCTION TUBE HEAT DAMAGED 5.VARIOUS FUEL, OIL AND DRAIN HOSES HEAT DAMAGED6.TURBOCHARGER SEIZED 7.TACHO GENERATOR HEAT AFFECTED 8.INTERCOOLER HEAT AFFECTED 9.VACUUM PUMP HEAT AFFECTED 10. OIL PUMP HEAT AFFECTED 1L72 3O3 O A7CE E7CE 5 CP22EA 20020304001482002030400148SO 2002 3 4 AUS20020127 120020215G3232455946 ACTUATOR PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR DOOFAULTY W K NONE OJ OTHER WARNING INDICATION CLCLIMB 1 AUS 3552 (AUS) RH MAIN LANDING GEAR INBOARD DOOR ACTUATOR FAULTY. SUSPECTINTERNAL LOCK FAILURE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001492002030400149SO 2002 3 4 AUS20020128 120020215G3710215CC PUMP AIRBORNE 215CC PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL VACUUM DISTRIBUTINOPERATIVE W K NONE OJ OTHER WARNING INDICATION CRCRUISE 1 AUS 3AU1603 (AUS) LH VACUUM PUMP DRIVE SHEARED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001502002030400150NM 2002 3 4 AUS20020130 120020206G291366087 PUMP BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU HYDRAULIC PUMP, SEIZED W K NONE KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 AUS K0169 (AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP SEIZED AND LEAKING. RH MAINLANDING GEAR RETRACTION ACTUATOR HOSES ALSO LEAKING. 2L72 4F4 FRTA16WE E21EU 20020307001102002030700110CE 2002 3 7 AUS20020132 120020122G3230504501025 TORQUE TUBE CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MLG DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR TORQUE TUBE DAMAGED. SUSPECT DAMAGE ORIGINATED FROM CRACKING AROUND THE FORK BOLT AREA. 1L72 3O3 O 3A10 E5CE 20020304001512002030400151NE 2002 3 4 AUS20020133 320020219G611454547AB SPIDER HAMSTD 22D40505 AIRTRCAT300 AT301 0390103SW PWA R1340 R1340AN1 52016NE HAMSTD22D 22D40 NE PROPELLER HUB SECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 570 82087 (AUS) PROPELLER SPIDER CRACKED. CRACK LENGTH 50.8MM (2IN). 1L71 3R3 R A9SW 5E2 5 CP736 20020304001522002030400152CE 2002 3 4 AUS20020136 120020221G3710215CC PUMP CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL VACUUM DISTRIBUTUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VACUUM PUMP FAILED. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020304001532002030400153CE 2002 3 4 AUS20020137 120020221G3710215CC PUMP CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL VACUUM DISTRIBUTFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VACUUM PUMP FAILED. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020307001132002030700113CE 2002 3 7 AUS20020138 120020212G3230574122214 HOOK CESSNA441 441 2076020CE MLG UPLOCK CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN LANDING GEAR UPLOCK HOOK CRACKED. 1L72 3T RTA28CE 20020307001152002030700115CE 2002 3 7 AUS20020139 120020225G3230MS935302 CLAMP CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL MLG BLOWDOWN UNAPPROVED PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR EMERGENCY BLOWDOWN SYSTEM CONTROL CABLE CLAMP INCORRECT ITEM. THE INCORRECT ITEM WAS A RUBBER CUSHIONED CLAMP WHICH ALLOWED THE CONTROL CABLE TO SLIP AND JAM THE FIRINGSYSTEM. WHEN THE CORRECT CLAMP WAS FITTED THE SYSTEM OPERATED NORMALLY. UNAPPROVED PART. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020304001542002030400154SO 2002 3 4 AUS20020141 120020225G54118617903 WEB PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE NACELLE/PYLON, FCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH ENGINE NACELLE TOP OUTBOARD WEB CRACKED IN AREA OF TOP REARENGINE MOUNT ATTACHMENT POINT. 1L72 3O3 O A19S0 E286 5 CP25EA 20020307001242002030700124EA 2002 3 7 AUS20020142 220020223G8530SL19034 EXHAUST VALVE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE BURNED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS (AUS) EXHAUST VALVE BURNED. VALVE NOT SEATING CORRECTLY. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020304001552002030400155CE 2002 3 4 AUS20020144 120020212G561010138402515 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL FLIGHT COMPARTMECRACKED W K NONE O OTHER CRCRUISE 1 AUS 94055H2855 (AUS) WINDSHIELD CRACKED WHEN HEAT TURNED ON. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020304001562002030400156EA 2002 3 4 AUS20020145 220020225G8520LW18840 CAMSHAFT LYC O360A4M PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA AMTR C8289 C8289 GL RECIPROCATING ENFAILED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) CAMSHAFT LOBE FAILED. METAL CONTAMINATION OF OIL SYSTEM. OILPRESSURE RELIEF VALVE OFF SEAT. LOW OIL PRESSURE LED TO BEARING FAILURE AND SUBSEQUENT ENGINE SEIZURE. 1L71 3O3 O 2A13 E286 5 NEXPP5N 20020304001572002030400157NM 2002 3 4 AUS20020146 120020223G2913165W01020 PUMP BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU HYDRAULIC PUMP, FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STANDBY HYDRAULIC PUMP FAILED. 2L72 4F4 FRTA16WE E21EU 20020408000462002040800046NE 2002 4 8 AUS20020147 220020220G74205336761 CABLE PWA HEIU EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE IGNITION HARNESSSPLIT W K NONE O OTHER ININSP/MAINT 1 AUS 24034 97180405 (AUS) LH ENGINE IGNITION CABLE FROM HIGH ENERGY IGNITION UNIT (HEIU) TO IGNITER PLUG CHAFED THROUGH REINFORCED OUTER LAYER THROUGH TO THE INNER LAYER DUE TO RUBBING AGAINST THE FIREWALL AND OTHER ENGINEMOUNTED COMPONENTS. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20020408000472002040800047SO 2002 4 8 AUS20020148 120020221G55214007514 SPAR PIPER SPAR PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR1 GL ELEVATOR, SPAR/RCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH ELEVATOR SPARS CRACKED AT OUTBOARD ENDS. LH ELEVATORSPAR PNO 40075-14. RH ELEVATOR SPAR PNO 40075-16. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020408001222002040800122EU 2002 4 8 AUS20020149 120020228G2910SA7670006127 HOSE BAC 146 146100A 1500260EU LYC ALF502ALF502R5 41580NE NLG BURST W O OTHER K FLUID LOSS CRCRUISE 1 AUS (AUS) NOSE LANDING GEAR ACTUATOR RETRACTION HOSE BURST. LOSS OF GREEN HYDRAULIC SYSTEM FLUID. 2H74 4F4 FRTA49EU E6NE 20020408000482002040800048NM 2002 4 8 AUS20020150 120020228G2823 SHUTOFF VALVE BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUEL SELECTOR/SHFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CENTRE TANK FUELLING SHUTOFF VALVE FAILED IN THE OPEN POSITION. VALVE COULD BE OPERATED MANUALLY. 2L72 4F4 FRTA16WE E21EU 20020408001232002040800123EA 2002 4 8 AUS20020151 220020226G7322DC0156 PIN CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL FUEL CONTROL MISSING W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS LDLANDING 1 AUS (AUS) CARBURETOR THROTTLE LEVER LOCKNUT SPLIT PIN MISSING AND LOCKNUT LOOSE. 1H71 3O3 ONT3A12 E274 5 NP910 20020408001242002040800124CE 2002 4 8 AUS20020152 120020226G3244 TIRE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C93 GL NLG DEFLATED W O OTHER O OTHER LDLANDING 1 AUS (AUS) NOSE WHEEL TIRE DEFLATED. FENDER DAMAGED BY TIRE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020408001262002040800126NM 2002 4 8 AUS20020153 120020301G3040 CONNECTOR BOEING747 747238B 1384828NM RROYCERB211 RB211524D41954555NE WINDOW HEAT LOOSE W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 AUS (AUS) CAPTAINS NR 1 WINDOW HEAT CONNECTION LOCATED IN THE LOWER LT CORNER LOOSE AND ARCING. 2L74 4F4 F A20WE E12EU 20020408001282002040800128NE 2002 4 8 AUS20020154 220020301G7230 FAN BLADE BOEING747 747400 NM PWA 4056 PW4056 NE TURBINE ENGINE SEPARATED W O OTHER EF VIBRATION/BUFFET FLT CONT AFFECTED NRNOT REPORTED 1 AUS (AUS) NR 3 ENGINE FAN BLADE SEPARATED. ASSOCIATED DAMAGE TO ENGINE. AIRCRAFT IS BRITISH REGISTERED. 2L74 4F4 FRTA20WE E24NE 20020408000492002040800049SO 2002 4 8 AUS20020155 220020301G741410357281 CAPACITOR BENDIX S6LN25 PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360F 17025SO HARTZLHCC2Y BHCC2YF2 GL MAGNETO/DISTRIBUFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS A175117 (AUS) LH MAGNETO CAPACITOR WIRE INTERMITTENT CONTACT. 1L71 3O3 O 2A13 E9CE 5 CP920 20020408000502002040800050SO 2002 4 8 AUS20020156 220020205G741410357281 CAPACITOR BENDIX S6LN25 PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360F 17025SO HARTZLHCC2Y BHCC2YF2 GL MAGNETO/DISTRIBUFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS A223385 (AUS) RH MAGNETO CAPACITOR WIRE INTERMITTENT CONTACT. 1L71 3O3 O 2A13 E9CE 5 CP920 20020408000512002040800051SW 2002 4 8 AUS20020157 120020223G28447G1075 PRESSURE SWITCH BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE FUEL PRESSURE INFAILED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS 1097 (AUS) FUEL PRESSURE SWITCH INTERNAL FAILURE. FUEL LEAKING FROM BODY. 1G72 4U4 U H4SW E22EA 20020408001292002040800129SW 2002 4 8 AUS20020158 120020307G5711 SPAR SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR SPAR WEB CRACKED ON RT SIDE AT WS 27.063. FOUND DURING INSPECTION IAW AD/SWSA226/86. 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20020408001312002040800131NM 2002 4 8 AUS20020159 120020305G2722654486112 ACTUATOR BOEING737 737400 138449ANM CFMINTCFM56 CFM563C 13802EU YAW DAMPER FAULTY W O OTHER F FLT CONT AFFECTED CRCRUISE 1 AUS 4210 (AUS) RUDDER YAW DAMPER ACTUATOR SUSPECT FAULTY. 2L72 4F4 FRTA16WE E21EU 20020408000522002040800052NM 2002 4 8 AUS20020160 120020301G2912AN81510D FITTING DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYDRAULIC FILTERFAILED W K NONE KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) NO2 HYDRAULIC SYSTEM MAIN FILTER PRESSURE MANIFOLD BULKHEAD FITTING FRACTURED. LOSS OF HYDRAULIC FLUID. INVESTIGATION FOUND THE FRACTURE SURFACE WAS COARSE TEXTURED WITH CHEVRON MARKINGSINDICATING OVERLOAD FRACTURE DUE TO ROTATION IN A CLOCKWISE MANNER. THE FITTING FAILED BY OVERLOAD FRACTURE CONSISTENT WITH OVERTIGHTENING. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020408000532002040800053NE 2002 4 8 AUS20020161 220020304G7321 BEARING PWA PW123D DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE FUEL CONTROL/TURFAULTY W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) NO1 ENGINE POWER LEVER JAMMED. INVESTIGATION FOUND THEHYDROMECHANICAL UNIT (HMU) POWER LEVER INPUT BEARING FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020408000542002040800054EU 2002 4 8 AUS20020162 220020305G7260 BEARING GE CFM563C BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU TURBINE ENGINE AGALLED W K NONE EF VIBRATION/BUFFET FLT CONT AFFECTED NRNOT REPORTED 1 AUS (AUS) NO2 ENGINE TRANSFER GEARBOX INPUT ROLLER BEARING GALLED. METALCONTAMINATION OF OIL SYSTEM. 2L72 4F4 FRTA16WE E21EU 20020408001342002040800134NE 2002 4 8 AUS20020163 220020307G7320 LINE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE P3 AIR BLOCKED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS DEDESCENT 1 AUS 372 (AUS) NR 2 ENGINE RPM REDUCED TO IDLE DURING FLIGHT. EXTENSIVE INVESTIGATION COULD FIND NO FAULT AND THE AIRCRAFT WAS RETURNED TO SERVICE. SUSPECT PROBLEM CAUSED BY TEMPORARY BLOCKAGE OF P3 AIR SUPPLY LINE. 1G72 4U4 U H4SW E22EA 20020408000552002040800055CE 2002 4 8 AUS20020164 120020131G3260951F04 LIGHT BEECH 1900 1900 1154160CE LANDING GEAR POSFAILED W K NONE OP OTHER NO WARNING INDICATION LDLANDING 1 AUS (AUS) RH MAIN LANDING GEAR POSITION LIGHT FAILED. 2L72 4T RTA24CE 20020408000562002040800056GL 2002 4 8 AUS20020165 220020121G732123070613 FCU ALLSN 250C30P BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL FUEL CONTROL/TURFAULTY W K NONE EM VIBRATION/BUFFET OVER TEMP NRNOT REPORTED 1 AUS 10 72412 (AUS) FUEL CONTROL UNIT FAULTY. FCU HAD JUST BEEN FITTED BUT GAVE CONTINUAL HOT STARTS. 1G71 3U3 U H2SW E1GL 20020408001512002040800151EA 2002 4 8 AUS20020166 120020221G3250711709 LEVER DHAV DHC6 DHC6300 2802606EA NLG STEERING SYSBROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 AUS (AUS) NOSE WHEEL STEERING LEVER ASSEMBLY LOCATED BETWEEN THE NOSE STEERING ACTUATOR AND THE NOSE STEERING COLLAR BROKEN IN TWO. 1H72 3T RTA9EA 20020408001522002040800152CE 2002 4 8 AUS20020167 120020301G5711 SPAR CESSNA441 441 2076020CE WING DELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT AFT SPAR WEBS DELAMINATED. 1L72 3T RTA28CE 20020408001532002040800153CE 2002 4 8 AUS20020168 120020302G5711 SPAR CESSNA441 441 2076020CE WING DELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT AFT SPAR WEBS DELAMINATED. 1L72 3T RTA28CE 20020408000572002040800057SO 2002 4 8 AUS20020169 220020222G8540653882 SHAFT CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL ENGINE BROKEN W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE DEDESCENT 1 AUS (AUS) STARTER SHAFT AND CRANKSHAFT GEAR HAD SEVERAL MISSING TEETH. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020408000582002040800058SO 2002 4 8 AUS20020170 220020218G8540537721 BEARING CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STARTER SHAFT BEARING BROKEN UP. BEARING DEBRIS LOCATED IN SUMP.CRANKCASE DAMAGED IN AREA OF BEARING SUPPORT. STARTER SHAFT AND CRANK GEARS EXHIBITED DEFORMATION OF PROFILE. THE ENGINE WASFITTED WITH PNO EQ6642 ADAPTER KIT AS PER AD/CON/71. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020408000592002040800059EA 2002 4 8 AUS20020171 220020106G7313 INJECTOR LYC TIO540J2BD PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL FUEL INJECTOR NOBLOCKED W K NONE E VIBRATION/BUFFET CLCLIMB 1 AUS (AUS) RH ENGINE NO1 CYLINDER FUEL INJECTOR NOZZLE CLOGGED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020408000602002040800060CE 2002 4 8 AUS20020172 120020206G3222MS28775329 SEAL CESSNA206 TU206F 2073353CE NOSE/TAIL LANDINFAILED W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) NOSE LANDING GEAR OLEO LEG MAIN SEAL PNO MS28775-329 ROLLED AND SPLIT IN THREE PLACES. 1H71 3O A4CE 20020408001552002040800155EU 2002 4 8 AUS20020173 120020218G7603 THROTTLE BNORM BN2 BN2A20 1520220EU LYC O540 IO540K1B5 41532EA LT ENGINE BROKEN W O OTHER O OTHER DEDESCENT 1 AUS (AUS) LT ENGINE THROTTLE SLIDING END ASSEMBLY BROKEN. 1H72 3O3 O A17EU 1E4 20020408000612002040800061EU 2002 4 8 AUS20020175 120020127G3230A78730421 UPLOCK FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU LANDING GEAR RETFAULTY W K NONE OJ OTHER WARNING INDICATION TOTAKEOFF 1 AUS 21782 BE3585 (AUS) RH MAIN LANDING GEAR UPLOCK LATCH FAULTY. 2L72 4F4 FRTA20EU E2EU 20020408001572002040800157 2002 4 8 AUS20020176 420020126G2350X00011413 ACCESSORY UNIT FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU AUDIO SYSTEM FAULTY W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 AUS 370 67059 (AUS) AUDIO ACCESSORY UNIT FAULTY. 2L72 4F4 FRTA20EU E2EU 20020408000622002040800062EU 2002 4 8 AUS20020177 120020122G243223531 BATTERY FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU BATTERY/CHARGER OVERHEATED W K NONE J WARNING INDICATION CRCRUISE 1 AUS 45 F1537 (AUS) AFT BATTERY OVERHEATED. AFT BATTERY OVERHEAT MILLIAMPMETER NOTOPERATING DUE TO A PART OF THE BROKEN PERSPEX COVER WEDGED INSIDE THE INDICATOR. 2L72 4F4 FRTA20EU E2EU 20020408001602002040800160EU 2002 4 8 AUS20020179 120020107G3260 SWITCH FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU MLG OUT OF ADJUST W O OTHER N FALSE WARNING CRCRUISE 1 AUS (AUS) RT MAIN LANDING GEAR DOOR FORWARD UPLOCK SWITCH OUT OF ADJUSTMENT. 2L72 4F4 FRTA20EU E2EU 20020408000632002040800063EU 2002 4 8 AUS20020180 120020116G243223531 BATTERY FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU BATTERY/CHARGER OVERHEATED W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 AUS 73 C02676C02677 (AUS) AFT BATTERY OVERTEMPERATURE. 2L72 4F4 FRTA20EU E2EU 20020408000642002040800064NM 2002 4 8 AUS20020182 120020308G324082970009151 HOSE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR BRALOOSE W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) RH BRAKE PRESSURE INPUT LINE TO THE TOP OF THE SWIVEL PNO AE82556E LOOSE. LOSS OF HYDRAULIC FLUID. PERSONNEL/MAINTENANCEERROR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020408000652002040800065EU 2002 4 8 AUS20020184 120020115G2410 SENSOR FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU ALTERNATOR-GENERFAULTY W K NONE O OTHER CRCRUISE 1 AUS (AUS) NO2 CONSTANT SPEED DRIVE TEMPERATURE SENSOR FAULTY. 2L72 4F4 FRTA20EU E2EU 20020408000662002040800066EU 2002 4 8 AUS20020185 120020115G3610 TUBE FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU PNEUMATIC DISTRILEAKING W K NONE MJ OVER TEMP WARNING INDICATION CLCLIMB 1 AUS (AUS) PNEUMATIC TUBE LEAKING FROM DOWNSTREAM PRESSURE TAPPING. 2L72 4F4 FRTA20EU E2EU 20020408001872002040800187EU 2002 4 8 AUS20020186 120020101G243223521 BATTERY FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU BATTERY BAY OVERHEATED W O OTHER HM ELECT. POWER LOSS-50 PC OVER TEMP LDLANDING 1 AUS 10 (AUS) FORWARD BATTERY OVERHEATED. 2L72 4F4 FRTA20EU E2EU 20020408001882002040800188NM 2002 4 8 AUS20020187 120020309G7830S315A1026 SEGMENT BOEING737 73733A 1384673NM CFMINTCFM56 CFM563C 13802EU THRUST REVERSER MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE THRUST REVERSER NR 12 CASCADE SEGMENT MISSING. FORWARD ANDAFT FLANGES CRACKED. 2L72 4F4 FRTA16WE E21EU 20020408000672002040800067NM 2002 4 8 AUS20020188 120020307G262032422D121212G FITTING BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU EXTINGUISHING SYCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO1 ENGINE FIRE EXTINGUISHING SYSTEM T' FITTING CRACKED BIN TWO PLACES ON THE SEALING SURFACES AND THREADS OF THE FITTING. 2L72 4F4 FRTA16WE E21EU 20020408001892002040800189NE 2002 4 8 AUS20020189 220020312G725030723112 TURBINE BLADES GARRTTTFE731TFE73131G 29003NE ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 AUS 522 (AUS) TWO FIRST STAGE LOW PRESSURE TURBINE BLADES FRACTURED CAUSING DAMAGE TO TURBINE BLADES AND NOZZLE ASSEMBLIES. ONE RIVET HAD BROKEN OFF THE LP TURBINE NOZZLE SEAL ASSEMBLY AND IMPINGED ONTHE FORWARD FACE OF THE TURBINE DISC BEFORE FINALLY WEDGING ONTHE SHAFT SEAL BOLT. 4 F E6WE 20020408001902002040800190CE 2002 4 8 AUS20020190 120020311G281060170010604 FUEL TANK BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AMTR C8289 C8289 GL RT WING CONTAMINATED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) RT WING TIP TANK CONTAMINATED. SUSPECT NON-APPROVED SEALANT USED. POSSIBLE FILTER BLOCKAGE. 1L72 3O3 O 3A16 E5CE 5 NEXPP5N 20020408000682002040800068EA 2002 4 8 AUS20020191 220020311G852072877 TAPPET LYC IO540K1B5 BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1390 (AUS) RH ENGINE NO6 CYLINDER INLET TAPPET AND NO4 CYLINDER EXHAUSTTAPPET BODIES CRACKED. 1H72 3O3 O A17EU 1E4 5 CP920 20020408001912002040800191CE 2002 4 8 AUS20020192 120020313G781099102962 SLIP JOINT CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL ENGINE COLLECTORUNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS 189 (AUS) LT ENGINE EXHAUST SYSTEM SLIP JOINT HARDWARE UNAPPROVED PARTS AND NOT INSTALLED IAW RELEVANT DATA. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020408001922002040800192CE 2002 4 8 AUS20020193 120020313G781099102962 SLIP JOINT CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL ENGINE COLLECTORUNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) RT ENGINE EXHAUST SYSTEM SLIP JOINT HARDWARE UNAPPROVED PARTS AND NOT INSTALLED IAW RELEVANT DATA. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020408000692002040800069SO 2002 4 8 AUS20020194 120020213G27216666100 ARM PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA RUDDER TAB CONTRCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RUDDER TRIM ARM ASSEMBLY CRACKED AROUND WELD. 1L71 3O3 O 2A13 E274 5 NP88614 20020408001932002040800193CE 2002 4 8 AUS20020195 120020301G5711 SPAR CESSNA441 441 2076020CE LT WING DELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT WING REAR SPAR WEB DELAMINATED IN THREE AREAS. 1L72 3T RTA28CE 20020408001942002040800194CE 2002 4 8 AUS20020196 120020223G2751 SWITCH CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL TE FLAPS MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) SWITCH ON FLAP PRESELECT ARM MISSING. ALL ATTACHING HARDWARE ALSO MISSING AND CONNECTING WIRES STOWED. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000702002040800070 2002 4 8 AUS20020197 420020223G3432 CONNECTOR CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL GLIDE SLOPE SYSTFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) GLIDESLOPE RECEIVER CONNECTOR INPUT VOLTAGE PIN BENT. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000712002040800071 2002 4 8 AUS20020198 420020223G3454 CONVERTER CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL VOR SYSTEM FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VOR CONVERTER FAULTY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408001952002040800195 2002 4 8 AUS20020199 420020223G2310 TRANSCEIVER CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL HF COMMUNICATIONUNSECURE W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) HF TRANSCEIVER NOT SECURED IN RACK. FURTHER INVESTIGATION FOUND THE TRANSCEIVER UNSERVICEABLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408001972002040800197 2002 4 8 AUS20020200 420020223G2310 RADIO CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL COMMUNICATIONS FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LIMITED RECEIVE RANGE ON BOTH COM1 AND COM2. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408001982002040800198 2002 4 8 AUS20020201 420020223G2310 RADIO CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL HF COMMUNICATIONFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HF SYSTEM FAULTY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408001992002040800199CE 2002 4 8 AUS20020202 120020223G3411 VENT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL PITOT/STATIC SYSMISMARKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) STATIC VENT INCORRECTLY MARKED. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000722002040800072 2002 4 8 AUS20020203 420020223G3451 ANTENNA CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL DME/TACAN SYSTEMFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DME ANTENNA PAINTED OVER. SIGNS OF CORROSION AROUND EDGES OFANTENNA. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000732002040800073 2002 4 8 AUS20020204 420020223G3434 MOUNT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL MARKER BEACON SYCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MARKER BEACON ANTENNA MOUNT CONTAINED SURFACE CORROSION. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000742002040800074CE 2002 4 8 AUS20020205 120020223G1400 STATIC WICK CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL MISCELLANEOUS HAFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ALL STATIC WICKS (10OFF) UNSERVICEABLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002002002040800200EA 2002 4 8 AUS20020206 220020223G7297 WIRE HARNESS CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ENGINE BAY WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE BAY WIRING LOOMS WORN THROUGH IN NUMEROUS PLACES. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002012002040800201CE 2002 4 8 AUS20020207 120020223G2434 FILTER CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL DC GENERATOR-ALTCHAFED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ALTERNATOR FILTER TOUCHING AUX' TERMINAL OF ALTERNATOR. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000752002040800075CE 2002 4 8 AUS20020208 120020223G2497 WIRE CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ELECTRICAL POWERWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EXTERNAL POWER SWITCH LEAD WORN THROUGH ON AIRCRAFT RIB. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000762002040800076CE 2002 4 8 AUS20020209 120020223G3310 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL FLIGHT COMPARTMEUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) OVERHEAD FLOOD LIGHT AND TRIM POST LIGHTS UNSERVICEABLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000772002040800077CE 2002 4 8 AUS20020210 120020223G3310 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL FLIGHT COMPARTMEUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH POST LIGHTS AND PEDESTAL POST LIGHTS UNSERVICEABLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002022002040800202 2002 4 8 AUS20020211 420020223G3455 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ADF SYSTEM UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ADF INTERNAL LIGHTS UNSERVICEABLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002032002040800203CE 2002 4 8 AUS20020212 120020223G1100 PLACARD CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL COCKPIT MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MULTIPLE LABELS MISSING FROM EQUIPMENT IDENTIFIERS IN COCKPIT. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000782002040800078 2002 4 8 AUS20020213 420020223G2210 SWITCH CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL AUTOPILOT SYSTEMUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AUTO-PILOT CONTROLLER BACK COURSE SWITCH INOPERATIVE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000792002040800079CE 2002 4 8 AUS20020214 120020223G2437 AMMETER CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL DC INDICATING SYFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AMMETER FAULTY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002042002040800204 2002 4 8 AUS20020215 420020223G2210 SELECTOR SWITCH CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL AUTOPILOT SYSTEMMISMARKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) AUTOPILOT NAV2 EXTERNAL SWITCH SELECTOR HAD NO MARKINGS. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000802002040800080CE 2002 4 8 AUS20020216 120020223G3310 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL FLIGHT COMPARTMEUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CONTROL COLUMN MAP LIGHT FAULTY. LAMP AND LAMP HOLDER MISSING. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000812002040800081CE 2002 4 8 AUS20020217 120020223G7931 PIPE LYC O540J3C5 CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ENGINE OIL PRESSCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PIPE BETWEEN OIL PRESSURE INDICATOR AND HOUR-METER BLOCK CORRODED AND FLARE SPLIT. HOUR-METER BLOCK FIREWALL FITTING LOOSE AND REAR FITTING HAD INCORRECT THREAD TYPE. OIL LEAKING FROM BEHIND DASH. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002052002040800205CE 2002 4 8 AUS20020218 120020223G2437 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL DC INDICATING MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) ALTERNATOR LOW VOLTAGE WARNING LIGHT SECURED TO RT DASH WITH PVC ELECTRICAL TAPE. UNAPPROVED PART. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002062002040800206CE 2002 4 8 AUS20020219 120020223G3310 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT AND RT INSTRUMENT PANEL COVER POST LIGHT CONNECTION WIRES FITTED WITH INCORRECT TERMINALS. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002082002040800208 2002 4 8 AUS20020220 420020223G3497 WIRE CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL NAVIGATION CUT W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WIRING TO RT SIDE OF ADF RACK CUT THROUGH BY RACK. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000822002040800082 2002 4 8 AUS20020221 420020223G3197 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL INSTRUMENT WIRINUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH ARTIFICIAL HORIZON HAD NO INTERNAL OR EXTERNAL LIGHTING. INTERNAL LIGHTS WIRING CONNECTED TO AN UNKNOWN SOURCE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002092002040800209CE 2002 4 8 AUS20020222 120020223G3340 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL STROBE FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) BOTH STROBE LIGHT FLASH TUBES BLACKENED. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002102002040800210CE 2002 4 8 AUS20020223 120020223G3340 LENS CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL NAV LIGHT MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) RT NAVIGATION LIGHT LENS GLUED IN WITH SILASTIC. UNAPPROVED PART. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000832002040800083CE 2002 4 8 AUS20020224 120020223G3340 LENS CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL EXTERIOR LIGHTINLOOSE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAIL LIGHT LENS LOOSE. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000842002040800084CE 2002 4 8 AUS20020225 120020223G3310 LIGHT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL FLIGHT COMPARTMEUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH CLOCK/MICROPHONE JACK POST LIGHT UNSERVICEABLE. THE CENTRE CONTACTOR ASSEMBLY WAS MISSING FROM THE LIGHT HOLDER. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000852002040800085 2002 4 8 AUS20020228 420020223G2210 INDICATOR CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL AUTOPILOT SYSTEMUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AUTOPILOT TURN AND BANK UNIT FAULTY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000862002040800086CE 2002 4 8 AUS20020229 120020223G3340 BALLAST CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL EXTERIOR LIGHTINBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAIL BEACON BALLAST RESISTOR BROKEN IN THREE PLACES. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408002122002040800212 2002 4 8 AUS20020230 420020223G3425 SCREW CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL HSI MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HSI TOP RT SCREW MISSING. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000872002040800087CE 2002 4 8 AUS20020231 120020223G7933 INDICATOR LYC O540J3C5 CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ENGINE OIL TEMPEFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE OIL TEMPERATURE INDICATOR FAULTY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000882002040800088 2002 4 8 AUS20020232 420020223G3452 MOUNT CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ATC TRANSPONDER LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TRANSPONDER MOUNT LOOSE. MOUNT MADE OF THIN METAL. 1H71 3O3 O 3A13 E295 5 CP7EA 20020409000042002040900004 2002 4 9 AUS20020233 420020223G3452 RESISTOR CESSNA182 TR182 2072735CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C214 GL ATC TRANSPONDER MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) TRANSPONDER VOLTAGE DROPPING RESISTOR INCORRECTLY MOUNTED. THE RESISTOR IS MOUNTED ON THE REAR OF THE TRANSPONDER MOUNTING RACK. THE INSTALLATION MANUAL STATES THAT IT MUST BE MOUNTED AWAY FROM THE AVIONICS STACK TO AVOID OVERHEATING OF THE POWER SUPPLY. 1H71 3O3 O 3A13 E295 5 CP7EA 20020408000892002040800089SO 2002 4 8 AUS20020236 120020314G78103031988 DUCT PWA PT6A34 EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL ENGINE COLLECTORCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1172 PCE57045 (AUS) EXHAUST DUCT CONTAINED HAIRLINE CRACKS. 1L72 4T4 T A21SO E4EA 6 CP15EA 20020408000902002040800090NM 2002 4 8 AUS20020237 120020313G3231XD4N RELAY DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR DOOFAULTY W K NONE O OTHER CLCLIMB 1 AUS (AUS) LH MAIN LANDING GEAR DOOR RELAY SUSPECT FAULTY. INVESTIGATION COULD NOT DUPLICATE FAULT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020408000912002040800091EA 2002 4 8 AUS20020238 220020315G7314RJ9080J4A PUMP LYC LTIO540J2BD PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2 GL ENGINE FUEL PUMPFAILED W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE LDLANDING 1 AUS 132 C6223 (AUS) RH ENGINE DRIVEN FUEL PUMP FAILED ON LOW SIDE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020408000922002040800092NM 2002 4 8 AUS20020239 120020314G275265766061 BOLT BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TRAILING EDGE FLSHEARED W K NONE F FLT CONT AFFECTED TOTAKEOFF 1 AUS (AUS) NO1 TRAILING EDGE FLAP SCREWJACK TO TRANSMISSION ATTACHMENT BOLTSHEARED. 2L72 4F4 FRTA16WE E21EU 20020408000932002040800093NM 2002 4 8 AUS20020240 120020215G5523 BALANCE WEIGHT BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE ELEVATOR, TAB STCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) RH ELEVATOR TAB CENTRE BALANCE WEIGHT SPLIT OPEN DUE TO CORROSION. 2L73 4F4 F A3WE E2EA 20020408000942002040800094NM 2002 4 8 AUS20020241 120020214G5512 PANEL BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE HORIZONTAL STABICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) HORIZONTAL STABILISER PANEL LOCATED ABOVE BAY THREE CORRODED IN AREA OF REAR AUXILIARY SPAR LH SIDE. 2L73 4F4 F A3WE E2EA 20020408000952002040800095NM 2002 4 8 AUS20020242 120020122G5347BAC1520843 TRACK BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE SEAT/CARGO ATTACCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) FORWARD CARGO TIEDOWN TRACK CORRODED. 2L73 4F4 F A3WE E2EA 20020408000962002040800096NM 2002 4 8 AUS20020243 120020122G5347 TRACK BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE SEAT/CARGO ATTACCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) CARGO TRACK CORRODED. TRACK IS LOCATED IN ZONE 1-13 SECTION 43, STN 540 TO STN 600 WL 156, BL16. 2L73 4F4 F A3WE E2EA 20020408000972002040800097NM 2002 4 8 AUS20020244 120020123G534469339561 PLATE BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE FUSELAGE DOOR HICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) CARGO DOOR HINGE SUPPORT PLATE CORRODED. PLATE IS LOCATED IN ZONE 2-48, STN 520 TO STN 530, STRINGER 55LH. 2L73 4F4 F A3WE E2EA 20020408000982002040800098NM 2002 4 8 AUS20020245 120020125G5343 FRAME BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE LANDING GEAR ATTCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) RH MAIN LANDING GEAR WHEEL WELL DOOR SEQUENCING STRIKER FRAME CORRODED. FRAME LOCATED IN ZONE 1-36, STN 880, STRINGER 520RH,WL157, BL70RH. 2L73 4F4 F A3WE E2EA 20020408000992002040800099NM 2002 4 8 AUS20020246 120020130G5343 SUPPORT BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE LANDING EAR ATTACORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) LH MAIN LANDING GEAR DOOR SEQUENCING STRIKER FRAME CORRODED.LOCATION OF CORROSION ZONE 1-35, STN 880, STRINGER 20LH, WL 152,BL70LH. 2L73 4F4 F A3WE E2EA 20020409000052002040900005NM 2002 4 9 AUS20020247 120020129G5320 STIFFENER BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE MLG WW CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) LT MAIN LANDING GEAR BAY STIFFENER CHORD CORRODED IN SEVERAL AREAS INCLUDING ATTACHMENT TO PRESSURE DECK. CORROSION LOCATED IN ZONE 1-35, STN 870, STRINGER 20 LT TO STRINGER 17, WL 208 TO WL184, BL 67 LT. 2L73 4F4 F A3WE E2EA 20020409000062002040900006NM 2002 4 9 AUS20020248 120020130G5710 STRUCTURE BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE RT WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) UPPER RT WING TOP CHORD CORRODED. CORROSION LOCATED AT ZONE 6-76, WS 351RT TO WS 355 RT. 2L73 4F4 F A3WE E2EA 20020409000072002040900007NM 2002 4 9 AUS20020249 120020130G5711 SPAR BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE LT WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) LT REAR WING SPAR UPPER AND LOWER CHORDS CORRODED IN AREA LOCATED BEHIND THE VERTICAL STIFFENER. CORROSION LOCATED AT ZONE 6-72, WS 437 TO WS 438 LT. 2L73 4F4 F A3WE E2EA 20020408001002002040800100NM 2002 4 8 AUS20020250 120020206G5230 DOOR BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE CARGO/BAGGAGE DOCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) MAIN CARGO DOOR STRUCTURE CORRODED AT THE LAP JOINT LOCATED ATSTN 620. CORROSION LOCATED AT ZONE 2-48, STN 620 TO STN 623,STRINGER 4LH TO STRINGER 5. 2L73 4F4 F A3WE E2EA 20020408001012002040800101NM 2002 4 8 AUS20020251 120020206G5230 DOOR BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE CARGO/BAGGAGE DOCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) MAIN CARGO DOOR STRUCTURE LAP JOINT CORRODED AT STN 620.CORROSION IS LOCATED AT ZONE 2-48, STN 620 TO STN 623, STRINGER 9LH TO STRINGER 11. 2L73 4F4 F A3WE E2EA 20020408001022002040800102NM 2002 4 8 AUS20020252 120020206G5310 SKIN BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE FUSELAGE MAIN, SCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) MAIN CARGO DOOR SUPPORT STRUCTURE TOP FORWARD CORNER CORRODED.CORROSION LOCATED AT ZONE 2-24, STN 48D, STRINGER 1LH TO STRINGER 3. 2L73 4F4 F A3WE E2EA 20020408001032002040800103NM 2002 4 8 AUS20020253 120020127G5330 SKIN BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE FUSELAGE MAIN, PCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 58266 (AUS) SKIN CORRODED IN AREA BELOW TOILET SERVICE DOOR. CORROSIONLOCATED AT ZONE 2-11, STN 350 TO STN 370, STRINGER 18RH. 2L73 4F4 F A3WE E2EA 20020409000082002040900008EU 2002 4 9 AUS20020254 120020226G3260 SWITCH PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG FAILED W O OTHER N FALSE WARNING DEDESCENT 1 AUS (AUS) LT MAIN LANDING GEAR DOWNLOCK SWITCH FAILED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020408001042002040800104NM 2002 4 8 AUS20020256 120020316G274091238071 RELAY BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU STABILIZER CONTRFAULTY W K NONE F FLT CONT AFFECTED CLCLIMB 1 AUS (AUS) STABILISER TRIM RELAY FAULTY. 2L72 4F4 FRTA16WE E21EU 20020408001052002040800105SO 2002 4 8 AUS20020257 120020306G323041963001 HOOK PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN LANDING GEAR DOWNLOCK HOOK ASSEMBLY CLIP SECURING RIVETS CORRODED. ONE RIVET HEAD SHEARED AND ONE RIVET HEAD CORRODED. THE DEFECTIVE PART IS LOCATED IN THE AREA OF THE ENGINE EXHAUST. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020408001062002040800106CE 2002 4 8 AUS20020259 120020222G5342 MOUNT BEECH 23 A2324 1151226CE LYC O360 IO360A1B 41514EA MCAULY2D34C 2D34C9 GL FUSELAGE, STABILCORRODED W K NONE D INFLIGHT SEPARATION LDLANDING 1 AUS (AUS) STABILATOR MOUNTING BLOCK RIVETS SHEARED. INVESTIGATION FOUND THE UNDERSIDE OF THE ATTACHMENT BLOCK BADLY CORRODED AND THE RIVETS CORRODED. 1L71 3O3 O A1CE 1E10 5 CP7EA 20020409000092002040900009 2002 4 9 AUS20020260 420020315G34206466350 INDICATOR BAC 146 146100A 1500260EU LYC ALF502ALF502R5 41580NE COCKPIT INACCURATE W O OTHER O OTHER CRCRUISE 1 AUS (AUS) STANDBY HORIZON OUT OF LIMITS COMPARED WITH ADI. 2H74 4F4 FRTA49EU E6NE 20020408001072002040800107NE 2002 4 8 AUS20020262 220020318G72601155550259 SHAFT PWA PT6A42 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE TURBINE ENGINE ASHEARED W K NONE O OTHER NRNOT REPORTED 1 AUS (AUS) RH ENGINE AIRCONDITIONING COMPRESSOR PULLEY DRIVE QUILL SHAFT SHEARED. LOSS OF ENGINE OIL. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020409000102002040900010CE 2002 4 9 AUS20020263 120020312G271157152801 PUSHROD CESSNA441 441 2076020CE GARRTTTPE331TPE3318 01514WP HARTZLHCB3T HCB3TN5 GL AILERON TAB CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AILERON TRIM TAB PUSH ROD AFT ROD END CRACKED ACROSS BEARING RETAINER. RODEND BEARING CORRODED. CRACK FOUND WHEN PUSHROD WAS REMOVED FOR REPLACEMENT DUE TO WEAR. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20020408001082002040800108SW 2002 4 8 AUS20020264 120020303G29102781032626 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE HYDRAULIC SYSTEMWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HYDRAULIC SUCTION LINE WORN THROUGH BY ELECTRICAL WIRINGASSOCIATED WITH THE LH OUTBOARD GEAR DOOR POSITION SWITCH. THELINE IS VISIBLE THROUGH PANEL 513 LOCATED IN THE LH WHEEL WELL. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20020409000112002040900011CE 2002 4 9 AUS20020265 120020313G3297 WIRE BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE MLG POSITION BROKEN W O OTHER N FALSE WARNING LDLANDING 1 AUS (AUS) LANDING GEAR POSITION SYSTEM WIRE BROKEN. WIRE WAS LOCATED IN THE WIRING LOOM IN THE UNDERCARRIAGE BAY. 1L72 4T4 T A24CE E4EA 20020408001092002040800109EU 2002 4 8 AUS20020266 120020315G7920B590065 PIPE LYC IO540K1B5 BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL ENGINE OIL DISTRLOOSE W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS (AUS) RH ENGINE CRANKCASE TO OIL COOLER PIPE LOOSE AND LEAKING. ENGINEHAD BEEN RECENTLY REPLACED. PERSONNEL/MAINTENANCE ERROR. 1H72 3O3 O A17EU 1E4 5 CP920 20020409000122002040900012CE 2002 4 9 AUS20020267 120020320G143012NB126 NUT BEECH 58 58 1152740CE CONT O520 IO520C 17032SO RT WING WRONG PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LOWER RT WING REAR ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART. 1L72 3O3 O 3A16 E5CE 20020409000132002040900013CE 2002 4 9 AUS20020268 120020320G143012NB126 NUT BEECH 58 58 1152740CE CONT O520 IO520C 17032SO LT WING WRONG PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LOWER LT WING REAR ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART. 1L72 3O3 O 3A16 E5CE 20020409000142002040900014CE 2002 4 9 AUS20020269 120020320G5741EB126 NUT BEECH 58 58 1152740CE CONT O520 IO520C 17032SO LT WING WRONG PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) UPPER LT WING FORWARD ATTACHMENT NUT INCORRECT PART. UNAPPROVED PART. 1L72 3O3 O 3A16 E5CE 20020409000152002040900015SW 2002 4 9 AUS20020270 120020321G2731DL504DM5 ACTUATOR SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ELEVATOR TAB FAILED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 AUS 2635 (AUS) PITCH TRIM ACTUATOR MOTOR FAILED. 2L72 4T4 TRTA8SW E4WE 20020409000162002040900016NM 2002 4 9 AUS20020271 120020321G7830LJ34179 BLOCKER DOOR BOEING747 747438 NM RROYCERB211 RB211524G19 NE THRUST REVERSER SEPARATED W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 AUS (AUS) NR 4 ENGINE THRUST REVERSER NR 5 BLOCKER DOOR SEPARATED IN FLIGHT. DAMAGE CAUSED TO RT OUTBOARD AILERON. 2L74 4F4 FRTA20WE E30NE 20020408001102002040800110SW 2002 4 8 AUS20020272 120020301G2710730006000 LINK MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA MCAULY2D34C 2D34C53 GL AILERON CONTROL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AILERON CONTROL LINK CRACKED IN WELD JOIN. 1L71 3O3 O 2A3 E286 5 CP7EA 20020408001112002040800111SW 2002 4 8 AUS20020273 120020301G27107300051 LINK MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA MCAULY2D34C 2D34C53 GL AILERON CONTROL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AILERON CONTROL LINK CRACKED AT WELDED JOIN. 1L71 3O3 O 2A3 E286 5 CP7EA 20020409000172002040900017EU 2002 4 9 AUS20020274 120020115G2424700122490420 GCU BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE AC REGULATOR FAULTY W O OTHER J WARNING INDICATION CLCLIMB 1 AUS 28394 (AUS) NR 1 GENERATOR CONTROL UNIT (GCU) FAULTY. 2H74 4F4 F A49EU E6NE 20020409000182002040900018SW 2002 4 9 AUS20020275 120020321G6120 ROD END SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE PROP CONTROL DISCONNECTED W O OTHER O OTHER CRCRUISE 1 AUS (AUS) PROPELLER GOVERNOR CONTROL ROD RODEND DISCONNECTED. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020408001122002040800112NM 2002 4 8 AUS20020276 120020308G6310405H ACTUATOR ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA ENGINE/TRANSMISSUNSERVICEABLE W K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS 6 (AUS) CLUTCH ACTUATOR UNSERVICEABLE. ACTUATOR UP LIMIT SWITCH STUCK INOPEN CIRCUIT POSITION PREVENTING RETENSIONING OF DRIVE BELTS. 1G71 3O3 O H10WE E286 20020408001132002040800113EA 2002 4 8 AUS20020277 220020207G8520L714361A BEARING LYC TIO540J2BD PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA MCAULY3DF36CB3DF36C526 GL RECIPROCATING ENFAILED W K NONE O OTHER ININSP/MAINT 1 AUS 720 L714361A (AUS) CONNECTING ROD BEARINGS AND MAIN BEARINGS LOOSING WHITE-METAL.METAL CONTAMINATION OF OIL FILTER. 1L72 3O3 O A20SO E14EA 5 C 20020408001142002040800114SO 2002 4 8 AUS20020278 120020203G5341 FITTING PIPER PA36 PA36285 7103610SO CONT 6285 6285C 17038SO HARTZLHCC2Y HCC2YF1 GL FUSELAGE, WING ACRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING ATTACHMENT LUG BROKEN. SUSPECT DAMAGED DURING A PREVIOUSCRASH. 1L71 3O3 O A10SO E12CE 5 CP920 20020408001152002040800115GL 2002 4 8 AUS20020279 120020319G2434ES4139 HOUSING FORD DOFF10300D PAC CT4 CT4B GL CONT O360 IO360HB 17025SO HARTZLHCC2Y BHCC2YF1 GL DC GENERATOR-ALTCRACKED W K NONE H ELECT. POWER LOSS-50 PC CLCLIMB 1 AUS 160 9070246 (AUS) ALTERNATOR FRONT HOUSING WEBS CRACKED. 1L71 3O3 ORTA9PC E1CE 5 CP920 20020408001162002040800116EU 2002 4 8 AUS20020280 120020326G7922230379401 VALVE LYC ALF502R3A BAC 146 146100A 1500260EU LYC ALF502ALF502R3A 41580NE ENGINE OIL TEMPEFAULTY W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS (AUS) NO3 ENGINE OIL COOLER FUEL SYSTEM VERNATHERM VALVE SUSPECTFAULTY. 2H74 4F4 FRTA49EU E6NE 20020409000192002040900019NM 2002 4 9 AUS20020281 120020323G29109741735 HOSE BOEING747 747238B 1384828NM RROYCERB211 RB211524D41954555NE HYDRAULIC SYSTEMRUPTURED W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 AUS (AUS) NR 1 ADP PRESSURE HOSE LOCATED BETWEEN THE PUMP AND THE PRESSURE MODULE RUPTURED. LOSS OF HYDRAULIC FLUID. 2L74 4F4 F A20WE E12EU 20020408001172002040800117NM 2002 4 8 AUS20020282 120020326G2912271T006810 MODULE BOEING767 767238 1385114NM PWA JT9 JT9D7R4E 52054NE HYDRAULIC FILTERFAULTY W K NONE KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 AUS 00477 (AUS) HYDRAULIC FILTER MODULE FAULTY. 2L72 4F4 FRTA1NM E3NE 20020409000202002040900020SW 2002 4 9 AUS20020283 220020311G85304300C CYLINDER CESSNA195 195 2073102CE JACOBPR755 R755A2 35006SW HAMSTD2B 2B20 NE ENGINE SEPARATED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS 271 (AUS) ENGINE CYLINDERS (2OFF) LEAKING PAST EXHAUST VALVE. DURING CYLINDER REMOVAL THE CYLINDER HOLD DOWN NUTS WERE FOUND TO BE LOOSE. RED SILICONE SEALANT WAS ALSO FOUNDS AROUND THE BASE OF THE CYLINDERS AND STUCK TO THE CYLINDER BASE O-RINGS. 1H71 3R3 RNCA790 TC237 5 CP255 20020409000212002040900021NE 2002 4 9 AUS20020284 120020318G63207635109500043 GEARBOX SKRSKYS76 S76A 8143006NE TMECA ARRIELARRIEL1S 60030NE MAIN ROTOR MAKING METAL W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 AUS 1534 A08100352 (AUS) MAIN TRANSMISSION CHIP DETECTOR CONTAMINATED WITH METAL. AMOUNT OF METAL ON DETECTORS WAS BEYOND MANUFACTURERS LIMITS AND THE TRANSMISSION WAS CHANGED. 1G72 3U3 U H1NE E19EU 20020408001182002040800118SO 2002 4 8 AUS20020285 120020326G323095299 STUD PIPER PA32 PA32R300 7103213SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK2 GL LANDING GEAR RETCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN LANDING GEAR SIDE BRACE STUDS (2OFF) CRACKED IN RADIUS.FOUND DURING MPI INSPECTION IAW AD/PA32/79. 1L71 3O3 O A3SO 1E4 5 CP920 20020409000222002040900022EU 2002 4 9 AUS20020286 120020315G3260L1336 BULB BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE MLG INDICATOR BURNED OUT W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT LANDING GEAR DOWN AND LOCKED INDICATOR BULB BLOWN. 2H74 4F4 F A49EU E6NE 20020509000702002050900070NM 2002 5 9 AUS20020287 120020329G2731 BEARING DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE ELEVATOR TAB LACK OF LUBE W O OTHER F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) ELEVATOR TRIM TAB BEARING DRY. MOISTURE AND PAINT STRIPPER FOUND AROUND TRIM TAB BEARINGS AND ACTUATORS. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020510000012002051000001CE 2002 5 10 AUS20020288 120020328G32215842000211 TRUNNION CESSNA441 441 2076020CE NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 500 (AUS) NLG TRUNNION CRACKED. FOUND DURING INSPECTION IAW SBCQB00-3. 1L72 3T RTA28CE 20020510000022002051000002SW 2002 5 10 AUS20020289 120020327G3230KRP5064B ROLLER SWRNGNSA227 SA227* SW LANDING GEAR RETMISSING W O OTHER O OTHER CLCLIMB 1 AUS (AUS) LT MAIN LANDING GEAR UPLOCK ROLLER MISSING. SUSPECT ATTACHMENT BOLT SHEARED. 2L72 4T RTA5SW 20020510000032002051000003SW 2002 5 10 AUS20020290 120020125G52702720039039 SWITCH SWRNGNSA227 SA227* SW DOOR WARNING SYSFAULTY W O OTHER N FALSE WARNING CRCRUISE 1 AUS (AUS) CARGO DOOR WARNING SWITCH FAULTY. 2L72 4T RTA5SW 20020507000692002050700069GL 2002 5 7 AUS20020291 120020320G5302 SKIN ENSTRM F28C ENSTRMF28 F28C 3300407GL LYC O360 HIO360E1AD 41514EA ROTORCRAFT TAIL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 640 (AUS) TAIL CONE SKIN CRACKED IN AREA UNDER RADIO AERIAL. 1G71 3O3 O H1CE 1E10 20020510000042002051000004GL 2002 5 10 AUS20020292 120020320G5302VARIOUS BULKHEAD ENSTRMF28 F28C 3300407GL LYC O360 HIO360E1AD 41514EA TAILBOOM DAMAGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS 640 (AUS) TAIL BOOM BULKHEAD AND SKINS CRACKED. INCORRECT ANCHOR NUTFITTED. 1G71 3O3 O H1CE 1E10 20020510000052002051000005CE 2002 5 10 AUS20020293 120020327G5312 BULKHEAD CESSNA182 182P 2075816CE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT FORWARD DOORPOST BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/C180/75 A2. 1H71 3O NTTA13 20020507000702002050700070SO 2002 5 7 AUS20020294 120020327G3233451826 ACTUATOR PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR ACTLEAKING W K NONE O OTHER LDLANDING 1 AUS (AUS) NOSE LANDING GEAR ACTUATOR LEAKING. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020507000712002050700071EA 2002 5 7 AUS20020295 220020320G73102540888 DIAPHRAGM BENDIX 25241784 GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA HARTZLHCC3Y HCC3YR2 NE ENGINE FUEL DISTDAMAGED W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE CRCRUISE 1 AUS 1817 UJ6 (AUS) LH ENGINE MANIFOLD VALVE DIAPHRAGM TORN. LENGTH OF TEAR APPROXIMATELY 12.7MM (0.5IN). 1H72 3O3 O 6A1 1E4 5 CP25EA 20020510000062002051000006EU 2002 5 10 AUS20020296 120020402G2910HTE9531101 ISOLATION VALVE BAC 146 146100A 1500260EU LYC ALF502ALF502R3A 41580NE HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 AUS (AUS) NR 2 HYDRAULIC SYSTEM ISOLATION VALVE LEAKING INTERNALLY. 2H74 4F4 FRTA49EU E6NE 20020510000072002051000007 2002 5 10 AUS20020297 420020329G2565 BOTTLE BOEING767 767338 1385151NM GE CF6 CF680C2* GL ESCAPE SLIDE DISCHARGED W K NONE O OTHER ININSP/MAINT 1 AUS GV207 (AUS) FORWARD RT DOOR SLIDE INFLATION BOTTLE HAD NO PRESSURE. 2L72 4F4 FRTA1NM E23EA 20020510000082002051000008GL 2002 5 10 AUS20020298 320020327G6114C471658 HUB CESSNA188 A188A 2073008CE CONT O520 IO520* 17032SO MCAULY2A34C D2A34C98 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER HUB NR 2 SOCKET CRACKED. 1L71 3O3 O A9CE E5CE 5 CP3EA 20020510000092002051000009NM 2002 5 10 AUS20020299 120020327G3320BV0330211150 SOCKET DHAV DHC8 DHC8315 2809010NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE CABIN ARCED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 AUS (AUS) LT SIDE NR 2 FLUORESCENT TUBE END SOCKET ARCING. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020510000102002051000010WP 2002 5 10 AUS20020300 220020330G72618659307 SHAFT SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE SCAV PUMP SHEARED W O OTHER KEJFLUID LOSS VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 AUS 2578 (AUS) RT ENGINE OIL SCAVENGE PUMP SHAFT SHEARED. SHAFT THEN MIGRATED OUT OF THE SUPPORT HOUSING CAUSING DAMAGE TO ENGINE GEAR TRAIN AND SHAFT. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020507000722002050700072CE 2002 5 7 AUS20020301 120020321G28222B729 PUMP AIRBORNE 2B729 CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL FUEL BOOST PUMP RUSTED W K NONE E VIBRATION/BUFFET CLCLIMB 1 AUS 6AC181 (AUS) FUEL BOOST PUMP SOLENOID RUSTY CAUSING THE PUMP TO INTERMITTENTLY SWITCH TO HIGH' WHEN SELECTED TO LOW'. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020507000732002050700073NM 2002 5 7 AUS20020302 120020403G2841114001224 INDICATOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUEL QUANTITY INBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAGNA STICK INNER INDICATOR SCALE AND END FITTING MISSING.DAMAGE CAUSED TO LOWER WING SKIN. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020510000112002051000011CE 2002 5 10 AUS20020303 120020328G2460 CURRENT LIMITER BEECH 76 76 1153005CE LYC O360 O360A1G6D EA HARTZLHCM2Y HCM2YR GL DC POWER FAILED W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 AUS (AUS) PILOT EXPERIENCED COMPLETE LOSS OF ELECTRICAL POWER WHEN THE UNDERCARRIAGE WAS RETRACTED AFTER TAKE-OFF. INVESTIGATION FOUND THE BUS 1 AND 2 CURRENT LIMITERS BLOWN. FURTHER INVESTIGATION FOUND THE ALTERNATOR BLOCKING DIODE HAD AN UNSERVICEABLEINSULATOR THAT WAS SHORTING ALTERNATOR OUTPUTS TO EARTH. 1L72 3O3 O A29CE E286 5 CP43GL 20020510000122002051000012NM 2002 5 10 AUS20020304 120020329G3250257T4120 TILLER BOEING767 767338 1385151NM GE CF6 CF680C2* GL MLG STEERING STIFF W O OTHER O OTHER LDLANDING 1 AUS 00231 (AUS) FIRST OFFICERS TILLER GEARBOX STIFF IN OPERATION. 2L72 4F4 FRTA1NM E23EA 20020510000132002051000013NM 2002 5 10 AUS20020305 120020403G5210 HANDLE BOEING747 747338 NM RROYCERB211 RB211524D41954555NE PAX DOOR OUT OF ADJUST W O OTHER J WARNING INDICATION CRCRUISE 1 AUS (AUS) L5 DOOR HANDLE RIGGING OUT OF ADJUSTMENT. 2L72 4F4 FRTA20WE E12EU 20020507000742002050700074NM 2002 5 7 AUS20020307 120020403G56108SC0043008 WINDSHIELD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FLIGHT COMPARTMEDELAMINATED W K NONE O OTHER CRCRUISE 1 AUS (AUS) FIRST OFFICERS WINDSHIELD DELAMINATED BEYOND LIMITS. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020507000752002050700075NM 2002 5 7 AUS20020308 120020403G573085700001001 SKIN DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE WING, PLATES/SKIDAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LOWER WING SKIN DAMAGED WHEN MAGNA STICK FAILED AND SEPARATED FROM THE AIRCRAFT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020507000762002050700076EU 2002 5 7 AUS20020310 120020106G54207254200016 CHANNEL SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE ROTOL R390 R3904123F27 NE NACELLE/PYLON, MCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 34097 (AUS) RH ENGINE NACELLE CHANNEL CRACKED UNDER DOUBLER AT STN NS 240. 2L72 4T4 TRTA52EU E8NE 6 CP31NE 20020513000012002051300001EA 2002 5 13 AUS20020311 120020323G2430A700ZF RELAY CURTISP40 P40NREED 2622206EA ALLSN V1710 V1710* GL DC GENERATING SYFAULTY W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 AUS AVR605 (AUS) REVERSE CURRENT RELAY (RCR) FAILED. BATTERY DISCHARGED ANDRESULTED IN A TOTAL POWER FAILURE. 1L71 4V4 V L182 EXPE4V 20020507000772002050700077NM 2002 5 7 AUS20020312 120020405G5610NAS44037 SCREW DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FLIGHT COMPARTMEBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FIRST OFFICERS FORWARD WINDSHIELD HAD TWO SCREWS WITH BROKENHEADS. SHANK AND THREADS STILL IN PLACE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020507000782002050700078NM 2002 5 7 AUS20020313 120020301G3210MS24586C192 SPRING DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MAIN LANDING GEABROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR LOCK SPRING BROKEN. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020510000512002051000051EU 2002 5 10 AUS20020314 120020404G2421503106680003 GENERATOR PLESSEY 50306710000 BAC 146 146100A 1500260EU LYC ALF502ALF502R3A 41580NE AC GENERATOR CONTAMINATED W O OTHER H ELECT. POWER LOSS-50 PC CLCLIMB 1 AUS TE1206 (AUS) NR 1 INTEGRATED DRIVE GENERATOR CONTAMINATED. OPEN CIRCUIT ON FIELD WINDINGS. 2H74 4F4 FRTA49EU E6NE 20020507000792002050700079SW 2002 5 7 AUS20020315 120020407G5753NAS130838D BOLT SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL TRAILING EDGE FLBROKEN W K NONE F FLT CONT AFFECTED NRNOT REPORTED 1 AUS PN2736043010 (AUS) RH OUTBOARD FLAP ATTACHMENT BRACKET AND FLAP DISTORTED. INVESTIGATION FOUND THE BELLCRANK ATTACHMENT BOLT BROKEN. DAMAGEWAS FOUND TO A NUMBER OF RIBS AND BRACKETS LOCATED IN THE FLAPRECESS. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20020510000662002051000066NM 2002 5 10 AUS20020316 120020328G5514 BEAM BOEING737 73733A 1384673NM CFMINTCFM56 CFM563B2 13802EU HORIZONTAL STAB CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT HORIZONTAL STABILIZER UPPER TRAILING EDGE BEAM CORRODED IN AREA OF ELEVATOR STA 111. 2L72 4F4 FRTA16WE E21EU 20020510000672002051000067WP 2002 5 10 AUS20020317 220020402G7261 O-RING FLTCHR24 FU24AIRPTS 3530202WP GARRTTTPE331TPE33110 01514WP OIL FILTER FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE OIL FILTER O-RING SEAL RETAINING LAND WORN AND BROKEN AWAY. 1L71 3O4 T 4A12 E4WE 20020510000682002051000068NM 2002 5 10 AUS20020318 120020406G2910BACT16AS060608W FITTING BOEING737 737400 138449ANM CFMINTCFM56 CFM563C 13802EU HYD SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) HYDRAULIC SYSTEM TEE FITTING CRACKED AND CORRODED. FITTING IS IN THE HYDRAULIC LINE TO THE LH HEAT EXCHANGER. 2L72 4F4 FRTA16WE E21EU 20020507000802002050700080NM 2002 5 7 AUS20020319 120020406G7830315A18141 NUT GE CFM563C BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU THRUST REVERSER WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO1 ENGINE THRUST REVERSER FAULTY. FEEDBACK LEVER AND CABLE COULD BE MOVED FROM THE STOWED POSITION TO THE DEPLOYED POSITION WITH THE THRUST REVERSER LOCKED OUT. INVESTIGATION FOUND THE PROBLEM WAS CAUSED BY WEAR ON THE FEEDBACK NUT PNO 315A1814-1. 2L72 4F4 FRTA16WE E21EU 20020507000812002050700081NM 2002 5 7 AUS20020320 120020404G27616544851 HOUSING BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU DRAG CONTROL ACTBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING NO4 GROUND SPOILER OUTBOARD ACTUATOR HOUSING HAD A SMALLPIECE OF THE BEARING LUG BROKEN AWAY. 2L72 4F4 FRTA16WE E21EU 20020507000822002050700082EA 2002 5 7 AUS20020321 220020302G853073413 PUSHROD LYC O320B2C ROBSINR22 R22ALPHA 7640104WP LYC O320 O320B2C 41508EA RECIPROCATING ENDISTORTED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 AUS 330 L1180039A (AUS) NO4 CYLINDER EXHAUST VALVE PUSHROD BENT. EXHAUST VALVE DID NOTAPPEAR TO BE STUCK OR TIGHT IN THE VALVE GUIDE. 1G71 3O3 O H10WE E274 20020510000692002051000069WP 2002 5 10 AUS20020323 220020327G72613102173 PUMP CESSNA441 441 2076020CE GARRTTTPE331TPE3318 01514WP HARTZLHCB3T HCB3TN5 GL LT ENGINE CRACKED W O OTHER KE FLUID LOSS VIBRATION/BUFFET CRCRUISE 1 AUS 72 (AUS) LT ENGINE OIL PRESSURE PUMP CRACKED. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20020507000832002050700083EA 2002 5 7 AUS20020324 220020330G8520 CRANKSHAFT LYC O540E4C5 BNORM BN2 BN2A 1520204EU LYC O540 O540E4C5 41532EA RECIPROCATING ENFAILED W K NONE ED VIBRATION/BUFFET INFLIGHT SEPARATION CLCLIMB 1 AUS (AUS) CRANKSHAFT FRACTURED IN AREA JUST FORWARD OF THE NO2 MAIN BEARING. CRANKCASE FRACTURED AND SEPARATED FROM ENGINE. PROPELLER SEPARATED. DAMAGE TO COWLS AND FUSELAGE. AIRCRAFT ISREGISTERED IN VANUATU. 1H72 3O3 O A17EU E295 20020507000842002050700084CE 2002 5 7 AUS20020325 120020313G2720VARIOUS BOLT BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE RUDDER CONTROL SLOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 3775 (AUS) FORWARD RUDDER PUSH-PULL TUBE FORWARD BELLCRANK BOLTS LOOSE. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020507000852002050700085NM 2002 5 7 AUS20020326 120020405G3250980222001 SWITCH PIPER PA60 PA60601P 7106012NM LYC O540 TIO540S1AD 41532EA HARTZLHCC3Y HCC3YR2 NE LANDING GEAR STEINTERMITTENT W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NOSE LANDING GEAR STEERING SWITCH INTERMITTENT IN OPERATION.BRAKE CALIPERS LEAKING. 1M72 3O3 ORTA17WE E14EA 5 CP25EA 20020510000702002051000070EA 2002 5 10 AUS20020327 220020405G7314BB017 SEAL NEWZE FU24 FU24954 6280102WP LYC O720 IO720A1B 41546EA HARTZLHCC3Y HCC3YR GL ENGINE FUEL PUMPLEAKING W K NONE O OTHER ININSP/MAINT 1 AUS 284 (AUS) ENGINE FUEL PUMP REAR SEAL LEAKING. FOUND DURING INSPECTION IAW AD/FSM/25. 1L71 3O3 O A9PC 1E15 5 CP25EA 20020510000712002051000071CE 2002 5 10 AUS20020328 120020328G2700 CONTROL CABLE CESSNA206 U206G 2073356CE CONT O520 IO520* 17032SO MCAULYD3A34 D3A34C404 GL FLIGHT CONTROLS WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ALL AILERON SYSTEM CABLES AND FLAP CABLES (4OFF) HAD BROKEN STRANDS OR WERE WORN EXCESSIVELY. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020510000722002051000072CE 2002 5 10 AUS20020329 120020328G7603 BRACKET CESSNA206 U206G 2073356CE CONT O520 IO520* 17032SO MCAULYD3A34 D3A34C404 GL POWER LEVER MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) THROTTLE AND MIXTURE CABLE CLAMP BRACKET INSTALLED UPSIDE DOWN. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020510000732002051000073SO 2002 5 10 AUS20020330 220020328G8550 LINE CESSNA206 U206G 2073356CE CONT O520 IO520* 17032SO MCAULYD3A34 D3A34C404 GL ENGINE OIL LOOSE W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) CRANKCASE OIL PRESSURE LINE LOOSE. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020507000862002050700086GL 2002 5 7 AUS20020331 220020328G753223039404 BLEED VALVE ALLSN 23039404 HUGHES369 369E 4470707WP ALLSN 25OC 250C20R GL COMPRESSOR BLEEDFAULTY W K NONE E VIBRATION/BUFFET DEDESCENT 1 AUS 678 FF32777 (AUS) COMPRESSOR BLEED VALVE SUSPECT STICKING. 1G71 3U3 U H3WE E4CE 20020507000872002050700087CE 2002 5 7 AUS20020332 120020328G712005510171 MOUNT LYC O320E2D CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE MOUNT SECCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE MOUNT CRACKED IN AREA OF LOWER CROSSOVER TUBE. 1H71 3O3 ONT3A12 E274 5 NP910 20020507000882002050700088CE 2002 5 7 AUS20020333 120020321G712005510171 MOUNT LYC O320E2D CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE MOUNT SECCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE MOUNT CRACKED IN AREA OF LOWER CROSSOVER TUBE. 1H71 3O3 ONT3A12 E274 5 NP910 20020510000742002051000074NM 2002 5 10 AUS20020334 120020408G2750 CONTROL CABLE BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE TE FLAPS MISROUTED W O OTHER WF INADEQUATE Q C FLT CONT AFFECTED LDLANDING 1 AUS (AUS) FLAP CABLE RUN NR 244B BROKEN. FLAP CABLE RUN NO 242B FRAYED. INVESTIGATION FOUND THE CABLES HAD BEEN INCORRECTLY ROUTED ON THE WRONG SIDE OF THE PULLEY CABLE KEEPER. SUSPECT CAUSED DURINGAIRCRAFT MANUFACTURE. PERSONNEL/MAINTENANCE/MANUFACTURING ERROR. 2L72 4F4 FTRA6WE E00061EN 20020510000792002051000079NE 2002 5 10 AUS20020335 220020402G73211853M33P06 EEC BOEING737 737800* NM GE CFM56 CFM567B24 NE LT ENGINE FAILED W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION LDLANDING 1 AUS (AUS) LT ENGINE ELECTRONIC CONTROL UNIT (EEC) SUSPECT FAILED. 2L72 4F4 FRTA16WE E00055EN 20020507000892002050700089NM 2002 5 7 AUS20020336 120020124G5312 BULKHEAD BOEING727 7272J4 1384006NM PWA JT8 JT8D17 52049NE FUSELAGE MAIN, BCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 55274 (AUS) FUSELAGE BULKHEAD LOCATED AT BS 950 CONTAINED LEVEL 2 CORROSION IN LOWER CHORD. 2L73 4F4 FRTA3WE E2EA 20020510000802002051000080NM 2002 5 10 AUS20020337 120020124G5314 KEELBEAM BOEING727 7272J4 1384006NM PWA JT8 JT8D17 52049NE FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 55274 (AUS) KEELBEAM EXTENSION CONTAINED LEVEL 2 CORROSION IN THE AREA LOCATED BETWEEN STN BS 950.12 AND BS 957.12 BL6L. 2L73 4F4 FRTA3WE E2EA 20020510000812002051000081NM 2002 5 10 AUS20020338 120020409G26206546858302 LINE BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU EXTINGUISHER DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FIRE EXTINGUISHER LINE AND B-SYSTEM CASE DRAIN LINE CHAFING IN AREA ADJACENT TO NR 6 FLAP TRACK. HOLE WORN IN EXTINGUISHER LINE. 2L72 4F4 FRTA16WE E21EU 20020510000822002051000082CE 2002 5 10 AUS20020339 120020410G81204066109028 TURBOCHARGER CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL ENGINE FAILED W C ABORTED TAKEOFF RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET TOTAKEOFF 1 AUS 94 (AUS) ENGINE TURBOCHARGER FAULTY. INVESTIGATION FOUND BLADE TIP RUBBING AND SHAFT BENT. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020507000902002050700090CE 2002 5 7 AUS20020340 120020329G534212324001 BRACKET CESSNA210 210M 2073450CE LYC MCAULYD3A34 D3A34C402 GL FUSELAGE, STABILCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH REAR HORIZONTAL STABILISER ATTACHMENT BRACKET CRACKED. 1H71 3O 3A21 5 CP47GL 20020510000832002051000083SW 2002 5 10 AUS20020342 120020410G291027810322683 LINE SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UA 01514WP MCAULY4HFR344HFR34C652 NE HYD SYSTEM LEAKING W O OTHER K FLUID LOSS LDLANDING 1 AUS (AUS) STAINLESS STEEL HYDRAULIC PRESSURE LINE WORN THROUGH ON ADEL CLAMP BOLT. PIPE IS LOCATED BETWEEN HYDRAULIC PUMP AND FIREWALL. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020507000912002050700091NE 2002 5 7 AUS20020343 220020319G73200301037290 PIPE TMECA ARRIEL1D1 SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE FUEL CONTROLLINGLOOSE W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS 9103 (AUS) P2 REGULATOR PIPE FROM THE COMPRESSOR SCROLL TO THE FCU LOOSE.PERSONNEL/MAINTENANCE ERROR. 1G71 3U3 U H9EU E19EU 20020510000842002051000084SW 2002 5 10 AUS20020344 120020411G6220471201171 HUB BELL 47 47G3B1 1181028SW LYC O435 TVO435B1A 41516EA MAIN ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 968 (AUS) MAIN ROTOR HUB CRACKED IN AREA OF BEARING SPINDLE RADIUS. FOUND DURING INSPECTION IAW AD/BELL47/72 A2. 1G71 3O3 O 2H3 1E13 20020507000922002050700092CE 2002 5 7 AUS20020345 120020303G574112210302 FITTING CESSNA 210M CESSNA210 210M 2073450CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C404 GL WING, FUSELAGE AFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING ATTACHMENT FITTING CONTAINED A SUBSURFACE DEFECT IN THE AREA ADJACENT TO BUT NOT INTO THE MAIN WING ATTACHMENT BOLT HOLE. FOUND DURING EDDY CURRENT INSPECTION. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020510000852002051000085EU 2002 5 10 AUS20020346 120020412G2910HTE96352 SELECTOR VALVE BAC 146 146100A 1500260EU LYC ALF502ALF502R5 41580NE HYD SYSTEM LEAKING W C ABORTED TAKEOFF KJ FLUID LOSS WARNING INDICATION TOTAKEOFF 1 AUS (AUS) YELLOW HYDRAULIC SYSTEM SELECTOR VALVE INTERNAL LEAK. 2H74 4F4 FRTA49EU E6NE 20020507000932002050700093CE 2002 5 7 AUS20020347 120020403G554051310123 HINGE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL RUDDER STRUCTURECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CENTRE RUDDER HINGE CRACKED ON LH SIDE OF THE LOWER SIDE OF THE FORWARD HALF. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020510000862002051000086NM 2002 5 10 AUS20020348 120020415G2761NAS161210 O-RING BOEING767 767338 1385151NM GE CF6 CF680C2* GL DRAG ACTUATOR LEAKING W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 AUS (AUS) NR 1 SPOILER ACTUATOR FILTER BLANKING PLUG O-RING SEAL LEAKING. LOSS OF HYDRAULIC FLUID. 2L72 4F4 FRTA1NM E23EA 20020510000872002051000087EU 2002 5 10 AUS20020349 120020415G2740AN2418A BOLT PARTENP68 P68B 6780104EU LYC O360 IO360A1B6 41514EA HARTZLHCC2Y HCC2YK2 GL STAB CONTROL MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) STABILATOR FORWARD CONTROL ROD BOLT INSTALLED IN INCORRECT DIRECTION. 1H72 3O3 O A31EU 1E10 5 CP920 20020510000882002051000088EU 2002 5 10 AUS20020350 120020416G274068330252 KEY PARTENP68 P68B 6780104EU LYC O360 IO360A1B6 41514EA HARTZLHCC2Y HCC2YK2 GL STAB CONTROL UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) STABILATOR KEYS (2OFF) WERE UNAPPROVED HANDMADE PARTS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1H72 3O3 O A31EU 1E10 5 CP920 20020507000942002050700094SW 2002 5 7 AUS20020351 120020408G32135200011 STRUT MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA MCAULY2D34C 2D34C53 GL MAIN LANDING GEACRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH MAIN LANDING GEAR LEG ASSEMBLY CRACKED AT THE UPPER FORWARDWELD JOINT. 1L71 3O3 O 2A3 E286 5 CP7EA 20020507000952002050700095SW 2002 5 7 AUS20020352 120020415G2510 SEAT BELT MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA MCAULY2D34C 2D34C53 GL FLIGHT COMPARTMEFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) BOTH FORWARD SEAT BELTS WERE OF UNKNOWN ORIGIN WITH NOIDENTIFICATION LABLES. BELTS WERE IN EXTREMELY POOR CONDITION.BELTS DID NOT MEET THE REQUIREMENTS OF AD/RES/29. UNAPPROVEDPART. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O 2A3 E286 5 CP7EA 20020510000892002051000089 2002 5 10 AUS20020353 420020318G2565 PIN BOEING767 767338 1385151NM GE CF6 CF680C2* GL ESCAPE SLIDE INSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT AND RT FORWARD DOORS AND LT AFT DOOR ESCAPE SLIDES HAD MAINTENANCE SAFETY PINS INSTALLED. PERSONNEL/MAINTENANCE ERROR. 2L72 4F4 FRTA1NM E23EA 20020510000902002051000090EU 2002 5 10 AUS20020354 120020414G2460MS33205 CIRCUIT BREAKER SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE ROTOL R375 R3754123F21 NE DC POWER FAULTY W O OTHER BN SMOKE/FUMES/ODORS/SPARKS FALSE WARNING CRCRUISE 1 AUS (AUS) CARGO/LAVATORY CIRCUIT BREAKER SUSPECT FAULTY. 2L72 4T4 TRTA52EU E8NE 6 CP17NE 20020510000912002051000091CE 2002 5 10 AUS20020355 120020417G323398820041 PISTON CESSNA210 210R 2073458CE CONT O520 IO520L 17032SO MLG ACTUATOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN LANDING GEAR ACTUATOR PISTON AND GEAR TEETH DAMAGED. FOUND DURING INSPECTION IAW SEB 01-2 REV1. SUSPECT DAMAGE OCCURRED DURING A PREVIOUS ACCIDENT. 1H71 3O3 ORT3A21 E5CE 20020510000922002051000092GL 2002 5 10 AUS20020356 320020412G6114C32303 HUB PIPER PA28 PA28236 7102815SO LYC O540 O540J3A5 41532EA HARTZLHCF2Y HCF2YR1 GL PROPELLER MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) PROPELLER HUB HAD BEEN MACHINED IN THE AREA OF THE PRELOAD PLATE SHELF TO REMOVE DAMAGE CAUSED BY A GROUND STRIKE. MACHINING INTHIS AREA IS NOT APPROVED BY THE MANUFACTURER. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O 2A13 E295 5 CP27EA 20020510000932002051000093CE 2002 5 10 AUS20020357 120020410G250018836C200 RELAY BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE STRETCHER LOAD FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STRETCHER LOADING DEVICE RELAY FAILED. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020510000942002051000094NM 2002 5 10 AUS20020358 120020414G27824135T1003 ACTUATOR BOEING767 767338 1385151NM GE CF6 CF680C2* GL LE SLATS FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) INBOARD LEADING EDGE SLAT DRIVE ACTUATOR FAILED. 2L72 4F4 FRTA1NM E23EA 20020510000952002051000095NE 2002 5 10 AUS20020359 120020316G64107610105501042 BLADE SKRSKYS76 S76B 8143007NE TAIL ROTOR CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAIL ROTOR BLADE HONEYCOMB CONTAMINATED WITH WATER. 1G72 4U H1NE 20020510000962002051000096SW 2002 5 10 AUS20020360 120020320G2434302391 DIODE BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA NR 2 DC GEN FAILED W O OTHER H ELECT. POWER LOSS-50 PC CLCLIMB 1 AUS (AUS) NR 2 GENERATOR OFF LINE, THE EMERGENCY BUS INTERCONNECT CIRCUIT BREAKER POPPED, PILOT LOST POWER TO THE NR 2 BUS. INVESTIGATION FOUND 2 DIODES ON THE EMERGENCY BUS FAILED RESISTANCE CHECK. 1G72 4U4 U H4SW E22EA 20020510000972002051000097EA 2002 5 10 AUS20020361 220020320G731010544E SLEEVE BELL 412 412 1182202SW PWA PT6T PT6T3 52045EA FUEL LINE WORN W K NONE O OTHER ININSP/MAINT 1 AUS 920 (AUS) THE FIRE SLEEVE OF FUEL HOSE (PN 10544E) WAS FOUND CHAFFED APPROX 0.005 IN (0.127MM) IN DEPTH THROUGH WALL OF FUEL HEATER. 1G72 4U4 U H4SW E22EA 20020510000982002051000098NM 2002 5 10 AUS20020362 120020413G7830LJ76662 SEGMENT BOEING757 75723A 1384967NM RROYCERB211 RB211535E4 54555NE THRUST REVERSER SEPARATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING INSPECTION, THE LT ENGINE INBOARD THRUST REVERSER NR 1 CASCADE (PN LJ76662) AND THE SUPPORT RING SECTION (PN LJ7599) WERE FOUND MISSING. 2L72 4F4 FRTA2NM E12EU 20020507000962002050700096NM 2002 5 7 AUS20020363 120020412G3230AS4624J030055 HOSE BOEING767 76733A 1385209NM LANDING GEAR RETRUPTURED W K NONE O OTHER CLCLIMB 1 AUS (AUS) RH MLG WOULD NOT RETRACT DURING CLIMB. GROUND INVESTIGATION FOUND THE HYDRAULIC HOSE CONNECTED TO THE 'UP' ACTUATOR HAD RUPTURED. 2L72 4F RTA1NM 20020507000972002050700097EA 2002 5 7 AUS20020364 220020418G853015F22200 PUSHROD LYC O235L2C CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1091 L1909915 (AUS) DURING PERIODIC ENGINE INSPECTION, THREE PUSHRODS WERE FOUNDCRACKED AT THE BALLENDS. TWO HAD CRACKS 0.470IN (12MM) LONG AND THE THIRD HAD A CRACK JUST STARTING. 1H71 3O3 ONT3A19 E223 20020510000992002051000099EU 2002 5 10 AUS20020365 120020418G3230SA7670006128 HOSE BAG BAE146BAE146300A 1500267EU LYC ALF502ALF502R5 41580NE MLG RUPTURED W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 AUS (AUS) AIRCRAFT SUFFERED GREEN SYSTEM HYDRAULIC FLUID LOSS DURING TAXI.INSPECTION FOUND THAT THE FLEXIBLE EXTEND HOSE TO THE NOSELANDING GEAR ACTUATOR HAD RUPTURED. 2H74 4F4 FRTA49EU E6NE 20020510001002002051000100NM 2002 5 10 AUS20020366 120020404G3830NAS192201253 CLAMP BOEING737 737800* NM WASTE DISPOSAL MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) FORWARD GALLEY SINK DRAIN HOSE FOUND NOT CONNECTED TO FLOOR HOSE DUE TO A MISSING CLAMP, CAUSING LEAKAGE THROUGHOUT GALLEY AREA. PERSONNEL/MAINTENANCE ERROR. 2L72 4F RTA16WE 20020507000982002050700098SO 2002 5 7 AUS20020367 120020417G3260922AA2YA6PZ722 PROXIMITY SENSOR EMB 120 EMB120 3260201SO LANDING GEAR POSFAULTY W K NONE J WARNING INDICATION DEDESCENT 1 AUS (AUS) ON APPROACH TO LAND, LANDING GEAR WAS SELECTED DOWN AND THE LH MAIN LANDING GEAR SYSTEM 'A' RED LIGHT REMAINED ILLUMINATED. GROUND INVESTIGATION FOUND THE LH MAIN LANDING GEAR SYSTEM 'A'PROXIMITY SENSOR OPERATING INTERMITTENTLY. 2L72 4T RTA31SO 20020510001012002051000101NM 2002 5 10 AUS20020368 120020420G7120 FAIRING BOEING747 747438 NM RROYCERB211 RB211524* NE ENGINE MOUNT MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING A TRANSIT INSPECTION OF NR 3 ENGINE, THE FAIRING AROUNDTHE 'A' FRAME STRUT (10 O'CLOCK POSITION) WAS FOUND MISSING. 2L74 4F4 FRTA20WE E12EU 20020510001022002051000102NM 2002 5 10 AUS20020369 120020420G2910AS11708K0165 LINE BOEING767 767338 1385151NM GE CF6 CF680C2* GL HYDRAULIC SYSTEMRUPTURED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) DURING TAXI FOR TAKE-OFF, THE RT HYDRAULIC QUANTITY DECREASED TO ZERO WITH ASSOCIATED SYSTEM AND PRESSURE LIGHTS ILLUMINATING. INVESTIGATION FOUND THAT THE PRESSURE LINE FROM THE AC PUMP HAD BURST. 2L72 4F4 FRTA1NM E23EA 20020507000992002050700099NM 2002 5 7 AUS20020370 120020411G2620 LANYARD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE EXTINGUISHING SYMISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING SCHEDULED MAINTENANCE IT WAS DISCOVERED THAT A LANYARD INSTALLED BY SB8-26-9 WAS MISSING. IT WAS ALSO FOUND THAT THE P2AND P4 LANYARDS HAD BEEN FITTED TO THE INCORRECT SQUIBS.PERSONNEL/MAINTENANCE ERROR. 2H72 4T4 TRTA13NM E20NE 20020510001032002051000103NM 2002 5 10 AUS20020371 120020420G2781189929 SENSOR BOEING737 737400 138449ANM LE SLAT FAILED W O OTHER N FALSE WARNING CLCLIMB 1 AUS (AUS) AFTER TAKE-OFF, THE LEADING EDGE TRANSIT LIGHT REMAINED ILLUMINATED. INVESTIGATION FOUND THAT THE NR 2 LEADING EDGE FLAP EXTEND SENSOR HAD FAILED. 2L72 4F RTA16WE 20020510001042002051000104NM 2002 5 10 AUS20020372 120020418G275265B156398 CAM BOEING747 747438 NM RROYCERB211 RB211524* NE TE FLAPS SHEARED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING A TRANSIT INSPECTION, A FLAP ROD WAS FOUND PROTRUDING FROM THE NR 7 FLAP TRACK FAIRING.INVESTIGATION FOUND THE AFT FLAP SEQUENCING ROD BROKEN AND THE 'GENEVA' CAM MECHANISM SHEARED. 2L74 4F4 FRTA20WE E12EU 20020510001052002051000105EU 2002 5 10 AUS20020373 120020423G32465010488 WHEEL SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE MLG FRACTURED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING A TURN-A-ROUND INSPECTION, THE PILOT DISCOVERED A 7.8IN(20CM) BEAD SECTION MISSING FROM THE NR 3 MAIN WHEEL AND THE TIRE WAS DEFLATED. 2L72 4T4 TRTA52EU E8NE 20020510001062002051000106NM 2002 5 10 AUS20020374 120020422G3240AS11506K0280 LINE BOEING767 767338 1385151NM GE CF6 CF680C2* GL MLG BRAKES LEAKING W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) AT AIRCRAFT ARRIVAL, HYDRAULIC FLUID WAS NOTED FLOWING FROM THE TOP OF THE RH MAIN LANDING GEAR.LEAK WAS TRACED TO A FLEXIBLE BRAKE LINE ABOVE THE OLEO. 2L72 4F4 FRTA1NM E23EA 20020510001072002051000107NM 2002 5 10 AUS20020375 120020423G215078279016 ACM DHAV DHC8 DHC8202 2809007NM CABIN COOLING FAULTY W O OTHER O OTHER CRCRUISE 1 AUS 2250 (AUS) UNABLE TO REDUCE AIR CONDITIONING DUCT TEMPERATURE BELOW 18 DEGREES MANUAL AND AUTO CABIN TEMPERATURE WAS EXCESSIVE. INVESTIGATION FOUND THAT THE AIR CYCLE MACHINE HAD A SMALL AIRLEAK EMINATING FROM THE TURBINE SEAL FACE. 2H72 4T RTA13NM 20020513000022002051300002NM 2002 5 13 AUS20020376 120020425G32338300101 ACTUATOR DHAV DHC8 DHC8315 2809010NM PWA PW120 PW123 NE MLG CONTAMINATED W O OTHER J WARNING INDICATION LDLANDING 1 AUS (AUS) WHEN LANDING GEAR WAS SELECTED DOWN, THE NLG FAILED TO EXTEND WITH BOTH THE GEAR DOOR AND UNSAFE LIGHTS ILLUMINATED. AFTER APPROXIMATELY ONE MINUTE THE NLG EXTENDED AND LOCKED DOWN WITH NO INPUT FROM CREW. INVESTIGATION FOUND THAT THE NLG ACTUATOR CONTAINED A CONTAMINANT WITHIN THE UNIT. 2H72 4T4 TRTA13NM E20NE 20020507001002002050700100SO 2002 5 7 AUS20020378 220020419G8530643767P005 VALVE GUIDE CONT IO520L CESSNA210 210L 2073448CE CONT O520 IO520L 17032SO RECIPROCATING ENLOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 517 (AUS) NO.2 CYLINDER REVEALED A LEAKING EXHAUST VALVE DURING A COMPRESSION TEST AND ON DISASSEMBLY THE EXHAUST AND INLET GUIDESFELL OUT OF THE HEAD. FURTHER INVESTIGATION OF THE REMAINING CYLINDERS FOUND THAT THE NO.4 CYLINDER INLET GUIDE WAS ALSO LOOSE IN HEAD. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 O 3A21 E5CE 20020513000032002051300003SO 2002 5 13 AUS20020379 120020205G2913 BRUSHES PIPER PA28 PA28R180 7102809SO LYC O360 IO360B1E 41514EA HARTZLHCC2Y HCC2YK1 GL HYD PUMP MOTOR WORN W O OTHER J WARNING INDICATION DEDESCENT 1 AUS (AUS) MLG HYDRAULIC PUMP MOTOR FAILED TO OPERATE DUE TO WORN BRUSHES. 1L71 3O3 O 2A13 1E10 5 CP920 20020513000042002051300004NE 2002 5 13 AUS20020380 220020425G7200RB211 ENGINE BOEING747 747338 NM RROYCERB211 RB211524D41954555NE NR 4 FAILED W C ABORTED TAKEOFF XJ ENGINE FLAMEOUT WARNING INDICATION TOTAKEOFF 1 AUS 7010 (AUS) ON ROTATION A LOUD BANG WAS HEARD AND NR 4 EPR INDICATION DROPPED AND SPARKS WERE REPORTED FROM THE NR 4 ENGINE. THE ENGINE WAS SHUT DOWN. 2L72 4F4 FRTA20WE E12EU 20020513000052002051300005SW 2002 5 13 AUS20020382 120020228G27107300051 CONTROL ROD MOONEYM20 M20C 5870208SW CONT IO360 IO360* 17025CE AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT AILERON CONTROL LINKS CRACKED. FOUND IAW AD/M20/52 & MOONEY SB M20-264. 1L71 3O3 O 2A3 E1CE 20020507001012002050700101NE 2002 5 7 AUS20020383 220020415G75322856201 BLEED VALVE SEMCA 2856201 SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE COMPRESSOR BLEEDMALFUNCTIONED W K NONE R PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS 27 178 (AUS) PILOT REPORTED CHANGES IN ENGINE PERFORMANCE WITH DECREASE IN ENGINE TORQUE AND INCREASE IN COMPRESSOR RPM. SUSPECT A RECENTLY FITTED COMPRESSOR BLEED VALVE WAS INCORRECTLY SET-UP AT OVERHAULFOR MODULATION POINT OPERATION. 1G71 3U3 UNCH9EU E19EU 20020513000062002051300006 2002 5 13 AUS20020384 420020419G34244714E INDICATOR GULSTM500 500B 0141106SW LYC O540 IO540E1B5 41532EA TURN AND BANK DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 636 (AUS) TURN COORDINATOR INDICATION ON RT TURN ONLY. INVESTIGATION FOUND INTERNALLY THAT THE INDICATOR FORK HAD DISLODGED FROM THE ROTOR BUMP POST. 1H72 3O3 O 6A1 1E4 20020507001022002050700102CE 2002 5 7 AUS20020385 120020422G323024411001 PIVOT CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA LANDING GEAR RETCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) BOTH LH AND RH MLG PIVOT ASSEMBLIES SUSPECTED CRACKED. DYECHECKING PIVOTS LATER DID NOT SHOW CLEARLY ANY DEFECTS. INSPECTION CARRIED OUT IAW AD/CESSNA 170/69. 1H71 3O3 O 3A17 E286 20020613000342002061300034CE 2002 6 13 AUS20020386 120020422G323312810013 ACTUATOR CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT MLG ACTUATOR CRACKED. FOUND DURING INSPECTION IAW SEB01-2. 1H71 3O3 O 3A17 E286 5 CP7EA 20020613000362002061300036NM 2002 6 13 AUS20020390 120020321G57206512601185 BRACKET BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE LT WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 40425 (AUS) LT WING BRACKET ATTACHED TO LOWER CHORD DELAMINATED FROM CORROSION ZONE 72, STN WS204.0. CPCP - LEVEL 2 CORROSION. 2L73 4F4 F A3WE E2EA 20020613000382002061300038NM 2002 6 13 AUS20020392 120020322G5511 SPAR BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE HORIZONTAL STAB CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 40425 (AUS) HORIZONTAL STABILISER CENTRAL UPPER REAR SPAR AREA CORRODED ZONE97 STN BS1586.81. CPCP - LEVEL 2 CORROSION. 2L73 4F4 F A3WE E2EA 20020613000422002061300042NM 2002 6 13 AUS20020398 120020315G5347CZ4952 SEAT TRACK BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 40425 (AUS) SEAT TRACK CORRODED AT ZONE 24 STA 1130 TO STA 1110 LBL 2475 LT.CPCP - LEVEL 2 CORROSION. 2L73 4F4 F A3WE E2EA 20020613000892002061300089EA 2002 6 13 AUS20020404 220020430G7314RG17980 PUMP BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL ENGINE FUEL WRONG PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) AFTER ENGINE CHANGE AND DURING GROUND RUNS THE ENGINE FAILED WHEN THE BOOST PUMP WAS TURNED OFF. SUBSEQUENT INVESTIGATION FOUND THAT THE INCORRECT FUEL PUMP PN RG17980 WAS FITTED AT OVERHAUL IN LIEU OF PUMP PN RG17980D. BECAUSE THE INLET PORT IS ON THE OPPOSITE SIDE OF THE PUMP THE USE OF THIS PUMP CAUSES THE AIRFRAME SUPPLY TO BE CONNECTED TO THE PUMP OUTLET AND VICE VERSA. THE SPLINE LENGTH OF THE INCORRECT PUMP IS SHORTER THAN THAT OF THE CORRECT ITEM AND ONLY ENGAGES BY APPROXIMATELY 6.3MM(0.25IN). 1H72 3O3 O A17EU 1E4 5 CP920 20021127000642002112700064CE 2002 11 27 AUS20020407 120020502G32221158200683 FORK BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL NOSE/TAIL LANDINUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NLG ASSEMBLY TUBE UNCHROMED PORTION EXCEEDED 1.27MM (0.050IN) AND LENGTH OF THE TUBE EXCEEDED 91MMM (23.10IN). FOUND DURING INSPECTION IAW AD/BEECH200/45 AND SB2102 REV5. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020613001272002061300127SO 2002 6 13 AUS20020410 220020405G73221048931 CARBURETOR CESSNA182 182K 2072724CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL ENGINE MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) DURING GROUND RUNS FOLLOWING ENGINE CHANGE THE ENGINE WAS FOUND TO BE RUNNING ROUGH, TOO LEAN AND MIXTURE ADJUSTMENT WOULD NOT CORRECT THE FAULT. CARBURETOR WAS DISMANTLED AND THE FOLLOWING DEFECTS DISCOVERED:- 1. MAIN JET INCORRECT PN. 2. AIR METERING JET INCORRECT PN (USED) 3. AIR METERING PIN SPRING UNSERVICEABLE. 4. AIR METERING/ACCELERATION PUMP LINKAGE WORN AND NOT SECURED CORRECTLY TO THROTTLE SHAFT5. FLOAT BRACKET WORN (USED)6. FLOAT NEEDLE WORN (USED) 7. STEEL SPLIT PINS USED IN LINKAGE CARBURETTOR WAS NEWLY OVERHAULED BY CONSOLIDATED FUEL SYSTEMS ON FAA FORM 8130-3. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020613000452002061300045WP 2002 6 13 AUS20020411 220020429G72614235530121 INSERT SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL ENGINE DISLODGED W O OTHER EKJVIBRATION/BUFFET FLUID LOSS WARNING INDICATION CRCRUISE 1 AUS 6178 (AUS) LT ENGINE OIL BYPASS VALVE ATTACHMENT STUD INSERT PN 423-553-0121 (COMPLETE WITH BOLT) CAME LOOSE IN THE GEARBOX CASING ALLOWING THE OIL FILTER BYPASS VALVE BODY TO SEPARATE FROM THE CASING. 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20020614000012002061400001NM 2002 6 14 AUS20020412 120020216G2823D406 SELECTOR SWITCH BAC MK3A MK3A 05623P4NM DHAVXXGIPSY GIPSYMAJOR1 20004WP AMTR C8289 C8289 GL FUEL SYSTEM LOOSE W O OTHER E VIBRATION/BUFFET DEDESCENT 1 AUS (AUS) DURING THE FIRST FLIGHT FOLLOWING AIRCRAFT RESTORATION THE ENGINE DEVELOPED POWER SURGES. INVESTIGATION FOUND THAT THE FUEL SELECTOR LEVER WAS LOOSE AND NOT ALIGNED WITH THE TANK SELECTION. 1L71 3T3 IRTEXPA1L71A8EU 5 NEXPP5N 20020614000032002061400003EA 2002 6 14 AUS20020416 220020412G8530L16068A PISTON PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL NR 3 CYLINDER DAMAGED W A UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CLCLIMB 1 AUS (AUS) RT ENGINE VIBRATION. CRANKCASE PRESSURISED AND OIL VENTED OVERBOARD. ENGINE SEIZED ON SHUTDOWN. INVESTIGATION FOUND A HOLE BURNED IN THE NR 3 CYLINDER PISTON. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020614000042002061400004 2002 6 14 AUS20020417 420020328G611305501623 PLATE CESSNA170 170 2072302CE CONT C145 C1452 17012SO AMTR C8289 C8289 GL PROP SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER SPINNER BACKPLATE CRACKED. CRACK TRAVELED AROUND PROPELLER FLANGE AREA AND RADIATED OUT TO THE FLANGE. 1H71 3O3 ONTA799 E253 5 NEXPP5N 20020614000052002061400005WP 2002 6 14 AUS20020418 120020422G3213AN626A BOLT NEWZE FU24 FU24A954 6280104WP LYC O720 IO720A1B 41546EA MLG BROKEN W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 AUS (AUS) MAIN LANDING GEAR TORQUE LINK BOLT FAILED. LOWER HALF OF OLEO STRUT, TORQUE LINKS, AXLE AND WHEEL ASSEMBLY POPPED OUT AFTER TAKEOFF. 1L71 3O3 O A9PC 1E15 20020614000062002061400006EA 2002 6 14 AUS20020422 220020424G7414 BEARING SLICK 6330 GIPPLDGA200 GA200 EU LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YR1 GL MAGNETO MISOVERHAULED W A UNSCHED LANDING WE INADEQUATE Q C VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) RT MAGNETO BEARING INCORRECTLY ASSEMBLED. ROTOR HARD TO ROTATE. COIL FAULTY. 1L71 3O3 ONCA00001LA1E4 5 CP920 20020613000512002061300051SO 2002 6 13 AUS20020424 120020502G323067031002 FITTING PIPER PA34 PA34200 7103405SO LYC O360 IO360C1E6 41514EA HARTZLHCC2Y HCC2YK2 GL MLG BROKEN W O OTHER J WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) LANDING GEAR RETRACTION FITTING BROKEN. DOWNLOCKS JAMMED IN THE UP POSITION. 1L72 3O3 O A7SO 1E10 5 CP920 20020614000122002061400012 2002 6 14 AUS20020432 420020501G2562012096 BATTERY CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ELT MISINSTALLED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) ELT BATTERIES INCORRECTLY FITTED. 1H71 3O3 ONT3A12 E274 5 NP910 20020614000132002061400013GL 2002 6 14 AUS20020434 320020417G6114D5858C402 HUB CESSNA188 188B 2073007CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C402 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER HUB CORRODED IN AREA OF BLADE SOCKETS AND ON SHIM FACES. 1L71 3O3 O A9CE E5CE 5 CP47GL 20020614000232002061400023SO 2002 6 14 AUS20020447 120020503G57513539200LH RIB PIPER PA28 PA28151 7102805SO LYC O320 O320E3D 41508EA SNSNCH74D 74DM EA AILERONS CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT AILERON RIBS PN 35392-00 (LT) AND PN 35392-01 (RT) CRACKED ALONG RADIUS OF FRONT FLANGE. 1L71 3O3 O 2A13 E274 5 NP88614 20020614000262002061400026GL 2002 6 14 AUS20020450 120020408G5712 RIB AMTR VANS RV8 GL ROTAX 912 ROTAX912 55555EU WING ROOT DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT WING ROOT RIB FAULTY DUE TO MOISTURE INGRESS. FOUND DURING INSPECTION IAW AD/CA25/7-1. 1L71 3O3 INTEXPA1L71EXPE3I 20020614000272002061400027GL 2002 6 14 AUS20020451 120020502G5712 RIB AMTR VANS RV8 GL ROTAX 912 ROTAX912 55555EU WING ROOT DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WING RIB LOCATED THIRD OUTBOARD FROM THE WING ROOT CONTAMINATED WITH MOISTURE. FOUND DURING INSPECTION IAW AD/CA25/7-1. 1L71 3O3 INTEXPA1L71EXPE3I 20020614000282002061400028CE 2002 6 14 AUS20020452 120020510G2711 CONTROL CABLE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL AILERON TAB MISRIGGED W O OTHER F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) AILERON TRIM SYSTEM RIGGED IN REVERSE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020614000302002061400030CE 2002 6 14 AUS20020454 120020403G561007135381 WINDSHIELD CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C C2A34C204 GL COCKPIT MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) REPLACEMENT FRONT WINDSCREEN WAS THE WRONG SIZE. THE HEIGHT OF THE SCREEN WAS TOO SHORT AND THE RT SIDE WAS NOT LONG ENOUGH. A SECOND REPLACEMENT WINDSCREEN HAD SIMILAR PROBLEMS. BOTH SCREENSWERE GENUINE MANUFACTURER SUPPLIED PARTS. MANUFACTURING ERROR. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020613000582002061300058CE 2002 6 13 AUS20020455 120020517G572008113508 FITTING CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL STUB WING CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 14201 (AUS) LT AND RT LOWER STUB WING FITTINGS CRACKED. FOUND DURING NDTINSPECTION. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021125000272002112500027NE 2002 11 25 AUS20020459 120020509G2435 STARTER GEN SKRSKYS76 S76A 8143006NE TMECA ARRIELARRIEL1S 60030NE NR 2 MALFUNCTIONED W K NONE L NO TEST ININSP/MAINT 1 NM04 (AUS) DC GENERATING SYSTEM FAULTY. INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM BUT THE FOLLOWING ITEMS WERE REPLACED; NR 2 ENGINE STARTER-GENERATOR NR 2 GENERATOR CONTROL UNIT NR 2 TRIPLE TACHO INDICATOR NR 2 ENGINE T5 GAUGE. SUSPECT CAUSED BY A VOLTAGE SPIKE. 1G72 3U3 U H1NE E19EU 20020613000652002061300065CE 2002 6 13 AUS20020473 120020506G551400244002373 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO HARTZLHCJ3Y PHCJ3YF2 GL HORIZONTAL STAB WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT HORIZONTAL STABILISER ATTACHMENT HOLES WORN. HOLES IN STUB SPAR ALSO WORN. 1L72 3O3 O 3A16 E5CE 5 CP36EA 20020614000412002061400041EA 2002 6 14 AUS20020474 220020211G7200PCE22284 ENGINE PIPER PA36 PA36285 7103610SO PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL NACELLE MAKING METAL W A UNSCHED LANDING ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 AUS (AUS) ENGINE SURGING. INVESTIGATION FOUND METAL CONTAMINATION OF THE ENGINE. 1L71 3O3 T A10SO E4EA 6 CP15EA 20020613000662002061300066EA 2002 6 13 AUS20020475 220020519G7421L1316339A SPARK PLUG LYC O320D2A AVIONSR2160 R2160 0960101EU LYC O320 O320D2A 41508EA SNSNCH74D 74DM EA NR 4 CYLINDER FOULED W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS 2032 L1316339A (AUS) NR 4 CYLINDER SPARK PLUGS FOULED. 1L71 3O3 ORTA48EU E274 5 NP88614 20020613000702002061300070CE 2002 6 13 AUS20020481 120020510G7170 FITTING CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL ENGINE DRAIN LOOSE W O OTHER K FLUID LOSS NRNOT REPORTED 1 AUS (AUS) LT AFT INDUCTION DRAIN FITTING LOOSE ALLOWING FUEL TO RUN DOWN THE OUTSIDE OF THE DRAIN LINE AND DRIP ONTO THE EXHAUST. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020614000502002061400050EA 2002 6 14 AUS20020483 220020411G8500 ENGINE PIPER PA25 PA25150 7102503SO LYC O320 O320A2B 41508EA SNSNCH74DM M74DM EA NACELLE MALFUNCTIONED W O OTHER EK VIBRATION/BUFFET FLUID LOSS NRNOT REPORTED 1 AUS (AUS) ENGINE REMOVED FOR INVESTIGATION INTO LOW OIL PRESSURE AND HIGH OIL TEMPERATURE. 1H71 3O3 O EXPA1H71E274 5 NP88614 20020708000922002070800092CE 2002 7 8 AUS20020506 120020530G5711HDHEO00636 STRAP CESSNA 421C CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO MCAULY3FF32 3FF32C501 GL WING SPAR FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AIRCRAFT HAS HDH SPAR STRAP MODIFICATION FITTED. INVESTIGATIONFOUND NO EVIDENCE OF ONGOING NDT INSPECTION IAW HDH EDD/6 ISSUE 2 BEING CARRIED OUT. NDT TECHNIQUE IS NOT POSSIBLE IN THIS MODELAIRCRAFT. 1L72 3O3 O A7CE E7CE 5 CP45GL 20020708000932002070800093CE 2002 7 8 AUS20020507 120020530G531412136643 KEEL CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL FUSELAGE MAIN, KCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD FUSELAGE RH KEEL MEMBER CRACKED IN UPPER FLANGE. 1H71 3O3 O A4CE E5CE 5 CP21EA 20020708000942002070800094SO 2002 7 8 AUS20020508 120020527G3241426871 CONTROL BOX EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE BRAKE ANTISKID SFAULTY W K NONE OJ OTHER WARNING INDICATION TOTAKEOFF 1 AUS 290 (AUS) ANTISKID CONTROL BOX FAULTY. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20020708000952002070800095NE 2002 7 8 AUS20020510 220020524G73209580115900 SENSOR TMECA ARRIEL1S1 SKRSKYS76 S76A 8143006NE TMECA ARRIELARRIEL1S 60030NE FUEL CONTROLLINGFAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 15069 (AUS) NO2 ENGINE OVERSPEED SENSOR FAULTY. 1G72 3U3 U H1NE E19EU 20020708000962002070800096NM 2002 7 8 AUS20020516 120020527G5210 DOOR BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU PASSENGER/CREW DLEAKING W K NONE O OTHER CLCLIMB 1 AUS (AUS) AIRCRAFT UNABLE TO MAINTAIN PRESSURISATION. LOUD AIR NOISE COMING FROM DOOR L1. 2L72 4F4 FRTA16WE E21EU 20020708000972002070800097GL 2002 7 8 AUS20020520 220020522G7261 OIL SYSTEM GE CF680C2 BOEING767 76733A 1385209NM GE CF6 CF680C2* GL TURBINE ENGINE OCONTAMINATED W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS (AUS) RH ENGINE D SUMP OIL SCAVENGE LINES AND D SUMP OIL FILTER COKED WITH CARBON BUILDUP CAUSING SUMP TO FILL WITH OIL AND VENTOVERBOARD. OIL TYPE HAD BEEN CHANGED FROM 2830 TO MJ2 SIX MONTHSPREVIOUSLY. 2L72 4F4 FRTA1NM E23EA 20020708000982002070800098NM 2002 7 8 AUS20020524 120020510G2913312A101029 PIPE BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU HYDRAULIC PUMP, WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE HYDRAULIC PUMP CASE DRAIN PIPES LOCATED IN LH AND RH PYLONS CHAFED BEYOND LIMITS IN AREAS LOCATED ADJACENT TO PYLONSKIN CUTOUT PANELS 5726L AND 5826R. 2L72 4F4 FRTA16WE E21EU 20020708000992002070800099CE 2002 7 8 AUS20020525 120020529G53122112136 BULKHEAD CESSNA 210N CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO HARTZLHCJ3Y PHCJ3YF1 GL FUSELAGE MAIN, BCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 21063317 (AUS) REAR FUSELAGE BULKHEAD CRACKEDIN AREA OF TOP LH HORIZONTALATTACHMENT BOLT LOCATION. 1H71 3O3 O 3A21 E5CE 5 CP36EA 20020708001002002070800100CE 2002 7 8 AUS20020526 120020529G532012324001LH BRACKET CESSNA 210N CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO HARTZLHCJ3Y PHCJ3YF1 GL FUSELAGE, MISCELCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 21063317 (AUS) BRACKETS PNO 1232400-1 (LH) AND PNO 1232400-2 (RH) CORRODED. 1H71 3O3 O 3A21 E5CE 5 CP36EA 20020708001012002070800101 2002 7 8 AUS20020528 420020603G2565D31354433 SLIDE BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU ESCAPE SLIDE FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 3185 1649 (AUS) DOOR 2R ESCAPE SLIDE FAILED TO INFLATE DURING FUNCTIONAL TEST.SLIDE INFLATED USING THE MANUAL INFLATION SYSTEM. SLIDE LIGHTINGALSO INOPERATIVE. 2L72 4F4 FRTA16WE E21EU 20020708001022002070800102EU 2002 7 8 AUS20020533 120020112G3260 WARNING SYSTEM AIRBUS310 A310324 3930206EU PWA 4152 PW4152 NE LANDING GEAR POSFAULTY W K NONE ON OTHER FALSE WARNING APAPPROACH 1 AUS (AUS) NLG DOOR INTRANSIT LIGHT ILLUMINATED. INVESTIGATION COULD FIND NO CAUSE FOR THE DEFECT. 2L72 4F RTA35EU E24NE 20020708001032002070800103EU 2002 7 8 AUS20020538 120020203G3230 DIODE FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU LANDING GEAR RETFAULTY W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) LANDING GEAR RETRACTION SYSTEM DIODE FAULTY. 2L72 4F4 FRTA20EU E2EU 20020708001042002070800104EU 2002 7 8 AUS20020539 120020205G2410 FITTING FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU ALTERNATOR-GENERLEAKING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) OIL PRESSURE FITTINGLEAKING. 2L72 4F4 FRTA20EU E2EU 20020708001052002070800105EU 2002 7 8 AUS20020540 120020204G2930 SWITCH FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU HYDRAULIC INDICAFAULTY W K NONE KMJFLUID LOSS OVER TEMP WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) HYDRAULIC TEMPERATURE SWITCH FAULTY. 2L72 4F4 FRTA20EU E2EU 20020708001062002070800106EU 2002 7 8 AUS20020541 120020206G3230200498005 ACTUATOR FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU LANDING GEAR RETFAULTY W K NONE OJ OTHER WARNING INDICATION LDLANDING 1 AUS 3363 CWDDDH292 (AUS) RH MAIN LANDING GEAR DOWNLOCK ACTUATOR FAULTY. 2L72 4F4 FRTA20EU E2EU 20020708001072002070800107NM 2002 7 8 AUS20020542 120020602G56105893543129 WINDSHIELD BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FLIGHT COMPARTMECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 22409 94116H5469 (AUS) CAPTAINS NO1 WINDOW CRACKED. 2L72 4F4 FRTA16WE E21EU 20020708001082002070800108GL 2002 7 8 AUS20020543 220020605G72611537L6850603 OIL SYSTEM GE CF680C2 BOEING767 76733A 1385209NM GE CF6 CF680C2* GL TURBINE ENGINE OCONTAMINATED W K NONE EK VIBRATION/BUFFET FLUID LOSS CLCLIMB 1 AUS (AUS) LH ENGINE NO6 BEARING SCAVENGE FILTER BLOCKED WITH CARBON PARTICLES AND D' SUMP SCAVENGE LINES COKED CAUSING OIL TO BE VENTED OVERBOARD. ENGINE OIL TYPE HAD BEEN CHANGED FROM EXXON 2380 TO MOBIL JET II. 2L72 4F4 FRTA1NM E23EA 20020708001092002070800109 2002 7 8 AUS20020546 420020516G6122C290D4T4 CSU MCAULY C290D4T4 CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL PROPELLER GOVERNLEAKING W K NONE O OTHER ININSP/MAINT 1 AUS 792168 (AUS) PROPELLER GOVERNOR (CSU) LEAKING OIL. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020708001102002070800110 2002 7 8 AUS20020547 420020305G6122C290D4T2 CSU MCAULY C290D4T2 CESSNA210 P210N 2073454CE CONT O520 TSIO520P 17040SO MCAULYD3A34 D3A34C402 GL PROPELLER GOVERNFAULTY W K NONE O OTHER CRCRUISE 1 AUS 792 794696 (AUS) PROPELLER GOVERNOR (CSU) FAULTY. SUSPECT CAUSED BY FAULTY SPEEDER SPRING. 1H71 3O3 O 3A21 E8CE 5 CP47GL 20020708001112002070800111 2002 7 8 AUS20020552 420020512G2565D31591478 SLIDE BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU ESCAPE SLIDE FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 9369 1706 (AUS) DOOR 1L ESCAPE SLIDE LANYARD ATTACHMENT FROM BATTERY FIRING PIN FAULTY. SLIDE LIGHTING FAILED. 2L72 4F4 FRTA16WE E21EU 20020708001122002070800112NM 2002 7 8 AUS20020556 120020608G561057176244 WINDOW BOEING737 7373Q8 1384670NM CFMINTCFM56 CFM563C 13802EU FLIGHT COMPARTMECRACKED W K NONE OB OTHER SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 AUS 97119H5359 (AUS) FIRST OFFICER'S SLIDING WINDOW CRACKED ACCOMPANIED BY ELECTRICALBURNING OF THE SEALS AND CONDUCTORS. 2L72 4F4 FRTA16WE E21EU 20020708001132002070800113CE 2002 7 8 AUS20020560 120020531G7820K70105 MUFFLER CONT IO520BA BEECH 33 F33A 1151425CE CONT O520 IO520BA 17032SO MCAULY2A36C 2A36C23 GL ENGINE NOISE SUPDISTORTED W K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) RH MUFFLER BUCKLED AND DISTORTED IN AREA UNDER THE HEATER SHROUD. ONE HEAT TRANSFER STUD MISSING. EXHAUST GAS ESCAPING INTO CABIN HEATER SYSTEM. 1L71 3O3 O 3A15 E5CE 5 CP880 20020708001142002070800114SO 2002 7 8 AUS20020561 120020521G2140A23D0475 REGULATOR JANITROL FR65D793EL PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE O OTHER ININSP/MAINT 1 AUS A99110013 (AUS) COMBUSTION HEATER FUEL REGULATOR LEAKING. FOUND DURING INSPECTION IAW AD/AIRCON/9 PT2. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020708001152002070800115 2002 7 8 AUS20020563 420020529G3457KA33 COOLING FAN GULSTM500 500B 0141106SW LYC O540 IO540E1B5 41532EA HARTZLHCA3V HCA3VK4 GL GLOBAL POSITIONISEIZED W K NONE B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 AUS (AUS) GPS COOLING FAN SEIZED. 1H72 3O3 O 6A1 1E4 5 CP6EA 20020708001162002070800116SO 2002 7 8 AUS20020564 220020606G8530 PISTON CONT IO470F CESSNA210 2105A 2073406CE CONT O470 IO470F 17026SO MCAULY2A34C D2A34C58 GL RECIPROCATING ENBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO4 CYLINDER PISTON SKIRT BROKEN IN AREA BELOW THE BOTTOM PISTONRING. INVESTIGATION FOUND SIMILAR DAMAGE TO THE NO2 PISTON. 1H71 3O3 O 3A21 3E1 5 CP3EA 20020708001172002070800117EU 2002 7 8 AUS20020569 120020418G21311026445 CONTROLLER FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU CABIN PRESSURE CFAULTY W K NONE O OTHER TOTAKEOFF 1 AUS 11564 30156 (AUS) CABIN PRESSURE CONTROLLER FAULTY. 2L72 4F4 FRTA20EU E2EU 20020708001182002070800118EA 2002 7 8 AUS20020572 220020410G72103037080 GEARBOX PWA PT6A34 DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA TURBINE ENGINE RSEIZED W K NONE E VIBRATION/BUFFET LDLANDING 1 AUS (AUS) LH ENGINE REDUCTION GEARBOX SEIZED. METAL CONTAMINATION OF OILSYSTEM. 1H72 3T4 TRTA9EA E4EA 20020708001192002070800119EU 2002 7 8 AUS20020575 120020216G3233 ACTUATOR FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU LANDING GEAR ACTFAULTY W K NONE ON OTHER FALSE WARNING CLCLIMB 1 AUS (AUS) RH MAIN LANDING GEAR FAULTY. INVESTIGATION FOUND RH MAIN LANDINGGEAR ACTUATOR SLOW TO RETRACT. 2L72 4F4 FRTA20EU E2EU 20020708001202002070800120 2002 7 8 AUS20020578 420020502G6122C290D4T4 CSU MCAULY D3A32C90 CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL PROPELLER GOVERNFAULTY W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS 246 (AUS) CONSTANT SPEED UNIT (CSU) FAULTY. 1H71 3O3 O A4CE E5CE 5 CP21EA 20020708001212002070800121CE 2002 7 8 AUS20020579 120020605G571211812004826 RIB BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3A NE WING, RIB/BULKHECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH WING CORRODED IN AREA OF LOWER AFT INBOARD CORNER. CORROSION AFFECTED LOWER WING SKIN, REAR SPAR AND THE UPPER SURFACE OF THEHORIZONTAL LEG OF THE CENTRE WING MAIN RIB. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020708001222002070800122EA 2002 7 8 AUS20020580 220020501G8520L1845851A CRANKCASE LYC IO360C1C6 PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA MCAULY2D34C B2D34C213 GL RECIPROCATING ENFAILED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS L1845851A (AUS) CRANKCASE FAILED. LIMITED INFORMATION PROVIDED. 1L71 3O3 O 2A13 1E10 5 CP7EA 20020708001232002070800123EU 2002 7 8 AUS20020586 120020306G2720 CABLE AIRBUS310 A310324 3930206EU PWA 4152 PW4152 NE RUDDER CONTROL SWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RUDDER CABLE WORN. 2L72 4F RTA35EU E24NE 20020708001242002070800124EU 2002 7 8 AUS20020587 120020306G2730A2737114500000 CABLE AIRBUS310 A310324 3930206EU PWA 4152 PW4152 NE ELEVATOR CONTROLWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELEVATOR CABLES PNO A2737114500000 AND PNO A2737114000000 WORN. 2L72 4F RTA35EU E24NE 20020708001252002070800125EU 2002 7 8 AUS20020588 120020318G2741 SWITCH FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU STABILIZER POSITFAULTY W K NONE FJ FLT CONT AFFECTED WARNING INDICATION TOTAKEOFF 1 AUS (AUS) STABILISER CONTROL SWITCH FAULTY. 2L72 4F4 FRTA20EU E2EU 20020708001262002070800126NM 2002 7 8 AUS20020592 120020613G562075620003103 WINDOW DHAV 85323917001 DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE PASSENGER COMPARFRACTURED W K NONE O OTHER CRCRUISE 1 AUS 17389 1348 (AUS) RH SIDE PASSENGER WINDOW OUTER PANE CRACKED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020708001272002070800127NM 2002 7 8 AUS20020596 120020612G2410 CSD BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU ALTERNATOR-GENERFAILED W K NONE J WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) NO2 GENERATOR CONSTANT SPEED DRIVE FAILED. 2L72 4F4 FRTA16WE E21EU 20020708001282002070800128NM 2002 7 8 AUS20020604 120020618G5230 FRAME BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU CARGO/BAGGAGE DOCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD CARGO DOOR LOWER CORNER FRAMES CRACKED. FOUND DURINGINSPECTION IAW ADB737/142. 2L72 4F4 FRTA16WE E21EU 20020708001292002070800129NM 2002 7 8 AUS20020607 120020521G5230 DOOR BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU CARGO/BAGGAGE DOCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD CARGO DOOR LOWER CROSSBEAM T' CHORD CRACKED IN TWO PLACES. AFT END OF WEB CRACKED. FOUND DURING INSPECTION IAW AD/B737/142. 2L72 4F4 FRTA16WE E21EU 20020708001302002070800130SO 2002 7 8 AUS20020608 120020607G32304204200 ARM PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR RETBROKEN W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) RH MAIN LANDING GEAR ARM BROKEN AND BENT. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020708001312002070800131WP 2002 7 8 AUS20020610 120020615G6420269A60923 BOLT HUGHES269 269C 4470504WP LYC O360 HIO360D1A 41514EA TAIL ROTOR HEAD BROKEN W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) TAIL ROTOR FORK BOLT BROKEN IN HALF. 1G71 3O3 O 4H12 1E10 20020708001322002070800132SO 2002 7 8 AUS20020611 120020618G5230 DOOR PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YK1 GL CARGO BAY SEPARATED W K NONE D INFLIGHT SEPARATION LDLANDING 1 AUS (AUS) NOSE BAGGAGE DOOR SEPARATED FROM AIRCRAFT. DOOR LOCK INSPECTED AND FOUND TO BE SERVICEABLE. 1L71 3O3 O A3SO 1E4 5 CP920 20020708001332002070800133EA 2002 7 8 AUS20020612 220020618G8520LW18840 CAMSHAFT LYC AEIO360B2F MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU RECIPROCATING ENWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CAMSHAFT LOBES AND ASSOCIATED LIFTERS (3OFF) BADLY WORN. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020708001342002070800134NM 2002 7 8 AUS20020618 120020625G7722 GAUGE GE CFM563C BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU ENGINE EGT/TIT IFAULTY W K NONE EJ VIBRATION/BUFFET WARNING INDICATION TOTAKEOFF 1 AUS (AUS) NO2 ENGINE EGT GAUGE FAULTY. FAULT LIGHT ON FIRE PANELILLUMINATED. 2L72 4F4 FRTA16WE E21EU 20020708001352002070800135EU 2002 7 8 AUS20020619 220020625G7261 OIL SYSTEM GE CFM563C BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TURBINE ENGINE OCONTAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH ENGINE OIL SYSTEM CONTAMINATED WITH FUEL. 2L72 4F4 FRTA16WE E21EU 20020808000692002080800069SO 2002 8 8 AUS20020623 120020620G5753 RIB PIPER PA28 PA28151 7102805SO LYC O320 O320E1A 41508EA SNSNCH74D 74DM EA TE FLAPS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TRAILING EDGE FLAP NOSE RIBS SEVERELY CORRODED. 1L71 3O3 O 2A13 E274 5 NP88614 20020808000702002080800070NM 2002 8 8 AUS20020624 120020626G2761251A12403 ACTUATOR BOEING737 737832 13844CFNM GE CFM56 CFM567B24 NE DRAG CONTROL LEAKING W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 AUS 705 (AUS) NR 9 FLIGHT SPOILER ACTUATOR LEAKING FROM ACTUATOR BODY. 2L72 4F4 FRTA16WE E00055EN 20020807000602002080700060NM 2002 8 7 AUS20020625 120020625G3242NAS1802311 SCREW BOEING767 767 UTILUSENM GE CF6 CF680C2* GL BRAKE MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) BRAKE RETAINING BOLT LOCK BOLTS MISSING. AIRCRAFT IS FOREIGNREGISTERED DQ-FJC. PERSONNEL/MAINTENANCE ERROR. 2L72 4F4 FRTA1NM E23EA 20020807000612002080700061NE 2002 8 7 AUS20020627 220020422G8530114651 CYLINDER PWA R183092 DOUG DC3 DC3CS1C3G 3021458WP PWA R1830 R183092 52020NE HAMSTD23E 23E50 NE RECIPROCATING ENSEPARATED W K NONE EF VIBRATION/BUFFET FLT CONT AFFECTED LDLANDING 1 AUS 645 355640 (AUS) RH ENGINE NO13 CYLINDER HEAD SEPARATED. INVESTIGATION FOUND THATTHE FRACTURE OCCURRED APPROXIMATELY 25.4MM (1IN) BELOW THEHEAD/BARREL JOIN AND WAS TEMPERATURE RELATED. 2L72 4R4 R A669 5E4 6 CP603 20020807000622002080700062SW 2002 8 7 AUS20020628 120020421G6322 STUD BELL 476618011 BELL 47 47G3B 1181026SW LYC O435 TVO435B1A 41516EA ROTORCRAFT COOLIFAILED W K NONE E VIBRATION/BUFFET DEDESCENT 1 AUS (AUS) COOLING FAN MOUNT STUD LOCATED ON CRANKCASE FAILED. LOSS OF TENSION ALLOWED BELT TO FALL OFF AND DESTROY THE COOLING FAN. 1G71 3O3 O 2H3 1E13 20020807000632002080700063EU 2002 8 7 AUS20020629 120020621G5743 FITTING MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU WING, LANDING GECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR LH FORWARD INBOARD LOWER AND RH FORWARD OUTBOARD LOWER ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPECTION IAWAD/CAP/4A2. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020807000642002080700064SO 2002 8 7 AUS20020631 220020614G8550632856 PUMP CONT IO520F CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE OIL PUMP HOUSING CRACKED. CRACK APPEARS TO ORIGINATE FROMA CASTING MARK. FOUND WHEN OIL FILTER ADAPTER WAS REMOVED FOR RECTIFICATION OF AN OIL LEAK. 1H71 3O3 O A4CE E5CE 5 CP21EA 20020807000652002080700065NE 2002 8 7 AUS20020632 220020627G72619505 PUMP TMECA ARRIEL1D1 SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE TURBINE ENGINE OFOD W K NONE EK VIBRATION/BUFFET FLUID LOSS TXTAXI/GRND HDL 1 AUS 9505 (AUS) ENGINE OIL PUMP INLET FOD. INVESTIGATION FOUND A SMALL PIECE OF RUBBER TUBING LODGED IN THE OIL PUMP INLET, RESTRICTING OIL FLOWTO THE PUMP. ENGINE WAS BEING GROUND RUN FOR INSTALLATION FOLLOWING REPAIR. PERSONNEL/MAINTENANCE ERROR. 1G71 3U3 U H9EU E19EU 20020809000022002080900002EU 2002 8 9 AUS20020635 120020613G255052801702 CARGO HOOK BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE CARGO BAY BROKEN W C ABORTED TAKEOFF D INFLIGHT SEPARATION TOTAKEOFF 1 AUS (AUS) CARGO HOOK KEEPER ASSEMBLY ARM (1OFF) BROKEN AND THE OTHER ARMBENT. THE LOAD BEAM WAS ALSO BENT. THE LOAD WAS UNINTENTIONALLY RELEASED. 1G72 3U3 UNCH13EU E5NE10 20020807000662002080700066 2002 8 7 AUS20020639 420020628G6122 SPRING HARTZL F624ZL PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL PROPELLER GOVERNFAILED W K NONE E VIBRATION/BUFFET TOTAKEOFF 1 AUS 170 (AUS) GOVERNOR SPEEDER SPRING FAILED. SPRING WAS A NEW ITEM FITTEDDURING OVERHAUL 169.7 HOURS PREVIOUSLY. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020807000672002080700067CE 2002 8 7 AUS20020642 120020411G27205052432634 ARM BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE RUDDER CONTROL SFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CAPTAINS RH RUDDER PEDAL ARM FAILED. INVESTIGATION FOUND THAT THE PIVOT BOLT HOLE WAS WORN AND ELONGATED. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020807000682002080700068SW 2002 8 7 AUS20020643 120020628G3233ED12758 CLEVIS GULSTM500 500B 0141106SW LYC O540 IO540E1B5 41532EA HARTZLHCA3V HCA3VK4 GL LANDING GEAR ACTFRACTURED W K NONE O OTHER DEDESCENT 1 AUS 3244 (AUS) MAIN LANDING GEAR HYDRAULIC RAM RODEND CLEVIS FRACTURED. 1H72 3O3 O 6A1 1E4 5 CP6EA 20020807000692002080700069CE 2002 8 7 AUS20020644 120020521G3230 GEARBOX CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520K 17040SO MCAULY3AF32C3AF32C87 GL LANDING GEAR RETWORN W K NONE O OTHER LDLANDING 1 AUS (AUS) LANDING GEAR ACTUATOR REDUCTION GEARBOX GEAR TEETH WORN. ELECTRIC DRIVE MOTOR INTERMITTENT IN OPERATION AND CLUTCH INEFFECTIVE. 1L72 3O3 O 3A25 E8CE 5 CP22EA 20020807000702002080700070CE 2002 8 7 AUS20020648 120020704G2810 FUEL TANK BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE FUEL STORAGE COLLAPSED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH AUXILIARY FUEL CELL COLLAPSED. VELCRO ATTACHMENT PADS HADBECOME UNGLUED AND SEPARATED FROM THE TOP SURFACE OF THE FUEL CELL. INSPECTION FOUND THAT THE RH FUEL VENT HEATING ELEMENT HADFAILED, ALLOWING THE VENT TO BECOME BLOCKED WITH ICE CAUSING THEFUEL CELL TO COLLAPSE. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020807000712002080700071 2002 8 7 AUS20020656 420020706G2564733M2537017 LIFE RAFT BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU LIFERAFT FOULED W K NONE O OTHER ININSP/MAINT 1 AUS 748 11208487 (AUS) DURING LIFERAFT REMOVAL FOR FITMENT TO ANOTHER AIRCRAFT, THE HOOK ATTACHED TO THE END OF THE ACTIVATION LANYARD BECAME LODGED INTHE CEILING STRUCTURE AT THE REAR OF THE OVERHEAD STOWAGE AREA. AS THE LIFERAFT WAS REMOVED FROM THE STOWAGE AREA, THELANYARD UNWOUND. 2L72 4F4 FRTA16WE E21EU 20020807000722002080700072SO 2002 8 7 AUS20020658 120020628G2823480700 PIN PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL FUEL SELECTOR/SHBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SELECTOR ROLL PINS BROKEN. RH FUEL SELECTOR HAD ONE ROLL PIN MISSING. 1L72 3O3 O 1A10 1E4 5 CP9EA 20020809000242002080900024NM 2002 8 9 AUS20020664 120020701G3260980209001 DOWNLOCK SWITCH PIPER PA60 PA60601B 7106011NM LYC O540 IO540S1A5 41532EA HARTZLHCC3Y HCC3YR2 NE MLG CONTAMINATED W O OTHER O OTHER LDLANDING 1 AUS (AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH CONTACTS DIRTY. 1M72 3O3 ORTA17WE 1E4 5 CP25EA 20020809000282002080900028SO 2002 8 9 AUS20020667 120020503G3233 BRUSHES PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA HARTZLHCC2Y HCC2YK1 GL MLG MOTOR LOOSE W O OTHER J WARNING INDICATION TOTAKEOFF 1 AUS (AUS) LANDING GEAR MOTOR BRUSHES ADRIFT IN BRUSH HOLDER. MOTOR FAILED. 1L71 3O3 O 2A13 1E10 5 CP920 20020807000732002080700073EA 2002 8 7 AUS20020669 220020709G741410349276 CONDENSER BENDIX S6LSC200 ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO/DISTRIBUFAILED W K NONE O OTHER ININSP/MAINT 1 AUS C119810E (AUS) MAGNETO CONDENSER INTERNAL FAILURE. 1G71 3O3 O H11NM E295 20020807000742002080700074CE 2002 8 7 AUS20020670 120020709G2701AN2278B STUD BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL CONTROL COLUMN SFRACTURED W K NONE OF OTHER FLT CONT AFFECTED ININSP/MAINT 1 AUS (AUS) AILERON CONTROL SYSTEM STUD FRACTURED. CLAMP PNO AN737TW56-66 LOOSE AT BOTTOM OF CONTROL COLUMN ALLOWING THE CONTROL COLUMN BOOT PNO 101-54149-37 TO MOVE UNSECURED AROUND THE CONTROLCOLUMN. LH AILERON CONTROL CABLE TURNBUCKLE LOCKWIRE CAUGHT ONBRACKET PNO 50-524466-7 WHEN THE CONTROL WHEEL WAS MOVED TO THE RIGHT. 1L72 4T4 T A24CE E4EA 5 CSTC 20020807000752002080700075SW 2002 8 7 AUS20020674 120020701G5711 WEB SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL WING SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 20624 (AUS) WING SPAR INNER WEB CRACKED. FOUND DURING INSPECTION IAWAD/SWSA226/86. 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20020807000762002080700076CE 2002 8 7 AUS20020679 120020710G3234MS166245018 RETAINER CESSNA500 550 2076604CE PWA 530 PW530A NE LANDING GEAR SELSEPARATED W K NONE O OTHER DEDESCENT 1 AUS (AUS) LANDING GEAR SELECTOR CIRCLIP (RETAINER) DISLOCATED. 1L72 4F4 F A22CE E00053EN 20020807000772002080700077GL 2002 8 7 AUS20020681 220020525G724023056130 LINER RROYCE A250C20R2 HUGHES369 369E 4470707WP ALLSN 25OC 250C20R GL TURBINE ENGINE CFAULTY W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS CAE295414 (AUS) ENGINE EXHIBITED LOW POWER FOLLOWING REPLACEMENT OF COMBUSTIONLINER. SUSPECT BOTTOM LOUVRES INCORRECTLY SET. THE LINER FITTED WAS ZERO HOURS TIME SINCE OVERHAUL. 1G71 3U3 U H3WE E4CE 20020807000782002080700078NM 2002 8 7 AUS20020682 120020708G241073511A CSD BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU ALTERNATOR-GENERFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 16787 B1966 (AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) FAILED. OIL LEAKING FROMDRAIN POINT. 2L72 4F4 FRTA16WE E21EU 20020807000792002080700079 2002 8 7 AUS20020684 420020706G2564733M2537011 LIFE RAFT BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU LIFERAFT FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 11686790 (AUS) LIFE RAFT HAD ONE INFLATION BOTTLE INDICATING APPROXIMATELY 50PSI (LOWER END OF RED SCALE). LIFE RAFT HAD BEEN RECEIVED FROMSTORES. 2L72 4F4 FRTA16WE E21EU 20020807000802002080700080SO 2002 8 7 AUS20020687 120020711G2820AN8336 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED ON THE LHFIREWALL. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000812002080700081SO 2002 8 7 AUS20020688 120020711G28208623810 PIPE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000822002080700082SO 2002 8 7 AUS20020689 120020711G28208623803 PIPE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000832002080700083SO 2002 8 7 AUS20020690 120020711G28208623809 PIPE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000842002080700084SO 2002 8 7 AUS20020691 120020711G28208623804 PIPE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000852002080700085SO 2002 8 7 AUS20020692 120020711G28208623808 PIPE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PIPE CORRODED. PIPE IS LOCATED IN LH WING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000862002080700086SO 2002 8 7 AUS20020693 120020711G2820AN8218 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000872002080700087SO 2002 8 7 AUS20020694 120020711G2820AN8376 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM 45 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000882002080700088SO 2002 8 7 AUS20020695 120020711G2820AN83364 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED IN LHWING. 1L72 3O3 O A19S0 E286 5 CP25EA 20020807000892002080700089SO 2002 8 7 AUS20020696 120020711G2820AN8336 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM 90 DEGREE ELBOW CORRODED. ELBOW IS LOCATED ON RHFIREWALL. 1L72 3O3 O A19S0 E286 5 CP25EA 20020809000432002080900043CE 2002 8 9 AUS20020698 120020605G5753 SKIN CESSNA182 182P 2075816CE TE FLAPS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FLAP SKINS CONTAINED EXTENSIVE SURFACE CORROSION. 1H71 3O NTTA13 20020807000902002080700090NE 2002 8 7 AUS20020699 220020711G73243019906 FLOW DIVIDER PWA PT6A42 BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE FUEL DIVIDER FAULTY W K NONE EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 AUS PCE93710 (AUS) ENGINE FUEL SYSTEM FLOW DIVIDER FAULTY. IGNITION LEAD ALSO FOUNDTO BE UNSERVICEABLE. ENGINE WAS UNDERGOING GROUND RUNS FOLLOWINGENGINE INSTALLATION. PERSONNEL/MAINTENANCE ERROR. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020807000912002080700091CE 2002 8 7 AUS20020702 120020613G5312 RIVET BEECH 1014100131 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE FUSELAGE MAIN, BCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. FOUND DURING INSPECTION OF FORWARD PRESSURE BULKHEAD LOCATED AT FS 84. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020807000922002080700092CE 2002 8 7 AUS20020703 120020531G5312 RIVET BEECH 1014100131 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL FUSELAGE MAIN, BCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. FOUND DURING INSPECTION OF FORWARD PRESSURE BULKHEAD LOCATED AT FS 84. 1L72 4T4 T A24CE E4EA 5 CSTC 20020807000932002080700093CE 2002 8 7 AUS20020704 120020619G5312 RIVET BEECH 1014100131 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE FUSELAGE MAIN, BFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AVIONICS SHELF SUPPORT ANGLE RIVET CORRODED AND RIVET HEADSHEARED. RIVET WAS THE FOURTH RIVET FROM THE INBOARD END. FOUND DURING INSPECTION OF FORWARD PRESSURE BULKHEAD LOCATED AT FS 84. 1L72 4T4 T A24CE E4EA 6 C3PNE 20020807000942002080700094EU 2002 8 7 AUS20020705 120020708G5743 FITTING MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU WING, LANDING GECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH MAIN LANDING GEAR ATTACHMENT BLOCKS CRACKED. RH FILLERDELAMINATED FROM SPAR ADJACENT TO UNDERCARRIAGE ATTACHMENT. FOUND DURING INSPECTION IAW AD/CAP10/4A2. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020807000952002080700095SW 2002 8 7 AUS20020706 120020701G731210544E HEATER PWA PT6T3BG BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE FUEL HEATER LEAKING W K NONE O OTHER ININSP/MAINT 1 AUS 39 63314 (AUS) FUEL/OIL HEATER LEAKING OIL FROM WELD LINE ON MAIN BODY. 1G72 4U4 U H4SW E22EA 20020807000962002080700096EU 2002 8 7 AUS20020708 120020717G80120174078030 DRAIN VALVE TMECA ARRIEL1B SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE START VALFAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 105 529 (AUS) ENGINE START DRAIN VALVE FAULTY. 1G71 3U3 U H9EU E19EU 20020807000972002080700097CE 2002 8 7 AUS20020710 120020620G5341817841232 BOLT BEECH 200 B200T 1152929CE PWA PT6 PT6A42 52043NE HARTZLHCB3T HCB3TN3 GL FUSELAGE, WING ACRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) UPPER FORWARD WING ATTACHMENT BOLT SUSPECT CRACKED. FOUND DURINGFLUORESCENT INSPECTION IAW AD/B200/38 A4 AND BEECH S.I.R.M. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020807000982002080700098EU 2002 8 7 AUS20020711 120020710G6720704A34130103 CONTROL CABLE SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU TAIL ROTOR FRAYED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT REAR TAIL ROTOR CONTROL CABLE CONTAINED BROKEN STRANDS IN AN AREA WHERE THE CABLE PASSES THROUGH FAIRLEAD. FAIRLEAD INSPECTED AND FOUND SERVICEABLE. 2G72 4U4 U H4EU E12NE 20020807000992002080700099SO 2002 8 7 AUS20020713 120020618G2731 CABLE PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360E 17025SO HARTZLHCE2Y HCE2YK2 GL ELEVATOR TAB CONSEPARATED W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) FORWARD LH STABILATOR TRIM CABLE DISCONNECTED FROM TRIM WHEEL.BALL END OF CABLE HAD COME OUT OF THE SOCKET ON THE SIDE OF THE WHEEL. 1L72 3O3 O A7SO E9CE 5 CP9EA 20020807001002002080700100SO 2002 8 7 AUS20020716 220020618G8530654833 PISTON CONT O470R CESSNA182 182L 2072726CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C50 GL RECIPROCATING ENDAMAGED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS 56 81880 (AUS) PISTON DAMAGED DUE TO DETONATION. PISTON RINGS BROKEN AND OIL RETURN DRAIN HOLE ENLARGED. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020807001012002080700101CE 2002 8 7 AUS20020717 120020320G7160MS35206218 SCREW LYC O360A4K BEECH 23 C23 1151242CE LYC O360 O360A4K 41514EA SNSNCH76E 76EM8 EA ENGINE AIR INTAKMISSING W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS L2093036A (AUS) CARBURETTOR HEAT INOPERATIVE DUE TO MISSING SCREWS (3OFF) AND NUTS ALLOWING THE BUTTERFLY VALVE TO ROTATE FREELY ON THE SHAFT PNO 169-910049-47. 1L71 3O3 O A1CE E286 5 NP4EA 20020807001022002080700102CE 2002 8 7 AUS20020718 120020607G32303581507711 BRACKET BEECH UPLOCK BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO MCAULY2AF34C2AF34C55 GL LANDING GEAR RETMISSING W K NONE O OTHER LDLANDING 1 AUS (AUS) RH MAIN LANDING GEAR UPLOCK ASSEMBLY BRACKET AND SPRING MISSING.THE BRACKET IS ATTACHED TO THE RIB LOCATED IN THE RH WHEEL BAY BY THREE RIVETS AND IT APPEARS THAT THE RIVETS FAILED PROBABLY DUE TO AGE HARDENING. LANDING GEAR COLLAPSED ON TOUCHDOWN. 1L72 3O3 ORT3A16 3E1 5 CP5EA 20020807001032002080700103NM 2002 8 7 AUS20020721 120020715G3230AE2464163E0192 HOSE BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU LANDING GEAR RETRUPTURED W K NONE K FLUID LOSS NRNOT REPORTED 1 AUS (AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR HYDRAULIC HOSE RUPTURED. LOSS OF HYDRAULIC FLUID. 2L72 4F4 FRTA16WE E21EU 20020807001042002080700104EA 2002 8 7 AUS20020725 220020716G741410357584 GEAR BENDIX S4LN20 FUJI FA200 FA200160 3730101WP LYC O320 O320D2A 41508EA MCAULY1C172 1C172MGM GL MAGNETO/DISTRIBUSTRIPPED W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 991 9215 (AUS) RH MAGNETO DISTRIBUTOR GEAR HAD FIFTEEN TEETH STRIPPED. 1L71 3O3 O A4PC E274 5 NP910 20020807001052002080700105EA 2002 8 7 AUS20020726 220020708G8530LW19001 EXHAUST VALVE LYC O320D2A FUJI FA200 FA200160 3730101WP LYC O320 O320D2A 41508EA MCAULY1C172 1C172MGM GL RECIPROCATING ENCRACKED W K NONE E VIBRATION/BUFFET CLCLIMB 1 AUS 991 (AUS) NO3 CYLINDER EXHAUST VALVE HEAD CRACKED AND BURNT. 1L71 3O3 O A4PC E274 5 NP910 20020807001062002080700106CE 2002 8 7 AUS20020727 120020722G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL FLIGHT COMPARTMECRACKED W K NONE O OTHER CRCRUISE 1 AUS 98180H9754 (AUS) RH WINDSHIELD INNER PLY SHATTERED. WINDSHIELD HEAT WAS OFF' AT THE TIME. 1L72 4T4 T A24CE E4EA 5 CSTC 20020807001072002080700107NM 2002 8 7 AUS20020728 120020704G323085420011061 DOOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR RETOUT OF ADJUST W K NONE ON OTHER FALSE WARNING CLCLIMB 1 AUS (AUS) RH MAIN LANDING GEAR CENTRE DOOR ASSEMBLY OUT OF ADJUSTMENT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807001082002080700108NM 2002 8 7 AUS20020730 120020717G2920849557 POWER UNIT DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE HYDRAULIC SYSTEMFAULTY W K NONE KJMFLUID LOSS WARNING INDICATION OVER TEMP CRCRUISE 1 AUS 3194 MX627765 (AUS) STANDBY HYDRAULIC POWER UNIT FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807001092002080700109NM 2002 8 7 AUS20020733 120020719G2410735511A CSD BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU ALTERNATOR-GENERLEAKING W K NONE O OTHER ININSP/MAINT 1 AUS B1377 (AUS) NO1 ENGINE CONSTANT SPEED DRIVE (CSD) LEAKING OIL. 2L72 4F4 FRTA16WE E21EU 20020807001102002080700110SO 2002 8 7 AUS20020735 120020716G29102677A4EE VALVE EMB EMB120 EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14SF 14SF9 NE HYDRAULIC SYSTEMFAILED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS 120135 (AUS) GREEN HYDRAULIC SYSTEM FILL CHECK VALVE CRACKED AND LEAKING.VALVE IS LOCATED IN THE AREA OF THE RH ENGINE NACELLE. 2L72 4T4 TRTA31SO E20NE 6 NP11NE 20020807001112002080700111NM 2002 8 7 AUS20020738 120020720G2820 LINE BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU AIRCRAFT FUEL DILEAKING W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) LH ENGINE FUEL FEED LINE LEAKING AT WING SPAR OUTLET CONNECTION. 2L72 4F4 FRTA16WE E21EU 20020809000702002080900070CE 2002 8 9 AUS20020742 120020725G3230 LANDING GEAR CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL MAINS MISRIGGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR INCORRECTLY RIGGED. LANDING GEAR COMPONENTS DAMAGED DUE TO THE EXTENT THAT THE LANDING GEAR WAS OUT OF RIG. THE DEFECTS INCLUDE BENT RETRACT RODS, DENTED AND BENT UNDERCARRIAGE DRIVE TUBES, CORROSION AND RUST ON DRIVE TUBES, SEIZED AND RUSTED HARDWARE, PHYSICAL CONTACT DAMAGE TO UPPER DRAG LINKS FROM UPLOCK HOOK ASSEMBLY. PERSONNEL/MAINTENANCE ERROR. POOR MAINTENANCE. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20020807001122002080700112SO 2002 8 7 AUS20020745 120020725G78202634505 MUFFLER LYC IO540E1A5 PIPER PA24 PA24260 7102406SO LYC O540 IO540E1A5 41532EA HARTZLHCC2Y HCC2YR1 GL ENGINE NOISE SUPCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 400 (AUS) LH MUFFLER OUTLET PIPE CRACKED AT REAR SUPPORT CLAMP. 1L71 3O3 O 1A15 1E4 5 CP920 20020807001132002080700113EA 2002 8 7 AUS20020746 220020724G72303018389 SPACER PWA PT6A41 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL TURBINE ENGINE CDAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 3748 PCE81011 (AUS) ENGINE FIRST STAGE COMPRESSOR SPACER DAMAGED DUE TO RUBBING ONTHE FIRST STAGE COMPRESSOR STATORS. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020807001142002080700114NM 2002 8 7 AUS20020747 120020725G53471A0870129 SEAT TRACK BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU SEAT/CARGO ATTACFAILED W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) CAPTAINS SEAT FAILED TO LOCK IN SEAT TRACKS. SEAT SLID COMPLETELY BACK DURING TAKEOFF. 2L72 4F4 FRTA16WE E21EU 20020807001152002080700115NE 2002 8 7 AUS20020749 220020717G74219550168760 IGNITER TMECA ARRIEL1B SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE SPARK PLUG/IGNITUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS 945 (AUS) ENGINE IGNITER CENTRE ELECTRODE MISSING. IMPACT DAMAGE ON FIRST STAGE TURBINE AND FREE TURBINE BLADES. 1G71 3U3 UNCH9EU E19EU 20020807001162002080700116CE 2002 8 7 AUS20020751 120020712G534204320049 BRACKET CESSNA150 A152 2071836CE LYC O235 O235L2C 41505EA MCAULY2A34C D2A34C98 GL FUSELAGE, STABILCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STEEL BRACKET ASSEMBLY CRACKED IN TWO PLACES. ONE CRACK LOCATED AT WELD SEAM AND ONE CRACK IN AREA OF ANCHOR NUT ATTACHMENT.BRACKET ATTACHES VERTICAL FIN TO TAILPLANE AND TAILPLANE TO FUSELAGE. 1H71 3O3 O 3A19 E223 5 CP3EA 20020809000802002080900080SO 2002 8 9 AUS20020752 120020719G3230751658 ARM PIPER PA23 PA23250 7102308SO AMTR C8289 C8289 GL MLG MISRIGGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EMERGENCY LANDING GEAR EXTENSION SYSTEM CO2 DISCHARGE UNIT LEVER ARM INCORRECTLY RIGGED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O 1A10 5 NEXPP5N 20020807001172002080700117EA 2002 8 7 AUS20020754 220020717G7414 MAGNETO LYC IO540K1B5 BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL MAGNETO/DISTRIBUFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO2 ENGINE NO2 MAGNETO FAULTY. MAGNETO MODELS 10-349370-4 AND 10-349310-8. 1H72 3O3 O A17EU 1E4 5 CP920 20020807001182002080700118EA 2002 8 7 AUS20020756 220020620G74141052948 SHAFT CONT 106006163 ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAGNETO/DISTRIBUBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS D129606E (AUS) RH MAGNETO ROTATING SHAFT BROKEN. 1G71 3O3 O H11NM E295 20020807001192002080700119CE 2002 8 7 AUS20020757 120020710G760399104351 CABLE CONT TSIO520VB CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C93 GL POWER LEVER FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE CONTROL CABLE INNER CABLE FAILED AT SWAGED ATTACHMENT TO THE COCKPIT END FITTING. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020809001022002080900102EU 2002 8 9 AUS20020759 120020717G29329738114306 PRESSURE SWITCH PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYDRAULIC SYSTEMFAILED W O OTHER J WARNING INDICATION CLCLIMB 1 AUS (AUS) HYDRAULIC PRESSURE SWITCH FAILED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020807001202002080700120CE 2002 8 7 AUS20020763 120020724G2820 CONNECTOR CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C 2A34C203 GL AIRCRAFT FUEL DIDETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FLEXIBLE FUEL LINE CONNECTORS PERISHED. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020807001212002080700121CE 2002 8 7 AUS20020765 120020724G2820 CONNECTOR CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C C2A34C204 GL AIRCRAFT FUEL DIDETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FLEXIBLE FUEL LINE CONNECTORS PERISHED. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020807001222002080700122EA 2002 8 7 AUS20020766 220020717G7421RHB37E SPARK PLUG CHAMPION RHB37E PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL SPARK PLUG/IGNITUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH ENGINE NO2 CYLINDER TOP SPARK PLUG DEFECTIVE. PLUG GAP WAS OUT OF ADJUSTMENT AND CERAMIC INSULATOR CRACKED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020807001232002080700123CE 2002 8 7 AUS20020774 120020724G7920124700210CR0310 HOSE CONT GTSIO520L CESSNA421 421 2076010CE CONT O520 GTSIO520L 17032SO MCAULY3FF32 3FF32C501 GL ENGINE OIL DISTRTRANSPOSED W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 1329 (AUS) LH ENGINE OIL FILTER SUPPLY AND DISCHARGE HOSES TRANSPOSED. OIL FILTER RUPTURED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 ORTA7CE E7CE 5 CP45GL 20020807001242002080700124NM 2002 8 7 AUS20020775 120020729G27505906989202 FITTING SUNDSTRANDEM745581A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE TRAILING EDGE FLSEPARATED W K NONE O OTHER ININSP/MAINT 1 AUS 1981 (AUS) SECONDARY DRIVE FLEXIBLE SHAFT ALUMINIUM END FITTING SEPARATEDFROM THE OUTER WIRE BRAID. THE INNER FLEX DRIVE WAS FOUND TO BE SLIGHTLY BENT AT ONE END. DURING REMOVAL OF THE DRIVE SHAFT, IT WAS FOUND THAT THE OTHER ALUMINIUM END FITTING HAD COME FREE FROM THE OUTER WIRE BRAID. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807001252002080700125NM 2002 8 7 AUS20020776 120020729G575185740005003 AILERON DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE AILERONS DAMAGED W K NONE C F.O.D. CLCLIMB 1 AUS 8824330429 (AUS) RH AILERON DAMAGED IN AREA OF LH TRAILING EDGE. DAMAGE WAS THEEXIT POINT OF A LIGHTNING STRIKE. THE AREA OF DAMAGE WASAPPROXIMATELY 193.5SQUAREMM (3SQIN) THROUGH SEVEN RIVET HEADS WITH A HOLE OF APPROXIMATELY 25.4MM (1IN). SEE MDR 02/0777 FORINFORMATION ON DAMAGE CAUSED AT THE OTHER LIGHTNING EXIT POINT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807001262002080700126NM 2002 8 7 AUS20020777 120020729G552085740001003 ELEVATOR DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE ELEVATOR STRUCTUDAMAGED W K NONE C F.O.D. CLCLIMB 1 AUS (AUS) AIRCRAFT STRUCK BY LIGHTNING. LIGHTNING EXITED AIRCRAFT AT THE RH OUTBOARD TRAILING EDGE OF THE RH ELEVATOR. DAMAGE WAS A DEFORMEDAREA OF APPROXIMATELY 200MM BY 100MM (8IN BY 4IN) AND AN EXIT HOLE OF APPROXIMATELY 38.1MM (1.5IN). SEE MDR 02/0776 FOR INFORMATION ON THE DAMAGE CAUSED AT THE OTHER EXIT POINT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020906000482002090600048NM 2002 9 6 AUS20020779 120020724G2731AR7077M3 ACTUATOR BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU ELEVATOR TAB CONFAULTY W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS 17816 AA0301 (AUS) STABILISER TRIM ACTUATOR FAULTY. 2L72 4F4 FRTA16WE E21EU 20020906000492002090600049NM 2002 9 6 AUS20020780 120020725G2510110764101 INERTIA REEL BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FLIGHT COMPARTMEFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FIRST OFFICERS SEAT BELT SHOULDER HARNESS RH INERTIA REEL FAILED. 2L72 4F4 FRTA16WE E21EU 20020909000012002090900001EU 2002 9 9 AUS20020781 120020429G27529787320307 ACTUATOR PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAPS FAULTY W O OTHER F FLT CONT AFFECTED DEDESCENT 1 AUS (AUS) FLAP ACTUATOR FAULTY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020906000502002090600050SO 2002 9 6 AUS20020782 120020730G27314173404 CABLE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ELEVATOR TAB CONBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR ELEVATOR TRIM CABLE PNO 41734-78 BROKEN AT TRIM SERVO. INSPECTION OF FORWARD ELEVATOR TRIM CABLE PNO 41734-77 DAMAGEDDUE TO CABLE OVERRUN ON DRUM. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906000512002090600051NM 2002 9 6 AUS20020784 120020729G2824 VALVE BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUEL TRANSFER VAFAILED W K NONE O OTHER DEDESCENT 1 AUS (AUS) FUEL CROSSFEED VALVE FAILED IN THE OPEN' POSITION. 2L72 4F4 FRTA16WE E21EU 20020906000522002090600052CE 2002 9 6 AUS20020788 120020711G325208424057 BARREL CESSNA 0842410 CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C93 GL SHIMMY DAMPER BROKEN W K NONE OF OTHER FLT CONT AFFECTED LDLANDING 1 AUS (AUS) NOSE LANDING GEAR SHIMMY DAMPER BODY BROKEN AWAY FROM ATTACHMENTLUG. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020906000532002090600053EA 2002 9 6 AUS20020789 220020614G8540STD2208 SCREW LYC VO540C2A HILLERUH12 UH12E 4360122WP LYC O540 VO540C2A 41532EA RECIPROCATING ENFAILED W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE CRCRUISE 1 AUS L89543 (AUS) ENGINE ACCESSORY DRIVE GEAR PNO 67609 TO STARTER DRIVE GEAR PNO 67583 ATTACHMENT STUDS (6OFF) PNO STD-2208 AND DOWELS (3OFF) PNO72139 SHEARED. 1G71 3O3 O 4H11 E304 20020906000542002090600054SW 2002 9 6 AUS20020790 120020710G7603660166007 CABLE LYC IO360A3B6 MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MCAULY2D34C B2D34C212 GL POWER LEVER WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE THROTTLE CABLE WORN. CABLE WAS STIFF TO OPERATE AND JAMMED ON SEVERAL OCCASIONS. 1L71 3O3 O 2A3 1E10 5 CP7EA 20020909000082002090900008SW 2002 9 9 AUS20020793 120020729G7120BC001198050 MOUNT SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE ENGINE BURNED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT ENGINE UPPER MOUNT HEAT DAMAGED. HEAT DAMAGE ALSO FOUND ON HOSES PN SS1001K000312 AND PN SS1001F0000100. NO CAUSE OF DAMAGE WAS FOUND BUT IT IS SUSPECTED THAT A FUEL LEAK HAD OCCURRED AT THE NR 10 FUEL NOZZLE FITTING ALTHOUGH THE FITTING WAS FOUND TO BE CORRECTLY TORQUED. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020906000552002090600055SO 2002 9 6 AUS20020797 120020518G3230AN8374D FITTING PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR RETBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HYDRAULIC ELBOW FITTING ON INNER LH LANDING GEAR DOOR ACTUATORBROKEN. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906000562002090600056EU 2002 9 6 AUS20020798 120020515G2700 RELAY FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU FLIGHT CONTROL SFAULTY W K NONE FJ FLT CONT AFFECTED WARNING INDICATION TOTAKEOFF 1 AUS (AUS) FLIGHT CONTROL TAKEOFF WARNING RELAY FAULTY. CONNECTOR LOCATED AT REAR PRESSURE BULKHEAD DIRTY. 2L72 4F4 FRTA20EU E2EU 20020906000572002090600057EU 2002 9 6 AUS20020799 120020526G2460 CONNECTOR FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU DC POWER DISTRIBFAULTY W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION TOTAKEOFF 1 AUS (AUS) NO2 GENERATOR FEED PLUG SUSPECT DIRTY. 2L72 4F4 FRTA20EU E2EU 20020906000582002090600058EU 2002 9 6 AUS20020800 120020510G243223531 BATTERY FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU BATTERY/CHARGER OVERHEATED W K NONE HMJELECT. POWER LOSS-50 PC OVER TEMP WARNING INDICATION TOTAKEOFF 1 AUS 87 (AUS) FORWARD BATTERY OVERHEATED. 2L72 4F4 FRTA20EU E2EU 20020906000592002090600059EU 2002 9 6 AUS20020801 120020502G3230 DOWNLOCK FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU LANDING GEAR RETCONTAMINATED W K NONE ON OTHER FALSE WARNING NRNOT REPORTED 1 AUS (AUS) LANDING GEAR DOWNLOCK SWITCH AND DOOR UPLOCK SWITCH CONTAMINATEDWITH DIRT AND GREASE. 2L72 4F4 FRTA20EU E2EU 20020906000602002090600060EU 2002 9 6 AUS20020804 120020516G32321252515 ACTUATOR FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU LANDING GEAR DOOLEAKING W K NONE OJ OTHER WARNING INDICATION LDLANDING 1 AUS 20074 AH665 (AUS) RH MAIN LANDING GEAR DOOR AFT ACTUATOR LEAKING INTERNALLY. 2L72 4F4 FRTA20EU E2EU 20020906000612002090600061EU 2002 9 6 AUS20020806 120020514G243223531 BATTERY FOKKERF28 F28MK4000 4990810EU RROYCESPEY SPEY55515 54521EU BATTERY/CHARGER OVERHEATED W K NONE O OTHER ININSP/MAINT 1 AUS 12 D1433 (AUS) FORWARD BATTERY OVERHEATED. 2L72 4F4 FRTA20EU E2EU 20020906000622002090600062NM 2002 9 6 AUS20020807 120020716G2421 GENERATOR DHAV DHC8 DHC8* NM PWA 120 PW123D 52152NE AC GENERATOR-ALTFAULTY W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) NO1 AC GENERATOR FAULTY. 2H72 4T4 TRTA13NM E20NE 20020906000632002090600063NM 2002 9 6 AUS20020809 120020724G2720 MODULE BOEING767 76733A 1385209NM GE CF6 CF680A 30025NE RUDDER CONTROL SFAILED W K NONE FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) RUDDER RATIO MODULE FAILED. 2L72 4F4 FRTA1NM E13NE 20020906000642002090600064NM 2002 9 6 AUS20020813 120020801G274091238071 RELAY BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU STABILIZER CONTRFAULTY W K NONE F FLT CONT AFFECTED NRNOT REPORTED 1 AUS (AUS) STABILISER TRIM RELAY FAULTY. RELAY R64 AUXILIARY CONTACTS 13 AND 14 FAILED TO OPEN WHEN ENERGISED. 2L72 4F4 FRTA16WE E21EU 20020906000652002090600065EA 2002 9 6 AUS20020818 220020510G7310 LINE LYC LTIO540J2BD PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2 GL ENGINE FUEL DISTLOOSE W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS (AUS) FUEL PRESSURE LINE ON FCU LOOSE. LOSS OF POWER. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906000662002090600066SW 2002 9 6 AUS20020819 220020604G7414105413Y SEAL JACOBP R755A2 CESSNA195 195 2073102CE JACOBPR755 R755A2 35006SW HAMSTD2B 2B20 NE MAGNETO/DISTRIBUDETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS 5396927866 (AUS) MAGNETO/DISTRIBUTOR OIL SEAL DETERIORATED AND LEAKING. FURTHERINVESTIGATION ALSO FOUND CONTACTS BURNT AND PITTED. CAPACITOR UNSERVICEABLE. 1H71 3R3 RNCA790 TC237 5 CP255 20020909000232002090900023CE 2002 9 9 AUS20020820 120020801G53130713006 STRINGER CESSNA180 180C 2072608CE CONT O470 O470R 17026SO FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT LOWER ENGINE MOUNT STRINGER CRACKED IN LOWER RH RADIUS OF "U" SECTION. CRACK RUNS FROM THE FORWARD EDGE AND ALONG THE AFT BEND. 1H71 3O3 O 5A6 E273 20020906000672002090600067NE 2002 9 6 AUS20020821 220020715G73105905587 FILTER PWA PW118A EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE ENGINE FUEL DISTDIRTY W K NONE J WARNING INDICATION CRCRUISE 1 AUS 2011TLZ (AUS) RH ENGINE FUEL FILTER LIGHTLY CONTAMINATED. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20020906000682002090600068SO 2002 9 6 AUS20020822 220020802G8530629690 PISTON PIN CONT TSIO360KB PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL RECIPROCATING ENDAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 661 315114 (AUS) NO1 ENGINE PISTON PINS (6OFF) HAD SEVERE DAMAGE TO THE ALUMINIUMEND CAPS. THE END CAPS HAD MIGRATED OUTWARDS AND WERE RUBBING ONTHE CYLINDER WALLS. METAL CONTAMINATION OF ENGINE OIL SYSTEM. 1L72 3O3 O A7SO E9CE 5 CP920 20020906000692002090600069SO 2002 9 6 AUS20020823 220020807G8530648002 SHAFT CONT TSIO360KB PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL RECIPROCATING ENSCORED W K NONE O OTHER ININSP/MAINT 1 AUS 1071 (AUS) ROCKER SHAFT AND BUSH SCORED. SUSPECT CAUSED BY LACK OF LUBRICATION. 1L72 3O3 O A7SO E9CE 5 CP920 20020906000702002090600070SO 2002 9 6 AUS20020824 120020716G2810492308 DRAIN VALVE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL STORAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH FUEL SYSTEM DRAIN VALVE CORRODED DUE TO WATER CONTAMINATION. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000712002090600071SO 2002 9 6 AUS20020825 120020716G2810492308 DRAIN VALVE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL STORAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH FUEL DRAIN VALVE CORRODED DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000722002090600072SO 2002 9 6 AUS20020826 120020716G28206390194 HOSE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH FUEL HOSE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000732002090600073SO 2002 9 6 AUS20020827 120020716G28206390194 HOSE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH FUEL HOSE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020909000242002090900024SO 2002 9 9 AUS20020828 120020717G2820AN83244 FITTING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL DIST UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM FITTING UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000742002090600074SO 2002 9 6 AUS20020829 120020716G28208623840 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000752002090600075SO 2002 9 6 AUS20020830 120020716G28208623839 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000762002090600076SO 2002 9 6 AUS20020831 120020716G28208623806 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000772002090600077SO 2002 9 6 AUS20020832 120020716G28208623805 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000782002090600078SO 2002 9 6 AUS20020833 120020717G28208625402 FITTING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM T' FITTING UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000792002090600079SO 2002 9 6 AUS20020834 120020716G2822AN8166 NIPPLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL BOOST PUMP UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PUMP NIPPLE UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000802002090600080SO 2002 9 6 AUS20020835 120020717G28208623812 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000812002090600081SO 2002 9 6 AUS20020836 120020717G28208623811 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000822002090600082SO 2002 9 6 AUS20020837 120020717G2820AN9196D REDUCER PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM REDUCER UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000832002090600083SO 2002 9 6 AUS20020838 120020717G2820AN8266D FITTING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM T' FITTING UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000842002090600084EA 2002 9 6 AUS20020839 220020717G7314LW15399 PUMP LYC O360E1A6 PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE ENGINE FUEL PUMPUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000852002090600085SO 2002 9 6 AUS20020840 120020716G2822480543 PUMP PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL BOOST PUMP UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000862002090600086SO 2002 9 6 AUS20020841 120020716G2822480543 PUMP PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL BOOST PUMP UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PUMP CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000872002090600087SO 2002 9 6 AUS20020842 120020716G2822AN8226 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE FUEL BOOST PUMP UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL PUMP ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000882002090600088SO 2002 9 6 AUS20020843 120020717G2820AN8376 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000892002090600089SO 2002 9 6 AUS20020844 120020717G2820AN8378 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000902002090600090SO 2002 9 6 AUS20020845 120020717G2820AN8218 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000912002090600091SO 2002 9 6 AUS20020846 120020716G2820AN8336 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW CORRODED AND UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000922002090600092SO 2002 9 6 AUS20020847 120020715G282063901101 HOSE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS 2816 (AUS) FUEL SYSTEM HOSE UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000932002090600093SO 2002 9 6 AUS20020848 120020715G28206390124 HOSE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS 281 (AUS) FUEL SYSTEM HOSE UNSERVICEABLE DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020909000252002090900025EA 2002 9 9 AUS20020849 220020717G7322105219 CARBURETOR PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CARBURETOR CORRODED DUE TO WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000942002090600094SO 2002 9 6 AUS20020850 120020717G28208623803 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000952002090600095SO 2002 9 6 AUS20020851 120020717G28208623804 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000962002090600096SO 2002 9 6 AUS20020852 120020717G28208623807 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000972002090600097SO 2002 9 6 AUS20020853 120020717G28208623810 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000982002090600098SO 2002 9 6 AUS20020854 120020717G28208623809 TUBE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM TUBE CORRODED AND UNSERVICEABLE DUE TO WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906000992002090600099SO 2002 9 6 AUS20020855 220020807G8530646460 EXHAUST VALVE CONT TSIO360KB PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL RECIPROCATING ENWORN W K NONE O OTHER ININSP/MAINT 1 AUS 1071 (AUS) NO3 CYLINDER EXHAUST VALVE TIP WORN EXCESSIVELY. CORRESPONDINGROCKER DAMAGED ON CONTACT AREA. EXHAUST VALVES PNO 646460 AND INLET VALVES PNO 646459 IN OTHER CYLINDERS ALSO SHOWING SIGNS OFPITTING ON THE TIPS. 1L72 3O3 O A7SO E9CE 5 CP920 20020906001002002090600100NM 2002 9 6 AUS20020857 120020807G3230AE2464163E0192 HOSE BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU LANDING GEAR RETRUPTURED W K NONE KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 AUS (AUS) LH MAIN LANDING GEAR UPLOCK ACTUATOR HOSE RUPTURED. LOSS OF HYDRAULIC FLUID CAUSED FAILURE OF LH ENGINE DRIVEN HYDRAULICPUMP. 2L72 4F4 FRTA16WE E21EU 20020909000272002090900027CE 2002 9 9 AUS20020858 120020704G2434A165235 BOLT CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL ALTERNATOR LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 290 (AUS) ALTERNATOR THROUGH BOLTS LOOSE. ROTOR RUBBING ON FIELD WINDINGS CAUSING DAMAGE TO STATOR. SUSPECT CAUSED BY FAILURE TO RETORQUE BOLTS AFTER FIFTEEN HOURS OPERATION. 1H71 3O3 O A4CE E5CE 5 CP21EA 20020906001012002090600101CE 2002 9 6 AUS20020859 120020725G32464075D WHEEL CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL WHEEL/SKI/FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WHEEL CRACKED ALONG INBOARD EDGE OF BEAD SEAT. CRACK LENGTH APPROXIMATELY 120MM (4.72IN). 1H71 3O3 O A4CE E5CE 5 CP21EA 20020906001022002090600102EU 2002 9 6 AUS20020860 120020725G554068340451 BRACKET PARTEN RUDDER PARTENP68 P68B 6780104EU LYC O360 IO360A1B6 41514EA HARTZLHCC2Y HCC2YK2 GL RUDDER STRUCTURECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 146 (AUS) TOP RUDDER HINGE BRACKET CRACKED. 1H72 3O3 O A31EU 1E10 5 CP920 20020909000282002090900028CE 2002 9 9 AUS20020861 120020624G5312 BULKHEAD BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LOWER REAR PRESSURE BULKHEAD CRACKED. CRACK IS LOCATED IN THE AREA ONE ROW OF RIVETS DOWN FROM THE LAP JOINT AND DIRECTLY ABOVE THE OUTFLOW VALVE. CRACKING IS SIMILAR TO THAT DESCRIBED IN AD/B200/67 BUT WAS NOT FOUND DURING THE AD CHECK. THE AIRCRAFT HAS 321 CYCLES TO RUN UNTIL THE NEXT INSPECTION IAW AD/B200/67. 1L72 4T4 T A24CE E4EA 20020906001032002090600103SO 2002 9 6 AUS20020864 120020717G2820AN8166 NIPPLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM NIPPLE CORRODED DUE TO FUEL SYSTEM WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001042002090600104SO 2002 9 6 AUS20020865 120020717G2820AN8166 NIPPLE PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM NIPPLE CORRODED DUE TO FUEL SYSTEM WATERCONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001052002090600105SO 2002 9 6 AUS20020866 120020717G2820AN8226 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001062002090600106SO 2002 9 6 AUS20020867 120020717G2820AN8226 ELBOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM ELBOW UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001072002090600107SO 2002 9 6 AUS20020868 120020717G2820AN9102 COUPLING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001082002090600108SO 2002 9 6 AUS20020869 120020717G2820AN9102 COUPLING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM AFT COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001092002090600109SO 2002 9 6 AUS20020870 120020717G2820AN9102 COUPLING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM FORWARD COUPLING UNSERVICEABLE AND CORRODED DUE TOFUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001102002090600110SO 2002 9 6 AUS20020871 120020717G2820AN9102 COUPLING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE AIRCRAFT FUEL DIUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUEL SYSTEM AFT COUPLING UNSERVICEABLE AND CORRODED DUE TO FUEL SYSTEM WATER CONTAMINATION. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001112002090600111SO 2002 9 6 AUS20020875 120020516G29101107212159 HOSE EMB 110 EMB110P1 3260122SO HYDRAULIC SYSTEMFAILED W K NONE K FLUID LOSS CRCRUISE 1 AUS (AUS) HYDRAULIC HOSE FAILED IN AN AREA APPROXIMATELY 200MM (8IN) ALONGTHE LENGTH ALONG THE HOSE. LOSS OF HYDRAULIC FLUID. SUSPECT HOSEHAD SUFFERED SOME DISTRESS DURING ITS LIFE. 1L72 4T A21SO 20020906001122002090600112CE 2002 9 6 AUS20020876 120020422G5312 BULKHEAD CESSNA206 U206G 2073356CE FUSELAGE MAIN, BCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH FORWARD DOORPOST BULKHEADCRACKED. 1H71 3O A4CE 20020906001132002090600113EA 2002 9 6 AUS20020877 120020712G5310 STRUCTURE DHAV DHC6 DHC6 2802606EA FUSELAGE MAIN, SDAMAGED W K NONE C F.O.D. LDLANDING 1 AUS (AUS) FORWARD BULKHEAD, NLG ATTACHMENT FITTINGS AND SURROUNDING LOWER FUSELAGE STRUCTURE DAMAGED WHEN THE NOSEWHEEL CONTACTED A ROCKDURING LANDING. 1H72 3T RTA9EA 20020906001142002090600114 2002 9 6 AUS20020878 420020520G2312 ANTENNA DHAV DHC6 DHC6 2802606EA VHF COMMUNICATIODAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VHF ANTENNA DAMAGED BY IMPACT FROM AN UNKNOWN OBJECT. FUSELAGESKIN AFT OF THE ANTENNA MOUNT SUFFERED A 50.8MM (2IN) TEAR. THE ANTENNA IS MOUNTED ON THE LOWER FUSELAGE AT STN 376. FOD 1H72 3T RTA9EA 20020906001152002090600115EA 2002 9 6 AUS20020879 120020716G3246JUN01727 WHEEL CLEVELAND 1500X12X14 DHAV DHC6 DHC6 2802606EA WHEEL/SKI/FLOAT DAMAGED W K NONE OE OTHER VIBRATION/BUFFET LDLANDING 1 AUS JUN01727 (AUS) LH MAIN WHEEL OUTER HUB DAMAGED. TYRE DEFLATED. 1H72 3T RTA9EA 20020906001162002090600116NM 2002 9 6 AUS20020880 120020523G2750 TORQUE TUBE DHAV DHC8 DHC8* NM TRAILING EDGE FLFAILED W K NONE FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) FLAP DRIVE TORQUE TUBE SEVERED AT A POINT APPROXIMATELY 4 METRESOUTBOARD OF THE LH NACELLE. 2H72 4T RTA13NM 20020906001172002090600117EA 2002 9 6 AUS20020881 220020702G7532 BLEED VALVE PWA PT6A41 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COMPRESSOR BLEEDCONTAMINATED W K NONE EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) NO2 ENGINE HP BLEED VALVE PISTON CONTAMINATED WITH GRIME. 1L72 4T4 T A24CE E4EA 20020906001182002090600118SO 2002 9 6 AUS20020885 220020802G8530637836 VALVE SPRING CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS 1310 268396R (AUS) NO6 CYLINDER INNER EXHAUST VALVE SPRING BROKEN. METAL CONTAMINATION OF OIL SYSTEM. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020906001192002090600119SO 2002 9 6 AUS20020886 120020812G324616103000 WHEEL CLEVELAND 4076A PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL WHEEL/SKI/FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NOSE WHEEL CRACKED FROM BEAD SEAT AREA THROUGH TO OUTER SURFACE.CRACK LENGTH 76.2MM (3IN). 1L72 3O3 O A20SO E14EA 5 CP33EA 20020909000392002090900039SO 2002 9 9 AUS20020890 120020503G2913 MOTOR PIPER PA32 PA32R300 7103213SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK1 GL HYDRAULIC PUMP, CONTAMINATED W O OTHER J WARNING INDICATION LDLANDING 1 AUS (AUS) POWER PACK ELECTRIC MOTOR CONTAMINATED BY OIL. DURING LANDING THE LT MAIN LANDING GEAR COLLAPSED. 1L71 3O3 O A3SO 1E4 5 CP920 20020906001202002090600120CE 2002 9 6 AUS20020891 120020318G8120BH003250 SEAL GARRTT 4659302 CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL EXHAUST TURBOCHAFAILED W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS BH003250 (AUS) TURBOCHARGER OIL SEAL FAILED ALLOWING OIL TO ENTER THE ENGINE VIA THE INDUCTION SYSTEM. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020906001212002090600121EA 2002 9 6 AUS20020892 220020726G74141050746Y GEAR BENDIX S6LN200 PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCA2X HCA2XL2 GL MAGNETO/DISTRIBUSTRIPPED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS A151211 (AUS) LH ENGINE RH MAGNETO DISTRIBUTOR GEAR TEETH STRIPPED. APPROXIMATELY HALF OF THE TEETH WERE SHEARED OFF AT THE ROOTENDS. SUSPECT CAUSED BY ENGINE BACKFIRE. 1L72 3O3 O 1A10 1E4 5 CP908 20020906001222002090600122EA 2002 9 6 AUS20020898 220020813G73137415125248642 INJECTOR BENDIX RSA5AD1 PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA MCAULY2D34C B2D34C213 GL FUEL INJECTOR NODIRTY W K NONE E VIBRATION/BUFFET TOTAKEOFF 1 AUS 896 58354 (AUS) NO2 CYLINDER FUEL INJECTOR NOZZLE DIRTY. 1L71 3O3 O 2A13 1E10 5 CP7EA 20020906001232002090600123SW 2002 9 6 AUS20020899 120020709G6220204011151001 BOLT BELL 205812001 BELL 205 205A1 1181414SW LYC T53 T5313A 41549NE MAIN ROTOR HEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS ADA05660 (AUS) MAIN ROTOR BLADE BOLT SUSPECT CRACKED. FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION. 1G71 4U4 U H1SW E17EA 20020906001242002090600124NM 2002 9 6 AUS20020901 120020813G78303810056105 MODULE GE CFM563C BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU THRUST REVERSER LEAKING W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS 01082 (AUS) RH ENGINE THRUST REVERSER HYDRAULIC ISOLATION LEVER ASSEMBLYFAILED ALLOWING HYDRAULIC FLUID TO LEAK. 2L72 4F4 FRTA16WE E21EU 20020906001252002090600125NE 2002 9 6 AUS20020903 120020813G2612 WIRE SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE FIRE DETECTION WORN W K NONE EBNVIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS FALSE WARNING CRCRUISE 1 AUS (AUS) NO2 ENGINE FIRE WARNING. PRIMARY AND SECONDARY FIRE EXTINGUISHERS DISCHARGED. INVESTIGATION COULD FIND NO EVIDENCE OF FIRE. CAUSEDBY CHAFING OF FIRE WARNING SYSTEM WIRE. 1G72 3U3 UNCH1NE E19EU 20020906001262002090600126SO 2002 9 6 AUS20020908 120020720G3230JE73 ACTUATOR PIPER PA28 PA28R180 7102809SO LYC O360 IO360B1E 41514EA HARTZLHCC2Y HCC2YK1 GL LANDING GEAR RETCRACKED W K NONE O OTHER LDLANDING 1 AUS (AUS) LH MAIN LANDING GEAR DOWNLOCK ACTUATOR DEFORMED AND CRACKED.INVESTIGATION FOUND WASHERS HAD BEEN ADDED BETWEEN THE FRONT ANDREAR HOOK ON THE LINK ASSEMBLY. 1L71 3O3 O 2A13 1E10 5 CP920 20020906001272002090600127SO 2002 9 6 AUS20020909 120020807G3230 DOWNLOCK PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR RETSEIZED W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) LH MAIN LANDING GEAR DOWNLOCK PARTIALLY SEIZED PREVENTING POSITIVE LOCKING. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906001282002090600128NM 2002 9 6 AUS20020910 120020816G3240 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR BRALOOSE W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) RH MAIN LANDING GEAR BRAKE HYDRAULIC LINE SWIVEL FITTING B' NUT LOOSE. INVESTIGATION FOUND THE RH MAIN LANDING GEAR DRAG STRUT ACTUATOR SWIVEL FITTING LINE ALSO LOOSE. A SIGNIFICANT LOSS OF HYDRAULIC FLUID OCCURRED. FURTHER INVESTIGATION FOUND THAT THERE WAS NO EVIDENCE OF FLUID LEAKING FROM THE LAST FLIGHT. FURTHER INVESTIGATION FOUND EVIDENCE OF SABOTAGE/CRIMINAL ACTION. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020906001292002090600129SO 2002 9 6 AUS20020911 220020720G8530537750 STUD CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENSHEARED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 551 PN653452 (AUS) CYLINDER ROCKER SHAFT BOLTS LOOSE. ONE STUD FRACTURED WITHSUBSEQUENT DAMAGE TO THE INLET VALVE PUSHROD AND TUBE. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020906001302002090600130SO 2002 9 6 AUS20020912 220020707G852065411912A2 CRANKCASE CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENCRACKED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 1077 810536R (AUS) ENGINE CRANKCASE CRACKED. NO5 CYLINDER REAR HOLDDOWN STUD NUT LOOSENED LEADING TO FAILURE OF THE OTHER HOLDDOWN NUTS ANDSEPARATION OF THE CYLINDER. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020906001312002090600131CE 2002 9 6 AUS20020913 120020805G2700051010544 CABLE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA AMTR C8289 C8289 GL FLIGHT CONTROL SCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CONTROL CABLE CORRODED WITH APPROXIMATELY 50% OF THE STRANDSBROKEN/FRAYED. 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20020906001322002090600132CE 2002 9 6 AUS20020914 120020725G7602S123411 CABLE LYC O320E2D CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA AMTR C8289 C8289 GL MIXTURE CONTROL WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MIXTURE CONTROL CABLE INNER WIRE WORN TO LESS THAN 50% OF NORMALTHICKNESS. CABLE DIAMETER WAS 62MM (0.024IN) INSTEAD OF THE NORMAL DIAMETER 1.6MM (0.062IN). 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20020906001332002090600133CE 2002 9 6 AUS20020915 120020725G7603S123017 CABLE LYC O320E2D CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA AMTR C8289 C8289 GL POWER LEVER WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) THROTTLE CONTROL INNER CABLE WORN BY MORE THAN 60% OF THE DIAMETER. WIRE DIAMETER WAS 0.5MM (0.019IN) INSTEAD OF THE NORMAL 1.5MM (0.059IN). 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20020906001342002090600134CE 2002 9 6 AUS20020916 120020805G2700051010545 CABLE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA AMTR C8289 C8289 GL FLIGHT CONTROL SCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CONTROL CABLE RUSTED IN AREA OF REAR FUSELAGE. 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20020906001352002090600135SO 2002 9 6 AUS20020917 120020818G522086602 WINDOW PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE EMERGENCY EXITS SEPARATED W K NONE D INFLIGHT SEPARATION CRCRUISE 1 AUS (AUS) EMERGENCY EXIT WINDOW SEPARATED FROM AIRCRAFT. THE EMERGENCY EXIT HAD BEEN REMOVED AND REINSTALLED THREE DAY PREVIOUSLY TO CARRYOUT AD/GEN/37 (EMERGENCY EXIT INSPECTION). THE WINDOW SEPARATED DURING THE FIRST FLIGHT FOLLOWING THE INSPECTION. INVESTIGATION FOUND THAT THE FORWARD LOCKING LUG MAY NOT HAVE BEEN COMPLETELY ENGAGED. THE CORRECT LOCKING OF THE FORWARD LUG CANNOT BE POSITIVELY CONFIRMED AS THERE IS NO INSPECTION HOLE. 1L72 3O3 O A19S0 E286 5 CP25EA 20020906001362002090600136EU 2002 9 6 AUS20020918 120020812G3240086170046 LINK REIMS 406 F406 7535723EU PWA PT6 PT6A112 52043NE MCAULY3G34C73GFR34C701 GL LANDING GEAR BRACRACKED W K NONE O OTHER NRNOT REPORTED 1 AUS 3859 (AUS) COPILOTS OUTBOARD BRAKE PEDAL RH LINK ASSEMBLY CRACKED IN THE AREA OF THE WELD ATTACHING THE CLEVIS RODEND. 1L72 3T3 TRTA54EU E4EA 5 CP60GL 20020906001372002090600137CE 2002 9 6 AUS20020926 120020821G2750 CABLE CESSNA500 550 2076604CE PWA 530 PW530A NE TRAILING EDGE FLFRAYED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TRAILING EDGE FLAP CABLES (14OFF) FRAYED. FLAP CABLE PART NUMBERS ARE:- PNO 6565007-102-1CR, PNO 6565007-100-1CR, PNO 6565007-114CR, PNO 6565007-112CR, PNO 6565007-401, PNO6565007-90CR, PNO 5565150-16CR (2OFF), PNO 5565150-3CR(2OFF), PNO 5565150-2CR, PNO 5565150-4CR, PNO 6565007-97-1CR & PNO6565007-95-1CR. CABLES ARE FRAYED ON THE INSIDE OF A TIGHT BEND RADIUS WHERE THEY ARE ATTACHED TO BELLCRANKS. 1L72 4F4 F A22CE E00053EN 20020906001382002090600138CE 2002 9 6 AUS20020927 120020821G5712651102829 RIB CESSNA500 550 2076604CE PWA 530 PW530A NE WING, RIB/BULKHECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WING RIB WEB CRACKED DUE TO FLEXING CAUSED BY AILERON PULLEYBRACKET AND FLAP PULLEY BRACKET ATTACHED TO RIB. 1L72 4F4 F A22CE E00053EN 20020906001392002090600139SO 2002 9 6 AUS20020928 120020821G57112355100 SPAR PIPER PA30160 PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 301785 (AUS) LH WING INBOARD SPAR LOWER SPAR CAP ASSEMBLY SEVERELY CORRODED. CORROSION IS INITIATED BY INGRESS OF EXHAUST GASSES THROUGH A FUEL DRAIN HOLE IN A PANEL FORWARD OF THE SPAR. THE FUEL DRAIN IS PART OF CANCELLED AD/PA30&39/20. 1L72 3O3 O A1EA 1E12 5 CP9EA 20020909000592002090900059GL 2002 9 9 AUS20020930 320020819G6114FE248 HUB AMTR VANS RV8 GL CONT IO360 IO360* 17025CE HARTZLHCF2Y HCF2YR1 GL PROPELLER UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) PROPELLER HUB IS A SUSPECT UNAPPROVED PART. INVESTIGATION FOUND THAT THE HUB SERIAL NUMBER IS NOT USED ON THIS TYPE OF AIRCRAFT. HUB FLANGE TYPE ALSO INCORRECT. FURTHER INVESTIGATION FOUND THAT THE ORIGINAL MODEL STAMPINGS HAD BEEN PREVIOUSLY REMOVED. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1L71 3O3 ONTEXPA1L71E1CE 5 CP27EA 20020909000602002090900060GL 2002 9 9 AUS20020931 320020816G6111F7666A2 BLADE AMTR VANS RV8 GL CONT IO360 IO360* 17025CE HARTZLHCF2Y HCF2YR1 GL PROPELLER UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) PROPELLER BLADE SUSPECT UNAPPROVED PART. INVESTIGATION FOUND THAT THE BLADE HAD ORIGINALLY BEEN AN FC7666A BLADE BUT HAD BEEN ILLEGALLY MODIFIED BY UNKNOWN PARTIES TO AN F7666A BLADE. THE BLADE MANUFACTURER WAS CONTACTED AND CONFIRMED THAT THE BLADE WITH THE SN E1230 WAS ORIGINALLY AN FC8468-6R BLADE. SUSPECT SERIAL NUMBER STAMPED ON BLADE WAS A BOGUS NUMBER. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 ONTEXPA1L71E1CE 5 CP27EA 20020906001402002090600140SO 2002 9 6 AUS20020933 120020813G5553 FITTING PIPER PA28 PA28RT201 7102818SO LYC O360 IO360C1C6 41514EA MCAULY2D34C 2D34C215 GL VERTICAL STABILICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VERTICAL FIN ATTACHMENT FITTING HEAVILY CORRODED. FIN SPAR ALSO CORRODED WITH RIVETS MISSING. PART NUMBERS OF AFFECTED ITEMS:-PNO 86548-02, PNO 78935-27, PNO 35697-02 & PNO 38622-02. 1L71 3O3 O 2A13 1E10 5 CP7EA 20020906001412002090600141SO 2002 9 6 AUS20020935 120020820G57204465502 PLATE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL WING, MISCELLANECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 12855 (AUS) WING SPLICE PLATE CONTAINED EXFOLIATION CORROSION ON THE RH AFT EDGE. FOUND DURING INSPECTION IAW AD/PA31/122 AMDT1. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906001422002090600142SO 2002 9 6 AUS20020937 220020701G8520SA42720 BEARING CONT O470U CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C C2A34C204 GL RECIPROCATING ENFAILED W K NONE O OTHER ININSP/MAINT 1 AUS 286516R (AUS) CRANKSHAFT MAIN BEARINGS SHOWED INDICATIONS OF PREMATURE FAILURE. BEARINGS PNO SA 633136 (2OFF) AND PNO SA 642720 (6OFF). ENGINEWAS BEING BULK STRIPPED FOLLOWING PROPELLER STRIKE. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020906001432002090600143NE 2002 9 6 AUS20020938 220020818G72303040689 IMPELLER PWA PW118A EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14SF 14SF9 NE TURBINE ENGINE CFOD W K NONE O OTHER ININSP/MAINT 1 AUS PCE115662 (AUS) RH ENGINE LOW PRESSURE IMPELLER DAMAGED BEYOND LIMITS BY FOD. 2L72 4T4 TRTA31SO E20NE 6 NP11NE 20020909000652002090900065SO 2002 9 9 AUS20020940 120020823G2140461731 REGULATOR PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 AUS 181 (AUS) FUEL PRESSURE REGULATOR LEAKING FUEL FROM DIAPHRAGM WHEN THE HEATER CYCLES OFF. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020906001442002090600144EA 2002 9 6 AUS20020942 220020722G8520STD2209 BOLT LYC O540A1D5 PIPER PA25 PA25235 7102504SO LYC O540 O540A1D5 41532EA MCAULY1A200 1A200FA GL RECIPROCATING ENLOOSE W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) ENGINE CRANKSHAFT GEAR RETAINING BOLT LOOSE. THE BOLT HEAD WASWORN DOWN FROM RUBBING ON THE INSIDE OF THE OIL PUMP DRIVESHAFT.THE CRANKSHAFT GEAR ROTATED ON THE BOLT, SHEARING THE DRIVE DOWEL AND GEAR TEETH. THE LH MAGNETO DRIVE GEAR DAMAGED IN AREA WHERE THE DRIVE COUPLING LUGS CONTACTED THE SIDES OF THE CUSHIONRETAINING POCKET. GEAR TOOTH DAMAGE TRANSFERRED BETWEEN GEARS,WITH BROKEN TOOTH FOUND WEDGED BETWEEN THE TEETH OF THE IDLER GEAR . ONE TOOTH BROKEN OFF IDLER GEAR. LH MAGNETODISTRIBUTOR GEAR TEETH STRIPPED. OIL PUMP HOUSING SCORED. GEAR PNO 13S19647. BOLT PNO STD 2209. CRANKSHAFT PNO 75039. 1L71 3O3 O 2A10 E295 5 NP874 20020906001452002090600145SO 2002 9 6 AUS20020944 220020811G7322194580 PUMP FACET MA45 CESSNA182 182A 2072704CE CONT O470 O470L 17026SO HARTZLHCC3Y PHCC3YF1 GL FUEL CONTROL/RECWORN W K NONE O OTHER ININSP/MAINT 1 AUS 873 PAM681305 (AUS) CARBURETTOR ACCELERATOR PUMP WORN AND BROKEN. 1H71 3O3 ONT3A13 E273 5 CP25EA 20020906001462002090600146CE 2002 9 6 AUS20020945 120020821G281005235221 STRAP CESSNA172 172K 2072430CE LYC O320 O320E2D 41508EA AMTR C8289 C8289 GL FUEL STORAGE BROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH FUEL TANK REAR STRAP ASSEMBLY LOOSE. RH FUEL TANK REAR STRAP ASSEMBLY BROKEN NEAR THE SCREW END. FOUND DURING INSPECTION IAW CESSNA CONTINUED AIRWORTHINESS PROGRAM 28-30-01. 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20020906001472002090600147SO 2002 9 6 AUS20020948 120020807G32309515340 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) LANDING GEAR UP' HYDRAULIC TUBE CORRODED AND LEAKING THROUGH CORROSION HOLE LOCATED UNDER P' CLAMP. 1L72 3O3 O A7SO E9CE 5 CP920 20020906001482002090600148SO 2002 9 6 AUS20020949 120020807G32309515339 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR HYDRAULIC PIPE CORRODED IN AREA UNDER P' CLAMP. 1L72 3O3 O A7SO E9CE 5 CP920 20020906001492002090600149SO 2002 9 6 AUS20020950 120020824G61237871300 PLATE HARTZL BHCC2YF2 PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL PROPELLER FEATHECRACKED W K NONE O OTHER NRNOT REPORTED 1 AUS (AUS) PROPELLER PITCH LEVER FEATHER STOP PLATE CRACKED PREVENTING OPERATION OF PITCH LEVER. 1L72 3O3 O A7SO E9CE 5 CP920 20020906001502002090600150SO 2002 9 6 AUS20020951 120020824G61237871300 PLATE HARTZL BHCC2YF2 PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL PROPELLER FEATHECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER PITCH CONTROL LEVER FEATHER STOP GATE PLATE CRACKED. 1L72 3O3 O A7SO E9CE 5 CP920 20020906001512002090600151CE 2002 9 6 AUS20020952 120020808G2710556555037R CABLE CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE AILERON CONTROL FRAYED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AILERON INTERCONNECT CABLE FRAYED IN AREA WHERE THE CABLEPASSES OVER THE CONTROL COLUMN UPPER PULLEY. PULLEY IS LOCATEDAPPROXIMATELY 200MM (8IN) BELOW THE CONTROL WHEEL. 2L72 4F4 FRTA22CE E25EA 20020906001522002090600152EA 2002 9 6 AUS20020955 220020828G741410391586 DISTRIBUTOR BENDIX S6LN1209 BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL MAGNETO/DISTRIBUUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS 324 A235988 (AUS) MAGNETO DISTRIBUTOR BLOCK BEARING LOOSE. MAGNETO CONTAMINATED WITH METAL DUE TO CONTACT BETWEEN DISTRIBUTOR GEAR ANDELECTRODES. SUSPECT FAILURE DUE TO APPLICATION OF GREASE PNO10-27165 TO THE DISTRIBUTOR GEAR SHAFT AND BLOCK BEARING. 1H72 3O3 O A17EU 1E4 5 CP920 20020906001532002090600153SW 2002 9 6 AUS20020959 120020816G2910212076006007 VALVE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE HYDRAULIC SYSTEMFAULTY W K NONE KF FLUID LOSS FLT CONT AFFECTED NRNOT REPORTED 1 AUS 897 3763 (AUS) NO1 HYDRAULIC SYSTEM INTEGRATED VALVE ASSEMBLY FAULTY. 1G72 4U4 U H4SW E22EA 20020906001542002090600154SW 2002 9 6 AUS20020960 120020805G731210544F HEATER PWA PT6T3BF BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE FUEL HEATER LEAKING W K NONE EK VIBRATION/BUFFET FLUID LOSS TOTAKEOFF 1 AUS 136 62109 (AUS) FUEL/OIL HEATER LEAKING FROM WELD ON THE TOP OF THE HEATER. NOCRACK OR HOLE WAS VISIBLE USING A X10 MAGNIFYING GLASS. 1G72 4U4 U H4SW E22EA 20020910000032002091000003CE 2002 9 10 AUS20020961 120020822G3230504501033 TORQUE TUBE CESSNA310 310R 2074245CE CONT O520 IO520* 17032SO MCAULY3AF32C3AF32C87 GL LT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT MAIN LANDING GEAR TORQUE TUBE CRACKED IN WELDED AREA AROUND THE FORK BOLT. TORQUE TUBE INTERNALLY CORRODED. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20020906001552002090600155NE 2002 9 6 AUS20020962 120020820G6321223414 PRESSURE SWITCH SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE MAIN ROTOR BRAKEFAILED W K NONE J WARNING INDICATION DEDESCENT 1 AUS (AUS) ROTOR BRAKE PRESSURE SWITCH FAILED INTERNALLY. 1G72 3U3 UNCH1NE E19EU 20020906001562002090600156NM 2002 9 6 AUS20020963 120020806G5320 ANGLE BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU FUSELAGE, MISCELCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ADJACENT INTERCOSTAL TO SKIN ATTACHMENT ANGLES (3OFF) CRACKED INAREA OF DOOR 1R SURROUND STRUCTURE. CRACKS RUN ALONG THE FOLD LINES OF THE ANGLES. ANGLES ARE LOCATED AT STN 290 BETWEENSTRINGERS NO9 AND NO13R. 2L72 4F4 FRTA16WE E21EU 20020906001572002090600157NM 2002 9 6 AUS20020965 120020806G5753654640716 FLAP TRACK BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU TRAILING EDGE FLCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 2406 (AUS) RH NO5 FLAP TRACK CRACKED IN LOWER OUTBOARD FLANGE. 2L72 4F4 FRTA16WE E21EU 20021016000222002101600022NM 2002 10 16 AUS20020968 120020829G24256229436101 SYMBOL GENERATOR BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU AC INDICATING SYFAILED W K NONE O OTHER CRCRUISE 1 AUS 3654 (AUS) FIRST OFFICERS SYMBOL GENERATOR FAILED. 2L72 4F4 FRTA16WE E21EU 20021018000512002101800051CE 2002 10 18 AUS20020970 120020827G3230504501032 TORQUE TUBE CESSNA310 310R 2074245CE CONT O550 IO550* SO MCAULY3AF32C3AF32C87 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT MAIN LANDING GEAR TORQUE TUBE CRACKED IN WELDED AREA AROUNDTHE FORK BOLT. TORQUE TUBE INTERNALLY CORRODED. 1L72 3O3 O 3A10 E3SO 5 CP22EA 20021016000232002101600023EA 2002 10 16 AUS20020971 220020814G8530SL73857 PISTON RING LYC TIO540A2C PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE2Y HCE2YR2 GL RECIPROCATING ENBROKEN W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS (AUS) NO6 CYLINDER OIL CONTROL PISTON RING BROKEN. BROKEN RING INGESTED BY OIL PUMP. 1L72 3O3 O A20SO E14EA 5 CP9EA 20021016000242002101600024GL 2002 10 16 AUS20020972 220020717G7250895007 SEAL RROYCE 250C30P BELL 206 206L1 1182107SW ALLSN 250C 250C30 03013GL TURBINE SECTION DAMAGED W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 895007 (AUS) ENGINE REMOVED DUE TO METAL CONTAMINATION. INVESTIGATION FOUNDTHE ROTATING POWER TURBINE LABYRINTH SEAL CONTACTED THE NO6 AND NO7 BEARING SUMP STATIONARY SEALS. WEAR PATTERN ON THE SEAL AREAS ARE OVAL SUGGESTING THAT THE ENGINE HAD BEEN SUBJECTEDTO A HEAVY LANDING AT SOME TIME PREVIOUS. 1G71 3U3 U H2SW E1GL 20021016000252002101600025NE 2002 10 16 AUS20020974 220020820G74219550168760 IGNITER TMECA ARRIEL1B SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE SPARK PLUG/IGNITUNSERVICEABLE W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 556 (AUS) ENGINE IGNITERS FAULTY. IGNITER IS MANUFACTURED BY EYQUEM. 1G71 3U3 UNCH9EU E19EU 20021016000262002101600026NM 2002 10 16 AUS20020975 120020830G3260864202 PROXIMITY SENSOR DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LANDING GEAR POSUNSERVICEABLE W K NONE ON OTHER FALSE WARNING CLCLIMB 1 AUS (AUS) NOSE LANDING GEAR NO2 WEIGHT ON WHEELS PROXIMITY SENSOR FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021016000272002101600027NM 2002 10 16 AUS20020976 120020625G3242NAS1802311 BOLT BOEING767 767 UTILUSENM GE CF6 CF680C2* GL BRAKE MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) BRAKE ROD PIN RETAINING BOLT LOCK BOLTS MISSING. AIRCRAFT ISFIJIAN REGISTERED DQ-FJC. PERSONNEL/MAINTENANCE ERROR. 2L72 4F4 FRTA1NM E23EA 20021016000282002101600028WP 2002 10 16 AUS20020977 220020831G731031024692 MANIFOLD GARRTT TPE33111U SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE ENGINE FUEL DISTCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH ENGINE SECONDARY FUEL MANIFOLD CRACKED IN AREA OF UPPERNOZZLE END SWAGED FITTING. LEAKING FUEL CAUGHT FIRE CAUSING DAMAGE TO FIRE TUBING ON MANIFOLDS, SUPPLY LINE, ENGINE MOUNTSAND COWLS. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20021016000292002101600029EU 2002 10 16 AUS20020983 120020627G6120 PROPELLER ROTOL R3544123F13 SAAB SF340 SF340A 7850100EU GE CT7TP CT75A 30030NE ROTOL R354 R3544123F13 NE PROPELLER CONTROFAULTY W K NONE O OTHER DEDESCENT 1 AUS (AUS) N2 ENGINE PROPELLER AUTOCOARSEN. CAUSED BY INCORRECT SELECTION OF PROPELLER CONTROLS. 2L72 4T4 TRTA52EU E8NE 6 CP61GL 20021016000302002101600030SO 2002 10 16 AUS20020984 120020901G32216705403 TRUNNION PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA MCAULY2D34C B2D34C213 GL NOSE/TAIL LANDINFAILED W K NONE O OTHER LDLANDING 1 AUS (AUS) NOSE LANDING GEAR TRUNNION ATTACHMENT LUG FOR THE EXTENSION SPRING FAILED. NOSE LANDING GEAR COLLAPSED DURING LANDING. 1L71 3O3 O 2A13 1E10 5 CP7EA 20021016000312002101600031NM 2002 10 16 AUS20020985 120020905G2120BACC10DU450Y CLAMP BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE AIR DISTRIBUTIONBROKEN W K NONE O OTHER CLCLIMB 1 AUS 40934 (AUS) LH PRIMARY HEAT EXCHANGER SUPPLY LINE CLAMP BROKEN. 2L73 4F4 F A3WE E2EA 20021016000322002101600032CE 2002 10 16 AUS20020991 120020830G2434DOFF10300B ALTERNATOR CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL DC GENERATOR-ALTFAILED W K NONE O OTHER ININSP/MAINT 1 AUS A164887 (AUS) ALTERNATOR FIELD SHORTED. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20021016000332002101600033CE 2002 10 16 AUS20020993 120020829G2434DOFF10300B ALTERNATOR CESSNA210 210L 2073448CE CONT O520 IO520L 17032SO MCAULY2A34C E2A34C73 GL DC GENERATOR-ALTFAILED W K NONE OH OTHER ELECT. POWER LOSS-50 PC ININSP/MAINT 1 AUS O661466 (AUS) ALTERNATOR FIELD SHORTED. 1H71 3O3 O 3A21 E5CE 5 CP3EA9 20021016000342002101600034CE 2002 10 16 AUS20020995 120020906G5711512204123 SPAR CAP CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 14201 (AUS) LH WING LOWER REAR SPAR CAP CORRODED IN AREA BETWEEN THE VERTICAL FLANGE AND THE SPAR WEB. CORRODED AREA IS LOCATED FORWARD OF THEAILERON FROM WS 206 TO WS 229. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021016000352002101600035CE 2002 10 16 AUS20020996 120020906G5730512201120 SKIN CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL WING, PLATES/SKICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 14201 (AUS) RH WING LOWER SKIN CONTAINED THREE CORROSION HOLES INTO THE TANK. AFT STRINGER CONTAINED EXFOLIATION CORROSION IN THE SAME LOCATION AS ONE OF THE HOLES. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021016000362002101600036SO 2002 10 16 AUS20020997 120020906G57306206105 DOUBLER PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK1 GL WING, PLATES/SKICRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WING WALK SKIN CORRUGATED DOUBLER CRACKED IN AREA NEAR RIB AT STN36.9. 1L71 3O3 O A3SO 1E4 5 CP920 20021016000372002101600037SO 2002 10 16 AUS20020998 120020906G57123821800 RIB PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK1 GL WING, RIB/BULKHECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH WING RIB CRACKED ALONG RIVET LINE IN THREE PLACES. 1L71 3O3 O A3SO 1E4 5 CP920 20021016000382002101600038NM 2002 10 16 AUS20021001 120020906G323060B0023813 FUSE BOEING767 767238 1385114NM PWA JT9 JT9D7R4E 52054NE LANDING GEAR RETFAILED W K NONE OJ OTHER WARNING INDICATION TOTAKEOFF 1 AUS 3092051 (AUS) RH MAIN LANDING GEAR UP' HYDRAULIC FUSE FAILED. FUSE MAIN RESET SPRING BROKEN. 2L72 4F4 FRTA1NM E3NE 20021016000392002101600039NM 2002 10 16 AUS20021002 120020906G2910272T3100411 PIPE BOEING767 767238 1385114NM PWA JT9 JT9D7R4E 52054NE HYDRAULIC SYSTEMCRACKED W K NONE K FLUID LOSS NRNOT REPORTED 1 AUS (AUS) LH HYDRAULIC SYSTEM HYDRAULIC PIPE TO HEAT EXCHANGER LOCATEDUNDER THE SAILBAOT FAIRING CRACKED. LOSS OF LH HYDRAULIC SYSTEM FLUID. LH HYDRAULIC CASE DRAIN FILTER CONTAMINATED. 2L72 4F4 FRTA1NM E3NE 20021016000402002101600040EA 2002 10 16 AUS20021005 220020726G8520UK BEARING LYC IO360A1A MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA HARTZLHCC2Y HCC2YK1 GL RECIPROCATING ENFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE OIL FILTERS CONTAMINATED WITH METAL. SUSPECT CAUSED BY FAILURE OF EITHER MAIN BEARING OR BIGEND BEARING. 1L71 3O3 O 2A3 1E10 5 CP920 20021016000412002101600041CE 2002 10 16 AUS20021008 120020830G534212310122 FITTING CESSNA206 U206B 2073322CE CONT O520 IO520A 17032SO MCAULYD3A34 D3A34C404 GL FUSELAGE, STABILCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD FIN ATTACHMENT FITTING CRACKED IN AREA ADJACENT TO THE LH BOLT HOLE. FOUND DURING INSPECTION IAW AD/C206/7A4. 1H71 3O3 O A4CE E5CE 5 CP47GL 20021016000422002101600042SO 2002 10 16 AUS20021009 220020801G7414103493505 MAGNETO CONT IO520F CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL MAGNETO/DISTRIBUWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) IMPULSE COUPLINGS WORN ON BOTH MAGNETOS. 1H71 3O3 O A4CE E5CE 5 CP47GL 20021018000802002101800080NM 2002 10 18 AUS20021012 120020909G27223790011107 ACTUATOR BOEING767 767338 1385151NM GE CF6 CF680C2* GL RUDDER LEAKING W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 AUS 0347 (AUS) RUDDER RATIO CHANGER ACTUATOR LEAKING. 2L72 4F4 FRTA1NM E23EA 20021016000432002101600043NM 2002 10 16 AUS20021013 120020822G52306546921225 BEAM BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU CARGO/BAGGAGE DOCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 002415 (AUS) FORWARD CARGO DOOR LOWER CROSS BEAM CRACKED ON THE FORWARD SIDE.CRACK STARTS AT THE EDGE OF THE CROSS BEAM AND RUNS INTO A RIVETHOLE. 2L72 4F4 FRTA16WE E21EU 20021016000442002101600044EU 2002 10 16 AUS20021014 120020910G7110 SCREW LYC IO540K1B5 BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL ENGINE COWLING SMISSING W K NONE D INFLIGHT SEPARATION CLCLIMB 1 AUS (AUS) LH ENGINE COWL SCREW MISSING. SCREW IS LOCATED ON THE FORWARD INBOARD SIDE OF THE LH COWL. 1H72 3O3 O A17EU 1E4 5 CP920 20021016000452002101600045NM 2002 10 16 AUS20021015 120020820G2897 HARNESS BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUEL WIRING WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO2 FUEL TANK ELECTRICAL HARNESS CHAFING. 2L72 4F4 FRTA16WE E21EU 20021018000812002101800081GL 2002 10 18 AUS20021016 320020814G6114D2483 HUB PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 702 (AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAGED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021018000822002101800082GL 2002 10 18 AUS20021017 320020814G6114D2483 HUB PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 702 (AUS) PROPELLER HUB DAMAGED IN AREA OF PRELOAD PLATE SHELF. SUSPECT PROPELLER HAD SUFFERED A GROUND STRIKE AND THE DAMAGED AREA HAD BEEN REMOVED BY WHAT APPEARS TO BE SCRAPING. UNAPPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021016000462002101600046EA 2002 10 16 AUS20021018 220020906G852013F17785 CRANKSHAFT LYC TIO540S1AD PIPER PA32 PA32RT300T 7103216SO LYC O540 TIO540S1AD 41532EA HARTZLHCE3Y HCE3YR1 GL RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1635 L537461A (AUS) CRANKSHAFT CRACKED IN FORWARD RADIUS OF NO4 MAIN BEARING JOURNAL. FOUND DURING MAGNETIC PARTICLE INSPECTION. ENGINE HAD A BULKSTRIP CARRIED OUT AT 86.2 HOURS DUE TO PROPELLER STRIKE. 1L71 3O3 O A3SO E14EA 5 CP33EA 20021016000472002101600047SO 2002 10 16 AUS20021019 120020902G57112355100 SPAR CAP PIPER PA30 PA30 7103002SO LYC O320 IO320C1A 41508EA HARTZLHCC2Y BHCC2YF1 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 5926 (AUS) LH AND RH WING LOWER FORWARD SPAR CAPS CONTAINED SEVERE EXFOLIATION CORROSION IN AREA LOCATED AT WS 62 DUE TO ENGINEEXHAUST GASSES. AT LEAST 10% OF THE SPAR CAP MATERIAL IS AFFECTED BUT CAN ONLY BE SEEN WITH THE FUEL TANK BAYS REMOVED. 1L72 3O3 O A1EA 1E12 5 CP920 20021016000482002101600048SO 2002 10 16 AUS20021020 120020601G5243120007993002 DOOR EMB EMB120 EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE HYDRAULIC COMPARSEPARATED W K NONE D INFLIGHT SEPARATION NRNOT REPORTED 1 AUS 22271 120056 (AUS) RH HYDRAULIC BAY ACCESS DOOR MISSING. DOOR HAD OPENED IN FLIGHT AND HAD TORN AWAY FROM PIANO HINGE. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20021016000492002101600049NM 2002 10 16 AUS20021025 120020525G5712 RIB BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE WING, RIB/BULKHECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) RH WING UPPER SKIN SUPPORT RIB CORRODED UNDER P' CLAMP LOCATED AT OUTBOARD END OF NO6 LEADING EDGE FLAP - ZONE 64 STN WS 330.5. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000502002101600050NM 2002 10 16 AUS20021026 120020606G5720 FITTING BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE WING, MISCELLANECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) WIRING LOOM STANDOFF CORRODED. STANDOFF IS LOCATED IN RH WING LEADING EDGE ZONE 64 STN 286.897. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000512002101600051NM 2002 10 16 AUS20021027 120020606G5720 SUPPORT BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE WING, MISCELLANECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) WIRING LOOM CLAMPS CORRODED. CLAMPS AT LOCATED AT UPPER SKINSUPPORT RIBS - ZONE 64 STN 244.217, STN 270.217, STN 298.497 ANDSTN 284.0. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000522002101600052NM 2002 10 16 AUS20021028 120020606G5713 STRINGER BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE WING, LONGERON/SCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) UPPER WING STRINGERS CORRODED. STRINGERS ARE THE SECOND AND THIRD STRINGERS FROM LEADING EDGE LOCATED OUTBOARD OF STN 210.217.FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000532002101600053NM 2002 10 16 AUS20021029 120020521G575165217271 HINGE BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE AILERONS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) RH OUTBOARD AILERON ATTACHMENT HINGE CORRODED. CORROSION IS LOCATED AT ZONE 88 WBL 492.0. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000542002101600054 2002 10 16 AUS20021031 420020911G25657A1323113 SLIDE ESCAPE SLIDE FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS GS1508 (AUS) ESCAPE SLIDE PACKING STRIP NOT REMOVED FOLLOWING OVERHAUL.PERSONNEL/MAINTENANCE ERROR. 20021016000552002101600055CE 2002 10 16 AUS20021032 120020911G326035361133 BRACKET BEECH 35 V35A 1151544CE CONT O520 IO520B 17032SO MCAULY2A36C 2A36C23 GL LANDING GEAR POSCORRODED W K NONE O OTHER CLCLIMB 1 AUS (AUS) RH MAIN LANDING GEAR STRUT SQUAT SWITCH ATTACHMENT BRACKETCORRODED THROUGH. 1L71 3O3 O 3A15 E5CE 5 CP880 20021016000562002101600056NM 2002 10 16 AUS20021033 120020517G575165137463 HINGE BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE AILERONS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) OUTBOARD AILERON INPUT ROD ATTACHMENT FITTING CORRODED. AILERON UPPER SKIN CRACKED AND LOWER SKIN CORRODED. LOCATED IN ZONE 81WBL 492.0. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000572002101600057NM 2002 10 16 AUS20021034 120020521G5754651626519 HINGE BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE LEADING EDGE DEVCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 61831 (AUS) LEADING EDGE FLAP LH HINGE FITTING CONTAINED SEVERE EXFOLIATION CORROSION AROUND BUSH. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20021016000582002101600058CE 2002 10 16 AUS20021036 120020908G323312810061 ACTUATOR CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL LANDING GEAR ACTCRACKED W K NONE O OTHER LDLANDING 1 AUS 1367 (AUS) LH MAIN LANDING GEAR COULD NOT BE EXTENDED. THE FAULT WAS TRACED TO A BROKEN ACTUATOR PISTON/RACK. BREAK OCCURRED IN THE RACK AREA TWO TEETH IN FROM THE END AND ORIGINATING AT THE BASE OF THESECOND TOOTH. THE CRACK FACE SHOWS EVIDENCE OF BEACH MARKS' INDICATING A FATIGUE FAILURE. SMOKE WAS ALSO REPORTED IN THE COCKPIT PRIOR TO LANDING FOLLOWING ATTEMPTS TO EXTEND GEAR. REASON STILL TO BE ESTABLISHED. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20021016000592002101600059NE 2002 10 16 AUS20021038 120020910G32311945E81 SWIVEL SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE LANDING GEAR DOOFRACTURED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH UNDERCARRIAGE DOOR LINK SWIVEL BROKEN. INVESTIGATION FOUND THAT THERE WAS AN INDICATION OF A PRE-EXISTING CRACK IN THE RADIUS THROUGH APPROXIMATELY ONE THIRD OF THE DIAMETER. 1G72 3U3 UNCH1NE E19EU 20021016000602002101600060SW 2002 10 16 AUS20021040 120020907G5302206031314037 LONGERON BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL ROTORCRAFT TAIL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAIL BOOM LONGERON CRACKED AROUND TWO RIVET HOLES. 1G71 3U3 U H2SW E1GL 20021018000992002101800099NM 2002 10 18 AUS20021045 120020916G573065C25204 SKIN BOEING737 737377 NM CFMINTCFM56 CFM563B1US GL WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 2632 (AUS) RT WING UPPER SURFACE CORRODED IN AREA LOCATED FORWARD OF THE FILLER CAP AT APPROXIMATELY WING STN 440. AN AREA OF 6.35MM (0.250IN) BY 25.4MM (1IN) WAS REMOVED AT THE FORWARD EDGE OF THE FILLER CAP HOUSING. 2L72 4F4 FRTA16WE E2GL 20021016000612002101600061NM 2002 10 16 AUS20021046 120020906G5753 BOLT BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TRAILING EDGE FLFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH INBOARD FLAP ELEPHANT MOUNTING PLATE BOLTS/ANCHOR NUTS FAILED. DURING FLAP RETRACTION AFTER TAKEOFF, THE ELEPHANT EAR DAMAGEDTHE WING/BODY FAIRING CAUSING A 304.8CM (12IN) CRACK IN THE COMPOSITE MATERIAL. 2L72 4F4 FRTA16WE E21EU 20021016000622002101600062SO 2002 10 16 AUS20021047 120020905G32306703102 FITTING PIPER PA28 PA28R180 7102809SO LYC O360 IO360B1E 41514EA HARTZLHCC2Y HCC2YK1 GL LANDING GEAR RETBROKEN W K NONE O OTHER CRCRUISE 1 AUS (AUS) LH MAIN LANDING GEAR FITTING BROKE INTO FOUR PIECES DURING FLIGHT AND LANDING GEAR FELL FREE BUT DID NOT LOCK. DURING INVESTIGATION THE SAME PART WAS REMOVED FROM THE RH MAIN LANDINGGEAR (PNO 67031-03) AND WAS ALSO FOUND TO BE BADLY CRACKED. 1L71 3O3 O 2A13 1E10 5 CP920 20021016000632002101600063NE 2002 10 16 AUS20021048 220020918G7260LP5 FITTING PWA JT8D17 BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE TURBINE ENGINE ALOOSE W K NONE JEKWARNING INDICATION VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS 40981 (AUS) NO2 ENGINE OIL QUANTITY INDICATION DROPPED FROM 7.6 LITRES (2GAL) TO 3.8 LITRES (1GAL) DURING APPROACH TO LAND. INVESTIGATION FOUND THAT THE AUXILIARY GEARBOX LP5 FITTING THREAD WAS DAMAGED AND LOOSE. PERSONNEL/MAINTENANCE ERROR. 2L73 4F4 F A3WE E2EA 20021016000642002101600064NM 2002 10 16 AUS20021049 120020903G5753654643814 FLAP TRACK BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU TRAILING EDGE FLCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 2406 (AUS) NO5 FLAP TRACK BEAM CRACKED ON THE AFT LOWER FLANGE. CRACK LENGTH APPROXIMATELY 38MM (1.5IN). 2L72 4F4 FRTA16WE E21EU 20021016000652002101600065SO 2002 10 16 AUS20021050 120020916G5751315359 DOUBLER PIPER 4020023 PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL AILERONS CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 315359 (AUS) RH AILERON SPAR DOUBLER CRACKED IN AREA LOCATED IMMEDIATELY BELOW THE INBOARD HINGE ATTACHMENT PLATE LOWER BOLT HOLE. CRACK LENGTH18MM (0.71IN). FOUND DURING DYE PENETRANT INSPECTION IAWAD/PA31/118 AMDT 1. 1L72 3O3 O A20SO E14EA 5 CP33EA 20021018001012002101800101EA 2002 10 18 AUS20021051 220020708G8520L89154A CONNECTING ROD PAC CT4 CT4A 05623UCGL LYC O720 IO720A1B 41546EA ENGINE FAILED W A UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) DURING AGRICULTURE OPERATIONS (SPREADING SUPER) THE PILOT ENCOUNTERED EXCESSIVE ENGINE VIBRATION AND A POSSIBLE OVERSPEED (WAS UNABLE TO READ GAUGES). ENGINE WAS SHUT DOWN AND A FORCED LANDING CARRIED OUT. INITIAL INVESTIGATION FOUND THAT NR 4 OR NR 6 CONNECTING ROD ON THE LT SIDE OF ENGINE HAD PUNCTURED THROUGH THE CRANKCASE. 1Q71 3I3 ORTA9PC 1E15 20021016000662002101600066EA 2002 10 16 AUS20021053 220020918G852072469 CRANKSHAFT LYC VO435B1A BELL 47 47G5A 1181034SW LYC O435 VO435B1A 41516EA RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1050 (AUS) CRANKSHAFT CRACKED. CRACK RAN THROUGH THE OIL GALLERY, ACROSS THE THRUST FACE AND THROUGH THE OPPOSITE OIL GALLERY. CRACK EXTENDS THROUGH ALMOST 60% OF THE CIRCUMFERENCE OF BEARING JOURNALSURFACE. 1G71 3O3 O 2H3 E279 20021016000672002101600067EU 2002 10 16 AUS20021056 220020828G7250725545 TURBINE GE CFM563C1 BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TURBINE SECTION FAILED W K NONE E VIBRATION/BUFFET TOTAKEOFF 1 AUS 725545 (AUS) NO1 ENGINE SURGED/STALLED ON TAKEOFF. EGT INCREASED AND EXCEEDEDLIMITS. ENGINE INSPECTION FOUND TURBINE FAILURE. 2L72 4F4 FRTA16WE E21EU 20021016000682002101600068NM 2002 10 16 AUS20021057 120020916G2421 GENERATOR BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU AC GENERATOR-ALTFAILED W K NONE H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 AUS (AUS) APU GENERATOR FAILED. 2L72 4F4 FRTA16WE E21EU 20021016000692002101600069EU 2002 10 16 AUS20021058 120020917G5540603300002 RUDDER REIMS 406 F406 7535723EU PWA PT6 PT6A112 52043NE MCAULY3G34C73GFR34C701 GL RUDDER STRUCTUREFOD W K NONE C F.O.D. TXTAXI/GRND HDL 1 AUS 6881 (AUS) RUDDER DAMAGED BY ANOTHER AIRCRAFT TAXIING PAST. THE RUDDER SKINWAS DENTED AND BUCKLED AT THE MID POINT OF THE TRAILING EDGE. DURING DISASSEMBLY FOR REPAIR A PORTION OF THE RIB WAS ALSO DAMAGED. 1L72 3T3 TRTA54EU E4EA 5 CP60GL 20021016000702002101600070SO 2002 10 16 AUS20021059 220020918G8530530348 PISTON CONT O200A CESSNA150 150G 2071816CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL RECIPROCATING ENBROKEN W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 1608 66186 (AUS) PISTON SIDE BROKEN AWAY. METAL CONTAMINATION OF OIL FILTER. 1H71 3O3 O 3A19 E252 5 NP918 20021016000712002101600071NM 2002 10 16 AUS20021061 120020921G5280113T820175SP DOOR MENASCO 161T0000665 BOEING767 76733A 1385209NM GE CF6 CF680A 30025NE LANDING GEAR DOOSEPARATED W K NONE OD OTHER INFLIGHT SEPARATION LDLANDING 1 AUS T8189 (AUS) LH MAIN LANDING GEAR TRUNNION DOORS MISSING. DAMAGE CAUSED TO BRAKE AND LANDING GEAR HYDRAULIC LINES. LH HORIZONTAL STABILISERHAD MINOR IMPACT DAMAGE TO THE LEADING EDGE. 2L72 4F4 FRTA1NM E13NE 20021016000722002101600072EA 2002 10 16 AUS20021062 220020913G8550 PLUG LYC TIO540A2B PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE2Y HCE2YK2 GL RECIPROCATING ENMISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE OIL PRESSURE DROPPING INTERMITTENTLY. INTERNAL INSPECTIONFOUND THE INTERNAL SUMP OIL PICKUP GALLERY PLUG MISSING. SUSPECTTHE PLUG WAS NOT INSTALLED DURING ENGINE OVERHAUL. 1L72 3O3 O A20SO E14EA 5 CP9EA 20021016000732002101600073EA 2002 10 16 AUS20021063 220020924G8520L224361 CRANKCASE LYC TIO540A2B PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE2Y HCE2YK2 GL RECIPROCATING ENCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS L224361 (AUS) ENGINE CRANKCASE CRACKED ON LH SIDE ADJACENT TO THE FRONT CYLINDER. THIS DEFECT IS LINKED WITH MDR 02/1062 (MISSING OIL PLUG). 1L72 3O3 O A20SO E14EA 5 CP9EA 20021018001572002101800157GL 2002 10 18 AUS20021066 220020923G7200 ENGINE BOEING767 767338 1385151NM GE CF6 CF680C2* GL LEFT MALFUNCTIONED W C ABORTED TAKEOFF ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 AUS (AUS) LT ENGINE PRODUCING LOW POWER. 2L72 4F4 FRTA1NM E23EA 20021016000742002101600074NE 2002 10 16 AUS20021067 220020912G731082821013103 TUBE PWA PW123D DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE ENGINE FUEL DISTLOOSE W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) RH ENGINE WASTE FUEL DRAIN TUBE DISCONNECTED FROM ENGINE FUEL NOZZLE MANIFOLD. INVESTIGATION FOUND THAT THE WASTE FUEL DRAINTUBE HAD BEEN DISCONNECTED THE PREVIOUS NIGHT AS PART OF THEPROCESS USED IN CARRYING OUT A COMPRESSOR WASH ON THE ENGINE. FOLLOWING THE COMPRESSOR WASH THE MAINTENANCE PERSONNEL FAILED TO RECONNECT THE LINE. PERSONNEL/MAINTENANCE ERROR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021016000752002101600075EA 2002 10 16 AUS20021068 220020309G7322252416315 FCU BENDIX RSA10ED1 PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE2Y HCE2YK2 GL FUEL CONTROL/RECOUT OF ADJUST W K NONE E VIBRATION/BUFFET TXTAXI/GRND HDL 1 AUS 25 2593524T (AUS) ENGINE FUEL CONTROL UNIT OUT OF ADJUSTMENT. 1L72 3O3 O A20SO E14EA 5 CP9EA 20021021000032002102100003CE 2002 10 21 AUS20021070 120020911G531207126161 BULKHEAD CESSNA182 182F 2072714CE HARTZLHC82X HC82XF1 GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR BULKHEAD LOCATED AT STA 309.187 CRACKED. 1H71 3O NT3A13 5 CP878 20021021000042002102100004CE 2002 10 21 AUS20021071 120020920G534707106582 SEAT TRACK CESSNA182 182F 2072714CE HARTZLHC82X HC82XF1 GL CABIN CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT FRONT SEAT OUTBOARD SEAT TRACK CONTAINED NUMEROUS CRACKS. 1H71 3O NT3A13 5 CP878 20021021000242002102100024CE 2002 10 21 AUS20021072 220020910G8550 FILTER AMTR VANS RV8 GL CONT IO360 IO360* 17025CE HARTZLHCF2Y HCF2YR1 GL ENGINE MISSING W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE SUMP FITTED WITH NO SUCTION FILTER IN THE OIL SYSTEM. APIECE OF LOCKWIRE APPROXIMATELY 15.875MM (0.625IN) LONG WAS FOUND IN AN OIL GALLERY. DAMAGE TO OIL PUMP, CRANKSHAFT REAR BEARINGAND THRUST BEARING SURFACES. ALL PISTON SKIRTS SEVERELY SCORED. 1L71 3O3 ONTEXPA1L71E1CE 5 CP27EA 20021021000272002102100027CE 2002 10 21 AUS20021073 220020910G8550 FILTER AMTR VANS RV8 GL CONT IO360 IO360* 17025CE HARTZLHCF2Y HCF2YR1 GL ENGINE UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) UNAPPROVED OIL FILTER INSTALLED. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1L71 3O3 ONTEXPA1L71E1CE 5 CP27EA 20021016000762002101600076 2002 10 16 AUS20021074 420020919G3417HG480B43 ADC BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU AIR DATA COMPUTEFAILED W K NONE IG FLT. ATTITUDE INST. MULTIPLE FAILURE CRCRUISE 1 AUS H115742 (AUS) AIR DATA COMPUTER FAILED. 2L72 4F4 FRTA16WE E21EU 20021016000772002101600077CE 2002 10 16 AUS20021075 120020815G3242RFS1030 ROTOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE HARTZLHCB3T HCB3TN3 GL BRAKE BROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH INNER BRAKE ROTOR BROKEN INTO THREE PIECES. 1L72 4T4 T A24CE E4EA 6 CP15EA 20021016000782002101600078NE 2002 10 16 AUS20021076 220020911G7230410100639 ROTOR GARRTT 410102080 BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101750B1 41560NE TURBINE ENGINE CDAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 86760A (AUS) NO2 ENGINE COMPRESSOR AXIAL ROTOR DAMAGED BEYOND LIMITS. SUSPECTCAUSED BY FOD. 1G72 3U3 U H13EU E5NE10 20021021000282002102100028SO 2002 10 21 AUS20021077 220020915G8550 OIL SYSTEM CESSNA210 210L 2073448CE CONT O520 IO520L 17032SO MCAULY3A32C D3A32C88 GL ENGINE LOW W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 AUS (AUS) ENGINE OIL QUANTITY LOW. ENGINE HAS A HISTORY OF HIGH OIL CONSUMPTION. 1H71 3O3 O 3A21 E5CE 5 CP21EA 20021106000922002110600092NM 2002 11 6 AUS20021079 120020924G2840 LIGHT BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU FUEL INDICATING W K NONE KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 AUS (AUS) LH AND RH AUXILIARY FUEL TRANSFER LIGHTS ILLUMINATED. RH LIGHTTHEN EXTINGUISHED LEAVING THE LH LIGHT STILL ILLUMINATED. THE RHLIGHT ILLUMINATED AGAIN LATER. 2L72 4F4 FRTA16WE E21EU 20021106000932002110600093NM 2002 11 6 AUS20021087 120021002G324082920010335 PIPE DHAV DHC8 DHC8315 2809010NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF15 NE LANDING GEAR BRALEAKING W K NONE K FLUID LOSS CRCRUISE 1 AUS (AUS) BRAKE ACCUMULATOR HYDRAULIC PRESSURE LINE LEAKING AT FLARE. SUSPECT CAUSED BY CORROSION PITTING OF THE FLARE. LOSS OF NO2 HYDRAULIC SYSTEM FLUID. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021108000142002110800014NM 2002 11 8 AUS20021094 120021004G28225006150A VALVE BOEING767 767338 1385151NM GE CF6 CF680C2* GL FUEL BOOST PUMP CONTAMINATED W O OTHER KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) LT FORWARD BOOST PUMP DISCHARGE CHECK VALVE CONTAMINATED BY DEBRIS. 2L72 4F4 FRTA1NM E23EA 20021108000152002110800015EA 2002 11 8 AUS20021095 220021008G853005K21232 CYLINDER GROB G115 G115 EU LYC O235 O235H2C 41505EA SNSNCH72C 72CK EA ENGINE SEPARATED W O OTHER EYJVIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION LDLANDING 1 AUS (AUS) NR 1 CYLINDER SEPARATED. THE CYLINDER BASE FLANGE WAS STILL CONNECTED TO THE CRANKCASE. 1L71 3O3 ONTA57EU E223 5 NP9045 20021106000942002110600094SW 2002 11 6 AUS20021096 120020927G632070061L275W210A HOSE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE MAIN ROTOR GEARBWORN W K NONE J WARNING INDICATION CLCLIMB 1 AUS (AUS) TRANSMISSION OIL HOSE HOLED AND LEAKING. HOSE WAS CHAFING ON AN ADJACENT PIPE. TRANSMISSION OIL LOST OVERBOARD. 1G72 4U4 U H4SW E22EA 20021108000172002110800017GL 2002 11 8 AUS20021098 320021003G6111 BLADE AMTR VANS RV8 GL LYC O360 AEIO360* EA AMTR C8289 C8289 GL PROPELLER DELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER LEADING EDGE DELAMINATING IN AREA OF TIP. 1L71 3O3 ONTEXPA1L711E10 5 NEXPP5N 20021108000182002110800018SO 2002 11 8 AUS20021099 120020930G5753 STRUCTURE PIPER PA25 PA25235 7102504SO LYC O540 O540H2A5 41532EA MCAULY1A200 1A200FA GL TE FLAP CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT TRAILING EDGE FLAPS SEVERELY CORRODED AT HINGE ATTACHMENT TO MAIN SPAR. 1L71 3O3 O 2A10 E295 5 NP874 20021106000952002110600095SO 2002 11 6 AUS20021102 120020927G32309515340 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR UP' HYDRAULIC PIPE CORRODED. 1L72 3O3 O A7SO E9CE 5 CP920 20021106000962002110600096SO 2002 11 6 AUS20021103 120020927G32309515339 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR DOWN' PIPE CORRODED. 1L72 3O3 O A7SO E9CE 5 CP920 20021106000972002110600097SO 2002 11 6 AUS20021104 120020909G32309515339 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR DOWN' HYDRAULIC PIPE CORRODED. 1L72 3O3 O A7SO E9CE 5 CP920 20021106000982002110600098SO 2002 11 6 AUS20021105 120020909G32309515340 TUBE PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO HARTZLHCC2Y BHCC2YF2 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR UP' HYDRAULIC PIPE CORRODED. 1L72 3O3 O A7SO E9CE 5 CP920 20021106000992002110600099NE 2002 11 6 AUS20021108 220021004G73218061965 FMU RROYCE BR700715A130BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE FUEL CONTROL/TURFAULTY W KE NONE ENGINE SHUTDOWN E VIBRATION/BUFFET CLCLIMB 1 AUS (AUS) LH ENGINE SPOOLED DOWN. FUEL METERING UNIT (FMU) PNO 18061-965AND ENGINE ELECTRONIC CONTROL (EEC) PNO 114E6112G119 CHANGED ON ADVICE FROM MANUFACTURERS. 2L72 4F4 FTRA6WE E00061EN 20021112000042002111200004EU 2002 11 12 AUS20021109 120021007G3320 BALLAST BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE GALLEY BURNED OUT W D RETURN TO BLOCK HB ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 AUS (AUS) REAR GALLEY WORK LIGHT BALLAST BURNED OUT. 2H74 4F4 F A49EU E6NE 20021106001002002110600100SO 2002 11 6 AUS20021112 220020522G85206419311075 BOLT CONT IO520M CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL RECIPROCATING ENFAILED W K NONE O OTHER ININSP/MAINT 1 AUS 80 (AUS) NO6 CYLINDER UPPER THROUGH BOLT FAILED. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20021106001012002110600101SW 2002 11 6 AUS20021113 120020925G3260 WARNING SYSTEM SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP MCAULY4HFR344HFR34C652 NE LANDING GEAR POSFAULTY W K NONE ON OTHER FALSE WARNING CLCLIMB 1 AUS (AUS) LANDING GEAR INDICATIONS INCORRECT. GROUND RETRACTION TESTS COULD NOT DUPLICATE THE DEFECT. 2L72 4T4 TRTA8SW E4WE 6 C3PNE 20021106001022002110600102EU 2002 11 6 AUS20021114 120020914G76036227911301 SERVO RROYCE TAY62015 FOKKERF28 F28MK0100 4990807EU RROYCETAY TAY62015 04564NE POWER LEVER STICKING W K NONE E VIBRATION/BUFFET LDLANDING 1 AUS 595 (AUS) LH AUTO THROTTLE SERVO BINDING. 2L72 4F4 FRT E25NE 20021106001032002110600103EA 2002 11 6 AUS20021115 120020917G5310C2FS533 FORMER DHAV DHC2 DHC2* 2800108EA PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE FUSELAGE MAIN, SCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR FUSELAGE FORMER AND SKIN STRUCTURE LOCATED IN AREA BENEATH THE FORWARD TAILPLANE ATTACHMENT PICKUP BRACKETS PNO C2FS5189ASEVERELY CORRODED. AIRCRAFT OPERATES AS A FLOATPLANE. 1H71 3R3 R A806 5E1 5 CP206 20021106001042002110600104EA 2002 11 6 AUS20021116 220021009G7414ES10382585 CONTACTOR CONT 103993101 PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL MAGNETO/DISTRIBUFAILED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS RAE2053 (AUS) MAGNETO CAM FOLLOWER SEPARATED FROM CONTACT ASSEMBLY. 1L72 3O3 O A20SO E14EA 5 CP33EA 20021106001052002110600105SO 2002 11 6 AUS20021119 220020929G731464621218 PUMP CONT 64621218 BEECH 35 V35A 1151544CE CONT O550 IO550B SO MCAULY3A32C 3A32C76 GL ENGINE FUEL PUMPLEAKING W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS L019915B (AUS) ENGINE DRIVEN FUEL PUMP LEAKING. SUSPECT FAULTY SHAFT SEAL. 1L71 3O3 O 3A15 E3SO 5 CP21EA 20021106001062002110600106NM 2002 11 6 AUS20021121 120021006G76033200940010 SENSOR GE CFM563C BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU POWER LEVER FAULTY W K NONE O OTHER CRCRUISE 1 AUS 12207 (AUS) ENGINE AUTOTHROTTLE SENSOR SUSPECT FAULTY. LIMITED INFORMATIONPROVIDED. 2L72 4F4 FRTA16WE E21EU 20021106001072002110600107CE 2002 11 6 AUS20021122 120020901G32303581512512 ROD BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL LANDING GEAR RETFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH MAIN LANDING GEAR RETRACTION ROD FAULTY. ROD HAD BEENILLEGALLY REPAIRED IN AN ATTEMPT TO STRAIGHTEN THE ROD. RIVETSHAD BEEN REPLACED WITH BOLTS AND PENNY WASHERS. UNAPPROVEDREPAIR. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001082002110600108CE 2002 11 6 AUS20021123 120020901G571295110233 RIB BEECH 95110234 BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL WING, RIB/BULKHECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING RIB PNO 9511023-3 AND RH WING RIB PNO 9511023-4 CORRODEDTHROUGH. LH WING RIB CHANNEL PNO 9511023-5 AND RH WING RIBCHANNEL PNO 9511023-6 CORRODED THROUGH. RIBS AND CHANNELS ARE LOCATED AT STN 66. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001092002110600109CE 2002 11 6 AUS20021125 120020901G2711135038 ROD END BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL AILERON TAB CONTCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AILERON TRIM TAB RODEND FORK RUSTY AND CLEVIS PIN SEIZED. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001102002110600110CE 2002 11 6 AUS20021126 120020901G5341 FITTING BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL FUSELAGE, WING ACORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WING ATTACHMENT TOP BATHTUB FITTINGS CORRODED AND DRAIN HOLES BLOCKED. NO CORROSION PROTECTION ON FITTINGS. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001112002110600111CE 2002 11 6 AUS20021127 120020901G5320 DOUBLER BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL FUSELAGE, MISCELCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH FUSELAGE DOUBLERS LOCATED AT STN 0.00 CONTAINED EXFOLIATION CORROSION. ADJACENT RIB PNO 95-410005-4 CORRODEDAWAY. AIRCRAFT HAS OPERATED IN A SALT AIR ENVIRONMENT FOR A CONSIDERABLE TIME. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001122002110600112CE 2002 11 6 AUS20021129 120020901G2720 BEARING BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL RUDDER CONTROL SSEIZED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RUDDER BEARINGS UNSERVICEABLE. TOP BEARING SEIZED WITH A GROOVE WORN IN THE ATTACHMENT PIVOT BOLT. CENTRE BEARING WORN. LOWER BEARING PARTIALLY SEIZED. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001132002110600113CE 2002 11 6 AUS20021130 120020901G3230 CABLE BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL LANDING GEAR RETCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH MAIN LANDING GEAR UPLOCK CABLES RUSTY. UPLOCK SPRINGS BROKEN AND RUSTY. CLOSING PANELS IN WHEEL WELL BAYS MISSING ALLOWING DIRT AND MUD ETC TO BUILD UP. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001142002110600114CE 2002 11 6 AUS20021131 120020901G5313 STRINGER BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL FUSELAGE MAIN, LCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUSELAGE STRINGER LOCATED AT STN 107.00 CONTAINED SEVEREEXFOLIATION CORROSION. EVIDENCE OF WATER ENTRY OVER AN EXTENDED PERIOD. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001152002110600115CE 2002 11 6 AUS20021132 120020901G531496410032601 KEEL BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL FUSELAGE MAIN, KCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH KEEL SPLICE JOINTS LOCATED IN NOSE LANDING GEAR WHEEL WELL AT STN 49.000 CONTAINED SEVERE EXFOLIATION CORROSION BETWEEN THE JOINT FACES. ATTACHMENT RIVET HEADS MISSING. AFFECTED PARTS WERE:-1. LH FORWARD KEEL PNO 96-410032-6012. LH AFT KEEL PNO 96410032-133. RH FORWARD KEEL PNO 96-410032-6084. RH AFT KEEL PNO 96410032-608 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001162002110600116CE 2002 11 6 AUS20021133 120020901G5712 RIB BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL WING, RIB/BULKHECORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH WING TRAILING EDGE RIBS CORRODED. RIBS AFFECTED ARE:- LH WING-PNO 95110014-121PNO 95110014-191PNO 95110014-153PNO 95110014-129PNO 95110014-135RH WING-PNO 95110014-122PNO 95110014-192PNO 95110014-154PNO 95110014-130PNO 95110014-120 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001172002110600117CE 2002 11 6 AUS20021135 120020901G326035361145 LINK BEECH 55 95C55 1152708CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C75 GL LANDING GEAR POSSEIZED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) SQUAT SWITCH LINKS SEIZED. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001182002110600118EU 2002 11 6 AUS20021139 220021009G7270 PANEL GE CFM563C BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TURBINE ENGINE BDAMAGED W K NONE EC VIBRATION/BUFFET F.O.D. TOTAKEOFF 1 AUS (AUS) RH ENGINE BIRDSTRIKE. INVESTIGATION FOUND ENGINE NACELLE FAN DUCT EXTENSION UPPER ACOUSTIC PANEL MISSING. 2L72 4F4 FRTA16WE E21EU 20021106001192002110600119EU 2002 11 6 AUS20021140 220021008G75301211175010 ACTUATOR GE CFM563C BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU COMPRESSOR BLEEDLEAKING W K NONE K FLUID LOSS TXTAXI/GRND HDL 1 AUS APHAL389 (AUS) NO2 ENGINE RH VARIABLE STATOR VANE ACTUATOR LEAKING. 2L72 4F4 FRTA16WE E21EU 20021106001202002110600120SO 2002 11 6 AUS20021144 220020910G8530654840C PISTON CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENDAMAGED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 239168R (AUS) LH ENGINE NO2 CYLINDER PISTON DAMAGED. SUSPECT CAUSED BYDETONATION. 1L72 3O3 O A25CE E7CE 5 CP45GL 20021112000182002111200018SO 2002 11 12 AUS20021145 120021009G57116205400 SPAR PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA SNSNCH74DM M74DM EA LT & RT WING CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT AFT SPAR ASSEMBLIES CORRODED BETWEEN SPAR AND ATTACHMENT PLATE PNO 66762-00. 1L71 3O3 O 2A13 E274 5 NP88614 20021106001212002110600121EA 2002 11 6 AUS20021146 120021009G5311C2FS537A CHANNEL DHAV DHC2 DHC2* 2800108EA PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE FUSELAGE MAIN, FCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH CHANNELS SEVERELY CORRODED. AIRCRAFT OPERATES AS AFLOATPLANE. 1H71 3R3 R A806 5E1 5 CP206 20021106001222002110600122CE 2002 11 6 AUS20021150 120021004G7331660526 TRANSDUCER PWA PT6A41 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL FUEL FLOW INDICALEAKING W K NONE ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS TOTAKEOFF 1 AUS 1399 (AUS) RH ENGINE FUEL FLOW TRANSDUCER OUTLET FITTING LOOSE AND LEAKING FUEL. TRANSDUCER IS MANUFACTURED BY SHADIN. 1L72 4T4 T A24CE E4EA 6 CP15EA 20021112000222002111200022EU 2002 11 12 AUS20021151 120021014G7714230362601 PICKUP BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE ENGINE RPM FAULTY W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 AUS (AUS) NO4 ENGINE N2 PICKUP FAULTY. 2H74 4F4 F A49EU E6NE 20021106001232002110600123EU 2002 11 6 AUS20021153 120021011G2710NB45B349 SLEEVE BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL AILERON CONTROL SPLIT W K NONE OF OTHER FLT CONT AFFECTED ININSP/MAINT 1 AUS (AUS) LH AILERON CONTROL ROD SLEEVE SPLIT THROUGH TAPER PIN HOLE. 1H72 3O3 O A17EU 1E4 5 CP920 20021106001242002110600124EU 2002 11 6 AUS20021155 120021014G2731SD3456028 CABLE STBROSSD3 SD360 8100606EU PWA PT6 PT6A67R 52043NE HARTZLHCA6A HCA6A3 NE ELEVATOR TAB CONBROKEN W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) ELEVATOR TRIM CABLE BROKEN. 2H72 4T4 T A41EU E26NE 6 CP14NE 20021112000292002111200029SO 2002 11 12 AUS20021159 220021009G85506320622 DIPSTICK CONT O520 IO520F 17032SO ENGINE OIL FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 1687 (AUS) ENGINE SUMP WORN INTERNALLY BY DIPSTICK ROD. DEPTH OF WEAR GROOVE APPROXIMATELY 0.635MM (0.025IN). THICKNESS OF SUMP SKIN 1.27MM (0.050IN). TWO OTHER SIMILAR DEFECTS FOUND FROM THE SAME OPERATOR. ALL HAVE BEEN ASSOCIATED WITH LATE MANUFACTURE RIVETED DIPSTICKS WITH SUFFIX AW OR BF. SUSPECT DESIGN PROBLEM WITH LATER MODEL DIPSTICKS. 3 O E5CE 20021112000322002111200032CE 2002 11 12 AUS20021162 120021015G3260P6340005 SWITCH CESSNA210 210M 2073450CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL MLG FAULTY W K NONE N FALSE WARNING LDLANDING 1 AUS (AUS) LT MAIN LANDING GEAR DOWN SWITCH INTERMITTENT IN OPERATION. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20021106001252002110600125SO 2002 11 6 AUS20021165 220021007G8520634503 BEARING CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL RECIPROCATING ENBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS 1214 (AUS) NO2 MAIN BEARING BROKEN. REMAINING MAIN BEARINGS MOVING SIDEWAYSCAUSING TANGS TO WEAR INTO CASE. 1L72 3O3 O A25CE E7CE 5 CP45GL 20021106001262002110600126EU 2002 11 6 AUS20021166 120020913G7120 MOUNT LYC O320D2A AVIONSR2160 R2160 0960101EU LYC O320 O320D2A 41508EA SNSNCH74D 74DM EA ENGINE MOUNT SECCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE MOUNT CRACKED IN SEVERAL AREAS. FURTHER INSPECTION FOUND BOTH LOWER ENGINE MOUNT BRACKETS LOCATED BEHIND THE FIREWALL ALSO CRACKED. LH AND RH TOP FUSELAGE SKINS REMOVED FOR INSPECTION ANDLH TOP MOUNT STRUCTURE FOUND CRACKED. LH RUDDER BAR ATTACHMENTPOINT CRACKED BENEATH ANCHOR NUT. 1L71 3O3 ORTA48EU E274 5 NP88614 20021106001272002110600127NE 2002 11 6 AUS20021171 220021017G74219550168760 IGNITER TMECA ARRIEL1B SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE SPARK PLUG/IGNITUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS 616 (AUS) ENGINE IGNITER BROKEN. BORESCOPE INSPECTION FOUND SEVEREDOWNSTREAM DAMAGE. IGNITER IS MANUFACTURED BY EQYEM. 1G71 3U3 UNCH9EU E19EU 20021106001282002110600128NE 2002 11 6 AUS20021180 220021009G7421SC2036 IGNITER TMECA ARRIEL1B SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE SPARK PLUG/IGNITFAILED W K NONE O OTHER ININSP/MAINT 1 AUS 678 (AUS) ENGINE IGNITER ELECTRODE BROKEN OFF. 1G71 3U3 U H9EU E19EU 20021106001292002110600129EU 2002 11 6 AUS20021181 120021011G5552NB310077 BRACKET BNORM BN2 BN2A26 1520226EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL ELEVATOR/TAB, ATWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELEVATOR OUTBOARD HINGE BRACKET WORN AND RIVETS LOOSE. FOUNDDURING INSPECTION IAW AD/BN2/70 AND BN2/SB259. 1H72 3O3 O A17EU 1E4 5 CP920 20021106001302002110600130EU 2002 11 6 AUS20021187 120021016G6120LW12920 PIPE LYC O360A1AD SOCATATB10 TB10TOBAGO 8680696EU LYC O360 O360A1A 41514EA HARTZLHCC2Y HCC2YK1 GL PROPELLER CONTROFRACTURED W K NONE K FLUID LOSS CRCRUISE 1 AUS 64 L3377336A (AUS) PROPELLER GOVERNOR EXTERNAL OIL PIPE FAILED AT CONNECTION TO THEGOVERNOR. 1L71 3O3 ORTA51EU E286 5 CP920 20021106001312002110600131NE 2002 11 6 AUS20021190 220021014G72103022383 SEAL PWA PW118A EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE TURBINE ENGINE RLEAKING W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 115108 (AUS) NO2 ENGINE REDUCTION GEARBOX AUXILIARY GENERATOR OIL SEAL LEAKING. SEAL HAD BEEN CHANGED ON THE PRECEDING DAY. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20021106001322002110600132SO 2002 11 6 AUS20021192 120021005G541270382 BULKHEAD PIPER PA42 PA42 7104202SO PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL NACELLE/PYLON, BCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH ENGINE NACELLE BULKHEAD CRACKED. 1L72 4T4 T A23SO E4EA 6 CP15EA 20021106001332002110600133SO 2002 11 6 AUS20021193 120021005G321140288006 TRUNNION PIPER PA42 PA42 7104202SO PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL MAIN LANDING GEACRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR TRUNNION CRACKED THROUGH VERTICAL WEB. CRACK LENGTHAPPROXIMATELY 12.7MM (0.5IN). AIRCRAFT OPERATES FROM ROUGHSTRIPS. 1L72 4T4 T A23SO E4EA 6 CP15EA 20021106001342002110600134NM 2002 11 6 AUS20021195 120021018G3246LM522546 BEARING BFGOODRICH 313061M BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE WHEEL/SKI/FLOAT DISINTEGRATED W K NONE OD OTHER INFLIGHT SEPARATION LDLANDING 1 AUS 27242941 (AUS) NO2 MAIN WHEEL OUTER BEARING COLLAPSED. WHEEL SEPARATED FROMAIRCRAFT LEAVING THE WHEEL NUT STILL SECURE ON THE AXLE. DAMAGE TO AXLE SLEEVE. 2L73 4F4 FRTA3WE E2EA 20021106001352002110600135NM 2002 11 6 AUS20021197 120021010G2750113T22507 TORQUE TUBE BOEING767 767238 1385114NM PWA JT9 JT9D7R4E 52054NE TRAILING EDGE FLCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH INBOARD FLAP TORQUE TUBE AND COLLAR FITTING CORRODED BEYONDLIMITS. FOUND DURING INSPECTION IAW AD/B767/108. 2L72 4F4 FRTA1NM E3NE 20021106001362002110600136NM 2002 11 6 AUS20021198 120021011G2421 CONNECTOR BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU AC GENERATOR-ALTDAMAGED W K NONE OH OTHER ELECT. POWER LOSS-50 PC ININSP/MAINT 1 AUS (AUS) NO1 GENERATOR PLUG AND SOCKET D5124 DAMAGED DUE TO ARCING. 2L72 4F4 FRTA16WE E21EU 20021106001372002110600137SO 2002 11 6 AUS20021200 120021002G8120L86661C BEARING LYC TIO540A2C PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE2Y HCE2YR2 GL EXHAUST TURBOCHACOLLAPSED W K NONE E VIBRATION/BUFFET TOTAKEOFF 1 AUS 1253 L86661C (AUS) RH ENGINE TURBOCHARGER PNO 406610-9020BEARING COLLAPSED.TURBINE ASSEMBLY CONTACTED OUTER CASING. 1L72 3O3 O A20SO E14EA 5 CP9EA 20021106001382002110600138CE 2002 11 6 AUS20021201 120021010G712008516004 BEAM CONT IO470V CESSNA310 310K 2074228CE CONT O470 IO470V 17026SO MCAULY2AF34CD2AF34C81 GL ENGINE MOUNT SECCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH ENGINE CROSSOVER BEAM CRACKED. FURTHER INVESTIGATION FOUND THAT THE LH MOUNTS DROPPED IN MOUNT BRACKETS AND PUT OUTWARD LOAD ON THE ENGINE LONGITUDINAL BEAMS. 1L72 3O3 O 3A10 3E1 5 CP5EA 20021106001402002110600140WP 2002 11 6 AUS20021209 120020719G7820G693 MUFFLER LYC O540F1B5 ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE NOISE SUPCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MUFFLER AND LH COLLECTOR CRACKED AND DISTORTED. 1G71 3O3 O H11NM E295 20021106001412002110600141SO 2002 11 6 AUS20021215 120021014G8120KHR0173 BEARING GARRTT LW12463 PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL EXHAUST TURBOCHAFAILED W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE TOTAKEOFF 1 AUS KHR0173 (AUS) LH ENGINE TURBOCHARGER FAILED. SUSPECT BEARING FAILED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20021106001422002110600142EU 2002 11 6 AUS20021216 120021021G56201379595C3 WINDOW BAC 137169C411 BAG JETSTMJETSTM3201 1500217EU GARRTTTPE331TPE33112UA 01514WP MCAULY4HFR344HFR34C653 NE PASSENGER COMPARCRACKED W K NONE O OTHER CLCLIMB 1 AUS (AUS) PASSENGER WINDOW OUTER PANE CRACKED. WINDOW IS THE THIRD WINDOW ON THE LH SIDE. 2L72 4T4 TRTA56EU E4WE 6 C3PNE 20021106001432002110600143SO 2002 11 6 AUS20021217 120021009G61205417500 BALL JOINT HARTZL HCE3YR2 PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL PROPELLER CONTROSHEARED W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) RH ENGINE CSU BALL JOINT FAILED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20021106001442002110600144CE 2002 11 6 AUS20021218 120021015G275264679 STUD CESSNA 210N CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL TRAILING EDGE FLSHEARED W K NONE F FLT CONT AFFECTED LDLANDING 1 AUS 17386 64679 (AUS) FLAP MOTOR MOUNT STUD BROKEN. MOTOR SEPARATED FROM ACTUATOR. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20021106001452002110600145CE 2002 11 6 AUS20021219 120021023G2410646655A1 HUB PRESTOLITE ALV9407 CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL ALTERNATOR-GENERWORN W K NONE O OTHER ININSP/MAINT 1 AUS 759 4M000043 (AUS) ALTERNATOR GEAR DRIVE HUB SLIPPING. FOUND DURING INSPECTION IAW MEB01-3. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20021106001462002110600146NE 2002 11 6 AUS20021220 220021014G7321324485318 FCU PWA PW123D DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE FUEL CONTROL/TURFAULTY W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS 937 (AUS) NO1 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021112000692002111200069SO 2002 11 12 AUS20021221 220020901G8520 CRANKSHAFT CONT O520 IO520L 17032SO ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CRANKSHAFT BIG END JOURNALS FOR NR 4 AND NR 5 CYLINDER CONNECTING ROD SEVERELY OVERHEATED. CRANKSHAFT AND CONNECTING RODS DAMAGED BEYOND REPAIR. FOUND DURING ENGINE STRIP INSPECTION FOR LOW OIL PRESSURE. 3 O E5CE 20021106001472002110600147CE 2002 11 6 AUS20021222 120021023G57410001100881 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ADAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) LH WING FORWARD LOWER ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001482002110600148CE 2002 11 6 AUS20021223 120021023G57410001100882 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ADAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) RH WING FORWARD LOWER ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001492002110600149CE 2002 11 6 AUS20021224 120021023G57410001102501 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ADAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) LH WING FORWARD TOP ATTACHMENT BATHTUB FITTING CORRODED AND DAMAGED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001502002110600150CE 2002 11 6 AUS20021225 120021023G57419511001621 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ACORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) RH WING REAR TOP ATTACHMENT BATHTUB FITTING CORRODED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001512002110600151CE 2002 11 6 AUS20021226 120021023G57410001102502 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ACORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) RH WING TOP FORWARD ATTACHMENT BATHTUB FITTING CORRODED.PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001522002110600152CE 2002 11 6 AUS20021227 120021023G5741951100161 FITTING BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL WING, FUSELAGE ACORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) LH WING REAR UPPER ATTACHMENT BATHTUB FITTING CORRODED. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001532002110600153CE 2002 11 6 AUS20021228 120021023G2820369200141 CONNECTOR BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) LH WING MAIN FUEL TANK OUTLET FUEL RESERVOIR CONNECTOR CORRODED DUE TO WATER CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001542002110600154CE 2002 11 6 AUS20021229 120021023G2820369200141 CONNECTOR BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF32C3AF32C512 GL AIRCRAFT FUEL DICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 7086 (AUS) RH WING MAIN FUEL TANK OUTLET FUEL RESERVOIR CONNECTOR CORRODED DUE TO WATER CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20021106001552002110600155SW 2002 11 6 AUS20021231 120021015G53402050308153 FITTING BELL 204 UH1H 1181407SW LYC T53 T5313B 41549NE FUSELAGE MAIN, AFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAILBOOM LH LOWER ATTACHMENT FITTING ON FUSELAGE HAD OVERSIZE HOLES ALLOWING THE HILOK' PINS TO LOOSEN. SUSPECT CAUSED BY POOR REPAIR WORK. 1G71 4U4 U EXPA1G71E17EA 20021106001562002110600156CE 2002 11 6 AUS20021234 120021025G554010152401215 TORQUE TUBE BEECH B200C BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL RUDDER STRUCTUREFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS BL137 (AUS) RUDDER TORQUE TUBE RIVETS LOOSE AND RIVET HOLES WORN BY UP TO APPROXIMATELY 0.254MM (0.010IN) OVERSIZE. 1L72 4T4 T A24CE E4EA 5 CSTC 20021106001572002110600157EA 2002 11 6 AUS20021235 220020808G854060096 GASKET LYC O235L2C CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL RECIPROCATING ENDAMAGED W K NONE OEKOTHER VIBRATION/BUFFET FLUID LOSS ININSP/MAINT 1 AUS (AUS) ENGINE FUEL PUMP/BLANK PLATE GASKET CUT BY LOCKWIRE WRAPPED AROUND THE TWO MOUNTING BOLTS. GASKET LEAKING ENGINE OIL. ENGINEWAS FITTED WITH A BLANKING PLATE AND NOT A FUEL PUMP. ENGINE WASA RECENTLY OVERHAULED AND FITTED UNIT. PERSONNEL/MAINTENANCEERROR. 1H71 3O3 ONT3A19 E223 5 NP50GL 20021106001582002110600158EU 2002 11 6 AUS20021237 120021027G5523HC552H0004003 TRIM TAB BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE ELEVATOR, TAB STLIGHTNING STRIKEW K NONE C F.O.D. DEDESCENT 1 AUS (AUS) RH ELEVATOR SERVO TAB DAMAGED BY LIGHTNING STRIKE. 2H74 4F4 F A49EU E6NE 20021106001592002110600159SW 2002 11 6 AUS20021238 120021024G3221AN415 BOLT GULSTM112 114 7630314SW LYC O540 IO540T4B5 41532EA HARTZLHCC2Y HCC2YR1 GL NOSE/TAIL LANDINBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NOSE LANDING GEAR ACTUATOR REAR MAIN ATTACHMENT BOLT BROKEN INAREA OF SHAFT. 1L71 3O3 O A12SO 1E4 5 CP920 20021106001602002110600160NM 2002 11 6 AUS20021240 120021001G2782111015 PISTON SMITHSIND 1U1110 BOEING727 727281 138408NNM PWA JT8 JT8D17 52049NE LEADING EDGE SLABROKEN W K NONE F FLT CONT AFFECTED TOTAKEOFF 1 AUS 6754DPGKMNP (AUS) NO1 LEADING EDGE FLAP ACTUATOR PISTON SHEARED IN HALF. RETAINER PITTED, KEY CHROME CHIPPED AND RODEND REQUIRED REPLACEMENT. 2L73 4F4 F A3WE E2EA 20021112000772002111200077NE 2002 11 12 AUS20021244 220021029G720012679 ENGINE BOEING747 747238B 1384828NM RROYCERB211 RB211524D41954555NE NR 4 VIBRATES W A UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS (AUS) NR 4 ENGINE VIBRATION EXCESSIVE. ENGINE VIBRATION WAS ACCOMPANIEDBY A NOTICEABLE AIRFRAME VIBRATION. 2L74 4F4 F A20WE E12EU 20021106001612002110600161NM 2002 11 6 AUS20021247 120021028G6520A0211 GEARBOX ROBSIN A0211 ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA TAIL ROTOR GEARBUNSERVICEABLE W K NONE J WARNING INDICATION CRCRUISE 1 AUS 0406 (AUS) TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED. GEARBOX WAS FLUSHED. THE AIRCRAFT WAS FLOWN AGAIN AND CHIP LIGHT ONCE MORE ILLUMINATED. TAIL ROTOR GEARBOX WAS THEN CHANGED. 1G71 3O3 O H10WE E274 20021202001312002120200131CE 2002 12 2 AUS20021248 120021024G2434X4087 BEARING PRESTOLITE ALV9510R CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO MCAULY3FF32 3FF32C501 GL DC GENERATOR-ALTDISINTEGRATED W K NONE H ELECT. POWER LOSS-50 PC CRCRUISE 1 AUS 20 7040992 (AUS) LH ALTERNATOR OUTER BEARING COLLAPSED. ALTERNATOR CONTAMINATEDWITH METAL FROM FAILED BEARING. 1L72 3O3 O A7CE E7CE 5 CP45GL 20021204000262002120400026SO 2002 12 4 AUS20021249 120021016G57116210500 DOUBLER PIPER PA28 PA28235 7102810SO LYC O540 IO540* 41532EA WING SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT WING AFT SPAR OUTBOARD AILERON HINGE DOUBLER CRACKED FOR APPROXIMATELY 50 PERCENT OF ITS LENGTH. 1L71 3O3 O 2A13 1E4 20021202001322002120200132 2002 12 2 AUS20021250 420021021G2211065004203 CONTROLLER KING KC192 CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL AUTOPILOT COMPUTFAULTY W K NONE F FLT CONT AFFECTED TOTAKEOFF 1 AUS 54245 (AUS) AUTOPILOT COMPUTER CONTROLLER FAULTY. 1H71 3T3 T A37CE E4EA 5 CP60GL 20021202001332002120200133NM 2002 12 2 AUS20021251 120021018G55512200141 FITTING PIPER PA60 PA60600A 7106002NM LYC O540 IO540K1J5 41532EA HARTZLHCC3Y HCC3YR2 NE HORIZONTAL STABICRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 13092 (AUS) RH HORIZONTAL STABILISER FORWARD ATTACHMENT FITTING CRACKED. 1M72 3O3 ORTA17WE 1E4 5 CP25EA 20021204000272002120400027SO 2002 12 4 AUS20021252 220021031G8530630354 CYLINDER BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE CYLINDERS (4OFF) SEVERELY ERODED ON EXHAUST FLANGES. GASKETS LEAKING AND CAUSING BLOW-BY. ENGINE, ENGINE COMPONENTS AND FIREWALL CORRODED DUE TO EXHAUST GAS CONTAMINATION. AIRCRAFT HAD COMPLETED 20.7 HOURS SINCE LAST PERIODIC INSPECTION. 1L71 3O3 O A1CE E3CE 5 NP88614 20021204000282002120400028EU 2002 12 4 AUS20021253 120021028G7714230322704 PROBE BAC 146 146100A 1500260EU LYC ALF502ALF502R5 41580NE ENGINE RPM FAULTY W O OTHER N FALSE WARNING CRCRUISE 1 AUS (AUS) NR 2 ENGINE N2 PROBE FAULTY. 2H74 4F4 FRTA49EU E6NE 20021204000292002120400029CE 2002 12 4 AUS20021254 120021031G5711 SPAR BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA RT WING DAMAGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) RT WING SPAR REPAIRED DUE TO CORROSION. A LARGE DOUBLER IS ATTACHED TO THE AFT SIDE OF THE SPAR WEB. NO RECORD OF REPAIR OR REFERENCE TO AN ENGINEERING ORDER OR APPROVED DATA IS RECORDED IN THE LOGBOOK. THE OWNER STATES THE REPAIRS WERE CARRIED OUT IN AUGUST 2000. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED REPAIR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021204000302002120400030CE 2002 12 4 AUS20021255 120021031G53411694000135 BRACKET BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA WING TO BODY CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT WING FORWARD ATTACHMENT BRACKETS CRACKED. CRACKS ARE LARGE AND EASILY VISIBLE TOTHE NAKED EYE. LAST PERIODIC INSPECTION WAS 20.7 HOURS PREVIOUSLY. FOUND DURING INSPECTION IAW AD/BEECH23/14A2 AND BEECH SI NO 0042-031 REVII. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001342002120200134 2002 12 2 AUS20021256 420021031G611316991003021 SPINNER SNSNCH M74DC BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA PROPELLER SPINNECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER SPINNER CRACKED IN SEVERAL PLACES. SPINNER APPEARS TO HAVE BEEN REPAIRED BY WELDING. THE QUALITY OF THE WELD REPAIRS IS VERY POOR WITH CRACKS EMANATING FROM THE WELDS. LAST PERIODIC INSPECTION 20.7 HOURS PREVIOUS. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001352002120200135 2002 12 2 AUS20021257 420021031G611316996001119 BULKHEAD SNSNCH M74DC BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA PROPELLER SPINNECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER SPINNER FORWARD BULKHEAD CRACKED IN SEVERAL PLACES. BULKHEAD APPEARS TO HAVE BEEN REPAIRED BY WELDING WITH THEQUALITY OF WELDS VERY POOR. CRACKS EMANATING FROM THE WELDS.AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE THE LAST PERIODICINSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001362002120200136CE 2002 12 2 AUS20021258 120021031G5347169400005519 ANGLE BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA SEAT/CARGO ATTACCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PILOTS INBOARD SEATBELT ATTACHMENT BRACKET CONTAINED SEVERE EXFOLIATION CORROSION. AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021204000312002120400031CE 2002 12 4 AUS20021259 120021031G5753AN201KP3A BEARING BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA TE FLAPS UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT TRAILING EDGE FLAP OUTBOARD HINGE BEARING LOOSE IN BRACKET.SUSPECT UNAPPROVED PART. AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021204000932002120400093CE 2002 12 4 AUS20021260 120021031G7160 DUCT BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA ENG AIR INTAKE UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) UNAPPROVED SCAT HOSE FITTED BETWEEN AIR FILTER AND CARBURETTOR. SCAT HOSE IS NOT DESIGNED FOR NEGATIVE PRESSURE SUCH AS FOUND ININDUCTION HOSES. WHEN REMOVED, THE HOSE WAS FOUND TO BE PARTIALLY COLLAPSED. CORRECT PNO 115167DXX100323. AIRCRAFT HADOPERATED FOR 20.7 HOURS SINCE LAST PERIODICINSPECTION. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001372002120200137CE 2002 12 2 AUS20021261 120021031G27013538006035 YOKE BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA CONTROL COLUMN SCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PILOTS CONTROL YOKE CRACKED. AN ATTEMPT HAD BEEN MADE TO REPAIR THE YOKE USING GLUE. AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE LAST PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001382002120200138CE 2002 12 2 AUS20021262 120021031G7120J107784 MOUNT CONT IO346A BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA ENGINE MOUNT SECDETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE MOUNT RUBBERS BADLY DETERIORATED. AIRCRAFT HAS OPERATEDFOR 20.7 HOURS SINCE PERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021202001392002120200139SO 2002 12 2 AUS20021263 120021029G24601709C02500 CONTACTOR EMB EMB120 EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE DC POWER DISTRIBUNSERVICEABLE W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION TOTAKEOFF 1 AUS 27360 120163 (AUS) BATTERY CONTACTOR SUSPECT FAULTY. WIRES W010-0013-24 ANDW010-0038-24 BURNT. INVESTIGATION FOUND THE BATTERY CONTACTOR K0455 PNO 170GC02-500 HAD A DISLODGED LEAF CONTACT ON TERMINAL S. THE LOOSE TERMINAL SHORT CIRCUITED CAUSING EXCESS CURRENT INWIRES. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20021204001462002120400146WP 2002 12 4 AUS20021264 220021102G7250 SEAL HONEYWELL SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE TURBINE SECTION FAILED W O OTHER EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS (AUS) LT ENGINE LOW OIL PRESSURE. INSPECTION FOUND AN OIL LEAK IN THE AREA OF THE TURBINE. INVESTIGATION FOUND THE CAUSE OF THE OIL LOSS TO BE TURBINE SEAL FAILURE. THE CARBON FACE OF THE SEAL HAD DISINTEGRATED AND THE BELLOWS RUPTURED RESULTING IN THE LOSS OF OIL. THE RUPTURED BELLOWS CAUSED FURTHER DAMAGE TO THE AFT CURVIC COUPLING. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20021202001402002120200140CE 2002 12 2 AUS20021266 120021029G323312810013 ACTUATOR CESSNA 98820152 CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL LANDING GEAR ACTCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 6007 (AUS) LH MAIN LANDING GEAR ACTUATOR BODY CRACKED FROM THE BEARING BOSSTO THE INTERNAL DIAMETER OF THE SECTOR GEAR ACCESS HOLE. 1H71 3O3 O 3A17 E286 5 CP7EA 20021202001412002120200141SO 2002 12 2 AUS20021267 220021030G73226405637 BUTTERFLY VALVE CONT IO360HB PAC CT4 CT4B GL CONT O360 IO360HB 17025SO HARTZLHCC2Y BHCC2YF1 GL FUEL CONTROL/RECSEIZED W K NONE O OTHER CLCLIMB 1 AUS 121 I049121AR (AUS) THROTTLE BUTTERFLY VALVE PARTIALLY SEIZED. 1L71 3O3 ORTA9PC E1CE 5 CP920 20021202001422002120200142SO 2002 12 2 AUS20021268 220021101G73226405637 BUTTERFLY VALVE CONT IO360HB PAC CT4 CT4B GL CONT O360 IO360HB 17025SO HARTZLHCC2Y BHCC2YF1 GL FUEL CONTROL/RECSEIZED W K NONE O OTHER CLCLIMB 1 AUS 6 C199101A (AUS) THROTTLE BUTTERFLY VALVE SEIZED. 1L71 3O3 ORTA9PC E1CE 5 CP920 20021202001432002120200143SO 2002 12 2 AUS20021269 120021030G5711620540 SPAR PIPER PA32 PA32260 7103206SO LYC O540 O540E4B5 41532EA HARTZLHCC2Y HCC2YK1 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING REAR SPAR CONTAINS SEVERE EXFOLIATION CORROSION BETWEEN THE SPAR AND ATTACHMENT PLATE. 1L71 3O3 O A3SO E295 5 CP920 20021202001442002120200144NM 2002 12 2 AUS20021274 120021104G7922SL53E19600 NUT SUPAIRPART VERNATHERM ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE OIL TEMPELOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 22099 (AUS) ENGINE OIL TEMPERATURE BYPASS VALVE (VERNATHERM) NUT LOOSE. SUSPECT ROLL PIN NOT FITTED DURING ASSEMBLY. 1G71 3O3 O H10WE E274 20021202001452002120200145CE 2002 12 2 AUS20021275 120021022G3230504501025 TORQUE TUBE CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL LANDING GEAR RETCRACKED W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) LH MAIN LANDING GEAR TORQUE TUBE CRACKED AND TWISTED. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20021202001462002120200146WP 2002 12 2 AUS20021277 120021025G6320369D2570421 HOSE DOUG 369D25100505HUGHES369 369E 4470707WP ALLSN 250C 250C20B 03013GL MAIN ROTOR GEARBWORN W K NONE B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 AUS 0022220016 (AUS) TRANSMISSION OIL HOSE CHAFING ON AIRCRAFT STRUCTURE. 1G71 3U3 U H3WE E4CE 20021205000082002120500008SO 2002 12 5 AUS20021279 120021015G2750 LEVER PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO TE FLAPS BINDING W O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 AUS (AUS) FLAP LEVER FOULING ON ENGINE CONTROL FRICTION LEVER. 1L72 3O3 O A7SO E9CE 20021202001472002120200147 2002 12 2 AUS20021280 420021031G6122782490A50 CONTROL UNIT HAMSTD 782490A50 DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE PROPELLER GOVERNFAULTY W K NONE J WARNING INDICATION LDLANDING 1 AUS 2593 970817 (AUS) LH PROPELLER CONTROL UNIT FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021202001482002120200148NM 2002 12 2 AUS20021281 120021025G282020C1444 VALVE BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU AIRCRAFT FUEL DIFAULTY W K NONE K FLUID LOSS CRCRUISE 1 AUS 2189 (AUS) FUEL TRANSFER SYSTEM CHECK VALVE FAULTY. 2L72 4F4 FRTA16WE E21EU 20021202001492002120200149NM 2002 12 2 AUS20021282 120021029G57536546486155 FLAP BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU TRAILING EDGE FLDAMAGED W K NONE OD OTHER INFLIGHT SEPARATION ININSP/MAINT 1 AUS (AUS) LH INBOARD MID FLAP UPPER SKIN DAMAGED. A SECTION OF METAL SKIN MEASURING APPROXIMATELY 150MM (5.9IN) BY 250MM (9.84IN) WAS MISSING. 2L72 4F4 FRTA16WE E21EU 20021205000092002120500009EU 2002 12 5 AUS20021283 120021031G32309740926112 RELAY PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG HYD SYS FAULTY W O OTHER O OTHER NRNOT REPORTED 1 AUS 227 (AUS) HYDRAULIC POWER RELAY FAULTY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021205000102002120500010EU 2002 12 5 AUS20021284 120021004G56109598110103 WINDSHIELD PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT CRACKED W O OTHER O OTHER NRNOT REPORTED 1 AUS (AUS) RT WINDSHIELD OUTER LAYER CRACKED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021205000112002120500011NE 2002 12 5 AUS20021285 220021101G7261 OIL SYSTEM EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE LT ENGINE LOW W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 AUS (AUS) LT ENGINE OIL QUANTITY BELOW MINIMUM LEVEL. PERSONNEL/MAINTENANCE ERROR. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20021205000122002120500012NM 2002 12 5 AUS20021286 120021106G2597TBY7MT006 WIRE HARNESS BOEING747 747438 NM RROYCERB211 RB211524G19 NE GALLEY BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 AUS (AUS) WIRING HARNESS LOCATED IN GALLEY 4C AREA BURNED. 2L74 4F4 FRTA20WE E30NE 20021202001502002120200150 2002 12 2 AUS20021288 420021021G3460 COMPUTER BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FLIGHT MANAGEMENFAILED W K NONE O OTHER CLCLIMB 1 AUS (AUS) FLIGHT MANAGEMENT COMPUTER FAULTY. 2L72 4F4 FRTA16WE E21EU 20021202001512002120200151EU 2002 12 2 AUS20021290 220021104G75307064004 MOTOR GE CFM563C BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU COMPRESSOR BLEEDLEAKING W K NONE K FLUID LOSS TXTAXI/GRND HDL 1 AUS 13711 (AUS) NO1 ENGINE VBV GEAR MOTOR LEAKING. 2L72 4F4 FRTA16WE E21EU 20021202001522002120200152NM 2002 12 2 AUS20021291 120021106G276182950010271 PIPE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE DRAG CONTROL ACTLEAKING W K NONE K FLUID LOSS CRCRUISE 1 AUS (AUS) RH INBOARD ROLL SPOILER ACTUATOR PRESSURE LINE LEAKING FROM PINHOLE. LOSS OF NO1 HYDRAULIC SYSTEM FLUID. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021205000162002120500016CE 2002 12 5 AUS20021293 120021104G2710 BELLCRANK CESSNA150 A152 2071836CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL AILERON CONTROL DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AILERON BELLCRANK STOP BENT. DAMAGE ALSO TO PUSH-PULL ROD AND ATTACHMENT HARDWARE AS WELL AS TO THE AILERON CONTROL BRACKET AND SECURING RIVETS. 1H71 3O3 O 3A19 E223 5 NP50GL 20021202001532002120200153CE 2002 12 2 AUS20021294 120021030G32332379828 PLUNGER WESTERNHYD 99101363 CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C87 GL LANDING GEAR ACTSTICKING W K NONE ON OTHER FALSE WARNING TOTAKEOFF 1 AUS 300 (AUS) RH MAIN LANDING GEAR ACTUATOR DOWN MICROSWITCH PLUNGER STUCK. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021202001542002120200154EA 2002 12 2 AUS20021298 220021101G852011F20022D3 CRANKCASE LYC LTIO540J2B PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2 GL RECIPROCATING ENCRACKED W K NONE E VIBRATION/BUFFET CLCLIMB 1 AUS 1699 L241661A (AUS) CRANKCASE PNO 11F20022-D3) CRACKED AT THROUGH BOLT LOCATION. NO4CYLINDER PNO LW-12066 HOLDDOWN STUDS (7OFF8) SHEARED ALLOWING PARTIAL SEPARATION OF THE CYLINDER FROM THE CRANKCASE. UNABLE TOASCERTAIN CHAIN OF EVENTS. 1L72 3O3 O A20SO E14EA 5 CP33EA 20021202001552002120200155CE 2002 12 2 AUS20021299 120021109G534724140021 SEAT TRACK CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL SEAT/CARGO ATTACWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH INBOARD AND LH OUTBOARD SEAT TRACKS WORN BEYOND LIMITS. FOUNDDURING INSPECTION IAW AD/C172/53 AMDT2. 1H71 3O3 ONT3A12 E274 5 NP910 20021202001562002120200156NM 2002 12 2 AUS20021300 120021103G7120LM43154 HOUSING LORD LM431SA18 DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE MOUNT SECCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH ENGINE REAR MOUNT HOUSING CRACKED. RH ENGINE REAR MOUNTHOUSING REWORKED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021202001572002120200157EU 2002 12 2 AUS20021303 120021106G57116814013B3 SPAR CAP PARTENP68 P68B 6780104EU LYC O360 IO360A1B6 41514EA HARTZLHCC2Y HCC2YK2 GL WING SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING SPAR CAP CRACKED. PREVIOUS CRACK HAD BEEN REPAIRED USINGSTAINLESS STEEL LAMINATIONS. DURING EDDY CURRENT INSPECTION IAW AD/P68/43 AMDT1 IT WAS FOUND THAT THE CRACK HAD GROWN FROM 10MM (0.39IN) TO 21MM (0.826IN) ON THE VERTICAL FACE. 1H72 3O3 O A31EU 1E10 5 CP920 20021202001582002120200158NM 2002 12 2 AUS20021304 120021107G2810 FUEL TANK DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE FUEL STORAGE FOD W K NONE J WARNING INDICATION CRCRUISE 1 AUS (AUS) MAIN AND AUXILIARY FUEL TANKS CONTAMINATED BY FOREIGN OBJECT. FOD WAS BLOCKING FUEL TRANSFER FROM RH AUXILIARY FUEL TANK. PERSONNEL/MAINTENANCE ERROR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021202001592002120200159NM 2002 12 2 AUS20021306 120021114G711065255172 PANEL PWA JT8D15 BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE ENGINE COWLING SSEPARATED W K NONE D INFLIGHT SEPARATION LDLANDING 1 AUS (AUS) NO2 ENGINE RH FORWARD COWL BLOWOUT PANEL MISSING. PANEL WAS FOUND ON RUNWAY. 2L73 4F4 FRTA3WE E2EA 20021202001602002120200160CE 2002 12 2 AUS20021307 120021031G5751512400098 AILERON CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL AILERONS OUT OF BALANCE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH AILERON OUT OF BALANCE. ACCESS PANELS (3OFF) IN LOWER SKIN AND A QUANTITY OF EPOXY RESIN IN THE TRAILING EDGE CAUSED THE AILERON TO BE APPROXIMATELY 700 GRAMS OUT OF BALANCE. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021202001612002120200161CE 2002 12 2 AUS20021308 120021031G322258420005 FORK CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL NOSE/TAIL LANDINCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NOSE LANDING GEAR FORK CRACKED. FOUND USING EDDY CURRENTINSPECTION. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021202001622002120200162CE 2002 12 2 AUS20021312 120021031G5343 STRUCTURE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL LANDING GEAR ATTCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN LANDING GEAR UPLOCK SUPPORT STRUCTURE CRACKED AND RIVETS LOOSE. BOLT HOLES ELONGATED. UPLOCK HOOK PIVOTS LOOSE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021202001632002120200163CE 2002 12 2 AUS20021313 120021031G532058130412 WEB CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL FUSELAGE, MISCELCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUSELAGE WEB LOCATED IN AREA BEHIND THE NLG DRAG BRACE PIVOTFITTING CRACKED. CRACK HAD BEEN PREVIOUSLY STOP DRILLED. 1L72 3O3 O A7CE E8CE 5 CP22EA 20021202001642002120200164SO 2002 12 2 AUS20021314 120021106G215010000029 ACTUATOR EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14RF 14RF9 NE CABIN COOLING SYWORN W K NONE O OTHER CLCLIMB 1 AUS (AUS) LH AIRCONDITIONING SYSTEM RAM AIR ACTUATOR AFT MOUNT WORN THROUGH ALLOWING ACTUATOR TO DISCONNECT. RAM AIR VALVE PARTIALLY CLOSED RESTRICTING COOLING AIR FLOW THROUGH THE HEAT EXCHANGER AND CAUSING THE AIRCONDITIONING PACK TO SHUT DOWN DUE TO OVERHEATING. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 20021205000252002120500025SO 2002 12 5 AUS20021315 120021107G3230 PIN PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL MLG XMSN BROKEN W O OTHER O OTHER NRNOT REPORTED 1 AUS (AUS) LANDING GEAR TRANSMISSION ASSEMBLY MOTOR RELEASE LINK PIN BROKEN AND JAMMING MECHANISM. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021205000262002120500026SO 2002 12 5 AUS20021316 120021112G57536232300 BRACKET PIPER PA28 PA28140 7102802SO LYC O320 O320* 41508EA SNSNCH74DM M74DM EA TE FLAPS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FLAP CENTER HINGE BRACKETS SEVERELY CORRODED. LT AND RT ATTACHMENT RIBS DESTROYED BY CORROSION. 1L71 3O3 O 2A13 E274 5 NP88614 20021205000292002120500029GL 2002 12 5 AUS20021319 320021108G6114727672 HUB MCAULY2A34C D2AF34C30 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROP HUB CRACKED IN BLADE SOCKET. FOUND DURING EDDY CURRENT INSP. VISUAL INSP IFRETENTION NUT FOUND CRACK IN THREADS. INSP CARRIED OUT FOLLOWING LONG TERM STORAGE. PROP HAD NO HRS SINCE OVERHAUL. 5 CP5EA 20021205000302002120500030GL 2002 12 5 AUS20021320 320021108G6114702987 HUB MCAULY2A34C D2AF34C30 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) PROPELLER HUB CRACKED IN BLADE SOCKET. FOUND DURING EDDY CURRENT INSPECTION IAW AD/PMC/41. PROPELLER WAS BEING INSPECTED FOLLOWING LONG TERM STORAGE AND HAD NO HOURS OPERATION SINCE OVERHAUL. 5 CP5EA 20021202001652002120200165NM 2002 12 2 AUS20021321 120021022G5320693535214 CONNECTOR BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUSELAGE, MISCELCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CABIN UPPER LOBE STRUCTURE FRAME TO STRINGER TIES CRACKED AND FAILED. 2L72 4F4 FRTA16WE E21EU 20021205000312002120500031 2002 12 5 AUS20021322 420021115G2562VARIOUS SPRING GROB G115 G115C 1660303EU ELT BATT CASE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELT BATTERY CASE COIL CONTACT SPRINGS CORRODED. 1L71 3O NTA57EU 20021205000322002120500032CE 2002 12 5 AUS20021323 220021104G7414 PIN PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360RB 17025CE MAGNETO CHAFED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAGNETO HARD TO TIME. INVESTIGATION FOUND THE SPLIT PIN SECURING THE MAGNETO COUPLING NUT WAS CONTACTING THE END OF THE DRIVE CUSHION BEARING STUD ON THE CRANKCASE. MAGNETO WAS A NEWLY FITTED UNIT. FURTHER INVESTIGATION FOUND OTHER SIMILAR MAGNETOS. THE STUDS WERE FOUND TO BE THE CORRECT LENGTH AND THE SPLIT PINS WERE INSTALLED CORRECTLY. SUSPECT CAUSED BY INSUFFICIENT CLEARANCE BETWEEN THE END OF THE MAGNETO SHAFT AND THE SUPPORT STUD IN THECRANKCASE (CLEARANCE IS APPROXIMATELY 2MM (0.078IN). 1L72 3O3 O A7SO E9CE 20021205000342002120500034NM 2002 12 5 AUS20021325 120021117G3210 LANDING GEAR BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU MAINS MALFUNCTIONED W O OTHER J WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) LANDING GEAR FAILED TO RETRACT. THE GROUND SENSING RELAY AND GROUND SENSING MODULE WERE CHANGED BUT THE DEFECT REMAINED. DURING TROUBLESHOOTING THE DEFECT DISAPPEARED. A THOROUGH SERVICEABILITY CHECK WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA16WE E21EU 20021202001662002120200166WP 2002 12 2 AUS20021327 120021108G6310A1851 BRACKET ROBSIN R44ASTRO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE/TRANSMISSCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LOWER ACTUATOR BRACKET CRACKED. 1G71 3O3 O H11NM E295 20021205000352002120500035SO 2002 12 5 AUS20021328 120021021G2622V825320 O-RING PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA AMTR C8289 C8289 GL FIRE BOTTLE FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 AUS (AUS) HAND HELD FIRE EXTINGUISHER CYLINDER TO DISCHARGE HEAD O-RING SEAL FAILED. LOSS OF FIRE EXTINGUISHING FLUID. 1L71 3O3 O 2A13 E274 5 NEXPP5N 20021205000362002120500036GL 2002 12 5 AUS20021329 320021106G6114107967 HUB SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 5107 (AUS) PROPELLER HUB SUSPECT CRACKED IN TWO ADJACENT MOUNTING BOLT HOLES. FOUND DURING INSPECTION IAW DOWTY ROTOL SB/61/1125. 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20021205000372002120500037CE 2002 12 5 AUS20021330 120021106G5312 BULKHEAD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE FUSELAGE DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR PRESSURE BULKHEAD DAMAGED. PUNCTURE HOLE IN BULKHEAD WEB LOCATED IN AREA BETWEEN THE CENTRELINE AND INBOARD OF THE OVERPRESSURE AND OUTFLOW VALVE CUTOUT. FOUND DURING INSPECTIONIAW RAYTHEON SB/53/3513 REV1. DAMAGE CAUSED DUE TO IMPACT BYTRIM. 1L72 4T4 T A24CE E4EA 20021205000382002120500038NM 2002 12 5 AUS20021331 120021108G1430 FASTENER BOEING747 747400 NM GE CF6 CF680C2* GL NACELLE LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STRUT INBOARD MIDSPAR FITTING HORIZONTAL AND VERTICAL TANGS HAD SEVERAL LOOSE FASTENERS. 2L74 4F4 FRTA20WE E23EA 20021202001672002120200167SW 2002 12 2 AUS20021333 120021115G2710500004267 CABLE GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA HARTZLHCC3Y HCC3YR2 NE AILERON CONTROL WORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AILERON CABLE FRAYED IN AREA OF FAIRLEAD LOCATED OUTBOARD OF LH NACELLE. 1H72 3O3 O 6A1 1E4 5 CP25EA 20021202001682002120200168SO 2002 12 2 AUS20021335 120021113G5711 SPAR PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING SPAR CONTAINED LIGHT CORROSION AND MINOR PITTING LOCATEDIN AREA JUST ABOVE LOWER SPAR CAP RADIUS. AREA OF CORROSION APPROXIMATELY 25MM (1IN) LONG BY 6MM (0.236IN) WIDE. FOUND DURING INSPECTION IAW AWB51-4. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021205000422002120500042GL 2002 12 5 AUS20021337 220021121G7321252465426H FCU ALLSN 250B 250B17 03012GL ENGINE FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 238 (AUS) FUEL CONTROL UNIT FLYWEIGHT CLIP FAULTY. LIMITED INFORMATIONPROVIDED. 3 T E10CE 20021205000462002120500046CE 2002 12 5 AUS20021341 120021115G5312805 FITTING BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE MCAULY4HFR344HFR34C754 NE BULKHEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) REAR PRESSURE BULKHEAD STIFFENER CLEAT CRACKED. CLEAT IS FITTED AS PART OF CARGO DOOR MODIFICATION. FOUND DURING INSPECTION IAW AD/BEECH200/55 (SB/2472). 1L72 4T4 T A24CE E4EA 6 C3PNE 20021205000472002120500047EU 2002 12 5 AUS20021342 120021121G7120115C6100 MOUNT GROB G115 G115C 1660303EU LYC O360 O360A1F6 41514EA HARTZLHCF2Y HCF2YR1 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 995 (AUS) ENGINE MOUNT FRAME CRACKED IN TUBE SEGMENT ADJACENT TO THE RT LOWER AFT LORD MOUNT. 1L71 3O3 ONTA57EU E286 5 CP27EA 20021202001692002120200169CE 2002 12 2 AUS20021343 120021122G3213169810000113 ROD BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA MAIN LANDING GEAWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH MAIN LANDING GEAR SHOCK ABSORBER RODS SEVERELY WORN. LH MLG RODS WORN APPROXIMATELY 0.863MM (0.034IN). RH MLG RODS WORN APPROXIMATELY 0.457MM (0.018IN). FOUND DURING INSPECTION IAWAD/BEECH23/13. AIRCRAFT HAD OPERATED FOR 20.7 HOURS SINCE LASTPERIODIC INSPECTION. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021205000482002120500048CE 2002 12 5 AUS20021344 120021122G3213169810000119 WASHER BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA MLG STRUT UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT AND RT MAIN LANDING GEAR SHOCK ABSORBERS FITTED WITH PLASTIC AUTOMOTIVE TYPE BUSHES ALONG WITH PNO 169-810000-119 WASHERS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021205000492002120500049CE 2002 12 5 AUS20021345 120021122G3213169810000609 LANDING GEAR BEECH 23 A23A 1151208CE CONT O346 IO346A 17033SO SNSNCH74DC M74DC EA LT & RT TRANSPOSED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT MAIN LANDING GEAR AND RT MAIN LANDING GEAR TRANSPOSED. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O A1CE E3CE 5 NP88614 20021205000512002120500051EA 2002 12 5 AUS20021347 220021121G853005K21232 CYLINDER GROB G115 G115 EU LYC O235 O235H2C 41505EA SNSNCH72C 72CK EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NR 2 CYLINDER CRACKED IN AREA ADJACENT TO THE ATTACHMENT FLANGE. CRACK LENGTH APPROXIMATELY 100MM (3.93IN). 1L71 3O3 ONTA57EU E223 5 NP9045 20021202001702002120200170SO 2002 12 2 AUS20021348 120021119G2150490150 SLEEVE HONEYWELL 22045402 EMB 120 EMB120 3260201SO PWA 118 PW118A NE HAMSTD14SF 14SF9 NE CABIN COOLING SYDAMAGED W K NONE OJ OTHER WARNING INDICATION NRNOT REPORTED 1 AUS 8135 89909214 (AUS) LH AIRCONDITIONING PACK ASSEMBLY LEAKING. INVESTIGATION FOUND THREE PIPELINE SLEEVE CONNECTORS SUSPECT FAULTY. 2L72 4T4 TRTA31SO E20NE 6 NP11NE 20021202001712002120200171CE 2002 12 2 AUS20021349 120021101G273005341221 BELLCRANK CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA AMTR C8289 C8289 GL ELEVATOR CONTROLCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELEVATOR BELLCRANK CONTAINED SEVERE EXFOLIATION CORROSION. SIGNSOF CORROSION ALSO FOUND ON RUDDER HINGES. 1H71 3O3 ONT3A12 E274 5 NEXPP5N 20021202001722002120200172EU 2002 12 2 AUS20021351 120021124G5230HC523B0018000 DOOR BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE CARGO/BAGGAGE DOFAULTY W K NONE J WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) FORWARD CARGO DOOR HANDLE AJAR. SUSPECT HANDLE HAD NOT BEEN FULLY CLOSED. PERSONNEL/MAINTENANCE ERROR. 2H74 4F4 F A49EU E6NE 20021205000532002120500053NM 2002 12 5 AUS20021352 120021124G2822433092032 MODULE BOEING747 747438 NM RROYCERB211 RB211524G19 NE BOOST PUMP FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) BOOST PUMP SWITCH MODULE FAULTY. 2L74 4F4 FRTA20WE E30NE 20021202001732002120200173NM 2002 12 2 AUS20021353 120021122G5210 PUSHROD BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU PASSENGER/CREW DBROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CABIN DOOR R2 JAMMED CLOSED. INVESTIGATION FOUND THE LOWER DOOR PUSHROD BROKEN. 2L72 4F4 FRTA16WE E21EU 20021205000552002120500055GL 2002 12 5 AUS20021355 320021120G6114D2483 HUB HARTZLHCE2Y HCE2YL2 GL PROPELLER DAMAGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) PROPELLER HUB HAD UNAPPROVED MODIFICATION CARRIED OUT TO THE SIX MOUNTING FLANGE COUNTER BORES. HUB EXHIBITS EVIDENCE OF DAMAGE TO THE PRELOAD PLATE SHELF AREA SUSPECT DUE TO GROUND STRIKE. SUSPECT HUB HAD NOT BEEN STRIPPED OF ANODIZING AND ETCHED AND PAINTED AS REQUIRED BY MANUAL 202A. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION. 5 CP9EA 20021205000562002120500056NM 2002 12 5 AUS20021357 120021127G7500MA20A10011 ACTUATOR BOEING737 73776N 13844CHNM GE CFM56 CFM567B24 NE ENGINE BLEED AIRFAULTY W O OTHER O OTHER NRNOT REPORTED 1 AUS (AUS) NR 2 ENGINE SPAR VALVE ACTUATOR SUSPECT FAULTY. 2L72 4F4 FRTA16WE E00055EN 20021202001742002120200174NE 2002 12 2 AUS20021358 220021124G7321114E6112G1 EEC RROYCE BR700715A130BOEING717 717200 1383700NM RROYCEBR700 BR700715A130 NE FUEL CONTROL/TURFAULTY W K NONE E VIBRATION/BUFFET DEDESCENT 1 AUS LHBR0148 (AUS) LH ENGINE SPOOLED DOWN. ENGINE ELECTRONIC CONTROLLER (EEC) PNO114E6112G1 AND FUEL METERING UNIT (FMU) PNO 8061-965 CHANGED ON ADVICE FROM MANUFACTURERS. 2L72 4F4 FTRA6WE E00061EN 20021202001752002120200175EU 2002 12 2 AUS20021361 120021102G53021053040212 FITTING BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE ROTORCRAFT TAIL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAIL ROTOR GEARBOX FITTING CRACKED. 1G72 3U3 UNCH13EU E5NE10 20021202001762002120200176SO 2002 12 2 AUS20021362 120021120G57112029607 SPAR CAP PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021202001772002120200177SO 2002 12 2 AUS20021363 120021120G57112029608 SPAR CAP PIPER PA30 PA30 7103002SO LYC O320 IO320B1A 41508EA HARTZLHCE2Y HCE2YL2 GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING MAIN LOWER SPAR CAP CORRODED. CORROSION IS LOCATED AT WS62 AS INDICATED IN AWB/51-4 ISSUE 1. 1L72 3O3 O A1EA 1E12 5 CP9EA 20021202001782002120200178SO 2002 12 2 AUS20021364 220021122G8530SA636242 VALVE GUIDE SUPAIRPART SA47000 CESSNA210 2105 2073404CE CONT O470 IO470S 17026SO MCAULY2A34C D2A34C58 GL RECIPROCATING ENUNSERVICEABLE W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 277 NA (AUS) NO2 CYLINDER EXHAUST VALVE GUIDE CARBON BUILDUP. EXHAUST VALVESEIZED IN GUIDE CAUSING PUSHROD TO BEND AND SHROUD TUBE TO BE BROKEN. 1H71 3O3 O 3A21 3E1 5 CP3EA 20030121002162003012100216GL 2003 1 21 AUS20021367 220020921G7230CAC35460 SEAL ALLSN COMPRESSOR BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL TURBINE ENGINE CSEIZED W K NONE O OTHER ININSP/MAINT 1 AUS CAC35460 (AUS) ENGINE COMPRESSOR SEIZED. INVESTIGATION FOUND THE REAR LABYRINTHSEAL HAD PICKED UP IN THE SEAL HOUSING. 1G71 3U3 U H2SW E4CE 20030121002172003012100217SW 2003 1 21 AUS20021368 120021025G2931 INDICATOR BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL HYDRAULIC FILTERCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HYDRAULIC FILTER DIFFERENTIAL PRESSURE INDICATOR FAULTY. INDICATOR APPEARED TO BE STUCK DUE TO CORROSION AND DIRT. 1G71 3U3 U H2SW E4CE 20030121002182003012100218SW 2003 1 21 AUS20021371 120021125G5553301971 PLATE AIRTRCAT500 AT502B 0390307SW PWA PT6 PT6A15AG 52043NE HARTZLHCB3T HCB3TN3 GL VERTICAL STABILICRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VERTICAL FIN FRONT SPAR ATTACHMENT FITTING FAILED. REAR SPARCRACKED. 1L71 3T4 TNCA17SW E4EA 6 CP15EA 20030121002192003012100219CE 2003 1 21 AUS20021377 120021119G5520 TORQUE TUBE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ELEVATOR STRUCTUCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH ELEVATOR TORQUE TUBE ASSEMBLIES SEVERELY CORRODED PARTICULARLY FITTINGS PNO 0734102-4 AND PNO 0734102-3. LOWER LEFT HAND SKIN PNO 0532001-91 ALSO CORRODED. 1H71 3O3 ONT3A12 E274 5 NP910 20030121002202003012100220CE 2003 1 21 AUS20021378 120021122G5347121040821 SEAT TRACK CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL SEAT/CARGO ATTACCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) SEAT TRACK CRACKED ACROSS LOCK PIN HOLES. 1H71 3O3 O A4CE E5CE 5 CP21EA 20030121002212003012100221CE 2003 1 21 AUS20021379 120021126G323312810013 HOUSING CESSNA 98820152 CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA MCAULY2D34C B2D34C220 GL LANDING GEAR ACTCRACKED W K NONE O OTHER LDLANDING 1 AUS 5822 (AUS) LH MAIN LANDING GEAR ACTUATOR HOUSING CRACKED. ACTUATOR RACKSEPARATED FROM SECTOR GEAR. 1H71 3O3 O 3A17 E286 5 CP7EA 20030121002222003012100222SO 2003 1 21 AUS20021380 220021014G8550632062 DIPSTICK CONT IO520F CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL RECIPROCATING ENDISTORTED W K NONE EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS 616 (AUS) ENGINE OIL DIPSTICK BENT, GIVING AN INCORRECT READING OF OILQUANTITY. SUSPECT CAUSED BY BENDING THE DIPSTICK WHILE WIPING OFF THE OIL. BENT DIPSTICK CAN ALSO WEAR ON THE BOTTOM OF THE SUMP. 1H71 3O3 O A4CE E5CE 5 CP21EA 20030121002232003012100223EU 2003 1 21 AUS20021384 120021203G2931523250 INDICATOR SAAB SF340 SF340A 7850100EU GE CT7TP CT75A 30030NE ROTOL R375 R3754123F21 NE HYDRAULIC PRESSUFAILED W K NONE K FLUID LOSS TOTAKEOFF 1 AUS (AUS) MAIN HYDRAULIC SYSTEM PRESSURE INDICATOR FAILED. 2L72 4T4 TRTA52EU E8NE 6 CP17NE 20030121002242003012100224CE 2003 1 21 AUS20021388 120021203G2710276455A BEARING CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL AILERON CONTROL COLLAPSED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AILERON YOKE BEARING COLLAPSED. 1L72 3O3 O A7CE E8CE 5 CP22EA 20030121002252003012100225EU 2003 1 21 AUS20021389 120021204G3240HTE90821 ACTUATOR BAC 146 146100A 1500260EU LYC ALF502ALF502R5 41580NE LANDING GEAR BRAFAULTY W K NONE OJ OTHER WARNING INDICATION TXTAXI/GRND HDL 1 AUS (AUS) PARK BRAKE ACTUATOR FAULTY. ACTUATOR WAS CONSISTENTLY MOTORING. 2H74 4F4 FRTA49EU E6NE 20030121002272003012100227EA 2003 1 21 AUS20021397 120021128G5751CZW151A BRACKET DHAV DHC2 DHC2* 2800108EA PWA R985 R985AN14B 52008NE HAMSTD2D 2D30 NE AILERONS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AILERON CENTRE HINGE BEARING SUPPORT BRACKET CONTAINED EXFOLIATION CORROSION. AREA OF CORROSION APPROXIMATELY 20MM (0.78IN) BY 5MM (0.196IN) AND 0.5MM (0.019IN) DEEP. AIRCRAFT IS A FLOATPLANE. 1H71 3R3 R A806 5E1 5 CP206 20030121002282003012100228EU 2003 1 21 AUS20021404 120021209G29104204001 PTU BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE HYDRAULIC SYSTEMFAULTY W K NONE KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 AUS (AUS) YELLOW HYDRAULIC SYSTEM POWER TRANSFER UNIT (PTU) FAULTY. 2H74 4F4 F A49EU E6NE 20030121002292003012100229SW 2003 1 21 AUS20021407 120021203G2460 CABLE MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MCAULY2D34C B2D34C214 GL DC POWER DISTRIBFAULTY W K NONE H ELECT. POWER LOSS-50 PC CLCLIMB 1 AUS (AUS) ALTERNATOR MAIN POWER CABLE FAULTY. CABLE WAS SPLICED CAUSING HIGH RESISTANCE. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 O 2A3 1E10 5 CP7EA 20030130000142003013000014EA 2003 1 30 AUS20021408 220021205G8530 GASKET CESSNA182 TR182 2072735CE LYC O540 O540L3C5 41532EA MCAULY2D34C B2D34C214 GL NR 1 CYLINDER LEAKING W O OTHER O OTHER CLCLIMB 1 AUS 842 (AUS) NR 1 CYLINDER LEAKING AT EXHAUST GASKET. DAMAGE TO COOLING FINS AND BAFFLE. 1H71 3O3 O 3A13 E295 5 CP7EA 20030121002302003012100230CE 2003 1 21 AUS20021412 120021209G5553513102057 BRACKET CESSNA 402C CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL VERTICAL STABILICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 513102057 (AUS) VERTICAL FIN FORWARD MOUNT BRACKET EXCESSIVELY CORRODED. 1L72 3O3 O A7CE E8CE 5 CP22EA 20030130000192003013000019CE 2003 1 30 AUS20021415 120021212G5710 STRUCTURE CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO MCAULY2A34C C2A34C204 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT WING COMPONENTS CRACKED. COMPONENTS AFFECTED INCLUDE: TRAILING EDGE RIB LOCATED AT STA 23.625. WING ROOT RT RIB ASSY LOCATED AT STA 23.625, WING SPAR REINFORCEMENT FITTING, WHEN CHANGING TRAILING EDGE RIB LOCATED AT WS 23.625, IT WAS NOTED THAT RIVETING HAD BEEN INCORRECTLY CARRIED OUT WITH 1/8 IN RIVETS IN 5/32 IN HOLES (SOME NOT ALL). WHEN SEALER WAS REMOVED FROM THE WING ROOT AT STA 23.625, THREE CRACKS WERE FOUND IN THE PART (RIB ASSEMBLY - WING ROOT). SUSPECT REPAIRS CARRIED OUT IN USA PRIOR TO AIRCRAFT ARRIVAL IN AUSTRALIA. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1H71 3O3 ONT3A13 E273 5 CP3EA 20030121002312003012100231SW 2003 1 21 AUS20021416 120021210G2820476822241 VALVE BELL 47 47G5A 1181034SW LYC O435 VO435B1A 41516EA AIRCRAFT FUEL DISEPARATED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS (AUS) AIRCRAFT SUFFERED INFLIGHT POWER LOSS. INVESTIGATION FOUND LH FUEL TANK CRASHWORTHY SYSTEM BREAKAWAY FUEL VALVE BEGINNING TOSEPARATE WHICH RESTRICTED FUEL FLOW FROM THE LH TANK. SUSPECT CAUSED BY UNKNOWN PERSON STANDING ON VALVE DURING MAINTENANCE ORPREFLIGHT. PERSONNEL/MAINTENANCE ERROR. 1G71 3O3 O 2H3 E279 20030121002322003012100232EU 2003 1 21 AUS20021420 120021207G5610D20543406 WINDSHIELD PPG D20543406 FOKKERF28 F28MK0100 4990807EU RROYCETAY TAY62015 04564NE FLIGHT COMPARTMECRACKED W K NONE O OTHER CRCRUISE 1 AUS 95317H8198 (AUS) RH WINDSHIELD CRACKED. SIGNS OF ELECTRICAL FAILURE. MANUFACTURERSUGGESTS PROBLEM COULD BE DUE TO MOISTURE INGRESS. SEE MDR02/1419 FOR FURTHER INFORMATION. 2L72 4F4 FRT E25NE 20030130000202003013000020EU 2003 1 30 AUS20021422 120021211G29109738114306 PRESSURE SWITCH PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYD SYSTEM FAILED W O OTHER KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 AUS (AUS) HYDRAULIC POWERPACK LOW PRESSURE SWITCH FAILED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030130000212003013000021 2003 1 30 AUS20021423 420021212G34189754421422 TRANSMITTER ROSEMOUNT PILATSPC12 PC12 7090550EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL STALL WARNING SEIZED W K NONE O OTHER ININSP/MAINT 1 AUS 0221 (AUS) RT ANGLE OF ATTACK TRANSMITTER SEIZED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030121002332003012100233SW 2003 1 21 AUS20021424 120021212G3242212033 BRAKE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL BRAKE FIRE W K NONE OB OTHER SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 AUS 2389AND5143 (AUS) LH MAIN LANDING GEAR BRAKE FIRE. BRAKES WERE BEING BURNED INFOLLOWING BRAKE REPLACEMENT. ON ARRIVING BACK AT THE MAINTENANCEFACILITY AND AFTER SHUTTING DOWN THE ENGINEERS SAW FLAMES FROMTHE LEFT HAND BRAKE PACK AND EXTINGUISHED THE FIRE. HYDRAULIC FLUID WAS LEAKING FROM ALL FOUR BRAKE ASSEMBLIES. DUE TO THE HEAT GENERATED FROM THREE HEAVY BRAKE APPLICATIONS THE SEALS IN THEBRAKES LET GO CAUSING THE BRAKES TO BECOME SPONGY AND ALLOWINGFLUID ONTO THE HOT DISCS WHICH THEN IGNITED AFTER SHUTDOWN. TWO TYRES WERE ALSO FLAT SPOTTED AND BURST ON TAXI BACK. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20030121002342003012100234NM 2003 1 21 AUS20021427 120021212G28225006003C PUMP BOEING767 767277 1385128NM GE CF6 CF680A 30025NE FUEL BOOST PUMP FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN FUEL TANK BOOST PUMPS (3OFF) DEFECTIVE. FOUND DURING INSPECTION IAW AAES ER B76-28-20-37 AND HAMILTON SUNDSTRAND SB5006003-28-2. 2L72 4F4 FRTA1NM E13NE 20030121002352003012100235NM 2003 1 21 AUS20021442 120021114G5310 DOUBLER BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUSELAGE MAIN, SCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD GALLEY DOORWAY FORWARD UPPER CORNER CRACKED AT FOUR FASTENER HOLES. ONE CRACK IN BEARSTRAP DOUBLER AND THREE CRACKS IN EXTRA INTERNAL DOUBLER. FOUND DURING EDDY CURRENT INSPECTION IAW AD/B737/24 AND EI 733-53-14R4. 2L72 4F4 FRTA16WE E21EU 20030121002362003012100236NM 2003 1 21 AUS20021443 120021122G5230 DOOR BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU CARGO/BAGGAGE DOCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD CARGO DOOR CRACKED IN FORWARD AND AFT LOWER CORNERS ASWELL AS THE LOWER CORNER OUTER T' CHORD. FOUND DURING EDDY CURRENT INSPECTION IAW AD/B737/142 AND EI 737-52-3. 2L72 4F4 FRTA16WE E21EU 20030210000602003021000060EA 2003 2 10 AUS20021446 220021215G855077852 HOUSING LYC IO540C4B5 PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA AMTR C8289 C8289 GL RECIPROCATING ENCRACKED W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 405 (AUS) ENGINE OIL FILTER HOUSING CRACKED FROM BOLT HOLE. SUSPECT CAUSEDBY OVERTORQUING. 1L72 3O3 O 1A10 1E4 5 NEXPP5N 20030210000612003021000061SO 2003 2 10 AUS20021450 120021218G7603455350 CABLE LYC O320D3G PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH74D 74DM EA POWER LEVER FAILED W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS (AUS) ENGINE THROTTLE CABLE FAILED. 1L71 3O3 O 2A13 E274 5 NP88614 20030210000622003021000062EU 2003 2 10 AUS20021455 120021223G2460L56225 FUSE BNORM BN2 BN2B20 1520302EU LYC O540 IO540K1B5 41532EA HARTZLHCC2Y HCC2YK2 GL DC POWER DISTRIBCORRODED W K NONE J WARNING INDICATION CRCRUISE 1 AUS (AUS) BUSBAR UNDERVOLTAGE FUSE F86 CORRODED AND BROKEN. 1H72 3O3 O A17EU 1E4 5 CP920 20030210000632003021000063EA 2003 2 10 AUS20021467 120020524G5751 ARM DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL AILERONS CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH OUTBOARD AILERON HINGE ARM CONTAINED EXFOLIATION CORROSION AROUND BOLT HOLE. 1H72 3T3 TRTA9EA E4EA 6 CP15EA 20030210000642003021000064NM 2003 2 10 AUS20021470 120021215G2612894120 FIRE DETECTOR BOEING727 7272J4 1384006NM PWA JT8 JT8D17 52049NE FIRE DETECTION FAULTY W K NONE EBNVIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS FALSE WARNING CLCLIMB 1 AUS (AUS) NO2 ENGINE FIRE WARNING ALERT. ENGINE WAS SHUTDOWN AND BOTTLESFIRED. FIRE WARNING LIGHT REMAINED ON' FOR A SHORT PERIOD, THEN WENT OUT. THE DETECTOR LIGHT REMAINED ON'. INVESTIGATION FOUND THE FIRE LOOP DETECTORS LOOSE AND DIRTY. 2L73 4F4 FRTA3WE E2EA 20030212000102003021200010EA 2003 2 12 AUS20021471 220021222G7414M3548 SHAFT SLICK PIPER PA28 PA28181 7102807SO LYC O320 O320* 41508EA SNSNCH76E 76EM8 EA MAGNETO BROKEN W O OTHER O OTHER NRNOT REPORTED 1 AUS 98040595 (AUS) MAGNETO ROTOR SHAFT BROKEN AT THE PRIMARY GEAR & CAM FORK SECTION. 1L71 3O3 O 2A13 E274 5 NP4EA 20030210000652003021000065GL 2003 2 10 AUS20021482 320021214G6114660709201 HUB ROTOL R321482F8 SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL PROPELLER HUB SECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1399 DR1DRS139681 (AUS) FOLLOWING PILOT REPORTS OF PROPELLER VIBRATION, AN ULTRASONIC EXAMINATION WAS CARRIED OUT ON THE PROPELLER HUB. ONE CRACK LIKEDEFECT WAS DETECTED ADJACENT TO A THREADED INSERT HOLE. THE CRACK WAS LOCATED AT A DEPTH OF 13MM (0.512IN) AND HAD A LENGTH OFAPPROXIMATELY 13MM (0.512IN). 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20030210000662003021000066NM 2003 2 10 AUS20021484 120021230G3240DSC252A40230 HOSE DHAV DHC8 DHC8202 2809007NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF23 NE LANDING GEAR BRARUPTURED W KE NONE ENGINE SHUTDOWN K FLUID LOSS NRNOT REPORTED 1 AUS (AUS) NO3 BRAKE PACK HYDRAULIC HOSE RUPTURED. LOSS OF NO2 SYSTEMHYDRAULIC FLUID. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020128000642002012800064CE 2002 1 28 B3OR20020001 120020122G291099121943 SWITCH CESSNA500 550 2076604CE HYD SYSTEM STUCK B B3ORD RETURN TO BLOCK P NO WARNING INDICATION TXTAXI/GRND HDL 1 SW0326494550 130 5500605 A GROUND RUN WAS PERFORMED ON THE AIRCRAFT PRIOR TO A SCHEDULED LAUNCH.UPON ENGINE SHUTDOWN THE MECHANIC NOTICED THAT THE "HYDRAULIC PRESSURE LOW" LIGHT ON THE RIGHT HAND ENGINE DID NOT ILLUMINATE.DURING TROUBLE-SHOOTING, IT WAS DICOVERED THAT THE RIGHT HAND HYDRAULIC FLOW SWITCH WAS STICKING, AND CAUSING AN INTERMITTENT INDICATION ON THE CAUTION PANEL.THE FLOW SWITCH WAS REPLACED AND THE AIRCRAFT PUT BACK INTO SERVICE. 1L72 4F A22CE 20020205000472002020500047CE 2002 2 5 B3OR20020002 120020201G7170555501125 DRAIN VALVE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE CRACKED B B3ORK NONE O OTHER ININSP/MAINT 1 SW0326494 5500605 DURING A PHASE 1 & 2 INSPECTION, THE ENGINES WERE DE-COWLED FOR THE OIL FILTER CLEANING ITEM. A MECHANIC NOTICED SOME FUEL RESIDUE AROUND THE FUEL DRAIN "EPA" CAN. UPON INSPECTION THE CAN WAS FOUND TO HAVE A MOUNTING BRACKET BROKEN OFF OF IT. THE BREAK WAS WHERE THE BRACKET WAS WELDED TO THE CAN AND IT ACTUALLY WAS THE CAN ITSELF THAT HAD BROKEN, NOT THE BRACKET. THE OPPOSITE ENGINE WAS INSPECTED AND IT HAD A SIMILAR CRACK. IN RESEARCHING THIS PART, IT WAS FOUND THAT IN THE PAST YEAR, THIS PART HAD BEEN REPLACED ON 6 OTHER ENGINES FOR THE SAME REASON AT THIS LOCATION. THIS DEFINITELY SEEMS TO BE AN ITEM THAT DESERVES MORE ATTENTION WHEN INSPECTING THE ENGINES. 1L72 4F4 F A22CE E1NE 20020208000272002020800027CE 2002 2 8 B3OR20020003 120020205G3242215286 STATOR CESSNA500 550 2076604CE BRAKE CRACKED B B3ORK NONE O OTHER ININSP/MAINT 1 SW0326494 5500605 ACFT WAS INDUCTED INTO A 1 & 2 AND 5 A&B INSPECTION. DURING INSPECTION DISCOVERED THE LT MLG BRAKE ASSY HAD A CRACK IN ONE OF THE STATOR DISCS. BRAKE ASSY WAS RECEIVED FROM OUR PARTS DEPT HAD ABNORMAL WEAR ON THE WEAR PLATES & LININGS. BRAKE ASSY WAS REPAIRED AT AN OVERHAUL SHOP FOR A DAMAGED HOUSING. HOUSING WAS NOT STAMPED WITH S/B, THE FORM 8130 HAS NO RECORD OF LANDINGS/TIME IN SERVICE OF BRAKE ASSY OR A RECORD OF COMPLIANCE WITH BF GOODRICH S/B 2-1528-32-2, LANDING GEAR BRAKE ASSEMBLY POSSIBLE CRACKED STATOR DISKS. 1L72 4F A22CE 20020313000632002031300063NE 2002 3 13 B3OR20020005 220020202G7270310863201 DUCT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENG BYPASS CRACKED B B3ORK NONE P NO WARNING INDICATION ININSP/MAINT 1 SW03264948237 1390 5500605 PCE71394 AIRCRAFT WAS INDUCTED INTO A PHASE1,2,5A & B INSPECTION.DURING THE INSPECTION OF THE NUMBER 2 ENGINE, THE FRONT BY-PASS DUCT WAS FOUND CRACKED AND A PIECE MISSING FROM IT. THE DUCT WAS REMOVED AND REPLACED WITH A SERVICEABLE DUCT. 1L72 4F4 F A22CE E1NE 20020719001422002071900142EU 2002 7 19 B3OR20020010 120020528G6220707A33640046 FREQ ADAPTER SNIAS 350 AS350B2 8680813EU MAIN ROTOR CORRODED B B3ORK NONE O OTHER ININSP/MAINT 1 SW035204X985 3099 DURING A 500 HOUR INSPECTION, THE M/R HEAD WAS DISSASSEMBLED. THE FREQUENCY ADAPTERS WERE REMOVED FOR INSPECTION. ATTEMPTS TO REMOVE THE BEARING BY PUSHING OR TAPPING LIGHTLY FAILED. THE DECISION WAS MADE TO CHANGE THE ADAPTER AND BEARING. THE BEARING WAS FINALLY REMOVED BY CUTTING THE FREQUENCY ADAPTER IN HALF. UPON REMOVAL OF THE BEARING, CORROSION WAS FOUND ON ALL OF THE MATING SURFACES. ALL THREE ADAPTERS WERE IN THE SAME CONDITION. 1G71 3U H9EU 20020813000732002081300073EU 2002 8 13 B3OR20020011 120020710G6420355A09103601 BEARING SNIAS 350 AS350B2 8680813EU TAIL ROTOR CRACKED B U0SMK NONE O OTHER ININSP/MAINT 1 SW035204J483 3118 THE TAIL ROTOR WAS REMOVED FOR THE 500 HOUR INSPECTION AND DURING INSPECTION, THE LAMINATED HALF BEARINGS WERE FOUND TO BE CRACKED. THE RUBBER IN THE BEARINGS WAS SPLIT BEYOND LIMITS. IT IS TO BE NOTED THAT THIS AIRCRAFT SPENDS MOST OF IT'S TIME OUTSIDE ON THE RAMP AND THE DETERIORATION IS PROBABLY DUE TO WEATHER EFFECTS. 1G71 3U H9EU 20020813000772002081300077EU 2002 8 13 B3OR20020014 120020529G6310350A35110205 HOUSING SNIAS 350 AS350B2 8680813EU MGB COUPLING WORN B U0SMK NONE O OTHER ININSP/MAINT 1 SW035204X986 3099 THE ENGINE TO MAIN GEAR BOX GIMBAL JOINT , WHICH HOUSES THE DRIVE SHAFT, HAD EXCESSIVE PLAY. UPON INSPECTION AT THE 500 HOUR, THE GIMBAL RING AND HOUSING WERE MEASURED AND FOUND TO BE OUT OF LIMITS AT THE GIMBAL PINS. A TECH REP WAS CONTACTED AND SUGGESTED THAT WE LOOK AT THE LEFT FOWARD MAIN GEAR BOX CROSSBEAM SUPPORT SHOCK MOUNT FOR THE CAUSE OF THIS PROBLEM. HE WAS CORRECT. THE LAMINATED MOUNT WAS DETERIORATED. WHEN THE CROSSBEAM WAS REMOVED, FOUND THE LAMINATED MOUNT HAD BEEN MOVING AND CAUSED CORROSION ON THE BEAM. THE RUBBER PORTION OF THE MOUNT APPEARS TO HAVE BEEN DAMAGED BY OILS. 1G71 3U H9EU 20030707001982003070700198EU 2003 7 7 B3OR20020019 120020906G2170900A4031 EVAPORATOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ZONE 100 BROKEN B B3ORK NONE O OTHER ININSP/MAINT 1 SW035204X 3099 9570 CRACKED HOUSINGS THAT CAUSE BLOWER MOTORS TO BECOME DISLODGED IN THE HOUSING, CAUSING BLOWER CAGES TO RUB ON THE HOUSING AND HOUSINGS TO BREAK APART. EVENTUAL FAILURE OF ENTIRE ASSEMBLY AND BLOWER MOTOR RENDERING THE AIRCONDITIONING SYSTEM INOPERATIVE. ONE OF HOUSING PARTS OR BLOWER CAGE PIECES COULD FALL OFF AND BECOME LODGED IN LT TAIL ROTOR CONTROL PEDDLES. THIS IS POSSIBLE DUE TO LOCATION OF EVAPORATOR ASSY, IT IS ALMOST DIRECTLY OVER TAIL ROTOR CONTROL PEDDLES ON L/H SIDE OF COCKPIT. THIS HAS TO BE PAID EVERYTIME ONE BREAKS BECAUSE UNITS ARE NOT FIELD REPAIRABLE, THEY HAVE TO BE RETURNED TO MANUFACTURER FOR REPAIR OR REPLACEMENT. WE WOULD LIKE TO RECOMEND THAT EVAPORATOR ASSY. 1G71 3U3 U H9EU E19EU 20030707001992003070700199CE 2003 7 7 B3OR20020020 120021009G3230NAS464P4A10 BOLT CESSNA CESSNA500 550 2076604CE TORQUE TUBE BROKEN B B3ORA UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 SW03264948533 NA 5500605 AFTER TAKEOFF, PILOT NOTICED NOISE IN NOSE AREA, WIND NOISE IN COCKPIT. CREW WAS ABLE TO SEE NOSE GEAR DOORS WERE OPEN AND STEADY. REDUCED SPEED AND LOWERED LANDING GEAR WITH NO PROBLEMS. DOORS REMAINED OPEN AND STEADY. A/C LANDED WITHOUT MISHAP. FOUND THAT BOLT HAD BROKEN THAT HOLDS DOOR BELLCRANK/TORQUE TUBE IN POSITION. BOLT IS AT PIVOT POINT ON RT SIDE OF A/C. WHEN TORQUE TUBE WAS REMOVED, CRACK WAS FOUND BUT DETERMINED THAT THIS WAS NOT RELATED AND HAD BEEN THERE A LONG TIME. BOLT FOUND BREAK WAS TYPICAL OF OVER TORQUEING. BREAK WAS AT FIRST THREAD, HAD NO STRESS INDICATIONS. BOLT IS CLOSE TOLERANCE BOLT, NORMALLY HAS SHEARING LOAD IN INSTALLATION. BOLT WAS NOT SHEARED. REPLACED BOTH BOLTS AND TORQU1L72 4F A22CE 20030529000682003052900068EU 2003 5 29 BAQA081077 120020927G6330L633M2001105 MOUNT UROCOPEC135 EC135T1 5620026EU MAIN ROTOR DAMAGED H BAQAO OTHER O OTHER NRNOT REPORTED 1 FS01575ME1655 0157 TRANSMISSION MOUNT BAD. REPLACED WITH SERVICEABLE UNIT. 1G72 3U H88EU 20021217000702002121700070 2002 12 17 BAQA081596 420021209G34214021541791 INDICATOR BOLKMS117 BK117A1 5626010EU ART HORIZON CONTAMINATED H BAQAK NONE O OTHER ININSP/MAINT 1 FS01955ME2118 7243 ARTIFICIAL HORIZON INDICATOR GLASS FOGGED. REPLACED WITH SERVICEABLE UNIT. 1G72 3U H13EU 20030103000112003010300011EU 2003 1 3 BAQA082149 120021220G6240117945641 INDICATOR BOLKMS117 BK117A3 5626015EU MAST MOMENT MALFUNCTIONED H BAQAK NONE L NO TEST ININSP/MAINT 1 FS01952CJ574 7052 MAST MOMENT INDICATOR POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE UNIT. 1G72 3U H13EU 20021023001292002102300129CE 2002 10 23 BN001 120021017G531150420013944 STRAP BEECH BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE FRAME CRACKED C K NONE O OTHER ININSP/MAINT 1 WP197232R7917 BL69 UPON REMOVAL OF AIRCRAFT INTERIOR TO TROUBLESHOOT WIRING PROBLEMS, TWO STRAP ASSEMBLIES ON THE RT SIDE OF THE FUSELAGE AT F.S. 227.0 AND 246.0, BUTTOCK LINE 119.0 WERE FOUND COMPLETELY CRACKED THROUGH. THE STRAP ASSEMBLY AT F.S. 246.0. THESE AREAS WOULD NOT NORMALLY BE INSPECTED UNTIL 10,000 CYCLES. RAYTHEON HAS CONFIRMED ONE OTHER SIMILAR INCIDENT ON THE BL MODEL AIRCRAFT EQUIPPED WITH A CARGO DOOR. THERE IS NO EVIDENCE OF PREVIOUS DAMAGE OR ABNORMAL OPERATION IN THE AIRCRAFT LOGBOOK. 1L72 4T4 T A24CE E4EA 20020910001642002091000164SO 2002 9 10 C41346022160 120020909G3320 BULB GULSTMG1159 GIV 3980115SO CABIN HEADLINER DAMAGED B K NONE L NO TEST ININSP/MAINT 1 SO11104AR 1346 OUT OF 8 BAD CABIN LIGHT BULBS, THREE WERE BURNT THROUGH OR SHOWING SIGNS OF BURNING THROUGH THE BULB CASE. TECHNICIAN STATED AN OPERATING VOLTAGE OF 600 VAC AND CONSIDERS THIS A SIGNIFICANT PROBLEM. 2L72 4F RTA12EA 20020214000152002021400015CE 2002 2 14 CA020102002 120020102G3240 STATOR BFGOODRICH 215286 CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE BRAKE ASSY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1411 (CAN) DISASSEMBLED BRAKE UNIT AND FOUND STATOR DISC P/N 133-89302 CHG "B" BROKEN. (SEE ATTACHED PHOTO'S). 1L72 4F4 F A22CE E1NE 20020214000512002021400051NM 2002 2 14 CA020104006 120020102G3213 COLLAR PIPER PA60 PA60600 7106001NM LYC O540 IO540K1F5 41532EA MLG CRACKED W O OTHER R PARTIAL RPM/PWR LOSS LDLANDING 1 CA (CAN) PILOT LANDED NORMAL: WHILE ROLLING ON RUNWAY AIRCRAF WENT RIGHT AND PILOT HAS A HARD TIME CONTROLLING AIRCRAFT BUT MANAGED TO GET AIRCRAFT STOPPED. SHUT DOWN ENGINES AND GOT OUT TO INVESTIGATE; NOTICED RIGHT MAIN GEAR TIRE 90 DEGREES FROM NORMAL WITH HELP GOT AIRCRAFT TO TARMAC.UNABLE TO GIVE PART NUMBER AS THERE IS NO FURTHER BREAKDOWN IN PARTS MANUAL. 1M72 3O3 ORTA17WE 1E4 20020215000172002021500017SW 2002 2 15 CA020104019 120020104G53100354130 TUBE MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MCAULY2D34C B2D34C212 GL FUSELAGE MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN INTERIOR OF THE A/C WAS REMOVED IT WAS NOTICED THAT THE TUBULAR STRUCTURE WELDED JOINT ON THE LT SIDE JUST FWD OF SPAR ON DIAGONAL BRACE BELOW THE FRONT OF REAR WINDOW IS MISSING A WELD. IN THE SAME AREA NOTICED A CLUSTER GUSSETS WITH INCOMPLETE WELDS. 1L71 3O3 O 2A3 1E10 5 CP7EA 20020215000732002021500073CE 2002 2 15 CA020111001 120020110G32601003810061 SWITCH BEECH 99 99 1154002CE PWA PT6 PT6A28 EA NLG INTERMITTENT W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) PILOT SELECTED GEAR DOWN AND GOT NO NOSE GREEN LIGHT. PILOT WAS READY TO DO A EMERGENCY EXTENTION WHEN THE GREEN LIGHT CAME ON. MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. 1L72 3T4 T A14CE E4EA 20020215000952002021500095SW 2002 2 15 CA020114002 120020108G6720206010793101 PITCH LINK BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL TAIL ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUR CRACKS FOUND TWO ON EACH END OF PITCH LINK SIMILAR TO THOSE DESCRIBED IN ASB 206-87-39 AND OSN 206-99-36. 1G71 3U3 U H2SW E4CE 20020228000032002022800003 2002 2 28 CA020115001 420020109G3425 SYMBOL GENERATORBENDIX 0660402111 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL INTERNAL INOPERATIVE W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA 4481 (CAN) WHEN A/C POWERED UP, LOWER PILOT'S EFIS DISPLAY REMAINED BLANK. LOWER CO-PILOTS EFIS DISPLAY SWITCHED FOR TROUBLE SHOOTING. DISPLAY ALSO REMAINED BLANK. WHEN DISPLAY RETURNED TO IT'S ORIG POSSITION, IT REMAINEDBLANK AS WELL. IT DETERMINED THROUGH FURTHER TROUBLE SHOOTING THAT PILOT'S SG-465 SYMBOL GEN P/N 066-04021-11-11, S/N 4481, DEFECTIVE. IT CAUSED INTERNAL DAMAGE TO LOWER PILOT'S EFIS DISPLAY, P/N 066-03125-2500, S/N 3486. WHEN CO-PILOT'S EFIS DISPLAY INST IN POSSITION, IT TOO DAMAGED BY DEFECTIVE SYMBOL GEN. WHEN EFIS DISPLAY RETURNED TO IT'S ORIG POSSITION, IT IN TURN DAMAGED CO-PILOTS SYMBOL GEN,S/N 3354. PI LOT'S SYMBOL GEN&LOWER EFIS DISPLAY, AND 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020215001032002021500103CE 2002 2 15 CA020116002 120020104G271005341251 BUSHING CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA BELLCRANK WORN W K NONE O OTHER ININSP/MAINT 1 CA 13746 (CAN) BUSHING WAS FOUND TO BE ROTATING IN BELLCRANK ASSEMBLY. 1H71 3O3 ONT3A12 E274 20020215001042002021500104CE 2002 2 15 CA020116004 120020104G5511053200198 SPAR CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK WAS FOUND DURING A SCHEDULED INSPECTION OF THE AIRCRAFT, IN THE AREA OF THE FRONT SPAR OF THE STABILIZER. AT THE LIGHTENING HOLE BETWEEN THE TWO NOSE RIBS. 1H71 3O3 ONT3A12 E274 20020215001052002021500105SW 2002 2 15 CA020116005 120020108G3220AN5C32A BOLT AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE TAIL WHEEL WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE ANNUAL INSPECTION MAINTENANCE REMOVED BOLT AN5C-32A, AS PER INSPECTION SCHEDULE. THEY FOUND THAT THE BOLT WAS BADLY WORN AND THAT THREADS WERE DAMAGED. 1L71 3T4 TNCA19SW E26NE 20020215001072002021500107SO 2002 2 15 CA020116008 120020105G324409231500 TIRE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL NLG PUNCTURED W O OTHER O OTHER LDLANDING 1 CA (CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS. AIRCRAFT WAS BROUGHT TO A STOP ON RUNWAY, WHERE IT WAS TOWED TO MAINTENANCE FACILITY. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020215001082002021500108SO 2002 2 15 CA020117001 120020114G32440923150 TIRE PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE NLG PUNCTURED W O OTHER O OTHER LDLANDING 1 CA (CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS. 1L72 3T4 TRTA8EA E4EA 20020219000702002021900070NE 2002 2 19 CA020117012 220020111G7412 EXCITER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL IGNITION SYSTEM FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) PILOT WENT TO START ENGINE AND HAD NO LIGHT OFF.TRIED TWICE TO START ENGINE AND HAD NO LIGHT OFF. IGNITION EXCITOR BOX WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.NOTE: THIS IS TYPICAL FOR PILATUS IGNITOR BOX. THE SAME BOX WILL LAST 2-3 TIMES LONGER ON A BEECH 99 OR A100. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020219001242002021900124EU 2002 2 19 CA020117016 120020102G2700 CONTROL UNIT AIRBUS330 A330243 3930330EU RROYCERB211 RB211TRENT77 NE COCKPIT MALFUNCTIONED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT RETURNED BACK TO GATE AFTER PUSH BACK. NO ECAM INDICATION OF RUDDER TRIM AND NO PEDESTAL INDICATION. TROUBLESHOOTING WAS CARRIED OUT PER CATTS , 2L72 4F4 FRTA46NM E39NE 20020219001312002021900131EU 2002 2 19 CA020118006 120020117G5230 HANDLE AIRBUS320 A320231 3930325EU IAE V2500 V2500A1 NE CARGO DOOR MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 2487324873 (CAN) AT APPRXIMATELY 10,000 FT ALTITUDE THE FWD CARGO DOOR INDICATED UNSAFE ON ECAM. THE AIRCRAFT DIVERTED AND WAS INSPECTED BY A COMPANY ACA. THE DOOR HANDLE WAS FOUND TO BE OUT OF THE DETENT BY ABOUT 1/4 OF AN INCH. THE HANDLE ASSY AND DOOR LOCKING MECHANISM WAS INSPECTED AND FOUND SERVICEABLE. THE INDICATING SYSTEM WAS CHECKED AND FOUND SERVICEABLE. AIRBUS HAS BEEN ADVISED AND IS UNDER INVESTAGATION. 2L72 4F4 FRTA28NM E311NE 20020219001332002021900133SW 2002 2 19 CA020118009 120020110G79102765030101 OIL TANK FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AN OIL LEAK WAS NOTED DURING A BASE INSPECTION. ON INVESTIGATION A .75 INCH LONG CRACK WAS FOUND IN THE SIDE WALL OF THE OIL TANK BETWEEN THE FILLER NECK BOSS AND THE SIGHT GAUGE BOSS. THE TWO BOSSES ARE CLOSE TO EACH OTHER ON THE SIDE OF THE TANK. THE CRACK FOLLOWED THE CURVE OF THE SIGHT GAUGE BOSS WELD BAND JUST OUTSIDE OF THE EDGE OF THE WELD. THE TANK WAS REMOVED REPAIRED AND REINSTALLED. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20020219001342002021900134SO 2002 2 19 CA020118010 120020102G79305581802 TRANSDUCER PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA OIL PRESSURE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) OIL PRESSURE GAUGE UNRELIABLE ON RIGHT ENGINE. AIRCRAFT ON FLIGHT FROM YXU TO YTZ, WHEN RIGHT ENGINE OIL PRESSURE GAUGE STARTED TO INDICATE OIL PRESSURE LOSS. ALL OTHER ENGINE PARAMETERS NORMAL. PRECAUTIONARY ENGINE SHUTDOWN WAS CARRIED OUT AND AIRCRAFT CONTINUED TO YTZ. TROUBLESHOOTING CARRIED OUT IAW PT6 MM AND OIL PRESSURE TRANSDUCER WASFOUND UNSERVICEABLE.OIL PRESSURE TRANSMITTER REPLACED AND ENGINE RUN C/W. ALL INDICATION NORMAL. 1L72 3T4 T A8EA E4EA 20020219001352002021900135CE 2002 2 19 CA020118011 120020108G273126612151 ACTUATOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL ELEVATOR TRIM FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AFTER TAKEOFF FROM YHM, THE AIRCRAFT LOST ELEVATOR TRIM ELECTRICAL AND MANUAL CONTROL AND THE AUTOPILOT FAILED. THE AIRCRAFT RETURNED TO THE AIRPORT. MAINTENANCE INVESTIGAITON FOUND ONE OF THE TWO RODS ON THE LT ELEVATOR TRIM ACTUATOR WAS BINDING A LITTLE WHEN THE ELEVATOR WAS IN THE NEUTRAL POSITION, BUT FREE WHEN THE ELEVATOR WAS DEFLECTED UP OR DOWN. THE ONE ROD WAS ADJUSTED 1/14 OF A TURN - SYSTEM TESTED AND FOUND TO BE FREE THROUGH THE RANGE OF TRAVEL OF THE ELEVATOR.THE ACTUATOR HAD RECENTLY BEEN REMOVED FOR OVERHAULED AND REINSTALLED. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020219001362002021900136SW 2002 2 19 CA020121001 120020117G531171470101L FRAME BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA FUSELAGE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) -TUBE FOUND BROKEN THROUGH NEAR WELD, AT FWD ENDOF LT LANDING GEAR FITTING. 1H71 3O3 O A21CE E286 20020219001372002021900137NM 2002 2 19 CA020121003 120020105G2781Y35A TRANSDUCER BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE FLAP / SLATS FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA (CAN) EICAS MESSAGE FOR FLAP / SLAT ELEC. DISPLAYED.REPLACED THE ROTARY DIFFERENTIAL TRANSDUCER M603 AND ADJUSTED AS PER AMM 27-51-26-424-020. FOUND SERVICEABLE. 2L72 4F4 FRTA1NM E3NE 20020219001382002021900138EU 2002 2 19 CA020121006 120020102G3260 SENSOR AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AIR TURN BACK TO MONTREAL DUE TO MAIN LANDING DOOR NOT SHOWING PROPERLY LATCHED. AFTER VERIFICATION, FOUND TO BE THE SENSORS CONTAMINATED WITH GREASE AFTER AN OVERNIGHT CHECK (OVERGREASED).SENSORS CLEANED, GEAR SWING COMPLETED, SYSTEMM FOUND SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000012002022000001EA 2002 2 20 CA020121011 220020107G7230 COMPRESSOR PWA PT6 PT6A20 52043EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE SENT FOR INVESTIGATION & REPAIR AFTER IT FOUND THAT ENGINE MAKING RUBBING NOISE COMING FROM COMPRESSOR SECTION WHILE SCHEDULE HSI BEING PERFORMED. THE COMPRESSOR HAD SUFFERED EXTENSIVE DAMAGE. DAMAGE STARTED WITH RUBBING AT 1ST STAGE COMPRESSOR STATOR & DISK SPACER&CONTINUED DOWNSTREAM TO IMPELLER. 1ST & 2ND STAGE COMPRESSOR SPACERS HAD RUBBING MARKS ON 180 DEG. OF SURFACE AREA. 3RD STAGE COMPRESSOR SPACER HAD SEVERE DAMAGE TO FRONT RIM. IT HAD HEAVY RUBBING MARKS & MISSING SUBSTANTIAL AMOUNT OF MATERIAL. COMPRESSOR 3RD STAGE BLADES & STATOR HAD EXTENSIVE DAMAGE. IMPELLER & IMPELLER HOUSING HAD RECD SECONDARY IMPACT DAMAGE FROM DEBRIS FROM THE MATERIAL LOST FROM 3D STAGE COMPRESSOR SPAC 3 T E4EA 20020220000032002022000003EA 2002 2 20 CA020122001 220020114G7414 GEAR BENDIX ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA MAGNETO STRIPPED W E ENGINE SHUTDOWN ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CA K049802ER (CAN) THE AIRCRAFT RAN ROUGH ON L/H MAGNETO (APPROXIMATELY 200 RPM MAGNETO DROP). LT MAG WAS REMOVED AND FOUND TO HAVE 8-10 TEETH MISSING FROM GEAR (NYLON) WHEN VIEWED THROUGH TIMING WINDOW. MAG WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1G71 3O3 O H10WE E274 20020220000042002022000004SO 2002 2 20 CA020122002 120020116G2910 HYDRAULIC SYSTEM PIPER PA44 PA44180 7104402SO MAIN SYSTEM CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING THE TRAINING FLIGHT THE PILOT NOTICED THE GEAR UNSAFE LIGHT WAS STILL ILLUMINATED. NOTICED THE NOSE LANDING GEAR ONLY PARTIALLY RETRACTED, HE SELECTED GEAR DOWN AND THE 3 GEAR DOWN INDICATION LIGHTS ILLUMINATED WITH GEAR UNSAFE LIGHT EXTINGUISHED. PILOT LANDED THE AIRCRAFT WITHOUT INCIDENT. A VISUAL CHECK OF THE HYDRAULIC FLUID LEVEL IN THE UNDERCARRIAGE HYDRAULIC PUMP RESERVOIR SHOWED THAT THE QUANTITY LEVEL BELOW LIMITS AND THE FLUID WAS VERY DARK IN COLOUR. THE HYDRAULIC PUMP AND MOTOR ASSEMBLY WERE DRAINED, FLUSHED WITH CLEAN NEW FLUID. THE HYDRAULIC PUMP AND MOTOR ASSEMBLY WERE REINSTALLED AND FLUID LEVEL TOPPED UP AND TEST CHECKED WITHOUT INCIDENT AND AIRCRAFT RETURNED TO SERVICE. 1L72 3O A19S0 20020220000062002022000006WP 2002 2 20 CA020122005 120020121G6310C1683 RETAINER ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA M/R CLUTCH CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CLUTCH WAS REMOVED FROM SERVICE DUE TO OIL LEAK.INVESTIGATION REVEALED THAT SEAL RETAINER PLATE EAR APPEARRED TO BE CRACKED. RETAINER WAS REMOVED AND EAR WAS FOUND TO BE NO LONGER ATTACHED TO RETAINER PLATE.NO OTHER CRACKS COULD BE FOUND IN RETAINER PLATE OR ON OPPOSITE RETAINER. RETAINER PLATE WILL BE REPLACED WITH NEW. 1G71 3O3 O H11NM E295 20020220000072002022000007WP 2002 2 20 CA020122006 120020121G6310C1883 SPRAG CLUTCH ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAIN ROTOR CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CLUTCH WAS REMOVED FROM SERVICE DUE TO AN OIL LEAK. UPON DISSASSEMBLY THE SPRAG WAS INSPECTED AND THE CAGE FOUND CRACKED.THE CRACK WAS BETWEEN TWO WINDOWS RUNNING FROM THE CORNERS. SPRAG WILL BE REPLACED WITH NEW. 1G71 3O3 O H11NM E295 20020220000082002022000008EA 2002 2 20 CA020123001 120020123G2897601R571351 WIRE HARNESS CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE WING FUEL CELL CHAFED W O OTHER N FALSE WARNING CRCRUISE 1 CA (CAN) WHILE IN FLIGHT, CREW REPORTED THAT THE LEFT FUEL QTY INDICATION AND TOTAL FUEL QTY INDICATION WENT TO DASHES. FUEL QTY INDICATION WAS DEFERRED PER MEL AND MLIS WRE USED TO CHECK FUEL QUANTITY BEFORE EACH FLIGHT. UPON FURTHER INVESTIGATION, MAINTENANCE DISCOVERED THAT THE WIRE HARNESS FOR THE NR 3 FUEL QTY PROBE WAS CHAFING ON THE FUEL DAM LOCATED INSIDE THE LEFT TANK. INSPECTION OF THE RT TANK ALSO DISCOVERED THAT THIS SAME CHAFING WAS PRESENT. BOTH LEFT AND RIGHT HARNESSES WERE REPLACED. THE HARNESS WAS REPOSITIONED SO AS NOT TO COME IN CONTACT WITH THE FUEL TANK. 2L72 4F4 FRTA21EA E15NE 20020220000092002022000009SO 2002 2 20 CA020123002 120020122G3245 TIRE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NLG PUNCTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILOTS VISUALLY NOTICED THAT THE NOSE WHEEL TIRE WAS FLAT AFTER THE AIRCRAFT WAS LANDED AND THE ENGINES WERE SHUT-DOWN. 1L72 3O3 O A20SO E14EA 20020220000102002022000010EA 2002 2 20 CA020123003 220020116G7210 GEARBOX BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA REDUCTION GEAR CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 14924 (CAN) IN CRUISE FLIGHT THE PILOT THE PILOT NOTED THE C-BOX CHIP LIGHT FLICKER FAINTLY FOLLOWED SHORTLY BY THE C-BOX OIL PRESSURE CAUTION LIGHT ILLUMINATING.C-BOX OIL PRESSURE WAS OBSERVED DROPPING AND AN UNSCHEDULED BUT NORMAL LANDING PROCEDURE WAS CARRIED OUT. AFTER LANDING THE C-BOX OIL PRESSURE WAS OBSERVED TO DROP TO ZERO AND THE ENGINES WERE SHUT DOWN. NO EXTERNAL LEAKS WERE FOUND. AN ACCUMULATION OF METAL WAS FOUND ON THE REDUCTION (C-BOX) CHIP DETECTOR AND IN THE REDUCTION GEARBOX OIL FILTER. 1G71 4U4 U H4SW E22EA 20020220000112002022000011NE 2002 2 20 CA020123004 120020122G2913 SHAFT ABEX SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30 03013GL HYD PUMP SHEARED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 195853 (CAN) INFLIGHT INDICATION OF PRESSURE LOSS NR 1 SYSTEM. INSPECTION REVEALED PUMP SHAFT SHEARED AND BRASS PARTICLES IN FILTER. 1G72 3U3 U H1NE E1GL 20020220000122002022000012EA 2002 2 20 CA020124002 120020123G3040M7A16 WIRE DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA WINDSHIELD WIPERSHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) WIRE INSULATION WAS FOUND BURNED AND APPEARED TO HAVE SHORTED OUT ON OVERHEAD SWITCH PANEL IN FLIGHT COMPARTMENT, WHICH CAUSED ELECTRICAL BURNING ODOR IN THE FLIGHT DECK. 1H72 3T3 TRTA9EA E4EA 20020220000142002022000014EA 2002 2 20 CA020124004 120020115G21618161014 CONTROLLER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE CABIN TEMP FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) SMOKE IN CABIN DUE TO RT PACK OVER TEMP IN AUTO, REVERTED TO MANUAL TEMPERATURE CONTROL. FOUND TO BE THE TEMP CONTROLLER AT FAULT. REPLACED THE TEMPERATURE CONTROLLER. 2L72 4F4 FRTA21EA E15NE 20020220000152002022000015EA 2002 2 20 CA020124005 120020114G32347179015 CONTROL HANDLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE MLG FAILED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) GEAR DISAGREE LIGHT ON APPROACH INTO WASHINGTON. CREW CONDUCTED A GO AROUND THEN CARRIED OUT A MANUAL EXTENSION. AFTER LANDING THE NOSE STEERING WAS INOPERATIVE. FOUND TO BE THE LANDING CONTROL LEVER AT FAULT. REPLACED LANDNG CONTROL LEVER, OPERATIONAL CHECK CARRIED OUT, SYSTEM FOUND SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020220000162002022000016NM 2002 2 20 CA020124006 120020106G2821AC92272080D2A FILTER BOEING767 767333 1385301NM GE CF6 CF680C2B6F 30025NE FUEL SYSTEM FAILED W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) FLIGHT CREW REPORT THAT THEY HAD A FUEL FILTER LIGHT ON EICAS FOR BOTH ENGINES. FOUND TO BE FINE MANUFACTURING DEBRIS (NEW AIRCRAFT). REPLACED TWO FILTERS AND DRAIN ALL RESERVOIRS, GROUND RUN AND LEAK CHECK CARRIED OUT. FLEET MANAGEMENT REQUEST TO HAVE BOTH FILTERS REPLACED AFTER 5 FLIGHT CYCLES. 2L72 4F4 FRTA1NM E13NE 20020220000172002022000017NM 2002 2 20 CA020124007 120020111G2910AE83580K COUPLING BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE HYD LINE BROKEN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF FROM TORONTO AS FLAPS WERE RETRACTING FROM 1 TO UP, CENTRE HYDRAULIC QUANTITY AND C HYDRAULIC SYSTEM PRESSURE DISPLAYED EICAS MESSAGES / CAUTIONS AND HYDRAULIC PRESS LIGHTS ANNUNCIATED, THE AIRCRAFT RETURNED TO TORONTO USING ALTERNATE FLAPS/GEAR EXTENSION.FOUND AIR DRIVEN PUMP PRESSURE LINE COUPLING BROKEN.REPLACED ADP PRESSURE LINE COUPLING, CASE DRAIN FILTER CHECKED FOR CONTAMINATION AND FOUND CLEAN. SYSTEM LEAK CHECKED AND OPERATIONAL CHECK ALSO CARRIED OUT, AIRCRAFT FOUND SERVICEABLE. 2L72 4F4 FRTA1NM E3NE 20020220000182002022000018 2002 2 20 CA020124008 420020118G23309700029005 CONTROL UNIT AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE SMU FAILED W H DEACTIVATE SYST/CIRCUITS BA SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE NRNOT REPORTED 1 CA (CAN) ON THE PRE-DEPARTURE CHECK THE SMU (SYSTEM MANAGEMENT UNIT) CAUGHT ON FIRE NO EXTERNAL FLAME BUT FLAME AND WITHIN THE UNIT AND SMOKE COMING OUT OF THE UNIT.THE UNIT WILL HAVE A STRIP REPORT DONE AT THE MANUFACTURER FOR ANALYSIS. UNIT REPLACED. 1L72 4F4 FRTA46NM E39NE 20020220000192002022000019SW 2002 2 20 CA020124009 120020123G1400AN313 BOLT SWRNGNSA226 SA226TC 8780404SW MLG WORN W L ABORTED APPROACH WJ INADEQUATE Q C WARNING INDICATION APAPPROACH 1 CA 1500015000 (CAN) DURING APPROACH FOR LDG, CREW SELECTED GEAR DOWN&GOT 2 MAIN GEAR RED IND.S, THEN 2 MAIN GEAR GREEN IND.S WITH NO NOSEGEAR IND.. CREW BROKE OFF APPROACH & CYCLED GEAR COUPLE OF TIMES WITH NO IMPROVEMENT.AS SOON AS EMERG EXTENSION PERFORMED, GEAR CAME DOWN NORMALLY,&NORMAL LDG MADE. INVEST. REVEALED THAT SLIGHT WEAR IN DIAMETER OF BOLT, P/N AN3-13 INST IN UPLOCK HOOK ASSY P/N 27-52004-017, (TOR QUE TUBE) ALLOWED SEVERAL DEGS ANGULAR PLAY BETWEEN HOOK ASSY&ACTUATION ARM ASSY P/N 27-52000-015. PLAY PREVENTED SUFFICIENT RETRACTION OF NOSEGEAR UPLOCK HOOK TO ALLOW NOSEGEAR TO RELEASE. MANUAL EXTENSION SYSTEM BYPASSED ASSY. BOLT REPLA 2L72 4T RTA8SW 20020220000232002022000023SO 2002 2 20 CA020125001 120020123G291041 HYDRAULIC SYSTEMCLEVELANDXXX30142 PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE FLUID CONTAMINATED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) LEFT BRAKE WAS DRAGGING DURING AIRCRAFT TAXIING. THE AIRCRAFT WAS TOWED TO HANGAR WHERE THE BRAKE SYSTEM WAS FOUND WORKING NORMALLY. THE BRAKE SYSTEM (CALIPER & MASTER CYLINDER) WAS DISASSEMBLED AND WATER CONTAMINATION WAS FOUND PRESENT IN THE HYDRAULIC FLUID. SYTEM WAS DRAINED, CLEANED AND REPLENISHED WITH NEW HYDRAULIC FLUID. NEW O-RINGS WERE INSTALLED. THE BRAKE SYSTEM WAS BLED AND TESTED OK. 1L72 3T4 TRTA8EA E4EA 20020220000242002022000024GL 2002 2 20 CA020125002 220020104G72106890493 BEARING ALLSN 6894171 BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GEARBOX CRACKED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA CAG35537 (CAN) THIS AIRCRAFT RUNNING NORMAL. PILOT ON START HEARD A LOUD SQUEELING NOISE, THEN GOT A CHIP LITE. MAINTENANCE FOUND HUGE AMOUNTS OF METAL ON BOTH PLUGS. PROBLEM FOUND TO BE 2 1/2 BEARING FAILURE. 2 1/2 BEARNING ON SPUR ADAPTER, REPLACED. PROBLEM SEEMS TO BE FROM A HIGH N1 GEAR TRAIN VIBRATION. POSSIBLE OUT OF BALANCE COMPRESSOR. 1G71 3U3 U H2SW E4CE 20020220000252002022000025GL 2002 2 20 CA020125003 320020114G6114A2202 BEARING PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YK1 GL PROPELLER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BALLS HAD SEVERELY DENTED BEARING RACE (INBOARD). REPLACED. FORK HAD SEVERE WEAR FROM PITCH CHANGE BLOCKS.BEARING P/N A2202 FORK P/N B2457-7 1L71 3O3 O A3SO 1E4 5 CP920 20020220000272002022000027CE 2002 2 20 CA020125004 120020114G531005132831 DOOR FRAME CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON A 200 HOUR INSPECTION WHILE INSTALLING LT HEATING DUCT LOOKING THROUGH LIGHTNING HOLE AT BOTTOM LT DOOR POST. FOUND AN 1 1/2 INCH CRACK AT DOOR HINGE SCREWS. 1H71 3O3 ONT3A12 E274 5 NP910 20020220000282002022000028SO 2002 2 20 CA020125005 120020114G531076467003 DOOR FRAME PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11790 (CAN) THE INNER DOOR FRAME WAS FOUND CRACKED ALSO THE OUTER FRAME OF FUSELAGE SKIN WAS CRACKED. THE INNER FRAME WAS REPLACED. THE OUTER FRAME WAS CLEANED OF CORROSION TREATED AND ZING CHROMATED. THE OUTER CRACK WAS STOP DRILLED USING 7/64 INCH DIA STOP DRILL HOLE.NOTE: THE OUTER SKIN CRACK WILL BE MONITORED IF IT EXTENDS BEYOND STOP DRILL HOLES IT WILL HAVE TO BE REPLACED. NOTE: P/N & DESCRIPTION FOUND IN PARTS MANUAL FIGURE 10-31. 1L72 3O3 O A19S0 E286 20020220000292002022000029EA 2002 2 20 CA020125006 120020110G2720C3CF1985 CONTROL CABLE DHAV DHC3 DHC3 2800202EA PWA R1340 S3H1G 52016NE RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABLE FOUND WORN DURING 800 HOUR INSPECTION. CABLE INSTALLATION WAS NORMAL. CABLE WAS WORN INSIDE C3CF383-7 FAIRLEAD. THE FAIRLEAD CONDITION AND INSTALLATION WAS NORMAL. 1H71 3R3 R A815 E142 20020220000452002022000045EU 2002 2 20 CA020125007 120020125G6720 ADJUSTER SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU ANTITORQUE PEDALCRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PEDAL ADJUSTER LOCATION PIN SUPPORT CRACKED CAUSING THE PEDAL ADJUSTER LEVER TO BE UNMOVEABLE AND THE PEDALS UNADJUSTABLE. 2G72 4U4 U H4EU E12NE 20020220000462002022000046NE 2002 2 20 CA020125008 220020121G7314 SEAL BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE FUEL PUMP FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA (CAN) NR 2 ENGINE LOW OIL PRESS AND QUANTITY IN CRUISE YHM-YWG.ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO YHM.ENGINE INSPECTED I.A.W. PW M.M. 72-00 PAGE 664 AND FUEL PUMP MAIN CARBON SEAL REPLACED. 2L73 4F4 F A3WE E2EA 20020220000472002022000047SW 2002 2 20 CA020128001 120020118G324616212401 WHEEL AIRTRCAT802 AT802 0390305SW MLG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 2027 (CAN) DURING ANNUAL INSPECTION THE MAIN WHEELS WERE REMOVED FOR BEARING LUBRICATION AND INSPECTION. THE BEARING RACES REQUIRED REPLACEMENT. UPON REMOVAL OF THE RACES THE WHEEL WAS FOUND CORRODED BEYOND LIMITS. BOTH WHEEL ASSEMBLIES HAVE BEEN REMOVED FROM SERVICE ANAD WERE REPLACED WITH SERVICEABLE MAIN WHEEL ASSEMBLIES. NOTE THE MAIN WHEEL ASSEMBLIES ARE MAGNESIUM. 1L71 3T NCA19SW 20020220000482002022000048EU 2002 2 20 CA020128002 120020118G5230D21761 DOOR AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL CARGO SEPARATED W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT LT BAGGAGE DOOR DEPARTED THE AIRCRAFT, HITTING THE LT ENGINE COWL. THE AIRCRAFT WAS INSPECTED BY A QUALIFIED AME, BAGGAGE DOOR REPLACED, ENGINE COWL REPAIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1G72 3U3 U H11EU E4CE 20020220000522002022000052CE 2002 2 20 CA020128004 120020115G541226530351 DOUBLER CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL FIREWALL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE LOWER FWD DOUBLER IS SITUATED ON BOTTOM OF FIREWALL & SUPPORTS NOSEGEAR SPRING ATTACH. DOUBLER FOUND CRACKED ON ITS LT WEB NEAR BOTTOM. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020220000582002022000058EA 2002 2 20 CA020129001 120020129G2840TJ13 TRANSMITTER DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE FUEL CELL LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) TWO FUEL TRANSMITTERS WERE FOUND TO BE LEAKING DURING ROUTINE MAINTENANCE.REFER TO FIQURE 42 OF THE DHC 2 PARTS MANUAL FOR CLARIFICATION.THE GASKET ITEM 42 WAS FOUND TO BE LEAKING BETWEEN ITEM 43(FLANGE) AND ITEM 3(CASE). THE GASKET THAT SEPERATED THE ITEMS APPEARED TO BE SWOLLEN AND DISTORTED, 1H71 3R3 R A806 5E1 20020220000592002022000059EA 2002 2 20 CA020129002 120020128G2701C2CF1977 STRUCTURE DHAV C2CF833A DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE CONTROL COLUMN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 26981 391 (CAN) DURING INSPECTION OF CONTROL COLUMN BASE AS PER CF-84-01-R1 A CRACK WAS NOTED ON THE REAR FACING WELD FILLET. WHERE THE VERTICAL TUBE IS WELDED TO THE HORIZONTAL TUBE.THE ASSEMBLY WAS REMOVED FOR REPAIR AND A SERVICABLE UNIT WAS REINSTALLED. 1H71 3R3 R A806 5E1 20020220000602002022000060EA 2002 2 20 CA020129003 220020108G72303039901 BLADE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A28 EA COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A POST LEASE INSPECTION ON THE AIRCRAFT BOTH ENGINES ARE SPLIT AT THE "C" FLANGE FOR HOT SECTION INSPECTION. DURING THE RIGHT H.S.I. THE ENGINEER NOTICED "LINES" ON SOME OF THE C.T. BLADES. NINE BLADES SEEM TO BE CRACKED. SEVEN BLADES CRACKED FROM TIP HEADING TOWARDS ROOT. TWO SEEM CRACKED ACROSS THE BLADE FROM LEADING EDGE TO TRAILING EDGE. 1H72 3T4 TRTA9EA E4EA 20020220000622002022000062EA 2002 2 20 CA020129005 220020118G73203031448 TUBE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA FUEL CONTROL CRACKED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 14606 (CAN) LEFT ENGINE WOULD NOT ACCELERATE ON INITIAL TAKEOFF. NG AT 44 PERCENT. NO RESPONSE FROM POWER LEVER, REJECTED TAKEOFF AND RETURNED TO RAMP. 1L72 3T4 T A8EA E4EA 20020220000632002022000063GL 2002 2 20 CA020129006 220020123G726023039794 PUMP RROYCE 250C30P BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL GEAR OIL GALLED W K NONE O OTHER ININSP/MAINT 1 CA CAG95735 (CAN) DURING REINSTALLATION OF ENGINE BY OPERATOR. ENGINE HAD NO OIL PRESSURE: OPERATOR NOTED UNUSUAL NOISE HEARD COMING FROM GEARBOX WHEN N1 GEAR TRAIN SPUN. GEARBOX RETURNED FOR REPAIR. UPON INSPECTION FUEL CONTROL / OIL PUMP FLEXIBLE COUPLING SHAFT FOUND FRACTURED. WHEN TURNED BY HAND N1 GEAR TRAIN ROTATED NORMALLY. OIL PUMP COULD NOT BE TURNED BY HAND. OIL PUMP REMOVED & DISASSEMBLED. ONEOF IDLER GEARS HAD METAL BUILD-UP ON END FACE. ADJACENT FACES ON GEAR POCKET & SEPARATOR WERE ALSO HEAVILY SCORED. GEAR END CLEARANCES WERE MEASURED&FOUND TO BE .0005 TO .0075, WHICH IS WITHIN ROLLS ROYCE OVERHAUL LIMITS. IT W AS CONCLUDED OIL PUMP HAD SEIZED DUE T 1G71 3U3 U H2SW E1GL 20020220000642002022000064EA 2002 2 20 CA020130001 120020110G2710 CONTROL CABLE CNDAIRCL215 CL2156B11415 EA AILERONS WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AILERON CABLE WORN BEYOND LIMITS. 2H72 4T RTA14EA 20020220000662002022000066SO 2002 2 20 CA020130004 120020124G78109904404 EXHAUST STACK PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKED EXHAUST STACK FROM CYLINDER NR 3 MELTED THE CARB HEAT CABLE INTERIOR LINING CAUSING THE CABLE TO BE VERY STIFF. CABLE. CRACK LOCATED INSIDE THE CARB HEAT SHROUD AT THE MOST FORWARD POINT WHICH IS VERY DIFFICULT TO INSPECT. RECOMMEND REMOVE SHROUD PERIODICALLY FOR BETTER INSPECTION. EXHAUST STACK WALL EROSION IS DIFFICULT TO DETECT. 1L71 3O3 O 2A13 E274 20020205001482002020500148SW 2002 2 5 CA020130005 120020122G6220206011118001 BEARING BELL 206011132113BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL CAGE FAILED W O OTHER I FLT. ATTITUDE INST. CRCRUISE 1 CA A5828 (CAN) PILOT REPORTED A "SPRINGY" FEELING IN CYCLIC ALONG WITH THE NECESSITY OF APPLYING CONSTANT FORWARD CYCLIC INPUT FOR CRUISE FLIGHT. NO PROBLEMS WERE FOUND IN THE FLIGHT CONTROLS. THE ROTOR HEAD WAS REMOVED AND DISASSEMBLED AND AT THIS TIME THE DAMAGED BEARING WAS NOTED. NO OTHER PARTS WERE FOUND DAMAGED. THE ROTOR HEAD, HAVING ONLY 80 HOURS REMAINING UNTIL OVERHAUL, HAS BEEN SENT FOR FURTHER EVALUATION AND OVERHAUL. THE FAILED BEARING IS BEING KEPT IN QUARANTINE FOR INSPECTION, IF REQUIRED. 1G71 3U3 U H2SW E1GL 20020321000902002032100090CE 2002 3 21 CA020130008 120020119G534712139902 BRACKET BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13347 (CAN) DURING THIRD INSPECTION WE FOUND NINE SEAT BRACKET CRACKED. THE CRACK WAS GENERATED FROM THE REAR THRU THE HOLE ADJACENT TO THE BEND.AFTER FLEET INVESTIGATION WE FOUND 33 BRACKET CRACKED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020321000912002032100091CE 2002 3 21 CA020130009 120020114G33409003312 LIGHT BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE STROBE FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) AFTER SELECTING THE BEACON SWITCH TO ON, FOUND THAT THE TAIL BEACON LIGHT WAS NOT FLASHING. THE LIGHT WAS REPLACED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020220000712002022000071SW 2002 2 20 CA020131002 120020118G5302222035231105 FITTING BELL 222 222U 1182140SW LYC LTS101LTS101750C1 41560NE VERTICAL FIN BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL LOWER FIN FITTING FOUND ATTACHMENT LUG BROKEN OFF ON A PRE FLIGHT. 1G72 3U3 U H9SW E5NE 20020220000732002022000073SW 2002 2 20 CA020131003 120020129G2910212076301001 LINE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA NR 1 HYD SYSTEM BROKEN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) HE AIRCRAFT NR 1 HYDRAULIC SYSTEM LOST SYSTEM PRESSURE(FLUID LOSS). THE ENGINEER FOUND A HYDRAULIC TUBE BROKEN IN THE MID POINT. 1G71 4U4 U H4SW E22EA 20020205001492002020500149SW 2002 2 5 CA020131004 120020129G6340204001736005 CHAIN BELL 204040806011BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA HYD DRIVE OIL BROKEN W AO UNSCHED LANDING OTHER JO WARNING INDICATION OTHER CRCRUISE 1 CA A1214562 (CAN) THE HELICOPTER WAS IN CRUISE WHEN ALL OF A SUDDEN THE ROTOR TACH GENERATOR INDICATOR WENT TO ZERO.BACK AT THE BASE AN ENGINEER TROUBLE SHOOTED THE PROBLEM AND FOUND THE TACH. GEN DRIVE WAS DISCONNECTED. THE ROTOR TACH GENERATOR DRIVE IS LOCATED IN THE #1 HYDRAULIC QUILL ASSEMBLY OF THE MAIN ROTOR TRANSMISSION. SUSPECT THE CHAIN HAS FAILED INSIDE THE HYDRAULIC/TACH GEN DRIVE QUILL. 1G71 4U4 U H4SW E22EA 20020308000332002030800033GL 2002 3 8 CA020131005 320020124G6110B2256 THRUST PLATE HARTZLHCE3Y HCE3YR2A GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND AROUND THIN LIP OF THRUST PLATE. 5 CP33EA 20020308000362002030800036EA 2002 3 8 CA020131006 120020120G2120600953373 CONNECTOR CNDAIRCL600 CL600* EA CABIN HEAT MISREPAIRED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) 1) ENROUTE LOSS OF CABIN HEAT & TEMP CONTROL. 2) AFTER LANDING FOUND DAMAGED CONNECTORS FROM DUCT AT RT ACU. 3) THIS DUCT INSTALLATION IS PART OF SB 600-0476. THE CONNECTORS ARE RTV SECURED AT ONE END OF THE DUCT. ASSEMBLY OF COUPLINGS TO DUCT ENDS WERE CARRIED OUT IMPROPERLY CAUSING SEPARATION. P/N 600-95337-3/600-95337-1 2L72 4F RTA21EA 20020321000932002032100093NM 2002 3 21 CA020131009 120020114G552385520271003 STOP DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE ELEVATOR DETERIORATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING CREW WALKAROUND, THEY NOTICED DAMAGE TO LT TRAILING EDGE OF THE ELEVATOR SPRING TAB. THE DAMAGE TO THE TAB WAS INBOARD, ADJACENT TO THE RUDDER. THE TRAILING RUDDER WAS ALSO DAMAGED FROM CONTACT WITH ELEVATOR SPRING TAB. THE LT ELEVATOR SPRING TAB REPLACED. RD 8-55-1214 ISSUED FOR 200 HOURS ALLOWANCE FOR DAMAGE TO LT SIDE OF THE TRAILING RUDDER. THE ELEVATOR BUMPER STOP WAS REPLACED, AS IT WAS DETERIORATED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020220000802002022000080NM 2002 2 20 CA020201003 120020118G612078249047 PCU DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE PROPELLER FAILED W C ABORTED TAKEOFF REJPARTIAL RPM/PWR LOSS VIBRATION/BUFFET WARNING INDICATION TOTAKEOFF 1 CA (CAN) JOURNEY LOG: TAKEOFF ABORTED DUE TO ENGINE NR 2 TORQUE NOT PASSING 60 PERCENT. ON SHUTDOWN PROP NR 2 WOULD NOT FEATHER. AIRCRAFT RETURNED TO GATE DUE TO NR 2 ENGINE SLUGGISH TO ACCELERATE, PROP FOUND NOT TO BE FEATHERING AUTOMATICALLY OR MANUALLY. INSPECTION ON PROP HUB ASSEMBLY, PCU REPLACED AS PER MM, ENGINE RUNS CARRIED OUT, OK. REPLACEMENT OF THE PCU WAS THE FINAL FIX. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020220000812002022000081NM 2002 2 20 CA020201004 120020122G3297471515 WIRE HARNESS DHAV DHC8 DHC8* NM PWC 150 PW150A EA NLG SQUAT SWITCHSHORTED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) WEIGHT ON WHEELS CAUTION LIGHT ILLUMINATED IN FLIGHT. RELANDING DUE TO CAUTION LIGHT "WT ON WHEEL" INTERMITTENTLY ON. UNEVENTFUL RE-LANDING.FOUND SENSORS WIRING, TWISTED SHIELDED PAIR, SHORTED TO SHIELD. SENSOR REPLACED. 2H72 4T4 TRTA13NM E00062EN 20020321000972002032100097NM 2002 3 21 CA020201007 120020121G3260854144465101 BRACKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA MLG FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) IT WAS NOTICED DURING ROUTINE MAINTENANCE THAT THE LT UPLOCK ACTUATOR SUPPORT BRACKETS WERE MISSING THE ATTACH HI-LITES (QTY 6) THRU AFT FRAME (THIS HAS INITIATED A FLEET WIDE INSPECTION AS DIRECTED BY DASH-8-400 AOM 050) AC SN 4033 HAS SUFFERED A STRUCTURAL DAMAGE DUE TO MISSING FASTENERS IN AFT END OF THE BRACKETS FOR THE LT MAIN LANDING GEAR. UPLOCK. MAINTENANCE WILL CHANGE THE ENTIRE SHEAR DIAPHRAGM , THE SUPPORT BRACKET DOUBLER , SUPPORT BRACKET SHIM , ATTACHMENT CLEATS AND REMOVE AND REPLACE BOTH UPLOCK BRACKETS. 2H72 4T4 TRTA13NM E00062EN 20020321000982002032100098NM 2002 3 21 CA020201008 120020124G3320404820 SOCKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA LIGHTS OVERHEATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA (CAN) BURNING SMELL FROM TOILET OBSERVED BY CABIN CREW. RIGHTHAND GENERATOR SWITCHED OFF. EMERGENCY DECLARED. AIRCRAFT LANDED SAFELY AND PASSENGERS DISEMBARKED ON RUNWAY AND TAKEN BY BUS TO TERMINAL. TOILET AND PANELS CHECKED BY FIREFIGHTERS. NO TRACE OF FIRE FOUND. AIRCRAFT TOWED TO GATE AND PASSENGERS BRIEFED BY COMMANDER.INVESTIGATION OF THE AIRCRAFT SHOWED A BURNED AND MELTED HOLDER FOR THE FLUORESCENT TUBE IN THE LAVATORY THAT HAD CAUSED THE SMOKE/SMELL. 2H72 4T4 TRTA13NM E00062EN 20020220000822002022000082EU 2002 2 20 CA020201010 120020121G2435 WIRE BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313R 01518WP STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET. 2L72 4F4 F A3EU E6WE 20020220000842002022000084EU 2002 2 20 CA020201012 120020121G2435257ES2873 FAIRLEAD BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313R 01518WP STARTER GEN BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET AND PHENOLIC FAIRLEAD BROKEN. 2L72 4F4 F A3EU E6WE 20020321001022002032100102NE 2002 3 21 CA020201013 220020122G73149234A8 PUMP AMD FALCONFALCON20 2730103EU GE CF700 CF7002D2 30010NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AFTER COMPLETION OF UNLOADING FREIGHT, OUR AIRCRAFT WAS REPOSITIONING TO THE MAINTENANCE FACILITY AT FBO. DURING ENGINE SHUTDOWN, AN ENGINEER FROM OUR CONTRACTED AMO NOTICED FUEL LEAKING FROM THE RIGHT ENGINE LOWER COWLING. IN ORDER TO STOP THE FUEL FROM LEAKING, THE RIGHT ENGINE EMERGENCY SHUT DOWN LEVER WAS PULLED.AFTER VISUAL INSPECTION, A SMALL HOLE ON THE FCU BOOST PUMP CASTING WAS OBSERVED.THE SMALL HOLE SEEMS TO ORIGINATE FROM A DEFECT IN THE CASTING. 2L72 4F4 FRTA7EU E7EA 20020220000872002022000087EA 2002 2 20 CA020201014 120020128G2720MS178264 NUT CNDAIRCL604 CL604 1900301EA RUDDER CONTROL MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A PRE-DELIVERY INSPECTION A NUT WAS DISCOVERED MISSING ON BOLT ON CONTROL ROD ASSEMBLY AND TORQUE TUBE AFFECTING THE PCU RUDDER TORQUE TUBE ASSEMBLY. A FLEET INSPECTION WAS CARRIED OUT AND NO OTHER AIRCRAFT FOUND WITH SIMILAR PROBLEM. 2L72 4F RTA21EA 20020220000892002022000089EU 2002 2 20 CA020201015 120020119G2611 SMOKE DETECTOR AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE E/E BAY FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AFTER TAKEOFF, AVIONIC VENT SMOKE MESSAGE, NO APPARENT OF SMOKE OR SMELL. RAT DEPLOYED. SMOKE INDICATION DISAPPEARED BEFORE LANDING. FLIGHT RETURNED TO FORT LADERDALE. AVIOINIC COMPARTMENT INSPECTED FOR EVIDENCE OF SMOKE, BLOWN DUCTS OR OVERHEATED EQUIPMENT. NO FAULT FOUND. SUSPECT BAD SMOKE DETECTOR INSTALLED. RAT RETRACTED AND TESTED. SMOKE DETECTION SYSTEM TESTED SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000902002022000090EA 2002 2 20 CA020201017 120020119G5270 SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE PAX DOOR CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON DEPARTURE THROUGH 4000 FT PAX OR LATCH. CAUTION MSG ILLUMINATED. CHECKLIST CARRIED OUT WITH PRESSURIZATION NORMAL. DECIDED ATO CONTINUE THROUGH 10000 FT, PASSENGER DOOR WARNING MSG WITH NORMAL PRESSURIZATION.AIRCRAFT RETURNED TO TORONTO. ON ARRIVAL FOUND DOOR HANDLE LATCH LOCK ALMOST UNLATCHED. FOUND EXCESS GREASE ON SENSORS, SENSORS CLEANED. PSEU MEMORY RESET AND DOOR OPERATION AND INDICATION CHECKED OK. 2L72 4F4 FRTA21EA E15NE 20020220000912002022000091EA 2002 2 20 CA020201018 120020120G5210 DOOR LATCH CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE PAX DOOR LACK OF LUBE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING FLIGHT, AIRCRAFT WAS DIVERTED DUE TO PASSENGER DOOR FAULT. FOUND PASSENGER DOOR LATCH RED HANDLE STICKING. CLEANED AND LUBED, OPERATED DOOR SEVERAL TIMES, DOOR OPERATION AND INDICATION OK. 2L72 4F4 FRTA21EA E15NE 20020220000932002022000093EA 2002 2 20 CA020201019 120020106G4940897889 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE APU BAY FAILED W FO ACTIVATE FIRE EXT. OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AT 10,000 FT TRIED TO START THE APU, NO LIGHT OFF. APU SELECTED OFF. 2 MINUTES LATER, ATTEMPTED ANOTHER START, START COMPLETED, FUEL TRANSFERRED WITH STRONG SMELL OF FUEL, EGT HIGHER THAN NORMAL WITH ONE FIRE DETECTOR LOOP INOP. APU SHUTDOWN AND FIRE BOTTLE DISCHARGED. APU FIRE EXTINGUISHER BOTTLE AND SQUIB REPLACED. FIRE DETECTION LOOP REPLACED. SYSTEM TESTED SERVICEABLE. APU AND ENGINES RUN FOR 3 MINUTES, NO SMELL OF FUEL, ALL SYSTEMS OPERATE NORMAL. AIRCRAFT SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020220000942002022000094EA 2002 2 20 CA020201020 120020110G322216050105 LANDING GEAR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE NLG FAILED W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) GEAR DISAGREE WARNING AFTER LANDING GEAR SELECTED UP ON TAKEOFF (NOSE GEAR UNSAFE). AIRCRAFT RETURNED TO BASE.AFTER EXTENSIVE TROUBLE SHOOTING, NEW NOSE LANDING GEAR ASSEMBLY INSTALLED. 2L72 4F4 FRTA21EA E15NE 20020220000952002022000095EU 2002 2 20 CA020201023 120020123G3230114079015 SELECTOR VALVE AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) ON FINAL APPROACH TO VANCOUVER AT 1600 AGL "L/G NOT DOWNLOCKED" WARNING CAME ON. GEARS CYCLED. ALL EXTENDED NORMALLY THE SECOND TIME. THE GEAR AT FAULT WAS THE RT MAIN. MAIN LANDING GEAR SELECTOR VALVE REPLACED AS PER AMM TASK 32-31-12-400-001, LEAK CHECKED AND GEAR RETRACTED SEVERAL TIMES, NO FAULT FOUND. 2L72 4F4 FRTA28NM E29NE 20020220000962002022000096EU 2002 2 20 CA020201024 120020124G3231201122006 UPLOCK AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE LT MLG DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) CLIMBING THROUGH 16,000 FT AT 265 KTS ECAM L/G DOOR OPEN. SLOWED TO 215 KTS. GEARS RECYCLED AS PER MAINTENANCE REQUEST, NO CHANGE. AMBER DOOR LIGHT INDICATION REMAINS ON UNTIL GEAR SELECTED DOWN. AIRCRAFT RETURNED TO TORONTO. LT MAIN LANDING GEAR DOOR UPLOCK REPLACED AS PER AMM 32-31-33. DOOR OPERATION CHECK CARRIED OUT. NO FAULT FOUND. AIRCRAFT SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000972002022000097SW 2002 2 20 CA020201025 120020123G3246 BEARING AIRTRCAT802 AT802 0390305SW MLG WHEEL CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE ANNUAL INSPECTION MAINTENANCE DISCOVERED SERIOUS CORROSION AT THE TOP AND BOTTOM OF OUTER BEARING RACE. 1L71 3T NCA19SW 20020220000992002022000099NE 2002 2 20 CA020201026 220020124G7200 ENGINE AIRBUS330 A330243 3930330EU RROYCERB211 RB211TRENT77 NE NR 2 VIBRATION W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) VIBRATION ON NR 2 ENGINE, (DURING CLIMB) INCREASING WITH ALTITUDE , ADVISORY 3.5 UNIT AT 22 000 FT AT 5.0 UNIT , FELT AIRFRAME VIBRATION. THE AIRCRAFT MADE AN AIR TURN BACK. A BLADES OFF INSPECTION WAS CARRIED OUT I.A.W. ENGINEERING ORDER 5-7231-001 ( BLADE ROOT INSP. C/OUT , NO FAULTS FOUND, BLADE ROOTS WERE CLEANED , LUBRICATED AND RE-INSTALLED) ENGINE RUN C/OUT SERVICEABLE.NOTE THE AIRCRAFT MADE AN OVERWEIGHT LANDING IN YMX AT 206 000 KGS , AUTOLAND PERFORMED , TOUCH DOWN AT 200 FEET/MINUTE.NO INSP. FOR HARD/OVERWEIGHT LANDING REQUIRED I.A.W. AMM 05-51-11-200-801. 2L72 4F4 FRTA46NM E39NE 20020220001002002022000100NE 2002 2 20 CA020204002 220020201G7200658536916 BULLET BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE NR 2 ENGINE SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) FLT CREW RPTED DURING CLIMB AFTER TAKEOFF THEY EXPERIENCED SERIES OF LOUD BANGS FROM NR 2 ENGINE ACCOMPANIED BY ABNORMAL HIGH EGT & LOW N 2 RPM. ALL IND.S WERE NORMAL PRIOR TO NOICE. PROBLEM OCCURRED AFTER CLIMB THRUST SET. THE CREW REDUCED NR 2 THRUST TO ALMOST IDLE, AS PER ENGINE LIMITS / SURGE / STALL QUICK REF CHART (QRC) AND ENGINE OPERATED NORMALLY. A/C RETURNED&LANDED W/O INCID. - CFR WERE NOTIFIED&ON STANDBY.INIT MAINT INSPECTION FOUND NR 2 ENGINE NOSE CONE BULLET HAD SEPARATED FROM ITS ATTACHMENTS & JAMMED INTO ENGINE INLET GUIDEVANES. MAINT REPL ENGINE, 2L72 4F4 F A16WE E2EA 20020220001022002022000102EU 2002 2 20 CA020205001 220020127G8530N854115 EXHAUST VALVE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU ENGINE CHIPPED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CLCLIMB 1 CA (CAN) SHORTLY AFTER T/O, A PARTIAL ENGINE POWER LOSS WAS EXPERIENCED WITH ASSOCIATED ENGINE VIBRATION AND REDUCED CLIMB PERFORMANCE.THE AIRCRAFT RETURNED TO THE AIRPORT TO LAND. THE COMPRESSION WAS FOUND TO BE LOW IN THE NR 3 CYLINDER. AIR WAS FOUND TO BE LEAKING OUT THE EXHAUST. THE EXHAUST VALVE WAS FOUND TO HAVE A 1/16 IN DIA HOLE.THE VALVE HAD ALSO MADE CONTACT WITH THE PISTON.TWO FLIGHTS PRIOR TO THE INCIDENT FLIGHT THE ENGINE EXPERIENCED A SUBSTANTIAL BACKFIRE ON SHUTDOWN DUE TO SHUTTING DOWN AT HIGH POWER.IT IS UNCLEAR IF THIS CONTRIBUTED TO THE DAMAGED VALVE. 1L71 3O3 INTTA4CH EXPE3I 20020220001052002022000105NE 2002 2 20 CA020205002 120020128G321314102B CYLINDER CONAERC2 C2 5110202NE LYC O360 O360A1A 41514EA MLG FAILED W O OTHER R PARTIAL RPM/PWR LOSS LDLANDING 1 CA (CAN) A/C C-2 SKIMMERS, BOTH UTILIZE COLONIAL STYLE MAIN UNDER CARRIAGE OLEOS. ONE OLEO PER A/C CAME APART.THE MAIN GEAR OLEOS ARE CRACKING AT LOWER END CAP TO CYLINDER (CASING) ATTACH BOLTS. WHEN THIS OCCURS, BEFORE LONG END CAP DISLODGES FROM OLEO CAUSING GEAR LEG & TRAILING DRAG ARM TO COLLAPSE.THE CRACKS IN THIS AREA HAVE ALSO BEEN FOUND ON NEWER STYLE GERDES & AEROFAB MANUFACTURED OLEOS, P/N 2-4111-11 INST ON LA-4 SERIES A/C. IF CRACKS ARE FOUND, LAKE A/C REPAIR IS TO ROTATE END CAP WITHIN CYLINDER, RE-DRILL & INST NEW HARDWARE. 1H71 3O3 O 1A13 E286 20020220001062002022000106NE 2002 2 20 CA020205003 120020124G791041650 CAP SKRSKYS61 S61N 8142104NE GE CT58 CT581401 30011NE OIL TANK FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING PHASE IVA OPS 6, WE FOUND OIL CONTAMINATION ON ENGINE NR 2 TANK. THE PACKING P/N MS29513-232 ON THE CAP ASSEMBLY P/N 416-50 TO BE THE CAUSE. REPLACED THE PACKING, FLUSHED OIL AND CHANGE OIL FILTER. RAN THE AIRCRAFT FOR 15 MINUTES AND AFTER OIL AND FILTER WILL BE REPLACED. IF NO FURTHER CONTAMINATION AIRCRAFT WILL BE RETURNED TO SERVICE. 2G72 4U4 U 1H15 1E3 20020220001072002022000107GL 2002 2 20 CA020205004 320020125G6111A0971 BEARING HARTZLHCA3V PHCA3VF2 GL PROPELLER DENTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BEARING WAS BADLY DENTED ON BALL SURFACE. MUSHROOM CRACKED AROUND BASE. ALL BEARINGS REPLACED.MUSHROOM REPLACED.BEARINGS P/N A0971MUSHROOM P/N A0856 5 CP6EA 20020322000012002032200001EU 2002 3 22 CA020207001 120020120G3520C24091 SQUAT SWITCH AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE73121C NE LT MLG CONTAMINATED W O OTHER O OTHER CLCLIMB 1 CA (CAN) LOSS OF PRESSURIZATION AFTER TAKEOFF. RECTIFICATION: MOISTURE WAS FOUND ON THE LT LANDING GEAR SQUAT SWITCH 9G1. SUSPECT SQUAT SWITCH 9G1 WAS COLD SOAKED, CLEANED AND LUBED. PASSENGER OXYGEN MASK HAD NO OXYGEN FLOW. SYSTEM IS OPERATING IAW F10 M.M. WHICH STATES THAT THERE IS NO OXYGEN FLOW BELOW 15,000 FT. AIRCRAFT SYSTEM GROUND CHECKED SERVICEABLE. 2L72 4F4 F A33EU E6WE 20020308000522002030800052EA 2002 3 8 CA020207002 220020203G72503027301 BLADE BEECH 200 B200 1152922CE PWA PT6 PT6A41 52043EA TURBINE SECTION CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TWO (2) CT BLADES CRACKED. 1L72 4T4 T A24CE E4EA 20020322000022002032200002EA 2002 3 22 CA020207003 120020118G3241 BRAKE CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF341A NE ANIT SKID MALFUNCTIONED W D RETURN TO BLOCK L NO TEST TXTAXI/GRND HDL 1 CA (CAN) DURING TAXI- ANTI-SKID TEST FAILURE - WIRES BG15B20BLU & GB30B20WHT - SUSPECT CYCLIC FAILURE. 2L72 4F4 FRTA21AE E15NE 20020304001212002030400121EA 2002 3 4 CA020207004 120020206G52106003189021 BELLCRANK CNDAIR CL6012A12 CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF341A NE NIL W K NONE O OTHER ININSP/MAINT 1 CA 3037 (CAN) DOOR HARD TO OPEN: INSPECTION FOUND CRANK ASSY CRACKED (P/N 600-31890-21) - PART CRACKED DUE TO IMPROPER INSTALLATION OF SB 601-0192 - DOGS OF LOST MOTION CRANK NOT CONTACTING DRIVE CRANK AND COLLAR SIMULTANIOUSLY. THIS CAUSED STRESS ON OPPOSITE EARS CAUSING EACH TO CRACK. 2L72 4F4 FRTA21AE E15NE 20020322000032002032200003CE 2002 3 22 CA020207005 120020130G5414016A1331621 HANDLE MTSBSI 016A133003 MTSBSIMU2 MU2B60 5780460CE COWLING FAILED W O OTHER D INFLIGHT SEPARATION DEDESCENT 1 CA (CAN) AFTER MAINTENANCE, AN ENGINEER AND A PILOT DID A WALK AROUND CHECK AND DID NOT NOTICE ANYTHING UNUSUAL. THE AIRCRAFT DEPARTED AND ON ROUTE ONE LATCH ON THE LEFT HAND UPPER COWLING SEEMED TO HAVE BECOME UNLATCHED. THE AIRCRAFT LANDED IN TIMMINS AND ON ENGINE SHUTDOWN THE COWLING CAME FORWARD AND CONTACTED THE PROP CAUSING THE COWLING TO FLY OFF ONTO THE RUNWAY.THE COWLING AND PROP WERE REPLACEDTHE COWL LATCH WAS INSPECTED AND NO DEFECTS COULD BE FOUNDWE HAVE INITIATED PROCEDURES TO PUT SCREWS INTO THE UPPER COWLINGS SO THIS PROBLEM WILL NOT HAPPEN AGAIN 1H72 3T RTA10SW 20020308000532002030800053CE 2002 3 8 CA020208001 120020125G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT FAILED W BGA EMER. DESCENT O2 MASK DEPLOYED UNSCHED LANDING O OTHER CRCRUISE 1 CA 97300H8611 (CAN) APPROX 15 MINS AFTER LEVELLING OFF AT CRUISE ALTITUDE OF 29,000 FEET, SMALL CRACK FORMED ON RIGHT WINDSHIELD. FEW SECONDS LATER, ENTIRE INNER PLY SHATTERED & CABIN PRESSURIZATION LOST AT RATE OF APPROX 2500 FT/MIN . EMERGENCY OXYGEN DEPLOYED & MASKS DONNED, & EMERGENCY DESCENT TO SAFE ALTITUDE OF 11,000 FEET CARRIED OUT BY CREW. A/C CARRIED ON TO MEDICINE HAT (CYXH), WHERE UNEVENTFUL APPROACH & LANDING WERE CARRIED OUT. INSPECTION OF WINDSHIELD UPON ARRIVAL CONFIRMED THAT ENTIRE INNER PLY HAD SHATTERED. HAD BEEN NO PREVIOUS REPORTS OF DAMAGE ON WINDOW,&WINDHSIELD HEAT OP NORMAL.INSPOF FUSELAGE WINDSHIELD ATTACH STRUCTURE REVEALED NO ABNORMALITIES. REPLACED WINDSHIELD. 1L72 4T4 T A24CE E4EA 20020322000042002032200004 2002 3 22 CA020208002 420020208G3422 VANE SIGMATEK 235010616 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL GYRO STUCK W K NONE O OTHER ININSP/MAINT 1 CA T53207J (CAN) COPPER VANE RUBS AGAINST POT ALUMINUM GYRO CASE CREATING BLACK RESIDUE CAUSING VANE TO STICK. THIS CAUSES HORIZION TO DIPLAY A PITCH OR ROLL WHEN LEVEL. 1H71 3O3 ONT3A12 E274 5 NP910 20020308000552002030800055CE 2002 3 8 CA020208004 120020127G2731043200122 SKIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11841 (CAN) - CRACK FOUND ON PRE-FLIGHT. - CRACK LOCATED AT OUTBOARD AFT CORNER OF ELEVATOR UNDER TRIM TAB HINGE. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020322000052002032200005CE 2002 3 22 CA020208005 120020206G2497 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FUSELAGE SHORTED W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) DURING PREFLIGHT CHECKS, CREW NOTICED FALSE FIRE WARNING, FUEL SHUTOFF VALVE ACTUATION, ALTHOUGHT VALVE ACTUATION WAS AUDIBLE. AIRCRAFT WAS FERRIED TO MAINTENANCE FACILITY FOR REPAIRS. WIRING SUSPECTED AS CAUSE OF FALSE INDICATIONS HOWEVERE MEG OF WIRING REVEALED NO SHORTS. PRIMARY WIRES WERE TO BE REPLACED BUT DURING PROCESS, A CHAFFED WIRE WAS DISCOVERED UNDER THE FORWARD CLOSET AREA, BEHIND THE TCAS RX / TX. OCCASIONALLY, THE WIRE WAS MAKING CONTACT WITH A KNURLED FITTING RELATING TO THE TCAS. THE WIRE WAS REPAIRED AND THE AREA PROTECTED FROM ADDITIONAL CHAFFING. AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020322000062002032200006NM 2002 3 22 CA020211001 120020210G542085310380 BEAM DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE NLG WW CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 27861 (CAN) NLG WHEEL WELL BOX STRUCTURE WAS FOUND CRACKED WHILE DOING TASK 5310/27D (DETAILED VISUAL INSPECTION).DAMAGE WAS REPAIRED IN ACCORDANCE TO REPAIR DRAWING RD 8-53-2376 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020228000042002022800004NE 2002 2 28 CA020211003 220020130G72605018T49P01 CARBON SEAL GE CF343A1 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ON R/H ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT TAT:4900.3 FLIGHT 5589 FROM CVG TO MKE.R. ENGINE LOW OIL PRESSURE WARNING IN FLIGHT. PERFORMED QRH. R. ENGINE TO IDLE, MSG WOULD NOT CLEAR. SHUT ENGINE DOWN. ENGINE OIL PSI FLUCTUATES BETWEEN 21 TO 30 PSI.DIVERTED TO GRR, DECLARED AN EMERGENCY AND LANDED.FOUND ENGINE 5 QTS LOW ON ARRIVAL AT GRR. REPLENISHED SYSTEM. SUBSEQUENTLY FAILED OIL CONSUMPTION RUN CHECK. (2 QUARTS USED). FOUND STARTER AND IDG CARBON SWALS CARBON SEALS P/N 5018T49P01 AND 5016T32P01 LEAKING.REPLACED SEALS. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020308000682002030800068EU 2002 3 8 CA020211015 120020206G6220350A31190703 STARFLEX 355A3100200 SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE MAIN ROTOR HUB DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA M1801 (CAN) AIRCRAFT TOTAL TIME 463 HOURS CONDUCTED A 500/A CALENDAR INSPECTION. BUSHING FOUND LOOSE ON STARFLEX ARM DURING INSPECTION AS PER WORK CARD 62.20.605 PARA. 5.3. 1G71 3U3 U H9EU E00054EN 20020322000082002032200008EA 2002 3 22 CA020211016 120020211G3222C3UF1085 STRUT DHAV DHC3 DHC3 2800202EA PWA R1340 S3H1G 52016NE FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 18089 (CAN) FLOAT STRUTS REMOVED TO PERFORM ANNUAL INSPECTION AS PER DEHAVILLAND SERVICE BULLETIN 3/30. SIX INCH LONG CRACK FOUND VISUALLY THROUGHOUT CENTER OF THE BASE OF THE STRUT CASTING. 1H71 3R3 R A815 E142 20020308000692002030800069EU 2002 3 8 CA020211017 220020209G7421897255 SPARK PLUG DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE ROUGHNESS WAS NOTED ON STARTUP AT ALL POWER SETTINGS BELOW 1600 RPM. NR 3 CYLINDER SPARK PLUG WAS FOUND TO HAVE ELECTRODE BROKEN OFF AT 90 DEGREE BEND. 1L71 3O3 INTTA4CH EXPE3I 20020322000092002032200009EU 2002 3 22 CA020212001 120020212G5210NOGIVEN ATTACH FITTING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN DOOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ATTACHMENT BRACKET FOR CABIN DOOR COUNTER BALANCE SYSTEM FOUND WITH LOOSE RIVETS. RIVETS REMOVED AND REPLACED WITH CR3243-4 BLIND RIVETS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020322000102002032200010NE 2002 3 22 CA020213001 220020211G72107826511 BRACKET DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE REDUCTION G/B CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 22926 (CAN) WHILE REMOVING THE ENGINE ACCESSORIES IN THE SHOP,AFTER AN ENGINE CHANGE, IT WAS DISCOVERED THAT THE PROPELLER DE-ICE BRUSH BLOCK MOUNTING BRACKET WAS CRACKED AROUND BOTH MOUNTING BOLT HOLES. THIS WOULD EVENTUALLY LEAD TO A COMPLETE FAILURE OF THE BRACKET AND THEREFORE PROPELLER DAMAGE AND LOSS OF DE-ICE CAPABILITY. THE BRACKET WAS REPLACED WITH A NEW UNIT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020322000112002032200011CE 2002 3 22 CA020213006 120020201G2435 BEARING LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP STARTER GEN FAILED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA (CAN) ON A TRIP FROM HOUSTON TO CALGARY, VIBRATION OCCURRED IN AIRCRAFT, RT GENERATOR FAILED, THE AIRCRAFT DIVERTED TO WICHITA WHERE THE RT STARTER/GENERATOR WAS REPLACED. AIRCRAFT AND COMPONENT TIME 871.0 HOURS, 454 CYCLES. 2L72 4F4 FRTT00008WIE6WE 20020322000122002032200012CE 2002 3 22 CA020213007 120020213G272003101965 SPRING CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL RUDDER CONTROL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RUDDER WAS ANGLED TO ONE SIDE UPON FURTHER INSPECTION FOUND THAT IT WOULD NOT RETURN TO NEUTRAL.RUDDER SPRING WAS FOUND HANGING IN POSITION DETACHED FROM ONE SIDE, THE END HAD BROKEN OFF. PART WAS REPALCED AND AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3O3 ONT3A12 E274 5 NP910 20020308000702002030800070GL 2002 3 8 CA020213008 220020208G7314P94C16602 PUMP AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL FUEL BOOST MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 1 ENGINE FUEL BOOST PUMP WAS MAKING TOO MUCH NOISE AND VIBRATING AS COMPARED TO NR 2 FUEL BOOST PUMP. INSPECTED THE NR 1 ENGINE DRIVEN FUEL PUMP FILTER AND FOUND NON-FERROUS METAL IN THE FILTER. INSPECTED THE FUEL CONTROL FILTER FOR CONTAMINATION AND FOUND NON-FERROUS METAL. THE NR 1 FUEL BOOST PUMP PRESSURE WAS LOWER THAN THE NR 2 FUEL BOOST PUMP PRESSURE. REPLACED FUEL CONTROL, ENGINE DRIVEN FUEL PUMP AND NR 1 FUEL BOOST PUMP. 1G72 3U3 U H11EU E4CE 20020308000712002030800071NE 2002 3 8 CA020213010 220020204G731070077200G600 B-NUT BELL 427 427 1182207SW PWC PW207 PW207D NE FUEL LINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) SMALL AMOUNT OF FUEL OBSERVED LEAKING FROM RT FLOOR CAVITY DRAIN. CAVITY WAS OPENED, FUEL TRANSFER LINE INSPECTED. LEAK ORIGINATED FROM AFT 'B' NUT FITTING. TORQUE WAS CHECKED ON 'B' NUT, WITHIN SPECS. AIRCRAFT DRAINED OF FUEL, LINE REMOVED AND INSPECTED. OUTCOME, STAINLESS BRAIDED FUEL LINE MANUFACTURED TOO SHORT. ORDERED NEW LINE FROM B.H.T. THIS LINE ALSO TOO SHORT. ORDERED NEW LINE, 2ND LINE LENGTH OK. NEW LINE INSTALLED. AIRCRAFT FUELED AND LEAK CHECK C/O. FUEL LEAK SOLVED. 1G71 3U3 U R00001RCE42NE 20020308000722002030800072CE 2002 3 8 CA020213011 120020201G322105411212 SUPPORT CESSNA182 182 2072702CE CONT O470 O470L 17026SO MCAULY2A36C 2A36C29 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT OUTBOARD LANDING GEAR SUPPORT CASTING FOUND TO BE CRACKED IN TWO PLACES. FAULT WAS DISCOVERED WHEN GEAR LEG WAS REMOVED FOR NDT OF LANDING GEAR COMPONENTS. NO OTHER FAULTS FOUND. LANDING GEAR NDT INSPECTION WAS CARRIED OUT AT OWNER'S REQUEST. 1H71 3O3 ONT3A13 E273 5 CP880 20020308000732002030800073SW 2002 3 8 CA020213012 120020125G7920427065244101 LINE BELL 427 427 1182207SW PWC PW207 PW207D NE ENGINE OIL CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MODIFICATION OF AIRCRAFT, NR 2 ENGINE OIL LINES WERE REMOVED. UPON REMOVAL OF LINES IT WAS OBSERVED THAT THE MAIN OIL FEED LINE (FROM OIL COOLER) WAS CHAFED TO A DEPTH OF 0.004 INCH. THE CHAFING OCCURRED IN THE AREA BELOW THE FORWARD ENGINE FIREWALL. THE FIREWALL HAS A STAINLESS STEEL 'TUNNEL' WHICH THE OIL LINES PASS THROUGH. THE FORWARD OUTBOARD EDGE OF THIS TUNNEL CHAFED INTO THE ALUMINUM OIL TUBE. THIS TUBE WAS REMOVED FROM SERVICE. 1G71 3U3 U R00001RCE42NE 20020308000742002030800074SW 2002 3 8 CA020213014 120020202G63202120400545 CASE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE TRANSMISSION CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE LIFT LINK BEARING BOSS WAS FOUND CRACKED DURING ROUTINE MAINTENANCE. 1G71 4U4 U H1SW E17EA 20020308000752002030800075EU 2002 3 8 CA020214002 120020205G24359740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL STARTER GEN FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE IN CRUISE FLT "ESSENTIAL BUS" WARNING LIGHT ILLUMINATED ON CAWS PANEL. NR 2 BATTERY OBSERVED TO BE DISCHARGING AT APPROX 35 AMPS & SELECTED TO OFF POSITION. DISCHARGE RATE FROM BATTERY STOPPED & "ESSENTIAL BUS" LIGHT WENT OUT. WITHIN 3 MINS AOA CAUTION LIGHT CAME ON & LT WINDSCREEN FROSTING OVER. EMERGENCY LANDING REQUIRED & CARRIED OUT WITHOUT INCIDENT. MAINT PERFORMED GROUND RUN & FOUND FOLLOWING: NR 2 GENERATOR INDICATING 28.5 VOLTS BUT NO AMPRE OUTPUT. WHEN PROBE HEAT & LT WINDSCREEN HEATING WERE SELECTED ON. NR 2 BATTERY WOULD SHOW DISCHARGE OF 35 AMPS. THE NR 2 GEN RELAY REMOVED & BENCH TESTED. MAINT FOUND THAT TOP SET OF CONTACTS IN RELAY WERE NOT CLOSING. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020322000132002032200013EA 2002 3 22 CA020215001 120020211G2612 WIRE HARNESS CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE FIRE DETECTION CHAFED W C ABORTED TAKEOFF EY VIBRATION/BUFFET ENGINE STOPPAGE TOTAKEOFF 1 CA (CAN) DURING TAKE-OFF ROLL, THE POWER SET TO TAKE OFF N1, THE SPEED WERE JUST CALLED ALIVE, WHEN THE LEFT ENGINE ROLLED BACK TO IDLE. THE AIRCRAFT WAS TAXIED CLEAR AND WHILE TAXIING BACK TO FBO LEFT ENGINE SHUT DOWN. THE CAS MESSAGE INDICATED HYD SOV 1 AND ENGINE FUEL SOV CLOSED WITH OUT SELECTION. TROUBLESHOOTING REVEALED WIRE BUNDLE LOCATED BEHIND NR 2 EFIS TUBE CHAFING ON THE EFIS CONNECTOR. THE LEFT ENGINE FIRE PUSH BUTTON WIRE MADE CONTACT WITH A LIVEWIRE AND ACTIVATED A FIRE PUSH SELECTION. FOUR WIRES REPAIRED AND WIRE BUNDLE SECURED AS REQUIRED. 2L72 4F4 FRTA21EA E15NE 20020304001222002030400122EA 2002 3 4 CA020215003 120020212G5610NP1393215 WINDSHIELD PPG NP1393215 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE WINDSHIELD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 00229H5665 (CAN) RIGHT WINDSHIELD FOUND CRACKED ON THE GROUND. WINDSHIELD REMOVED AND REPLACED.THE WINDSHIELD INSTALLED WAS A PRE SERVICE BULLETIN WINDSHIELD. 2L72 4F4 FRTA21EA E15NE 20020304001232002030400123EA 2002 3 4 CA020215006 120020116G2613356072310 ELEMENT FENWAL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ELEMENT FAILED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) LEFT 14TH DUCT WARNING ON AT TAKEOFF ROLL ABOVE V, ON EICAS, RED BY ENGINE. AIRCRAFT RETURNED TO TORONTO. RIGHT BLEED LEAK DETECTION CONTROL UNIT AND LOOP SENSING ELEMENT (A58WK) REPLACED.OPERATIONAL TEST OF 14TH STAGE BLEED PERFORMED AND OPERATION TEST OF BLEED LEAK DETECTION PERFORMED.ALL TESTS OK UNABLE TO FAULT SYSTEM, CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020308000772002030800077NM 2002 3 8 CA020215007 120020128G5754 ARM BOEING737 737217 1384464NM PWA JT8 JT8D17 52049NE LE SLAT DISLODGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MAINTENANCE FOUND NR 2 SLAT FOUND PROTRUDING 4 INCHES ON ONE SIDE ON WALKAROUND CHECK. SLAT MECHANISM FOUND OFF GUIDE TRACK. FLIGHT PERMIT (SPECIFIC PURPOSE, FERRY FLIGHT) ISSUED AND AIRCRAFT FLOWN TO BASE FOR REPAIRS. NR 2 LEADING EDGE SLAT DETENT ARM REPLACED AS PER MAINTENANCE MANUAL 51-81-00. SLAT OPERATED THROUGH ENTIRE RANGE SEVERAL TIMES AND OPERATION CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020228000052002022800005WP 2002 2 28 CA020215008 120020214G5302C0231 TAIL CONE ROBSIN C0231 ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA TOP SKIN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 0253 (CAN) 2 INCH CRACK FOUND ON TOP SKIN OF TAIL CONE AT LOCATION OF AFT FACTORY INSTALLED VHF ANTENNA MOUNT 51.5 TO 53.5 INCHES AFT OF FORWARD TAIL CONE SKIN. CRACK APPEARS TO HAVE ORIGINATED FROM TAPERED FACTORY SHIM PN B322-1. 1G71 3O3 O H11NM E295 20020308000852002030800085NE 2002 3 8 CA020215010 220020204G72703021436 DUCT CESSNA501 501 2076603CE PWA JD15 JT15D1A NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING DAILY INSPECTION, RT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED AND PIECE OF REAR UNDER BYPASS DUCT MISSING. AFTER REMOVAL OF THOSE ITEMS FROM THE ENGINE, THE INSPECTION REVEALED THAT THEY WERE PARTS WHICH WAS PREVIOUSLY WELDED/OVERHAUL ASSEMBLY INSTALLED AT THE LAST HOT SECTION INSPECTION.UNDER BYPASS DUCT P/N 3021436 & 3020330 1L72 4F4 F A27CE E25EA 20020228000062002022800006EU 2002 2 28 CA020215011 120020207G28209170M59P03 FUEL LINE GE CF650C2 AIRBUS300 A300B4203 3930306EU GE CF6 CF650C2 30018NE AT 'B' NUT RANGEBROKEN W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA 455262 (CAN) WHILE IN CRUISE THE #1 ENGINE SHUTDOWN BY ITSELF. COULD NOT RE-START THE ENGINE. CAPTAIN DECIDED TO LAND IN HOUSTON, TEXAS. MAINTENANCE FOUND A BROKEN FUEL LINE ON THE MEC GOING TO VARIABLE STATOR ACTUATOR. 2L72 4F4 FRTA35EU E23EA 20020417000682002041700068CE 2002 4 17 CA020215013 120020214G3213358152607 STRUT BEECH 33 35B33 1151406CE RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON INSPECTION PISTON LOWER SHOCK TUBE WAS FOUND WITH CHROME BLISTERED. NDT SHOWED A CRACK IN TUBE.CHROME WAS REMOVED TO EXPOSE THE CRACK WHICH WAS 8 1/4 INCH DOWN FROM THE TOP OF THE TUBE. THE CRACK RAN HORIZONTAL FOR 1 1/2 INCH THROUGH THE TUBE. 1L71 3O 3A15 20020426000732002042600073SW 2002 4 26 CA020215015 120020215G5270V31 SWITCH SWRNGNSA227 SA227AC 8780603SW CARGO DOOR OUT OF ADJUST W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) PART TIME UK PILOT REPORTED THE CARGO DOOR LIGHT CAME ON AFTER 15 MINUTES OF FLIGHT. AIRCRAFT RETURNED TO POINT OF ORIGIN AND DURING SHUTDOWN THE LIGHT WENT OUT. MAINTENANCE FOUND THE CARGO DOOR MICROSWITCH OUT OF ADJUSTMENT. MICROSWITCH ADJUSTED AND AIRCRAFT RETURNED OT SERVICE. 2L72 4T RTA8SW 20020322000142002032200014EU 2002 3 22 CA020215016 120020214G32309740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LANDING GEAR INTERMITTENT W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) LANDING GEAR WOULD NOT EXTEND. PILOT HAD TO USE EMERGENCY EXTENSION. MAINTENANCE FOUND THE POWER PACK RELAY WAS ACTUATING YET NO POWER WOULD GO THROUGH.RELAY WAS REPLACED AND AIRCRAFT RETURNED OT SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020426000742002042600074EU 2002 4 26 CA020218002 120020214G27809450202201 SHAFT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LT LE FLAP BROKEN W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) WHILE ON APPROACH, PILOT REPORTED THAT WHEN HE SELECTED 30 DEGS OF FLAP HE GOT FLAP WARNING ON CAWS PANEL. NO EFFECT ON FLT CONTROLS AND HE LANDED WITH OUT INCIDENT. PILOT RESET FLAPS ON GROUND AND TRIED TO RETRACT FLAPS. FLAPS WOULD NOT RETRACT AND FLAP WARNING ON CAWS PANEL CAME ON. PILOT COULD NOT GET FLAPS TO RESET. MAINTENANCE DISPATCHED FROM PRINCE ALBERT BASE. FLAPS WERE CHECKED FOR ASSEMETARY. IT FOUND THAT LT FLAP 1/2 INCH LOWER THAN RIGHT FLAP. WHEN LEFT INBOARD FLEX SHAFT DISCONNECTED FROM POWER DRIVE UNIT, FLEX SHAFT HAD SHEARED AT SWAGED END THAT GOES INTO POWER DRIVE UNIT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020322000152002032200015NM 2002 3 22 CA020219002 120020215G32321U1085 SEQUENCE VALVE BOEING727 727227 1384078NM PWA JT8 JT8D* NE LT MLG CRACKED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) ON ENGINE START UP FOR DEPARTURE, CREW NOTICED QUANTITY OF "A" SYSTEM HYDRAULICS DROPPING .ENGINE SHUT DOWN MAINTENANCE FOUND LT MLG DOOR LOCK SEQUENCE VALVE HOUSING WAS CRACKED AND LEAKING FLUID.MAINTENANCE REPLACED THE VALVE, A/C WAS POSITIONED GEAR DOWN TO A MAINTENANCE FACILITY FOR A GEAR SWING,WHICH WAS CARRIED OUT AND THE A/C WAS RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20020311000082002031100008CE 2002 3 11 CA020220008 120020213G278099100554 MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE LE FLAPS LOOSE W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) THE SUBJECT LT MOTOR WILL MOVE TO ITS EXTREME END TRAVEL AND LOCK THE ARMATURE CAUSING THE C.B. TO POP AND THE FLAP SYSTEM TO STOP. WHEN THE CB WAS RESET THE FLAPS WOULD OPERATE NORMALLY, THIS HAPPENED TWICE DURING FLAP SELECTION AND WAS SNAGGED IN THE LOG BOOK. WHILE TROUBLESHOOTING THE SNAG, THE LT MOTOR LOCKED AND THE RT MOTOR CONTINUED TO RUN, SHEARING THE DRIVE SPROCKET ON THE RT GEARBOX OUTPUT SHAFT. THE FLAPS STOPPED MOVING AND THE MOTOR CONTINUED TO RUN UNTIL THE LIMIT SWITCH WAS REACHED AND THE MOTOR SHUT OFF. BOTH MOTORS AND GEARBOXES WERE REPLACED. 1L72 4F4 F A22CE E1NE 20020417000692002041700069CE 2002 4 17 CA020220009 120020214G2497AIRDATA115VAC WIRE BEECH 100 B100 1152919CE ADC CHAFED W O OTHER GH MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) TWO DAYS RUNNING THE AIR DATA COMPUTER CIRCUIT PROTECTION FUSE OPENED CAUSING LOSS OF THECAPTAINS ALTIMETER, THE ALTITUDE PRE-SELECT, AND THE MODE C TRANSPONDER FUNCTION. ON THE FIRST DAY THE FAILURE OCCURRED WHILE THE AIRCRAFT WAS AWAY FROM BASE, AND HAD TO BE FERRIED VFR TO EDMONTON WHERE THE ADC AND THE FUSE WERE REPLACED. SPECIAL PERMISSION WAS OBTAINED TO ALLOW THE LANDING IN YXD. ON A RETURN FLIGHT TO CALGARY THE NEXT DAY THE SAME FAILURE OCCURRED AGAIN AFTER APPROXIMATELY 3 HOURS FLYING. THE PROBLEM IS CURRENTLY UNDER INVESTIGATION TO DETERMINE THE CAUSE. SO FAR THE SYSTEM HAS RUN FOR 4 HOURS ON THE GROUND WITHOUT FAILURE. 1L72 4T A14CE 20020311000092002031100009EU 2002 3 11 CA020220010 120020208G243580601401 STARTER GEN AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP ENGINE FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) DURING START SEQUENCE, NR 2 ENGINE FAILED TO ROTATE, START SEQUENCE WAS CANCELLED, AND TRIED A SECOND TIME WITH NO ROTATION OF ENGINE. FAULT WAS TRACED TO THE STARTER GENERATOR, UNIT WAS REPLACED WITH A NEW AND START SEQUENCE WAS OK. NR 2 ENGINE STARTED AS PER MM. THIS IS THE SECOND STARTER GENERATOR FAILURE, THE OTHER HAPPENED 100 HOURS AGO ON NR 3 ENGINE. INSTALLED UPGRADED STARTER/GENERATOR [/N 8060-150. FALCON JET IS AWARE OF THIS PROBLEM. THE NR 1 ENGINE STARTER GEN AND APU STARTER GEN ARE GOING TO BE UPGRADED TO -150. 2L73 4F4 FRTA46EU E6WE 20020409000232002040900023EU 2002 4 9 CA020220011 120020213G5753T700A575000001 INSERT SOCATATBM TBM700 8682000EU PWA PT6 PT6A6A 52043EA TE FLAPS LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING 100 HOUR INSPECTION NOTICED THAT FLAP CARRIAGE INBOARD IS MOVING AT ATTACHMENT. REMOVED FLAP AND CARRIAGE AND FOUND POTTED INSERTS THAT SECURE THE CARRIAGE TO FLAP WERE LOOSE CAUSING DAMAGE TO COMPOSITE RIB, HONEYCOMB (INTERNALLY). ONE OF THE INSERTS WAS FREE TO SPIN. BOND ON INSERT WAS NOT RETAINING. FLAP REMOVED FOR REPAIR. 1L71 3T3 TRTA60EU E4EA 20020325000022002032500002NM 2002 3 25 CA020220014 120020219G331018271 POWER SUPPLY DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE INSTRUMENT PANELFAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 30945 (CAN) THE FLIGHT CREW DETECTED A STRONG BURNING ODOUR SHORTLY AFTER TAKE OFF FROM YTZ - MUCH LIKE "A BURNING CIRCUIT BOARD". THE AIRCRAFT DIVERTED INTO YYZ FOR LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE 5 VOLT POWER SUPPLY FOR THE CAPTAIN'S INSTRUMENT PANEL LIGHTING WAS BURNING. THE POWER SUPPLY WAS REMOVED AND REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020311000112002031100011GL 2002 3 11 CA020220015 120020216G7410N965177 WIRE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU HOFMANHOV352HOV352F NE COIL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOLLOWING A FLIGHT THE ENGINE DID NOT SHUTDOWN WHEN IGNITION SELECTED TO OFF. NO RPM DROP WAS NOTED WHEN SWITCHING IGNITION FROM 'BOTH' TO 'R'.A BROKEN GROUND WIRE WAS FOUUND IN THE IGNITION CIRCUIT. 1L71 3O3 INTTA4CH EXPE3I 5 CTP5BO 20020325000032002032500003EA 2002 3 25 CA020221002 120020221G5711S66422024T8511 SPAR CAP CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK WAS DICOVERED WHILE PERFORMING NDT IN ACCORDANCE WITH AIRWORTHINESS DIRECTIVE CF93-07. WHILE CARRYING OUT REPAIR, ADDITIONAL CRACKING WAS FOUND IN AREA OUTSIDE OF THE INSPECTION PARAMETERS OF AD CF93-07 AT RBL 53 AND RBL 58. 2H72 4R4 RRTA14EA E231 6 CP871 20020426001072002042600107EA 2002 4 26 CA020221004 120020211G324650105711 WHEEL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LT MLG MISSING W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CA (CAN) AFTER FLT. CREW PERFORMED POST FLT INSPECTION AND FOUND LT OB WHEEL ASSY MISSING FROM A/C. THE MISSING WHEEL ASSY RECOVERED IN ATL FROM AIRPORT AUTH. IT OBVIOUSLY DEPARTED WHILE ON TAXI OR TAKEOFF. IT WAS RECOVERED WITH ANTI SKID DRIVE CAP INTACT. NEITHER INNER OR OUTER BEARINGS WERE FOUND IN WHEEL. INNER BORE OF WHEEL DAMAGED BY AXLE AS IT ROTATED AND CAME OFF AXLE. 2L72 4F4 FRTA21EA E15NE 20020228000072002022800007EA 2002 2 28 CA020221005 120020213G7620 ENGINE GE CF343B1 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA 872329 (CAN) AIRCRAFT WAS CLIMBING THROUGH 21K, ENGINE VIBE WENT TO 2.6, THEN ENGINE SHUT DOWN UNCOMMANDED. FLIGHT ATTENDANT REPORTED HEARING A "BANG" IN THE CABIN. ON THE GROUND, OIL WAS NOTED ON THE COWLINGS AND IN THE TAIL PIPE.PREPARATIONS BEING MADE FOR A CREW TO GO TO FWA TO PERFORM ENGINE CHANGE. REMOVED AND AREPLACED ENGINE. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020311000132002031100013 2002 3 11 CA020221006 420020214G22106229815704 CIRCUIT BOARD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE FCC CARD FAILED W K NONE F FLT CONT AFFECTED APAPPROACH 1 CA 56512 (CAN) "ON FINAL TO TXK A/C WAS ALMOST UNCONTROLLABLE. YAW DAMPER THREW A/C IN A LT BANK & THEN A RT BANK WITH AUTOPILOT OFF. IT SETTLED DOWN ENOUGH TO GET A/C ON GROUND."MAINT SIGN OFF AS FOLLOWS: PERFORMED FCC DIAGNOSTICS T/S IAW CRJ MM. NO DEFECTS NOTED. PERFORMED CHECK ON RUDDER PRIMARY & SECONDARY FEEL MECHANISM CENTERING SPRINGS. FOUND PRIMARY SPRING TENSION TO BE AT 5 LBS. SET PRIMARY SPRING TENSION TO 10 LBS IAW CRJ MM. CHECKED RUDDER CONTROL CABLE TENSIONS & PERFORMED RIGGING CHECK IAW CRJ MM. OPS CHECK GOOD. R&R NR 1 & 2 FCC IAPS CARDS IAW CARJ MM. OPS CHECKS WERE GOOD & A/C WAS TEST FLOWN. 2L72 4F4 FRTA21EA E15NE 20020426001122002042600112EA 2002 4 26 CA020221008 120020215G7603NAS464P416 BOLT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE THROTTLE WORN W E ENGINE SHUTDOWN E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) DURING DESCENT, THE FLIGHT CREW WERE UNABLE TO RETARD THE NR 1 THROTTLE LEVER. THE ENGINE WAS SHUTDOWN THROUGH THE GLARE SHIELD'S FIRE PUSH BUTTON. EMERGENCY LANDING WAS DECLARED. MAINTENANCE STAFF VERIFIED THE BOLT SECURING THE "THROTTLE CONTROL LEVER ASSEMBLY" TO THE DOUBLE SPLINE EXHIBITED WEAR. "ROD ASSEMBLY" FOUND DISPLACED, AWAY FROM THE GEARBOX ASSEMBLY UNTIL THE ROD END'S RIVET CONTACTED WITH THE HEAT SHIELD BRACKET (BINDING CONDITION).BOLT REPLACED, THROTTLE CONTROL LEVER ASSEMBLY AND ROD ASSEMBLY REINSTALLED AND SECURED AS PER AMM. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020325000042002032500004NM 2002 3 25 CA020221009 120020201G2170 CLAMP BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE PRECOOLER LOOSE W O OTHER O OTHER CLCLIMB 1 CA (CAN) WHEN REACHING FL330 , THE CABIN ALTITUDE LIGHT CAME NI AND THE RT PACK INOP LIGHT CAME N. WE STARTED DESCENT, THE CABIN STABILIZED AT FL 250. THE RT PACK WAS RESETTED AND FOUND OK. THE CREW STAYED AT THAT LEVEL FOR THE REMAINDER OF THE FLIGHT . MAINTENANCE FOUND A COUPLING /CLAMP ON THE PRECOOLER LINE LOOSE THE COUPLING / CLAMP WAS RESECURED & LEAK CHECKED SERVICEABLE. 2L72 4F4 FRTA2NM E12EU 20020426001152002042600115EA 2002 4 26 CA020221010 120020219G27106009117153 AILERON CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LT WING FROZEN W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA 12611 (CAN) "AT 24,000 FEET DURING CLIMB LEFT AILERON CONTROL FROZE - LIGHT PRESS UNSTUCK CONTROL". VERBAL REPORT FROM PILOT STATES: "PUDDLES OF WATER ON TAXI/RWY WHEN LEAVING MEMPHIS. DID NOT HAVE CONTROL OF AILERON AT 24,000 FEET & MINUS 20 DEG C. DISCONNECTED AILERON CONTROL & CONFIRMED THAT JAM ON PILOTS SIDE. THEN JERKED CONTROLS & RIGHT SIDE RELEASED. RECONNECTED & DESCENDING THROUGH 18,000 FT & WARMER TEMP SYS REMAINED FREE. CONTINUED ON TO DESTINATION AT CINCINNATI". 2L72 4F4 FRTA21EA E15NE 20020503000042002050300004 2002 5 3 CA020221012 420020202G3460 ADC AIRBUS310 A310300 3930305EU COCKPIT OUT OF ADJUST W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AIRCRAFT RETURNED AFTER TAKEOFF WITH MULTIPLE FLIGHT ENVELOPE AND SPEED PROTECTION FAULTS. MAINTENANCE FOUND LOADED FLIGHT PLAN DATA NOT IN AGREEMENT . IRS(INERTIAL REFERENCE SYSTEM) WERE REALIGNED , FLIGHT PLAN DATA REINSERTED AND ALL FMS (FLIGHT MANAGEMENT SYSTEM) FUNCTIONS NORMAL. 2L72 4F RTA35EU 20020426001202002042600120NE 2002 4 26 CA020221017 220020210G7200RB211524B4 ENGINE LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE NR 1 OVERHEATED W F ACTIVATE FIRE EXT. MJ OVER TEMP WARNING INDICATION TXTAXI/GRND HDL 1 CA 14838 (CAN) 2 MINUTES AFTER LANDING , AFTER THRUST REVERSER STOWING , THE FIRST OFFICER CALLED OUT HIGH TGT RAISING RAPIDALY AND ENGINE RUN DOWN , TEMPERATURE ROSE TO 850 DEGREES ON NR 1 ENGINE. THE TAIL PIPE FIRE DRILL WAS CARRIED OUT. MAINTENANCE CARRIED OUT AN HP TURBINE BOROSCOPE IAW MM, NO FAULTS FOUND. THE DFDR WAS REPLACED. THE ENGINE WAS REPLACED FOR COMPANY CONVENIENCE. 2L73 4F4 F A23WE E12EU 20020426001232002042600123NE 2002 4 26 CA020221018 220020202G7230RB21122B02 FAN BLADE LKHEED1011 10113851 5265010WP RROYCERB211 RB21122B02 54555NE NR 2 ENGINE DAMAGED W E ENGINE SHUTDOWN FEJFLT CONT AFFECTED VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF NR 2 ENGINE N1 INDICATION SHOWED 10 PERCENT HIGHER THAN NR 1 AND 3 ENGINES. ALL PARAMETERS WERE THE SAME. WHEN THRUST WAS REDUCED TO LOWER N1 SETTING, NR 2 ENGINE HIGH VIBRATION WAS CONFIRMED ON BOTH CHANNELS AT 2.5 UNITS (VIB. LIGHT ON). ENGINE NR 2 WAS SHUT DOWN PER QRH. AFTER INSPECTION , MAINTENANCE FOUND ICE ACCUMULATION STUCK IN THE DUCT AND MANY LP FAN BLADE TIPS WERE BENT. ALL LP FAN BLADES WERE REPLACED. 2L73 4F4 F A23WE E12EU 20020426001242002042600124EU 2002 4 26 CA020221019 220020218G8530N854115 EXHAUST VALVE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU NR 3 CYLINDER CHIPPED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CLCLIMB 1 CA (CAN) AFTER TAKE-OFF IT WAS NOTED THAT THE ENGINE WAS NOT DEVELOPING FULL POWER. WHEN THE POWER SETTING WAS REDUCED TO ESTABLISH THE AIRCRAFT ON A DOWNWIND LEG A LOW FREQUENCY ENGINE VIBRATION WAS NOTED. A 1/4 INCH DIA CHIP WAS FOUND MISSING ON THE CIRCUMFERENCE OF THE EXHAUST VALVE OF NR 3 CYLINDER. 1L71 3O3 ONTTA4CH E00051EN 20020426001562002042600156NM 2002 4 26 CA020222001 120020214G7830LJ76673 ACCESS PANEL LJ75010 BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE THRUST REVERSER MISSING W O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA 0044 (CAN) WHEN AIRCRAFT LANDED CREW SELECTED REVERSERS, THE NR 2 ENGINE, RT THRUST REVERSER WOULD NOT STOW. DURING THE WALK AROUND, THE CREW FOUND THE NR 2 ENGINE THRUST REVERSER DUCT ACCESS PANEL (P/N LJ76673) RIPPED OFF AND DAMAGE TO THE THE RT TRANSLATING COWL (P/N 75010 ; S/N 0044). THE NR 2 ENGINE THRUST REVERSER FORWARD LATCH ACCESS PANEL HAD A TEMPORARY REPAIR CARRIED OUT I.A.W. ROLLS-ROYCE REPAIR PROJECT-PRODUCT. THE AIRCRAFT RELEASED. 2L72 4F4 FRTA2NM E12EU 20020426000582002042600058CE 2002 4 26 CA020225001 120020225G2710MS276404 BEARING BEECH 1185210588 BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE BALL BEARING CORRODED W O OTHER F FLT CONT AFFECTED ININSP/MAINT 1 CA 1311513115 NA (CAN) R/H AILERON FOUND WITH EXSCESSIVE UP AND DOWN PLAY.PLAY WAS CAUSED DUE TO R/H AILERON TERMINAL BELLCRANK BEARING WORN.BALL INSIDE BEARING WAS FOUND HEAVILY CORRODED AND OUT OF SHAPE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020503000052002050300005EU 2002 5 3 CA020225002 120020220G21405113412233 FAN BLADE 9686781507 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN HEATER BENT W H DEACTIVATE SYST/CIRCUITS O OTHER TXTAXI/GRND HDL 1 CA 483767 (CAN) CREW REPORTS GROWLING NOISE WHEN TURNING ON CABIN HEATER. INSPECTED CABIN HEATER INLET DUCT AND FOUND I.D.TAG FROM BAGGAGE NET JAMMED IN FAN SHROUD. CABIN HEATER REQUIRED REPLACEMENT. INLET IS LOCATED BELOW REAR BAGGAGE AREA AND HAS FAIRLY LARGE GRILL OPENINGS. PILATUS S.B 25-016 REQUIRES INSTALLATION OF I.D. TAGS ON BAGGAGE NETS. TAGS WERE TO BE ATTACHED WITH WIRE CABLE. TAGS SHOULD BE INSPECTED PERIODICALLY FOR SECURITY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000052002032500005EA 2002 3 25 CA020225003 220020211G7200PT6A34 ENGINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA NACELLE DETERIORATED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 12395 (CAN) - DETERIORATION INTERNALLY- COATING DETERIORATED ON SMALL EXIT DUCT WHICH CAUSED DAMAGE TO TURBINE BLADES.- CORROSION THROUGHOUT ENGINE (UNEXPLAINABLE) INSIDE AND OUT - WHITE POWDER. 1H72 3T4 TRTA9EA E4EA 20020417000702002041700070EA 2002 4 17 CA020225004 220020211G7200PT6A34 ENGINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA NACELLE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) - DETERIORATION INTERNALLY- CORROSION THROUGHOUT ENGINE - WHITE POWDER 1H72 3T4 TRTA9EA E4EA 20020311000222002031100022EU 2002 3 11 CA020225005 220020225G8530N854105 INTAKE VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE POST-INSPECTION ENGINE RUN SUBSTANTIAL ENGINE VIBRATION WAS NOTED. THE NR 4 CYLINDER WAS REMOVED AND THE INTAKE VALVE WAS FOUND TO HAVE A CRACK EXTENDING FROM A CENTRAL LOCATION TO THE EDGE OF THE VAVLE. SMALL CHIPS WERE ALSO NOTED TO BE MISSING FROM THE VALVE NEAR THE EDGES. 1L71 3O3 INTTA4CH EXPE3I 20020311000232002031100023EU 2002 3 11 CA020225006 220020225G8530N854105 INTAKE VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE BASE OF THE INTAKE VALVE STEM FROM THE NR 2 CYLINDER WAS FOUND TO BE PITTED. 1L71 3O3 INTTA4CH EXPE3I 20020311000242002031100024EU 2002 3 11 CA020225007 220020225G8530N854115 EXHAUST VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE VALVE SEAT ON THE EXHAUST VALVE FROM CYLINDER NR 2 WAS FOUND TO BE DISHED. 1L71 3O3 INTTA4CH EXPE3I 20020311000252002031100025SW 2002 3 11 CA020226001 120020202G7810114018201 COVER BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE EXHAUST DIFUSER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE DAILY INSPECTOIN, DAMAGE TO THE M/R BLADE WAS NOTICED. INSPECTION OF THE AIRCRAFT REVEALED THAT THE COVER, EXHAUST DIFFUSER, HELD BY A SPEC. BOLT AND TABWASHER ON THE COVER, TURB., REAR WAS MISSING. THE BOLT & TABWASHER WHERE STILL IN PLACE ON THE REAR TURB. COVER. IT SEEMS THAT THE EXHAUST DIFFUSER COVER HAD DISINTEGRATED AND ONE PIECE, APPROX 1 INCH LONG AND .250 INCH WIDE (APPROX 1.0 GR.) WAS SENT THROUGH THE ROTOR DISC FROM THE TAILROTOR, CAUSING THE MAIN ROTOR BALDE DAMAGE. BLADE CHANGE AND SPEC. INSPECTION AS PER MAINTENANCE MANUAL WILL BE CARRIED OUT. 1G71 4U4 U H1SW E17EA 20020321000232002032100023CE 2002 3 21 CA020226002 120020226G7800175400125 MUFFLER CESSNA 175400125 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ON ENGINE CRACKED W O OTHER O OTHER ININSP/MAINT 1 CA NONE (CAN) FOUND DURING AD CF90-03R2 MUFFLER INSPECTION. CRACK FOUND AT BASE OF TAIL PIPE TO MUFFLER CAN CONNECTION. (ALONG WELD BEAD.)MUFFLER REPLACED IN ACCORDANCE ADCF90-03R2. PART 1 SUB PART 5. 1H71 3O3 ONT3A12 E274 5 NP910 20020325000062002032500006 2002 3 25 CA020226003 420020213G31609788132012 DISPLAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CAWS FAILED W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) - POWER FAILURE IN CAWS DISPLAY UPON START UP.- DISPLAY & CONTROL UNIT REMOVED DIRECTED FOR BENCH CHECK.- REPLACED DISPLAY & CONTROL UNIT, NORMAL OPERATION RESULTS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020503000062002050300006EU 2002 5 3 CA020226004 220020214G8550V9277 FITTING GODFREY 139153 GULSTMG159 G159 3952202SO RROYCEDART DART5298X 54507EU ROTOL R4304 R1844304 EU SUPERCHARGER FRACTURED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 23977 (CAN) GEARBOX LOW OIL PRESSURE LIGHT CAME ON, ENGINE SHUTDOWN AND AIRCRAFT LANDED. GEARBOX OIL LEVEL FOUND LOW BUT STILL ON DIP STICK. OIL LEAK TRACED TO FAILED FITTING ON SUPERCHARGER. UNIT HAS OVERHAUL LIFE OF 2,500 HOURS. LINE IS PRESSURE CHECKED (LOW PRESSURE) AT OVERHAUL. CRACK INITIATED FROM UNDER (B) NUT AND WOULD NOT HAVE BEEN VISIBLE AT OVERHAUL. OF 4 EXTERNAL LINES ON UNIT ONLY LINE FROM GEARBOX IS REPLACED AT OVERHAUL. THESE LINES ARE SUBJECT TO HANDLING STRESS. WE ARE LOOKING AT HAVING ALL LINES REPLACED AT EACH OVERHAUL. NOTE: SUPERCHARGER P/N 139312, USES AN OIL LINE WITH BANJO FITTINGS AND CAN THEREFORE BE INSPECTED TO GREATER DEGREE AT OVERHUAL. 2L72 4T4 T 1A17 E297 6 CP899 20020311000262002031100026NE 2002 3 11 CA020226005 220020207G731402532330003 PUMP BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, NOTICED A DRIP OF FUEL COMING OFF OF THE ENGINE DRIVEN FUEL PUMP TO ENGINE FLANGE. WITH A CLOSER LOOK FOUND A BROWN STAIN AS WELL. REMOVED ENGINE DRIVEN FUEL PUMP ASSEMBLY AND INSPECTED. FOUND SPLINE DRIVE COUPLING WHICH ENTERS THE ENGINE ACCESSORY CASE CORRDED AND SEVERELY WORN. ENGINE DRIVEN PUMP ASSEMBLY REPLACED. 1L72 4T4 T A24CE E4EA 20020325000072002032500007CE 2002 3 25 CA020226008 120020220G2823NAS561P36 ROLL PIN CESSNA 12161061 CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO YOKE SHEARED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) FUEL SELECTOR WOULD NOT ROTATE VALVE. DISASSEMBLED AND FOUND PIN SECTION MISSING ALLOWING HOUSING YOKE TO ROTATE ON SHAFT. PIN REPLACED. 1H71 3O3 O A4CE E5CE 20020325000082002032500008EA 2002 3 25 CA020226009 120020213G56106003303026 WINDSHIELD CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) ENROUTE TO KINGSTON, JAMAICA, FROM TORONTO, A CRACK OCCURRED IN THE FACEPLY OF THE CO-PILOT'S WINDSCREEN. ON DESCENT INTO KINGSTON, THE PLY BEGAN TO DELAMINATE. APPROXIMATELY 2/3'S OF THE FACE PLY DEPARTED THE AIRCRAFT PRIOR TO TOUCHDOWN IN JAMAICA. 2L72 4F4 FRTA21EA E15NE 20020325000092002032500009NM 2002 3 25 CA020226011 120020223G291082970009129 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 31242 (CAN) UPON A WALK AROUND INSPECTION, MAINTENANCE NOTICED A LARGE AMOUNT OF FLUID DRIPPING FROM THE LEFT NACELLE. THE LEFT MAIN LANDING GEAR DOORS MECHANICAL SEQUENCE VALVE "DOWN" PRESSURE LINE WAS FOUND LEAKING. THE LINE WAS REPLACED AND THE SYSTEM LEAK CHECKED AND SERVICED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000102002032500010NM 2002 3 25 CA020226012 120020222G291082950010269 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 28282 (CAN) THE FLIGHT CREW REPORTED A HYDRAULIC FLUID LEAK FROM THE RT NACELLE AND NR 4 FLAP TRACK AREA.MAINTENANCE FOUND THE NR 1 HYDRAULIC SYSTEM "DUMP" LINE FOR THE RT INBOARD SPOILER LEAKING. THE LINE WAS REPLACED AND THE SYSTEM LEAK CHECKED AND FUNCTION CHECKED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000112002032500011NM 2002 3 25 CA020226013 120020225G2497242110037C12A1 WIRE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUSELAGE BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 35067 (CAN) FLIGHT CREW REPORTED THAT THE LEFT INTAKE HEATER ADAPTER WAS INTERMITTANT AND LEFT AC "A" PHASE VOLTAGE SHOWED 64-80 VOLTS. AFTER MANY COMPONENTS WERE REPLACED FOR TROUBLESHOOTING, BURNED WIRING WAS FOUND BENEATH THE ENTRANCE FLOOR (WIRING TROUGH) FOR THE AC SYSTEM. THE WIRING WAS REPAIRED IN ACCORDANCE TO SYD 8-24-005. NOTE: AD CF 98-08R2 ADDRESSES SIMILAR PROBLEMS BUT DOES NOTAFFECT THIS AREA OF THE TROUGH!THIS WIRING WAS CHAFED AGAINST THE TROUGH WHICH OVERHEATED AND BURNT THROUGH "A" PHASE. "B" AND "C" PHASE WIRING WAS ALSO DAMAGED BUT NOT A BAD AS "A" PHASE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020503000072002050300007CE 2002 5 3 CA020226014 120020221G56101013840257 WINDSHIELD BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4M HCB4MP3 GL COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) ENROUTE AT FL210 THE OUTER PANE OF THE LEFT WINDSHIELD CRACKED. CREW MADE NORMAL DESCENT TO LOWER ALTITUDE, REDUCED PRESSURIZATION AND RETURNED TO LAND. PART WAS REPLACED WITH NEW P/N 101-384025-21. 1L72 4T4 T A31CE E4EA 6 CP56GL 20020325000122002032500012EU 2002 3 25 CA020226016 120020222G52445711012367 ATTACH FITTING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL OIL COOLER DOOR CRACKED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN ROUTE TO HOME BASE AND 20 MINUTES INTO ITS FLIGHT WNEN THE OIL TEMPERATURE DROPPED FROM 60 C TO 40 C AND THE OIL PRESSURE WENT UP THE BOTTOM OF THE RED LINE WHICH IS 130 PSI.THE PROBLEM WAS THE OIL COOLER DOOR HINGE HOLDER CRACKED AND ALLOWED THE DOOR TO BE INEFFECTIVE IN CONTROLLING THE TEMPERATURE OF THE OIL. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000132002032500013WP 2002 3 25 CA020227001 220020219G7322307080022 FUEL CONTROL LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP LT ENGINE DEFECTIVE W E ENGINE SHUTDOWN M OVER TEMP TXTAXI/GRND HDL 1 CA (CAN) LT ENGINE HOT START ON MANUAL AND COMPUTER MODE. LT FCU REPLACED, GROUND RUNS C/O, GROUD CHECK SERVICEABLE. 2L72 4F4 F A10CE E6WE 20020409000242002040900024SW 2002 4 9 CA020227002 120020225G6310CL422501 CAGE BELL 20604023013 BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL SPRAG CLUTCH WORN W K NONE O OTHER ININSP/MAINT 1 CA B12539 (CAN) THE FREEWHEEL UNIT WAS REMOVED EARLY FOR ITS 1500 HOUR INSPECTION FOR MAINTENANCE CONVIENIENCE. DURING INSPECTION IT WAS NOTED THAT THE CAGE WINDOWS WERE WORN BEYOND THE 0.004 1G71 3U3 U H2SW E4CE 20020304001242002030400124NE 2002 3 4 CA020227003 220020131G8520SL74309 BEARING LYC TIO540J2B PIPER PA31 PA31 7103102SO LYC O540 TIO540J2B NE HARTZLHCC4Y HCC4YR2 GL BEARING DESTROYED W K NONE Y ENGINE STOPPAGE ININSP/MAINT 1 CA L429361A (CAN) #6 CON ROD BEARING FAILURE. PARTS RETURNED TO SUPERIOR AIR PARTS FOR EXAMINATION.THESE BEARINGS ARE A BIMETAL AS OPPOSED TO A TRIMETAL THAT WAS USED FOR MANY YEARS. I HAVE RECIEVED REPORTS FROM AUSTRALIA OF SEVERAL FAILURES OF THIS TYPE OF BEARING 1L72 3O3 O A20SO E14EA 5 CP52GL 20020325000142002032500014EU 2002 3 25 CA020227004 120020226G32429462061335 SWIVEL PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG BRAKE SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYD BRAKE FLUID WAS NOTED LEAKING FROM THE SWIVEL FITTING ON THE BRAKE LINE ,LT MLG TRAILING LINK AREA. PART REPLACED WITH NEW, BRAKES BLED, RETURNED TO SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020503000082002050300008CE 2002 5 3 CA020227005 120020227G323311238002223 ACTUATOR BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE MLG INOPERATIVE W O OTHER N FALSE WARNING LDLANDING 1 CA (CAN) DURING NORMAL APPRAOCH, CREW EXTENDED LANDING GEAR BUT DID NOT GET A NOSE GREEN. GEAR WAS CYCLED WITHOUT CHANGE. EMERGENCY PROCEDURES PROVIDED FOR MANUAL EXTENSION BUT STILL WITHOUT GREEN. DUE TO SYSTEM WIRING, THE GEAR WAS ASSERTAINED DOWN DUE TO THE ABSCENCE OF A RED HANDLE LIGHT WHICH FUNCTIONED NORMALLY. THE GREEN AND RED LIGHTS FUNCTION OFF A DOUBLE POLE SWITCH PROVIDING SOME ASSURANCE OF ACTUAL GEAR POSITION DURING MALFUNCTIONS. DURING TROUBLESHOOTING, THE GEAR FUNCTIONED NORMALLY WITH ALL LIGHTS OPERATING PROPERLY, HOWEVER, THE NOSE GEAR ACTUATOR WAS REPLACED FOR PRECAUTIONARY REASONS AND THE AIRCRAFT RELEASED AFTER NUMEROUS GEAR CYCLES. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020417000712002041700071NE 2002 4 17 CA020227007 320020224G61971293640919 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE AUTOFEATHER SYS SHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS APAPPROACH 1 CA (CAN) DURING CRUISE FLT, CREW NOTICED FAINT SMOKE SMELL, & NOTICED THAT PROP AUTOFEATHER CIRCUIT BREAKER HAD POPPED. THEY DECIDED TO RETURN TO YYC. DURING APPROACH / LDG PHASE OF FLT, SMELL OF SMOKE BECAME MORE NOTICEABLE. THE LDG & TAXIING TO GATE WENT UNEVENTFULLY. DURING MAINT INVEST. SEVERAL WIRES ON BACK OF AUTOFEATHER OFF/ON/ TEST SWITCH WERE SHORTED / MELTED. FURTHER INVEST. REVEALED SHORTED / MELTED WIRES ON POWER LEVER MICROSWITCHES FOR AUTOFEATHER, TRACING SYS FURTHER IT NOTICED THAT A123 PRINTED CCT BOARD P/N 129-364091-9 HAD BURNT TRACKS & DAMAGED COMPONENTS ON IT. ALL COMPONENTS&WIRING WILL BE TESTED/REPL, FOLL OWED BY EXTENSIVE GROUND CHECK OF ENTIRE AU 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020311000292002031100029EU 2002 3 11 CA020227009 220020216G7322961215 NEEDLE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CARBURETOR SHEARED W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) DURING FLIGHT SUDDEN ROUGHNESS OCCURRED, PROP UNRESPONDSIVE WITH POWER FULL, AIRCRAFT RAN ROUGH THE WHOLE FLIGHT BACK, UNABLE TO MAINTAIN ALTITUDE, SLOW DESCENT APPROX 100 FEET/MIN FROM BIRDS HILL TO ST. ANDREWS. WINGS REMOVED AND AIRCRAFT TRANSOORTED TO WINNIPEG BASE, UPON INSPECTION FOUND L/H CARB NEEDLE SHEARED, NEEDLE AND CIRCLIP REPLACED, RT CARB INSP, WINGS REINSTALLED, SAFETIED AND TRAVEL CHECKED, PITOT STATIC TEST CARRIED OUT AS PER AWM 511 APPENDIX B. NO DEFECTS NOTED. AIRCRAFT GROUND RUN AND LEAK CHECKED SERVICEABLE. 1L71 3O3 INTTA4CH EXPE3I 20020325000162002032500016NM 2002 3 25 CA020227010 120020226G3230 LATCH BOEING727 727221 1384071NM PWA JT8 JT8D17 52049NE MLG FAILED W O OTHER O OTHER CLCLIMB 1 CA (CAN) DURING GEAR RETRACTION LEVER LATCH FAILED TO RELEASE ALL OTHER INDICATIONS NORMAL.REPAIRED WIRING AT LEVER LOCK SOLENOID BY REPLACING TERMINAL CONNECTOR LEVER LOCK SYSTEMM OPS TESTED AS PER MM 32-31-11. NO FURTHER DISCREPANCY. 2L73 4F4 F A3WE E2EA 20020325000172002032500017SO 2002 3 25 CA020227011 120020222G2510ASABOVE FRAME PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA SEAT CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY. THE SEAT ASSEMBLY IS VERY DIFFICULT TO INSPECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY. 1L71 3O3 O 2A13 1E10 20020325000182002032500018SO 2002 3 25 CA020227013 120020222G2520 FRAME PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA SEAT CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY.THE SEAT ASSEMBLY IS VERY DIFFICULT TO INSPECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY. 1L71 3O3 O 2A13 1E10 20020325000192002032500019 2002 3 25 CA020228001 420020217G341734100408 ADC BOEING737 737217 1384464NM PWA JT8 JT8D17 52049NE COCKPIT FAILED W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 CA (CAN) JUST AFTER TAKEOFF CAPTAINS AIRSPEED, STANDBY AIRSPEED, GROUND PROX WARNING, AND MACH TRIM INDICATORS FAILED. AIRCRAFT RETURNED TO AIRPORT. NR 1 CENTRAL AIR DATA COMPUTER REPLACED AND OPERATION CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020325000202002032500020NM 2002 3 25 CA020228002 120020123G3211NHA65B0150211 BEARING BOEING747 747475 NM GE CF6 CF680C2* GL RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA MHB950 (CAN) RT BODY GEAR RETRACT ACTUATOR,, LOWER BEARING FAILED.FOUND SPHERICAL BEARING INNER RACE CRACKED THROUGH. LARGE PIECE OF INNER RACE BROKEN OUT. ROLLERS CORRODED AND MISSING. WATER INGRESSION TO BEARING EVIDENT UPON DISASSEMBLY. HIGH LEVEL OF CORROSION TO ROLLERS AND INNER RACE. RETAINING RING AND ATTACHING HARDWARE WORN THROUGH. END ASSEMBLY REPLACED.END ASSEMBLY - 65B01531-4 P/N NHA 65B01502-11 S/N MHB950 2L74 4F4 FRTA20WE E23EA 20020325000212002032500021EU 2002 3 25 CA020228003 120020212G5530D5537002500800 PANEL AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANELS 322AL, 322CL AND 322BL CRACKED. PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. ALSO 322BL. PRODUCTION PERMIT RAISED FOR REPAIR IF BEYOND LIMITS. 2L72 4F4 FRTA28NM E29NE 20020325000222002032500022EU 2002 3 25 CA020228004 120020212G2740D55981002 FITTING AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE RT & LT STAB FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT AND RT THS REAR ATTACH BEARING FOUND LOOSE IN REAR YOKE FITTINGS.BORES IN THE THS LT AND RT REAR SUPPORT FITTING FOUND BEYOND PRODUCTION TOLERANCES. BUSHINGS WILL BE NICKEL PLATED TO RETURN OD DIAMETER. THIS CONSIDERED A PERMANENT FIX FOR THE RT FITTING AND TEMPORARY REPAIR & THE LT IS ACCEPTABLE FOR 4000 FLIGHT CYCLES, AWAITING AIRBUS FINAL DISPOSTION. 2L72 4F4 FRTA28NM E29NE 20020325000232002032500023NM 2002 3 25 CA020228005 120020212G5532D5537002500800 PANEL AIRBUSA319 A319114 3930350NM CFMINTCFM56 CFM565A1 NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANELS 322AL AND 322CL CRACKED. PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. 2L72 4F4 FRTA28NM E29NE 20020321000242002032100024EA 2002 3 21 CA020228008 120020214G5610NP1393225 WINDOW CNDAIR CL6002B19 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE CAPTAIN SIDE CRACKED W O OTHER O OTHER ININSP/MAINT 1 CA 7082 (CAN) DURING FLIGHT L-2 WINDOW DEVELOPED A CRACK. CAPTAINS SIDE WINDOW REPLACED AS PER AIRCRAFT MAINTENANCE MANUAL 56-12-01. 2L72 4F4 FRTA21EA E15NE 20020321000252002032100025EA 2002 3 21 CA020228009 120020204G27603G5209C SPOILER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE L/H OUTBOARD FAILED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) SPOILER FAULT EICAS INDICATES LEFT OUTBOARD SPOILER PROBLEM (WHITE BOX).SEVERAL PREVIOUS SNAGS OCCURRED WITH SYSTEM CHECKED OUT AND NO FAULTS FOUND (INTERMITTENT FAULT). WIRING CHECKED OUT NO FAULT FOUND.FLIGHT SPOILER CONTROL LEVER HANDLE REPLACED. 2L72 4F4 FRTA21EA E15NE 20020325000242002032500024EA 2002 3 25 CA020228010 120020205G2760270003 PCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE SPOILERS FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLIGHT SPOILER CAUTION MESSAGE CAME ON DURING APPROACH. WENT OUT AFTER LANDING. INTERMITTENT PROBLEM THAT OCCURRED SEVERAL TIME IN RECENT PAST. SECU (SPOILER ELECTRONIC CONTROL UNIT) NR 1 FAULT CODES 02,51,E8 DISPLAYED. SECU NR 2 FAULT CODES EC,52,EA DISPLAYED. RIGHT OUTBOARD SPOILER PCU (POWER COANTROL UNIT) REPLACED AND RIGGED. SECU NR 1 AND 2 REPLACED. SYSTEM RESET AND OPERATION CHECKED SERVICEABLE. PCU P/N 27000-3SECU P/N 49-164-05 2L72 4F4 FRTA21EA E15NE 20020304001252002030400125EA 2002 3 4 CA020228012 220020216G7323 GOVERNOR BENDIX 25249994 BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA GOVERNOR W D RETURN TO BLOCK E VIBRATION/BUFFET HOHOVERING 1 CA C8103 (CAN) COCKPIT INDICATION OF ENGINE TORQUE SPLIT DURING HOVER TAXI, AIRCRAFT RETURNED TO RAMP. TORQUE SPLIT CAUSED BY N2 GOVERNOR FAILURE CONFIRMED BY UNIT REPLACEMENT. 1G71 4U4 U H4SW E22EA 20020311000362002031100036SW 2002 3 11 CA020228013 120020201G6220222010405115 SLEEVE BELL 222010400121BELL 222 222B 1182124SW LYC LTS101LTS101750C1 41560NE SWASHPLATE WORN W K NONE O OTHER ININSP/MAINT 1 CA EA73 (CAN) WHEN SWASH PLATE ASSY WAS REMOVED TO FACILITATE 7 YEAR MAST REMOVAL FOR INSPECTION AND RECALIBRATION, THE SLIDER BEARINGS (2OF) P/N 222-310-464-003 WERE FOUND DETACHED AND LOOSE, CREATING AN EXCESSIVE WEAR ON THE SLEEVE JOURNALS THAT HOUSE THESE BEARINGS TO A POINT WELL BEYOND CONTINUED AIRWORTHINESS. THE BALL SLEEVE ASSY AND SUPPORT WERE DEEMED UNSERVICEABLE AND WERE REPLACED AT GREAT EXPENSE. 1G72 3U3 U H9SW E5NE 20020325000262002032500026EA 2002 3 25 CA020228014 120020222G27208220287401 CIRCUIT CARD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RUDDER CONTROL FAILED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AFTER EXCEEDING 250 KTS IAS, RUDDER FLUTTERED UNTIL AIRCRAFT WAS IN LANDING CONFIGURATION. REMOVED AND REPLACED LEFT (UPPER) LHP-4000 CARD IAW AIRCRAFT MM 22-12-01. OPS CHECKED GOOD ON GROUND. 2L72 4F4 FRTA21EA E15NE 20020416000072002041600007EA 2002 4 16 CA020228015 120020228G5610NP13932110 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 13551 (CAN) THE WINDSHIELD INSTALLED WAS A POST SERVICE BULLETIN WINDSHIELD. RT WINDSHIELD CORE PLY CRACKED IN CRUISE AT FL 350. FLIGHT DIVERTEDREMOVED AND REPLACED WINSHIELD. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020311000372002031100037NM 2002 3 11 CA020228016 120020202G7920920024647 HOSE PIPER PA60 PA60601P 7106012NM LYC O540 IO540S1A5 41532EA ENGINE RUPTURED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) TURBO OIL SUPPLY HOSE FROM OPTIONAL FILTER P/N 300180-501 TO WAISTGATE ACTUATOR ROUTED IN CLOSE PROXIMITY TO EXHAUST PIPES WITH SHARP BENDS DUE TO EXTREMITY TIGHT ROUTING. ADDITIONALLY THIS HOSE IS DISTURBED EVERY 50 HOURS DUE TO REMOVAL AND CLEANING OF FILTER ELEMENT CLEANING, SUBJECTING HOSE TO ADDITIONAL STRESSES. HOSE FAILED IN CLIMB OUT, RESULTING IN LOSS OF OIL PRESSURE. 1M72 3O3 ORTA17WE 1E4 20020325000272002032500027NM 2002 3 25 CA020228017 120020205G3320 LIGHT DHAV DHC8 DHC8* NM PWC 150 PW150A EA ROW 20A BURNED OUT W H DEACTIVATE SYST/CIRCUITS A FLAME/FIRE ININSP/MAINT 1 CA (CAN) DURING AN INSPECTION MAINTENANCE NOTICED THE LT SIDEWALL LAMP (FORWARD SHORT OR SECOND FROM THE BACK) AT ROW 20A WAS FOUND BURNED. THE LAMP WAS REPLACED AND APPROXIMATELY 1 HOUR LATER WE HAD A FIRE. THE CREW IMMEDIATELY TURNED THE LIGHTS OFF AND PULLED THE CB. THE 20 AMP CB DID NOT POP. THE ASSEMBLY WAS REMOVED AND REPLACED.IT WAS NOTED THAT THE LOCKING RELEASE DID NOT PROTRUDE AS MUCH AS THE NEW ASSEMBLY INSTALLED. 2H72 4T4 TRTA13NM E00062EN 20020325000282002032500028NM 2002 3 25 CA020228019 120020223G29136617302 PUMP DHAV DHC8 DHC8* NM PWC 150 PW150A EA HYD SYSTEM FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING A FLIGHT THE AIRCRAFT LOST THE RT HYDRAULIC SYSTEM DUE TO PUMP FAILURE DURING CRUISE, AFTER USING THE POWER TRANSFER UNIT (LEFT TO RIGHT HYDRAULIC PUMP) FOR GEAR EXTENSION, NO FLAP MOVEMENT OBSERVED (LEFT HYDRAULIC SYSTEM), A FLAPLESS LANDING WAS PERFORMED. NR 2 EDP REPLACED. CASE DRAIN FILTER BADLY CONTAMINATED WITH METAL. CASE DRAIN, RETURN AND PRESSURE FILTERS REPLACED. ENGINE UNS CARRIED OUT, ALL THREE FILTERS REPLACED, SYSTEM BLEED AND SERVICED. AIRCRAFT RELEASED FOR 25 HOURS PRIOR TO REPLACING FILTERS AGAIN. 2H72 4T4 TRTA13NM E00062EN 20020503000092002050300009EA 2002 5 3 CA020228020 120020215G32606015778827 INDICATOR CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF34* NE NLG MALFUNCTIONED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) AFTER LANDING, GEAR SELECTED TO DOWN, ALL 3 GEAR GREEN ILLUMINATED BUT FLASHING LIGHT IN GEAR HANDLE REMAINED ON. CYCLED GEAR UP, NLG GREEN DOWNLOCK INDICATION AND HANDLE FLASHER REMAINED ON. NO NOSEGEAR DOOR LIGHTS ILLUMINATED, DID NOT HEAR SOUND OF NOSEGEAR RETRACTING. CYCLED WITH SAME EFFECT. DID FLYBY OF TOWER. MAINS WERE DOWN BUT NO SIGN OF NOSEGEAR AND NOSE DOORS WERE CLOSED. RETURNED TO AIRPORT, SELECTED GEAR DOWN AND PULLED MANUAL RELEASE HANDLE. ALL 3 GEAR EXTENDED AS CONFIRMED BY GROUND SUPPORT. NOW INDICATIONS WERE BOTH MAIN GEAR GREEN DOWNLOCK ILLUMINATED, BUT NOSEGEAR GREEN DOWNLOCK LIGHT WENT OUT. FLASHER IN GEAR HANDLE ALSO WENT OUT. A/C LANDED WITHOUT INCIDENT. 2L72 4F4 FRTA21AE E15NE 20020325000292002032500029NE 2002 3 25 CA020301001 220020228G7250 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE RIGHT FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING DJ INFLIGHT SEPARATION WARNING INDICATION CLCLIMB 1 CA (CAN) A/C 7216, FLT 5266 FROM ATW TO CVG. PRELIM INFO.AT 3000 FEET IN CLIMB RIGHT ENGINE SHUTDOWN DUE TO VIBRATION. RETURNED TO ATW. AFT END (LPTM) OF NR 2 ENGINE MISSING. RIGHT HORIZ STAB L/E DAMAGED. VERTICAL STAB APPARENTLY HAS A SMALL HOLE. NO CONFIRMATION OF ANY FUSELAGE PENETRATION OR DENTS. PIE FAIRING DAMAGED. MAINT CREW ALREADY ON GROUND AT ATW SENDING REPL ENGINE, 2 CORE COWLS, PIE FAIRING&JETPIPE CONE. MORE DETAILS WILL BE FURNISHED WHEN KNOWN. ENGINE IS ORIG EQUIP, DELIVERED ON FEB 26, 1998. NO PREVIOUS HISTORY ON ENGINE OTHER THAN ON FEB 10/11 IN ORLANDO FAN BLADES 7 THRU 28 BLENDED OUT FOR ROUGHNESS & R. INLET CROSION ON LOWER HALF REPD.ADD: 2-28-2002 NEGEL KEYS - ARRIVE D ON-SITE AT 22:00 APPROX 2L72 4F4 FRTA21EA E15NE 20020325000302002032500030EA 2002 3 25 CA020301002 120020301G5610601R330331 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA 15704 (CAN) LEFT WINDSHIELD CRACKED DURING DESCENT. REMOVED AND REPLACED WINDSHIELD. 2L72 4F4 FRTA21EA E15NE 20020325000312002032500031EA 2002 3 25 CA020301003 120020301G5610NP1393222 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING CRUISE, COPILOT WINDOW INNER PLY SHATTERED. AIRCRAFT LANDED SAFELY. NEW WINDOW INSTALLED P/N NP-139322-6 AND S/N 01138H8148. 2L72 4F4 FRTA21EA E15NE 20020325000322002032500032 2002 3 25 CA020301004 420020301G6113055032111 BULKHEAD CESSNA 055032111 CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA NONE (CAN) SPINNER WAS NOTICED DEFORMED DURING GROUND HANDLING.SPINNER BULKHEAD FOUND CRACKED AND FLANGE SEPERATED CAUSING SPINNER DEFORMATION. 1H71 3O3 ONT3A12 1E10 5 NP857 20020325000332002032500033SO 2002 3 25 CA020304001 120020227G57404029400 FITTING PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1637016370 (CAN) INSPECTION REVEALED A SMALL CRACK IN THE WEB WHERE IT JOINS THE LOWER RIGHT BOLT HOLE.THE CRACK RUNS PERPENDICULAR TO THE WEB.PART TIME IS UNKNOWN, TIME GIVEN IS AIRFRAME TIME. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020325000342002032500034NE 2002 3 25 CA020304002 220020301G7200 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RIGHT LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 13218 (CAN) DEPARTURE FROM SAN ANTONIO, TEXAS DURING CRUISE PHASE OF FLT NR 2 ENGINE EXHIBITED OIL TEMP OF 185C & PRESSURE OF 27 PSI. CREW C/W WITH AFM PROCEEDURES & SHUTDOWN ENGINE. CREW DECLARED EMERGENCY & LANDED IN EL PASO, TEXAS. MESA SENT 2 MECHANICS TO INVESTIGATE. DURING INVEST. OIL FOUND IN TAIL PIPE & OIL FILTER FOUND TO HAVE CARBON RESIDUE / PIECES IN IT ALSO CARBON RESIDUE FOUND IN B-SUMP SCREENS. GE REP CONSULTED. IT DETERMINED WITH GE THAT ENGINE EXPERIENCED "B-SUMP COKE SHEDDING". GAE SUGGESTED THAT MX CLEAN ALL SCREENS REASSEMBLE & RUN ENGINE AT CRUISE POWER FOR 1 HR THEN REMOVE & CHECK FILTER&SCREENS. FINDING WERE GOOD. A/C THEN FAIRIED TO FRES NO & CHECKED AGAIN PER GE SB 79-0014&AD 2001 2L72 4F4 FRTA21EA E15NE 20020417000732002041700073EA 2002 4 17 CA020304003 120020225G2510C3FF3143 FORK DHAV DHC6 DHC6 2802606EA SEAT BELT MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) PART NOT MANUFACTURED AS PER DEHAVILLAND/BOMBARDIER SPEC. FOUR FORKS FROM INVENTORY FOUND NOT FILLET RADIUS TO O.031 INCH. SEVEN OF EIGHT ON AIRCRAFT SEATS NOT FILLET RADIUS TO O.031 INCH. THIS MAY PUT UNDUE STRESS ON HEAD OF BOLT LEADING TO SEAT BELT RETENTION FAILURE. THESE FORK ARE USED ON ALL POST MOD 6/1601 OR S.O.O.6104 SEATS 1H72 3T RTA9EA 20020503000102002050300010 2002 5 3 CA020304004 420020219G611307526371 BULKHEAD CESSNA182 182N 2072730CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C203 GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SPINNER BULKHEAD FOUND MOUNTED BETWEEN PROP AND CRANKSHAFT FLANGE - BULKHEAD SUPPOSED TO BE MOUNTED ON REAR RACK OF CRANKSHAFT FLANGE. INCORRECT MOUNTING RESULTED IN CRACKED BULKHEAD AND PROP HUB DISTORTION LEADING TO FLUID LOSS. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020325000352002032500035EA 2002 3 25 CA020304005 220020301G8520 CONNECTING ROD PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA LT ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) DURING A SHORT FLIGHT APPROXIMATLY 5 MINUTES. AFTER T/O, PILOTS NOTICED A FAINT CLICKING NOISE FOLLOWED IMMEDIATLY BY A SLIGHT VIBRATION THEN SMOKE FROM THE LT ENGINE. THE ENGINE WAS SHUT DOWN AND FEATHERED IMMEDIATLY. AFTER LANDING VISUAL INSPECTION CONFIRMED THE NR 6 CONNECTING ROD HAD PENETRATED THE CRANKCASE ABOUT 2-3 INCHES OUTBOARD OF THE CASE SPINE. 1L72 3O3 O A20SO E14EA 20020325000362002032500036EU 2002 3 25 CA020304006 220020222G732077208602 SLEEVE TRW CASC509 FOKKERF27 F27MK100 4990617EU RROYCETAY TAYMK65015 EU GOVERNOR ASSY MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 1751 (CAN) TWO FUEL FLOW REGULATORS RECEIVED HAD SLIPPER SLEEVE ASSEMBLIES INSTALLED IN REVERSE MODE. THESE UNITS HAD BEEN PREVIOUSLY REPAIRED BY ROLLS ROYCE BRAZIL AND IT IS ESTIMATED THAT THERE MAY BE 11 (ELEVEN) SIMILAR UNITS. THIS CONDITIION HAS BEEN ASSOCIATED WITH POSSIBLE LOW FLOW AND LOW EPR. 2H72 4T4 F A817 20020325000372002032500037 2002 3 25 CA020305002 420020220G2210 AUTOPILOT SYS BOEING737 73776N 13844CHNM CFMINTCFM567CFM567B22 13802NE COCKPIT MALFUNCTIONED W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ON APPROACH WITH THE AUTOPILOT ENGAGED WHEN AT APPROX. 6300 FT, THE AIRCRAFT PITCHED UP 5-10 DEGREES AND THE AUTO THROTTLES MOVED FORWARD. THE AUTOPILOT WAS DISENGAGFED BY THE COPILOT AND THE AIRCRAFT CONTINUED ITS APPROACH WITH THE AUTOPILOT OFF AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE COMPLETED A SERIES OF AUTOPILOT TESTS AND WERE UNABLE TO IDENTIFY ANY DISCREPANCIES. OPERATOR HAS SENT THE FLIGHT DATA ACQUISITION DATA TO BOEING AND THE AUTOPILOT MANUFACTURER, HONEYWELL ASKING THEM TO PROVIDE AN EXPLANATION AS TO WHAT MAY HAVE CAUSED THE DATA AIRPLANE TO DEPART THE FLIGHT PLAN. 2L72 4F4 FRTA16WE E00055EN 20020325000382002032500038NM 2002 3 25 CA020305003 120020222G2697 WIRE BOEING737 737297 1384480NM PWA JT8 JT8D9A 52048NE APU BAY CHAFED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLT A/C EXPERIENCED FLICKERING LT WING BODY OVERHEAT INDICATION WITH INCREASING FREQ. OVERHEAT LIGHT ILLUMINATED OFF & FLICKERED ON & OFF CONTINUOUSLY WHEN LT ENGINE BLEED VALVE & ISOLATION VALVE WERE CLOSED (WITH APU OFF). FLT CREW CONTACTED MCC & CYCLED VALVES WITH NO RESOLVE.DUE TO ICING CONDITIONS ENROUTE & INABILITY TO CONFIRM BLEED AIR WAS ISOLATED - A/C WAS DIVERTED TO FOR PRECAUTIONARY LDG. FLT CREW PERFORMED ENGINE RUNS & COULD NOT FAULT. MAINT CALLED OUT TO INSPECT - INDICATION PROBLEM WAS ISOLATED TO A SEVERELY CHAFED WIRE IN APU AREA OF OVERHEAT LOOP. TEMP REPAIR CARRIED OUT.A/C RT-SRV WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020325000392002032500039EA 2002 3 25 CA020306001 220020223G7200 COMPRESSOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA RT ENGINE FAILED W E ENGINE SHUTDOWN EA VIBRATION/BUFFET FLAME/FIRE CRCRUISE 1 CA 17593 (CAN) THE AIRCRAFT WAS IN CRUISE FLIGHT AT FL20000. THERE WAS A LOUD BANG THAT SHUCK THE AIRCRAFT AND FLAMES APPEARED COMING OUT OF THE EXHAUST STACKS. THE ENGINE WAS SHUT DOWN AND FEATHERED. FLAMES EXTINGUISHED RIGHT AWAY IN THE STAKES. THERE WAS A SMALL AMOUNT OF FLAME NOTICED IN THE LOUVERS OF THE BLEED AIR VALVE OUTLETS, THAT EXTINGUISHED AFTER A BRIEF PERIOD. THE AIRCRAFT CONTINUED AND LANDED WITHOUT ANY FURTHER DIFFICULTIES. 1L72 4T4 T A24CE E4EA 20020325000402002032500040EA 2002 3 25 CA020306002 120020304G32347179015 HANDLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE MLG SELECTOR FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE, LOUD NOISE COMING FROM NOSE AREA AND MESSAGES (GEAR DISAGREE(W) AND NOSE DOOR (W) POSTED. MESSAGE CLEARED BY THEMSELVES AFTER SEVERAL SECONDS. AIRCRAFT DID AN AIR TURN BACK WHERE IT LANDED SAFELY. AIRCRAFT WAS FERRIED FOR TROUBLESHOOTING. GEAR SWINGS WERE CARRIED OUT BUT UNABLE TO REPRODUCE SNAG. BASED ON THE SYMPTOMS, IT WAS ELECTED TO REPLACE THE PSEU AND THE LANDING GEAR HANDLE.PSEU REMOVED: P/N 8-648-08 S/N 221AIRCRAFT BACK IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020325000412002032500041NM 2002 3 25 CA020306003 120020301G2150 ACM BOEING737 737268 138448QNM PWA JT8 JT8D17 52049NE ACM BAY FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) FLIGHT 183 AIRCRAFT ON FLIGHT TO YWG FROM YHM AND AT CRUISING ALTITUDE, THE FORWARD LAV SMOKE DETECTOR ACTIVATED. THE FLIGHT ATTENDENTS ADVISED THE CAPTAIN OF SMOKE IN THE CABIN AND THE REAR SMOKE DETECTOR GOING OFF. FLIGHT CREW REQUESTED PRIORITY LANDING ING YAM AND LANDED WITHOUT INCIDENT. CFR WAS CALLED OUT AND FOLLOWED AIRCRAFT TO THE GATE - NO REPORT OF SMOKE.MAINTENANCE IN YAM INSPECTED THE AIR CONDITIONING SYSTEM AND SUSPECTED THE LT ACM OIL EAS OVERSERVICED - ACM WAS DRAINED AND AIR CONDITIONING SYSTEM WAS TESTED IAW MM 21-51-00 AND CHECKED SERVICEABLE - NO SMOKE (SMELL) PRESENT.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. AIRCRAFT GROUND CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020325000422002032500042EU 2002 3 25 CA020306004 120020228G56109598110111 WINDOW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A CRACK WAS FOUND IN THE LT SIDE WINDOW IN THE TOP CORNER EXTENDING FORWARD AND AFT FROM A SCREW HOLE. THE CRACK WAS NOT VISIBLE INSTALLED IN THE AIRCRAFT. IT WAS DISCOVERED WHILE REMOVING FOR A DIFFERENT REASON. SIDE WINDOW WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THE SIDE WINDOW CRACK WAS COVERED BY THE WINDOW/WINDSHIELD ONE PIECE RETAINER. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020321000262002032100026SW 2002 3 21 CA020306005 120020305G6220204011143005 BARREL BELL 204011140005BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE INTERIOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA A13534 (CAN) NDT REVEALED A 1.5 INCH CRACK ON THE INTERIOR OF THE COARSE THREADED END. THE CRACK IS NOT VISIBLE ON THE EXTERIOR. 1G71 4U4 U H1SW E17EA 20020409000832002040900083 2002 4 9 CA020307001 420020228G3457 POWER SUPPLY BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA GPS RECEIVER BURNED OUT W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 29472 (CAN) DURING ROUTINE SERVICEABILITY CHECK, WITH GROUND POWER APPLIED TO AIRCRAFT, STRONG BURING SMELL NOTICED IN AIRCRAFT.GPS RECEIVER DISPLAY WENT BLANK. (GPS KLN 90B RECEIVER) SUBSEQUENT INSPECTION FOUND & CONFIRMED BURNING SMELL ORIGINATED FROM GPS RECEIVER. RECEIVER REPLACED AND AIRCRAFT RETURNED TO SERVICE. 1L72 3T4 TRT3A20 E4EA 20020325000432002032500043CE 2002 3 25 CA020307002 120020222G531207126161 BULKHEAD CESSNA182 182K 2072724CE CONT O470 O470C 17026SO FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) REAR BULKHEAD FOUND CRACKED DURING IMPORT INSPECTION. 1H71 3O3 ONT3A13 E273 20020507001072002050700107CE 2002 5 7 CA020307003 120020307G32601148200773 BRACKET BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ATTACHMENT CRACKED W D RETURN TO BLOCK N FALSE WARNING TXTAXI/GRND HDL 1 CA (CAN) CREW BEGAN TAXI FROM OUTSTATION&NOTED THAT "GREEN" NOSEGEAR IND. EXTINGUISHED&"RED" UNSAFE IND. ILLUMINATED. A/C SHUTDOWN, PAX DEPLANED&A/C CHOCKED. MAINT FOUND BRACKET THAT PROVIDES DO WN MICRO SWITCH STRIKE PLATE HAD CRACKED ACROSS ATTACHMENT FLANGE&WORKED ITS WAY UP ALLOWING MICROSWITCH TO "UNMAKE" DURING TAXI. GEAR DOWN&LOCKED&ONLY INDICATING UNSAFE CONDITION. A/C FERRIED TO MAIN FACILITY FOR BRACKET REPL&GEAR SWINGS. A/C RT-SRV. DUE TO LOCATION OF CRACK, IT IS VERY DIFFICULT TO FIND AS HEADS OF ATTACH BOLTS&WASHERS OBSCURE CRACK BY APPROX 70%&ADDITIONAL LOCKWIRING A LSO HIDES DEFECT. ALL CO A/C HAVE BE 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020325000442002032500044CE 2002 3 25 CA020307004 120020222G321107416032 SUPPORT CESSNA 07416032 CESSNA182 182K 2072724CE CONT O470 O470C 17026SO MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT LANDING GEAR OUTBOARD SUPPORT BRACKET CRACKED IN REAR CORNER FROM LANDING GEAR LEG ATTACH BOLT. FOUND ON IMPORT INSPECTION. PERIODIC REMOVAL OF LANDING GEAR LEGS FOR INSPECTION WOULD FACILITATE INSPECTION. 1H71 3O3 ONT3A13 E273 20020325000452002032500045CE 2002 3 25 CA020307005 120020222G5330LM07133343 SKIN CESSNA182 182K 2072724CE CONT O470 O470C 17026SO FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FORWARD FUSELAGE SKIN CORRODED AT FORWARD SKIN BASE OF DOOR POST. STRINGER ENGINE MOUNT CORRODED AT ENGINE MOUNT STRINGER. 1H71 3O3 ONT3A13 E273 20020513000072002051300007SO 2002 5 13 CA020307006 120020306G3242754612 DISK PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA MLG BRAKE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION BOTH LT AND RT MAIN WHEEL BRAKE DISCS WERE FOUND CRACKED. EACH HAD ONE 1/2 INCH CRACK ON THE RING PORTION (BRAKING PORTION). 1L72 3O3 O 1A10 1E4 20020325000482002032500048GL 2002 3 25 CA020307007 320020304G6111A1633109 O-RING MCAULY 2A34C203BC MCAULY2A34C 2A34C203 GL PROPELLER FAILED W O OTHER K FLUID LOSS ININSP/MAINT 1 CA 921402 (CAN) PROPELLER LEAKING RED DYE OIL FROM BLADE NR 2. BLADE NR 2 O-RING FOUND SHREDED WHICH WAS THE REASON FOR THE OIL LEAK. ALSO FOUND 2 CRACKED SLOT BLOCKS AND A WORN ACTUATING PIN ASSEMBLY. 5 CP3EA 20020325000652002032500065CE 2002 3 25 CA020307008 120020228G3060C40536 BRACKET BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA MCAULY4HFR344HFR34C754 NE BRUSH BLOCK BENT W K NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA (CAN) PROP SYNCROPHASER TARGET CONTACTED THE SYNCROPHASER MONOPOLE DAMAGING THE MONOPOLE, MONOPOLE BRACKET AND PROP DE-ICE BRUSH BLOCK BRACKET. THE PROP DE-ICE BRUSH BLOCK BRACKET WAS BENT ENOUGH TO DISPLACE THE PROP DE-ICE BRUSHES ENOUGH TO SHORT ACROSS DE-ICE SLIP RING CAUSING PARALLEL PROTECTION BREAKERS TO POP.AS YOU CAN SEE WITH THE ILLUSTRATION PROVIDED THE WHOLE ASSEMBLY (PROP DEICE BRUSH BLOCK & PROP SYNCROPHASER PICKUP) IS SECURED TO (2) 'A' FLANGE BOLTS. THERE IS A SIGNIFICANT DISTANCE (ARM) THAT IS NOT SUPPORTED WHILE TRYING TO MAINTAIN TARGET TO MONOPOLE GAP (0.032 +/- 0.005). 1L72 4T4 T A24CE E4EA 6 C3PNE 20020325000682002032500068SW 2002 3 25 CA020307009 120020226G632068750121 INSERT BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL COMPESSOR MOUNT LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) OIL LEAKING FROM LOWER STARBOARD COMPRESSOR MOUNT INSERT. ENGINE REMOVED, DISASSEMBLED AND GEARBOX SENT TO ENGINE OVERHAUL FACILITY. 1G71 3U3 U H2SW E4CE 20020325000692002032500069SO 2002 3 25 CA020307010 220020304G8540627307A CASTING CESSNA150 150L 2071826CE CONT O200 O200A 17020SO RT MAG OPENING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE REMOVING COMPONENTS OFF OF THE ACCESORIE CASE, (UN RELATED REPAIR) DISCOVERED VER DEEP PITTING AND CORROSSION AROUND THE RIGHT MAGNETO OPENING.CASTING WAS REPLACED. 1H71 3O3 O 3A19 E252 20020325000702002032500070SW 2002 3 25 CA020307011 120020227G2520206031103043 ANGLE BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 10942 (CAN) WHILE COMPLETING INTERIOR REPAINTING PROCESS, TWO CRACKS WERE DISCOVERED ALMOST IDENTICAL, ORIGINATING FROM THE JOINTS BETWEEN EACH OF THE 3 SEAT PANELS. THE CRACKS WERE EACH APPROX. 2 INCHES IN LENGTH ON THE FORWARD SIDE OF THE ANGLE. 1G71 3U3 U H2SW E4CE 20020325000712002032500071CE 2002 3 25 CA020307012 120020305G326021EN96 SWITCH MTSBSIMU2 MU2B36 5780412CE MLG INTERMITTENT W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) DURING APPROACH, CREW SELECTED GEAR DOWN & NOTHING HAPPENED. THEY BROKE OFF APPROACH & FLEW LOCALLY MAKING SEVERAL ATTEMPTS. EMERGENCY EXTENSION PERFORMED & GEAR LOWERED NORMALLY. INVESTIGATION & SUBSEQUENT GEAR SWINGS COULD FIND NO FAULT & ALL FUNCTIONS WERE NORMAL. NOSE DOWNLOCK SWITCH CHANGED OUT FOR NEW SWITCH AS BEING MOST LIKELY CAUSE OF PROBLEM ALTHOUGH IT COULD NOT BE CONFIRMED. DOOR OPEN SOLENOID (ORIG PART WITH 20,007 HRS) ALSO CHANGED AS BEING NEXT MOST PLAUSIBLE SOURCE OF TROUBLE DUE TO COLD WEATHER, ALTHOUGH IT TESTED OK. A/C GEAR SYS LUBRICATED, RIG CHECKED&SWUNG SEVERAL TIMES & A/C RELEASED FOR RETURN TO SERVICE. 1H72 3T RTA10SW 20020325000722002032500072EA 2002 3 25 CA020307013 120020307G2130GG670800051 SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF34* NE BLEED TEMP INOPERATIVE W B EMER. DESCENT W INADEQUATE Q C CLCLIMB 1 CA (CAN) IN CLIMB, AT FL310 (GOING TO FL390), FLT CREW NOTICED CABIN PRESSURE OF 7700 FT. BY LOOKING AT ECSP, THEY OBSERVED THAT 2 BLEED PRESSURE WERE AT ZERO & THAT BOTH PACKS OUTLINES WERE WHITE. NO MORE PRESSURIZATION & NO MESSAGES WERE POSTED. FLT CREW CARRIED OUT EMERGENCY DESCENT TO FL100 DURING WHICH CABIN ALTITUDE REACHED 11200 FT (THEY GOT CAS MESSAGES CABIN ALT (C) & CABIN ALT (W) DURING DESCENT). AFTER 2 TENTATIVES OF RESETTNG PACKS, CREW ELECTED TO APPLY QRH ABN 2-12 "UNPRESSURIZED FLT PROC" & TO CONTINUE FLT TO DESTINATION AT FL100. ON GROUND MECHANICS REPLACED BOTH BLEED TEMPERATURE SENSORS. 2L72 4F4 FRTA21EA E15NE 20020325000732002032500073SO 2002 3 25 CA020307015 220020304G855022355 GEAR CESSNA150 150L 2071826CE CONT O200 O200A 17020SO OIL PUMP BROKEN W ED ENGINE SHUTDOWN RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) PILOT RETURNED TO BLOCKS AND SHUT ENGINE DOWN AFTER NOTICING THAT THE RPM GAUGE WAS UNSERVICABLE. UPON FURTHER INSPECTION FOUND THAT THE UPPER OIL PUMP GEAR, WHICH IS ALSO THE TACHOMETER DRIVE SHAFT. HAD SPLIT. THE PIECE WAS RECOVERED. AND THE GEAR / SHAFT WAS REPLACED WITH NEW. THE RESULTING DEFECT MAY HAVE ALSO CAUSED SOME WEAR TO THE BUSHING AND OIL PUMP HOUSING. 1H71 3O3 O 3A19 E252 20020325000742002032500074EU 2002 3 25 CA020307016 120020305G2913AE71112112CTD PUMP AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE HYD SYSTEM LOOSE W O OTHER K FLUID LOSS APAPPROACH 1 CA (CAN) DURING FINAL APPROACH INTO YVR, ECAM INDICATION OF GREEN SYSTEM RESERVOIR "UNDERFULL" WAS TRIGGERED, CREW CARRIED OUT PROCEDURES AS DETAILED ON ECAM WHICH INCLUDED DEPRESSURISING BOTH GREEN SYSTEM ENGINE DRIVEN PUMPS. AS A RESULT ON LANDING, AFTER ROLL-OUT A/C HAD TO BE TOWED FROM RUNWAY DUE TO NO NOSE WHEEL STEERING. INSPECTION WAS CARRIED OUT AND FOUND NR 1 HYDRAULIC PUMP(GREEN SYSTEM) ON NR 2 ENGINE PRESSURE LINE WAS LEAKING AT THE E.D.H.P DUE TO "B" NUT HAD BACKED OFF CAUSING A LEAK. "B" NUT WAS TIGHTENED, SYSTEM WAS SERVICED AND LEAK CHECK SERVICEABLE. AIRCRAFT WAS RETURNED TO SERVICE. 1L72 4F4 FRTA46NM E39NE 20020325000752002032500075EU 2002 3 25 CA020308001 120020308G2720102C32016 PULLEY GROB 103CATG103TWNASTIR1660202EU RUDDER PEDAL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PLASTIC PULLEY HAS RADIAL CRACKS COMING FROM THE BEARING, SOME CRACKS EXTEND TO OUTER EDGE. 1K00 G39EU 20020325000762002032500076NE 2002 3 25 CA020308002 220020305G73145008735G PUMP AIRBUS320 A320231 3930325EU IAE V2500 V2500A1 NE FUEL SYSTEM FAILED W CD ABORTED TAKEOFF RETURN TO BLOCK RWJPARTIAL RPM/PWR LOSS INADEQUATE Q C WARNING INDICATION TOTAKEOFF 1 CA 2419124191 (CAN) DURING INITIAL ROLL AT 1.2 EPR THE ECAM MESSAGE "COMP VANE NR 2" APPEARED ON THE UPPER ECAM SCREEN. THE ENGINE EXPERIENCED A LIGHT COMPRESSOR STALL. THE TAKE-OFF WAS REJECTED AT 50 KTS AND THE AIRCRAFT RETURNED TO THE GATE WITH BOTH ENGINES RUNNING. MAINTENANCE OPERATIONS CONTROL DISPATCHED ENGINEERS FROM YYZ. THE HP FUEL PUMP AND FUEL MANAGEMENT UNIT WERE REPLACED. A POWER ASSURANCE TEST WAS CARRIED OUT AND NO FAULTS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE. 2L72 4F4 FRTA28NM E311NE 20020325000782002032500078EU 2002 3 25 CA020308003 120020308G276130829100 VALVE AIRBUS310 A310 EU GE CF6 CF680C2A5 NE SPOILERS UNSERVICEABLE W H DEACTIVATE SYST/CIRCUITS K FLUID LOSS CRCRUISE 1 CA (CAN) FLT 757, LOST OF BLUE HYDRAULIC SYSTEM FLUID IN FLIGHT. HYDRAULIC LEAK WAS FOUND COMING FROM NR 3 RT SPOILER VALVE GROUP AT THE FILTER HOUSING CAP PACKING. AFFECTED SPOILER VALVE GROUP WAS REPLACED AND A/C WAS RETURNED TO SERVICE. 2L72 4F4 FRTA35EU E13NE 20020325000802002032500080WP 2002 3 25 CA020308004 120020308G3220152460101 SLEEVE LKHEED1011 1011385114 WP RROYCERB211 RB21122B02 54555NE NLG TORQUE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING WALKAROUND FOUND NLG UPPER TORQUE LINK RT DETENT SLEEVE BROKEN IN TWO. REPLACED UPPER TORQUE LINK'S RT SPRING, INDEX AND DETENT SLEEVES AND A/C WAS RETURNED TO SERVICE. 2L73 4F4 F A23WE E12EU 20020325000822002032500082CE 2002 3 25 CA020308005 120020307G21002419151133 TUBE LEAR 35 36LEAR 5170601CE PRESSURE MODULE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TUBE ASSEMBLY RUNNING FROM AFT PRESSURE BULKHEAD ALONG THE RT SIDE OF CABIN CEILING TO PRESSURE MODULE HAS VARIOUS AREAS OF CORROSION AND CHAFING DAMAGE ALONG FULL LENGTH. NEW PART INSTALLED. 2L72 4F A10CE 20020429000472002042900047EA 2002 4 29 CA020308006 220020224G741410382588 COIL BENDIX 1068255514 CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MAGNETO WRONG PART W O OTHER R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA GO1FA068 (CAN) NEW OVERHAUL ENGINE FROM LYCOMING. ENGINE 25 HOURS. ENGINE VERY ROUGH BACKFIRE, NO POWER. POINTS DEEPLY PITTED, BRUSH ASSEMBLY WORN AT 25 HOURS. CANADIAN AIRCRAFT COMPONENT CORD STRIP REPORT W/O 2244. WRONG PART NUMBER COIL FOR THIS MAGNETO 10-382588 18 FOR 8 CYLINDERS ENGINE. PARTS REQUIRED:COIL10-382790 QTY 2 BRUSH 10-160844 QTY 2 CONTACT ASSY10-382585 QTY 2 1H71 3O3 ONT3A12 E274 20020410000022002041000002EU 2002 4 10 CA020308007 120020225G5532D5537002600800 PANEL AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANEL 322AL AND 322BL CRACKED. PANEL 322AL APPEARS CRACKED ON BOTH LT AND RT SIDES APROX 4 INCHES BELOW UPPER EDGE. ALSO APPROX. 4 INCHES UP FROM LOWER EDGE ON LT SIDE APPEARS TO BE A THIRD CRACK. 322BL APPEARS TOBE DELAMINATED ON RT SIDE APPROX. 4 INCHES DOWN FROM UPPER EDGE. 2L72 4F4 FRTA28NM E29NE 20020410000032002041000003NM 2002 4 10 CA020308008 120020225G5532D5537002600800 PANEL AIRBUSA319 A319114 3930350NM VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANELS 322BL CRACKED. PANEL 322BL CRACKED. 2L72 4F RTA28NM 20020507001082002050700108NE 2002 5 7 CA020308009 220020217G7200 ENGINE GE CFM565A1 AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE ENGINE FAULTY W O OTHER O OTHER LDLANDING 1 CA 731697 (CAN) BIRD INGESTION/STRIKE ON #2 ENGINE AT TOUCHDOWN.NORMAL REVERSE USED. NO ABNORMAL ENGINE INDICATIONS IN COCKPIT. BIRD STRIKE INSPECTION CARRIED OUT NIL FAULTS FOUND.ENGINE RUN COMPLETE NIL FAULTS FOUND. THRUST REVERSER OPERATION CHECK COMPLETED NIL FAULTS FOUND. AIRCRAFT CONSIDERED SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020410000052002041000005EA 2002 4 10 CA020308011 120020222G2133601R386493 ROD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE OUTFLOW VALVE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT NOT PRESSURIZING ON CLIMB OUT. FLIGHT DIVERTED WITH OVERWEIGHT LANDING. FOUND MAIN PASSENGER DOOR PRESSURE VALVE PUSHROD BROKEN. PUSHROD REPLACED AND RIGGED. PRESSURIZATION CHECK AND OVERWEIGHT LANDING CHECK CARRIED OUT AS PER AMM 05-51-01.NO FAULTS FOUND. 2L72 4F4 FRTA21EA E15NE 20020325000852002032500085NM 2002 3 25 CA020308013 120020228G7931 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LEFT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) START OF THE DAY. NR 1 OIL PRESSURE WOULD GO TO 70PSI. THEN SPIKED TO 90PSI. ALL GROUND TEST SYSTEM NORMAL. ON TAKEOFF ROLL AT V1 NR 1 ENGINE OIL PRESSURE LIGHT CAME ON INTERMITTENTLY AS OIL DROPPED TO 40PSI AT LEAST 3 TIMES OIL PRESSURE THEN RESUMED NORMAL OPERATION. AIRCRAFT FLOWN BACK TO OTTAWA, THE OIL FILTERS, AND SCAVENGE FILTER CHECKED NO METAL FOUND. TALKING WITH ENGINE MANUFACTURER THEY ADVISE TO REPLACE THE PRESSURE REGULATING VALVE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020410000062002041000006CE 2002 4 10 CA020308014 120020306G5620010A31870 WINDOW MTSBSIMU2 MU2B60 5780460CE FUSELAGE MISSING W BA EMER. DESCENT UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) A/C LEVELED OFF AT 20,000 FT, LOUD BANG HEARD FOLLOWED BY IMMEDIATE DE-PRESSURIZATION. A/C WENT TO 6000 FT AND LANDED IN THUNDER BAY. FOUND 1ST WINDOW ON LEFT SIDE PARTIALLY GONE AND 2ND WINDOW ON LT SIDE COMPLETLY GONE. 1H72 3T RTA10SW 20020429000532002042900053SW 2002 4 29 CA020311003 120020306G2497 WIRE AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE HARTZLHCB5M HCB5MA3 GL MAIN BUSS FEEDERCHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION THE MAIN BUSS FEEDER WIRE BETWEEN THE MAIN 120 AMP CIRCUIT BREAKER AND THE COCKPIT BUSS BAR WAS TIE STRAPPED TO THE RT UPPER ENGINE MOUNT TUBE AND WAS CHAFING ON THE 2 BOLT HEADS THAT SECURE THE RT FORWARD FOAM TANK SUPPORT CLAMP. THE WIRE WAS INSPECTED AND FOUND SERVICEABLE. A STANDOFF GROMMET WAS INSTALLED TO ENSURE ADEQUATE CLEARANCE BETWEEN THE ENGINE MOUNT TUBE AND THE HARNESS. 1L71 3T4 TNCA19SW E26NE 6 CP44GL 20020410000072002041000007EA 2002 4 10 CA020311004 120020311G2120 DUCT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RT ACM DAMAGED W BA EMER. DESCENT UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) IN FLT A/C DEPRESSURIZED AT FL 300. CABIN ALTITUDE CLIMBED TO 14,000 FEET. EICAS MESSAGE AUTO PRESS 2 FAIL(S) POSTED. A/C LANDED UNEVENTFULLY. A/C THEN FERRY LYS FOR TROUBLESHOOTING. MDC INDICATON SHOWED CABIN PRESS CONTOLLER NR 2 AT FAULT. CPC 2 REPLACED & SYS TESTED SERVICEABLE. DURING FLT, A/C EXPERIENCED PRESSURIZATION PROBLEMS AGAIN. AT 1500 FT, CABIN ALTITUDE AT 5,800 FEET. A/C DID AIR TURNBACK. 2 OUTFLOW VALVES & THE CABIN PRESSURE CONTROL PANEL (CPCP) WERE REPLACED & SYS TESTED GOOD PENDING TEST FLT. DURING TEST FLT (WHICH ALSO A/C POSING), PRESSURIZATION PROBLEM REAPPEARED. A/C RETURNED. TROUBLESHOOTING REVEALED DAMAGED RT ACM SUPPLY DUCT. 2L72 4F4 FRTA21EA E15NE 20020410000092002041000009EA 2002 4 10 CA020312001 120020312G3213901230602 FITTING 4930 DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE STRUT ATTACHMENTCRACKED W K NONE O OTHER ININSP/MAINT 1 CA TB472 (CAN) RIGHT FLOAT WAS REMOVED FROM AIRCRAFT FOR REPAIRS TO BOTTOM SKIN. UPON REMOVAL, THE FRONT STRUT ATTACH FITTING WAS FOUND CRACKED AT HOLE FOR TAPER PIN. PART IS BEING REPLACED WITH NEW. 1H71 3R3 R A806 5E1 20020325000862002032500086EA 2002 3 25 CA020312002 220020301G8520AEL18840 CAMSHAFT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) METAL FOUND IN OIL FILTER DURING SCHEDULED MAINTENANCE. ENGINE DISMANTLED AT OVERHAUL FACILITY. NR 4 EXHAUST LOBE FOUND TO BE WEARING AFTER 85.2 HOURS SINCE NEW. 1H71 3O3 ONT3A12 E274 5 NP910 20020325000872002032500087EU 2002 3 25 CA020312003 120020222G5412 SKIN BOLKMS117 BK117A4 5626017EU LYC LTS101LTS101650B1 41560NE FIREWALL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) - FIREWALL ASSEMBLY AFT LT.- STA 5896, WL 2830, BL 430 AND WL 2740, BL570.- FIREWALL IS MADE OF 0.016" TITANIUM THROUGH WHICH BOTH THE FIRE EXTINGUISHER AND AIR CONDITIONER TUBING ASSEMBLY FITTINGS PASS. - CRACKS FORM AROUND FITTING HOLES IN TITANIUM. - SUSPECT CRACKS FORM DUE TO EXTREME VIBRATION AS HELICOPTER PASSES THRU TRANSLATIONAL LIFT. FITTINGS ARE RIGID - FIREWALL VIBRATES. 1G72 3U3 U H13EU E5NE 20020410000102002041000010EU 2002 4 10 CA020312004 220020306G85702072000002 LINE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU ENG COOLING LEAKING W B EMER. DESCENT KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) SMELL OF ANTI-FREEZE IN COCKPIT. INVESTIGTION REVEALED THAT COOLANT PIPE HAD MOVED AND RUBBED ON HEAT SHROUD, CAUSING SMALL HOLE ALLOWING ANTI-FREEZE TO LEAK OUT. 1L71 3O3 INTTA4CH EXPE3I 20020410000112002041000011SO 2002 4 10 CA020312005 120020304G2497761488 WIRE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA COCKPIT BURNED W HE DEACTIVATE SYST/CIRCUITSENGINE SHUTDOWN BB SMOKE/FUMES/ODORS/SPARKS SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WHILE THIS A/C WAS TAXIING OUT PILOT NOTICED A BURNING SMELL & THEN SMOKE IN VICINITY OF BREAKER PANEL ON LEFT SIDE OF COCKPIT. SHUT OFF MASTER SWITCH, SHUTDOWN ENGINES & EVACUATED A/C. ON INVESTIGATION FOUND THAT A 20 GAUGE WIRE WAS BURNED ABOUT 1.5 FT IN VICINITY OF BREAKER PANEL. IT ALSO BURNED ABOUT 4 OTHER WIRES IN THIS VICINITY AS WELL. WIRE THAT INITIATED PROBLEM WAS A POWER WIRE THAT OPERATES FASTEN SEAT BELT & NO SMOKING LIGHTS. IT WAS VERY HARD TO DETERMINE WHAT IT HAD SHORTED ON. ALL WIRES WERE REPLACED & PROTECTIVE SHIELDING WAS INSTALLED. BREAKERS FOR THIS SYS ALSO REPLACED. 1L72 3O3 O A20SO E14EA 20020325000882002032500088EU 2002 3 25 CA020312006 120020222G7920 ENGINE AMD FALC20FALCON200 2730150EU GARRTTATF3 ATF36A4 29002WP LEFT LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING BKJSMOKE/FUMES/ODORS/SPARKS FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) THE CREW HAD SMOKE IN THE COCKPIT. THEY NOTICED THAT THE LT ENGINE OIL PRESSURE HAD DROPPED. THEY TURNED OFF THE LT BLEED VALVE WHICH CLEARED THE SMOKE THEN THEY SHUT DOWN THE ENGINE AFTER THEY LANDED. I FOUND A LARGE AMOUNT OF OIL ON THE ENGINE'S TAIL CONE. THE OIL WAS COMING FROM THE NR 4 AND 5 SUMP VENT TUBE. THIS ENGINE HAS HAD THE NR 4 AND 5 CARBON SEALS REPLACED TWICE IN THE LAST YEAR DUE TO OIL LEAKING ON THE VENT TUBE AND HAVING HIGH SUMP PRESSURES. 2L72 4F4 FRTA7EU E7WE 20020503000112002050300011SW 2002 5 3 CA020312007 120020305G2821 CASE MICHDYNAMICS2223666213 BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FUEL FILTER RUPTURED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 4570 (CAN) - AFTER START, FUEL FILTER CLOG LIGHT CAME ON. AIRCRAFT SHUT DOWN AND FOUND FUEL LEAK FROM FILTER HEAD & FOUND BROKEN CASTING. INVESTIGATION FOUND THAT AN INPROPER FUEL VALVE ASSY WAS INSTALLED. THE ASSY DID NOT ALLOW THE SYSTEM TO BLEED OFF IN THE EVENT OF PRESSURE BUILD UP DUE TO EXPANSION OF THE FUEL IN THE SYSTEM WHEN THE AIRCRAFT FUEL VALVE IS IN THE "OFF" POSITION. FUEL EXPANDED WITH THE AIRCRAFT PARKED OUTSIDE, COVERS ON THE ENGINE COWL & CAR HEATER INSTALLED OVERNIGHT. A PROPER FUEL VALVE ASSEMBLY WAS INSTALLED AS PER THE TYPE REQIRED FOR THE "S/N" OF AIRCRAFT. THE FUEL VALVE ASSY INSTALLED HAS A PRESSURE RELIEF VALVE INSTALLED, THE OLD ONE DID NOT. 1G71 3U3 U H2SW E4CE 20020325000902002032500090EA 2002 3 25 CA020312008 220020305G8520LW13282 CRANKCASE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE DAMAGED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DEFECT OBSERVED DURING ROUTINE MAINTENANCE. OIL LEAKING FROM CRANKCASE LT HALF NEAR CENTRE BOLTS THAT SECURE CASES TOGETHER. FURTHER INSPECTION REVEALED A PIN HOLE THAT APPEARS TO ORIGINATE FROM WITHIN/INTERNAL TO THE CRANKCASE. ENGINE REMOVED SENT TO APPROVED OVERHAUL STATION FOR INSPECTION AND POSSIBLE REPAIR. 1H71 3O3 ONT3A19 E223 20020325000912002032500091NE 2002 3 25 CA020312009 220020219G7230310061601 BEARING PWA JT15 JT15D5 52112NE ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE OPERATOR REMOVED THE ENGINE FROM THE AIRCRAFT WHEN HE FOUND EXTENSIVE METAL CONTAMINATION OF THE OIL PRESSURE FILTER. AFTER PERFORMING AN OIL FLUSH, RUN & RECHECK AS SUGGESTED BY THE MAINTENANCE MANUAL. THE ENGINE WAS REMOVED AND SHIPPED TO ATI FOR INVESTIGATION AND CORRECTION.THE CAUSE OF THE METAL CONTAMINATION WAS FOUND TO BE A DAMAGED NR 1 BEARING. THE CAUSE OF THE BEARING FAILURE WAS NOT ABLE TO BE DETERMINED. 4 F E25EA 20020410000122002041000012NM 2002 4 10 CA020312010 120020312G2750734382D TORQUE TUBE DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE TE FLAPS WORN W K NONE F FLT CONT AFFECTED ININSP/MAINT 1 CA 2809528095 (CAN) DURING SHEDULED INSPECTION OF THE FLAP PRIMARY TORQUE TUBE DRIVES.IPC REFERENCE 27-51-00 FIG 5 ITEM 180 , FAULTY TUBE FOUND ON RT WING , 2ND TUBE IN FROM WING TIP ,INBORAD END OF TUBE END HAD RIVET HOLES DRASTICALLY ELONGATED . TORGE TUBE SCHEDULED TO BE REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000922002032500092EU 2002 3 25 CA020313002 120020222G6410355A12004008 BLADE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE TAIL ROTOR WILL NOT BALANCEW O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA (CAN) THE TAIL ROTOR HAS HAD A PROBLEM OF GOING OUT OF BALANCE. THE FIRST TIME IT WENT OUT OF BALANCE HAD TO REMOVE WEIGHT FROM ONE OF THE TIPS OF THE BLADE. THE SECOND TIME HAD TO ADD WEIGHT TO THE BLADE OUT OF BALANCE. THE THIRD TIME THE T/R WENT OUT OF BALANCE HAD TO ADD MAXIMUM WEIGHT TO THE BLADE TIP. REPLACED TAIL ROTOR BLADE ASSEMBLY. 1G71 3U3 U H9EU E19EU 20020410000132002041000013CE 2002 4 10 CA020313003 120020302G2910HYC5005 BRUSHES BEECH 76 76 1153005CE LYC O360 O360A1G6D EA HYD MOTOR WORN W O OTHER R PARTIAL RPM/PWR LOSS DEDESCENT 1 CA (CAN) LANDING GEAR HYDRAULIC POWER PACK MOTOR DID NOT RUN. AIRCRAFT PUT ON JACKS & GEAR SELECTED UP, WITH A LIGHT TAP ON MOTOR GEAR RETRACTED NORMALLY WITHIN ALLOWABLE TIME LIMITS. SAME PROBLEM OCCURRED WHEN GEAR SELECTED BACK DOWN. INVESTIGATION REVEALED BRUSHES WERE BADLY WORN AND COMMUTATOR DAMAGED. BRUSHES ARE INSPECTED PERIODICALLY BUT IT IS NOT A REQUIREMENT TO INSPECT I.A.W. BEECH 76 MAINTENANCE SCHEDULED. WE SUGGEST THAT FIELD WIRES ARE BREAKING DOWN IN MOTOR CAUSING UNUSUALLY SHORT LIFE OF BRUSHES, MOTOR AND POWER PACK ASSEMBLY REPLACED. AIRCRAFT TESTED SERVICEABLE. BRUSHES SHOULD BE INSPECTED NO LESS THAN 500 HOURS. 1L72 3O3 O A29CE E286 20020410000142002041000014CE 2002 4 10 CA020313004 120020308G2997S31064 DIODE CESSNA500 550 2076604CE PWA 530 PW530A NE HYD VALVE MISSING W O OTHER WJ INADEQUATE Q C WARNING INDICATION APAPPROACH 1 CA (CAN) HYDRAULIC POWER STAYED ON WHEN GEAR WAS SELECTED DOWN. FOUND WHEN CESSNA HAD INSTALLED SB 550-32-40 REV.3. THEY DID NOT INSTALL DIODE CAUSING POWER FEEDBACK AND HYDRAULIC CENTRE VALVE STAYING CLOSED. 1L72 4F4 F A22CE E00053EN 20020325000932002032500093EA 2002 3 25 CA020313005 220020305G8520LW12201 CAMSHAFT PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ENGINE ROCKER VALVES INSPECTION, NR 4 CYLINDER INTAKE VALVE LIFT WAS FOUND VERY LOW. THE CYLINDER WAS REMOVED AND CAMSHAFT INTAKE VALVE LOBE WAS FOUND WORN. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT FOR REPAIR. 1L72 3O3 O A20SO E14EA 20020325000942002032500094NE 2002 3 25 CA020313006 220020311G7314 SHAFT PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE FUEL PUMP STRIPPED W E ENGINE SHUTDOWN XY ENGINE FLAMEOUT ENGINE STOPPAGE DEDESCENT 1 CA (CAN) FCU AND FUEL PUMP WAS REMOVED FROM ENGINE. FUEL PUMP TO ENGINE SHAFT WAS FOUND STRIPPED, RESULTING IN FUEL STARVATION. 1L72 3T4 TRTA8EA E4EA 20020410000152002041000015CE 2002 4 10 CA020314001 120020312G2917MS28893C6 PRESSURE SWITCH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HYD PUMP STICKS W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF THE HYDRAULIC PUMP CYCLED ON FOR AN ABNORMAL LENGTH OF TIME WITH THE GEAR SELECTED TO THE UP POSITION. THE LANDING GEAR WAS SELECTED TO DOWN AND THE CIRCUIT BREAKER POPPED. THE CREW CARRIED OUT THE LANDING GEAR EMERGENCY EXTENSION PROCEDURE AND 3 GREEN, DOWN AND LOCKED WAS INDICATED. MAINTENANCE PLACED THE AIRCRAFT ON JACKS AND DETERMINED THAT THE PRESSURE RELIEF VALVE WAS NOT CYCLING AT THE CORRECT TIME ONCE PRESSURE HAD BUILT TO THE PRESCRIBED SETTING. THEREFORE THE HYDRAULIC PUMP WOULD CONTINUE TO RUN FOR LONGER THAN NORMAL. THE PRESSURE RELIEF VALVE / SWITCH WAS REPLACED AND THE LANDING GEAR FUNCTION CHECKS COMPLETED. 1L72 4T4 T A24CE E4EA 20020325000962002032500096EU 2002 3 25 CA020314002 120020312G3222AN427 BOLT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG LINK CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT WAS DELIVERED WITH S/B 32-006 COMPLIED WITH THEREBY NOT REQUIRING INSPECTION EVERY 100HRS OF THE MLG TRAILING LINK BOLTS THE SUBJECT AIRCRAFT HAD THE TRAILING LINK SAFETY BOLTS REMOVED FOR OTHER ACESS AND THEY WERE FOUND TO BE BADLY CORRODED AND GOUGED AND WORN. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020410000162002041000016EU 2002 4 10 CA020315001 120020217G2913704A33690004 BELT SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE HYD PUMP FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN PERFORMING A 100 HOUR INSPECTION ON AIRCRAFT. IT WAS NOTICED THAT THIS HYDRAULIC BELT WAS SPLITTING OR FRAYING AT ITS SEAM.THIS BELT WAS FOUND TO BE INSTALLED CORRECT AS PER EUROCOPTER MAINTENANCE MANUALS.WE INSTALLED A NEW BELT AS THIS ONE WOULD HAVE SPLIT IN TWO AFTER A FEW HOURS OF OPERATION. 1G71 3U3 UNCH9EU E19EU 20020410000172002041000017EA 2002 4 10 CA020315002 120020312G5610601R3303314 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) RT WINDSHIELD CENTRE PLY CRACKED DURING CLIMB. THE WINDSHIELD INSTALLED WAS A POST SERVICE BULLETIN WINDSHIELD. RT WINDSHIELD HAS BEEN REPLACED AND AIRCRFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020410000192002041000019EU 2002 4 10 CA020315005 120020304G2910AE7088224 LINE AIRBUSA340 A340313 EU CFMINTCFM56 CFM565C4 13802NE HYD SYSTEM LEAKING W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AFTER TAKEOFF, DURING FLAP RETACTION ECAM MSG HYDRAULIC BLUE ENGINE PUMP PRESSURE LOW CAME ON INTERMITTENTLY. AIRCRAFT RETURNED TO VANCOUVER. FOUND NR 2 ENGINE RETURN LINE LEAKING FROM A CRACK ELBOW. LINE REPLACED AND LEAK CHECKED OK. ALL FILTERS AND ENGINE GROUND RUN. 2L74 4F4 FRTA197 E37NE 20020410000202002041000020NM 2002 4 10 CA020315006 120020129G5753657094728 PANEL BOEING737 737275 1384485NM PWA JT8 JT8D9A 52048NE RT WING TE FLAPSSHEARED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) PRIOR TO DEPARTURE, FLAPS EXTENDED FOR SREVICE CHECK INSPECTION. UPON RETRACTION RT CLOSURE PANEL AT INBOARD FLAPS HUNG UP AT 10 UNITS.FOUND RT INBOARD CLOSURE PANEL SHEARED CAUSING FLAPS TO JAM. CLOSURE PANEL REMOVED. AIRCRAFT OPERATED PER CDL 57-52-01. AIRCRAFT FERRIED FOR SCRAPPING PROCESS. OPERATIONAL LIFE ENDED AT DESTINATION. 2L72 4F4 F A16WE E2EA 20020410000212002041000021NE 2002 4 10 CA020315007 220020306G72301442M66G06 TUBE BOEING747 747475 NM GE CF6 CF680C2B2 30025NE TURBINE COOLING CRACKED W A UNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA (CAN) ON CLIMB, EICAS ENGINE OVERHEAT NR 2 NAC. FLIGHT CREW FOLLOWED THE CHECK LIST, BLEED OFF, MESSAGE REMAINED. REDUCED THRUST TO APPROX 75 PERCENT POWER, MESSAGE DISAPPEARED. AIRCRAFT RETURNED TO HAWAII. FOUND CRACK AT UPPER BEND OF NR 2 HP TURBINE COOLING TUBE. NO PARTS AVAILABLE. TUBING WELDED AS PER RPODUCTION PERMIT. TUBING TO BE INSPECTED PRIOR EACH FLIGHT UNTIL REPLACED. ENGINE GROUND RUN CARRIED OUT, ALL INDICATIONS NORMAL AND NO LEAK FOUND. AIRCRAFT SERVICEABLE. 2L74 4F4 FRTA20WE E13NE 20020410000232002041000023NE 2002 4 10 CA020315009 220020311G72006558135 B-NUT BOEING737 737210C 1384459NM PWA JT8 JT8D9A 52048NE NR 1 ENGINE LOOSE W A UNSCHED LANDING J WARNING INDICATION TOTAKEOFF 1 CA (CAN) NR 1 ENGINE EPR READ HIGHER THAN NR 2 ENGINE AT TAKEOFF POWER. AIRCRAFT RETURNED TO MAINTENANCE BASE. NR 1 ENGINE INSPECTED AND PT7BD BLEED AIR LINE FOUND LOOSE. LINE TIGHTENED AND TAKEOFF POWER RUN ACCOMPLISHED. ALL PARAMETERS CHECKED NORMAL FOR TYPE. AIRCRAFT RELEASED FOR RETURN TO SERVICE. 2L72 4F4 F A16WE E2EA 20020410000242002041000024EU 2002 4 10 CA020315011 120020314G3310308135 BALLAST AIRBUS310 A310300 3930305EU CABIN FAILED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) ON PUSH BACK THE FLIGHT ATTENDANT NOTICED A STRONG ELECTRICAL BURNING SMELL , NO SMOKE , IN THE FORWARD CABIN LT SIDE . THE AIRCRAFT RETURNED TO THE GATE FOR INVESTIGATION . THE FORWARD CABIN CEILING AREA WAS INSPECTED FOR SIGNS OF A BURNED WIRE OR DISCOLORED EQUIPMENT. MAINTENANCE FOUND THE LT FORWARD CEILING LIGHT BALLASTS SLIGHTLY DISCOLORED. THE BALLAST WAS REPLACED IN ACCORDANCE WITH MM AND ALL ELECTRICAL SYSTEM CHECKED WHILE CEILING OPEN , NO MORE ODORS OR ANY SIGNS OF BURNING. THE BALLASTS WERE RETURNED TO YMX FOR INVESTIGATION. 2L72 4F RTA35EU 20020410000262002041000026EA 2002 4 10 CA020318001 120020315G571121510032242 SPAR CNDAIRCL215 CL2151A10 1900320EA RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKED RIGHT REAR LOWER SPAR CAP BEING REPLACED IN ACCORDANCE WITH CF92-26. FURTHER CRACKING DISCOVERED IN WING SPAR WEB AT RBL 50 DURING REPAIRS. THIS AREA IS OUTSIDE OF THE INSPECTION REQUIREMENTS OF THE AIRWORTHINESS DIRECTIVE. 2H72 4R RTA14EA 20020410000272002041000027EA 2002 4 10 CA020318002 120020318G57202153003156 ANGLE CNDAIRCL215 CL2151A10 1900320EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON THE LEFT HAND SIDE OF THE FUSELAGE, THE DRAG ANGLE THAT JOINS THE FUSELAGE AND WING AT WS 51 WAS FOUND CRACKED DURING THE NORMAL "B" CHECK.THE CRACK IS APPROXIMATLEY ONE INCH(1")LONG FROM THEFRONT FACE TOWARDS THE REAR OF THE ANGLE IN THE BEND RADIUS.* LANDING CYCLES=2451 * BOMB CYCLES=15247 2H72 4R RTA14EA 20020410000282002041000028WP 2002 4 10 CA020318003 220020307G7321UN SPRING GARRTTTPE331TFE33112UHR WP FUEL CONTROL WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN REMOVAL OF THE REAR COVER TO ALLOW RE INDEXING OF THE FLIGHT IDLE FUEL FLOW IT WAS NOTED THE COIL SPRING HAD COME IN CONTACT WITH THE REAR COVER. THE RESULTING FRICTION HAD WORN THE COILS OF THE SPRING 50 PERCENT THROUGH. THE FCU WAS REMOVED AND SENT FOR REPAIR. 4 T E4WE 20020410000292002041000029NE 2002 4 10 CA020318004 220020311G72503022312 TURBINE WHEEL BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE NR 2 ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) DURING HELI-SKI OPRATIONS UNUSUAL, INTERMITTENT VIBRATION FELT BY PILOT & NOTICED TO BE INCREASING WITH TIME. ON-SITE ENGINEER BEGAN TROUBLESHOOTING PROCESS BY REMOVING & INSPECTING ENGINE OIL COOLER BLOWER FANS. ON INSTATI ON NR 2 POWER SECTION COULD NOT BE ROTATED BY HAND TO ALIGN BLOWER. AS IS NOT NORMAL FOR PT6 TWIN PAC A/C GROUNDED & POWER SECTION REPL COMPLETE WITH AFCU, MFCU, FUEL PUMP&BLEED VALVE. GROUND RUN AND TEST FLT INDICATED NORMAL VIBRATION LEVEL&A/C FLOWN TO HOME BASE IN KELOWNA. SHORTLY BEFORE LDG WITH INCREASED POWER SETTINGS VIBRATION RETURNED TO IT'S PREVIOUS LEVEL. 1G71 4U4 U H4SW E22EA 20020410000302002041000030WP 2002 4 10 CA020318005 220020312G7321 FUEL CONTROL GARRTTTPE331TFE33112UHR WP ENGINE FAILED W K NONE O OTHER LDLANDING 1 CA (CAN) FUEL FLOW FROM FLIGHT IDLE TO GROUND IDLE TRANSITION WAS ERRATIC CAUSING AIRCRAFT TO PULL ERRATICALLY ON LANDING. REPLACING THE FCU CORRECTED THE PROBLEM. PREVIOUSLY THERE HAD BEEN MANY ATTEMPTS TO ADJUST THE FCU WITH NO SUCCESS. 4 T E4WE 20020410000312002041000031CE 2002 4 10 CA020318006 120020301G3243 SHUTTLE VALVE LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP BRAKE SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WHEN THE AIRCRAFT WAS PARKED FOR AN EXTENDED PERIOD IN MINUS 20-DEGREE WEATHER WITH THE PARKING BRAKES ON, A PUDDLE OF HYDRAULIC OIL WAS NOTICED UNDER AFT FUSELAGE. INVESTIGATION FOUND THE BRAKE SHUTTLE VALVE ASSY. WAS LEAKING, WHICH WAS THEN REPLACED. 2L72 4F4 FRTT00008WIE6WE 20020410000322002041000032 2002 4 10 CA020318007 420020308G3418 COMPUTER LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP STALL WARNING FAILED W O OTHER O OTHER CLCLIMB 1 CA (CAN) DURING CLIMB AFTER TAKEOFF CREW WAS UNABLE TO SELECT AUTOPILOT. INVESTIGATION FOUND RT STICK SHAKER REGISTER GROUNDED ON NR 2 INTEGRATED COMPUTER. REPLACED STALL WARNING COMPUTER. 2L72 4F4 FRTT00008WIE6WE 20020410000332002041000033WP 2002 4 10 CA020319001 220020308G7260358348 BEARING GARRTTTPE331TPE33110UA 01514WP GEARBOX DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SOAP SAMPLE SENT TO WINSOAP INDICATED INSPECT ENGINE IMMEDIATELY. INSPECTION OF GEAR BOX INDICATED BEARING ON PG DRIVE GEAR WAS FAILING AND MAKING METAL. 4 T E4WE 20020410000622002041000062GL 2002 4 10 CA020319003 220020320G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE FAILED W O OTHER Y ENGINE STOPPAGE TXTAXI/GRND HDL 1 CA 12288 (CAN) ON THE 3RD START OF THE DAY THE PILOT COULD NOT MOTOR THE ENGINE TO START THE AIRCRAFT. PULLED THE STARTER AND TRIED TO TURN N1 GEARTRAIN AND WAS UNABLE TO TURN. TRIED TO TURN THE COMPRESSOR THRU THE BYPASS DOOR BY HAND AND WAS UNABLE TO TURN. REMOVED THE ENGINE FROM THE AIRFRAME. TOOK THE COMPRESSOR OF THE GEARBOX AND WAS STILL UNABLE TO TURN THE COMPRESSOR. NO DAMAGE TO THE FIRST STAGES WAS FOUND ON THE COMPRESSOR. SUSPECTED THAT THE IMPELLAR CLEARANCES ARE TO TIGHT AND HAVE CONTACTED. COMPRESSOR OUT FOR EVALUATION. 1G71 3U3 U H3WE E4CE 20020410000652002041000065NM 2002 4 10 CA020319004 120020317G7500655386511 DUCT BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE NR 1 ENGINE MISSING W A UNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA (CAN) SHORTLY AFTER DEPARTING, FLIGHT CREW RECEIVED A NR 1 ENGINE OVERHEAT INDICATION AND IMMEDIATELY RETURNED TO BASE - AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION REVEALED THE CLAMP FOR THE 8TH STAGE ANTI ICE VALVE WAS MISSING AND THE BLEED DUCT FROM THE ENGINE CORE WAS BENT OUTWARD BLOWING UNREGULATED HOT BLEED AIR INTO THE COWLING CAUSING AN OVERHEAT CONDITION. MAINTENANCE REPLACED THE COWLING ANTI ICE DUCT, AND ATTACHED CLAMP, GROUND RUNS WERE COMPLETED WITH NO FAULTS FOUND - AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020410000662002041000066GL 2002 4 10 CA020320004 220020108G721023035178 GEARBOX BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL ENGINE SEIZED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING START N1 WAS LOST AT 55 PERCENT N1 TROUBLESHOOTING FOUND N1 TACH DRIVE SEIZED. INSPECTION OF GEARBOX BY STANDARD AERO REVEALED OIL PUMP SEIZED. ENGINE HAD JUST BEEN REINSTALLED AFTER REPAIRS TO OIL PUMP IN GEARBOX. ENGINE HAD BEEN RUN ON TEST STAND BEFORE FAILURE AFTER INSTALLATION IN AIRCRAFT. TIME SINCE REPAIR - 00.0 1G71 3U3 U H2SW E1GL 20020410000682002041000068GL 2002 4 10 CA020321001 220020212G7220NAS697A3 ENGINE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE BAY FOD W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UNUSUAL SOUND HEARD FROM THE A/C ON COOL DOWN COMING FROM THE ENGINE INLET AREA. UPON FURTHER INVESTIGATION THE COMPRESSOR HAD FOD. A NUTPLATE ON THE FORWARD SIDE OF THE PARTICLE SEPERATOR, THAT FASTEN THE FOWARD INLET COWLS ON, HAD SPLIT AND HALF OF THE NUT PLATE WENT THRU THE PARTICLE SEPERATOR AND WAS INGESTED BY THE ENGINE. THE NUT PLATE MADE IT THRU THRU THE ENTIRE ENGINE. 1G71 3U3 U H3WE E4CE 20020417000812002041700081NM 2002 4 17 CA020321002 120020315G2131 CONTROLLER BOEING737 7372E3 NM PWA JT8 JT8D15 52051NE CABIN PRESSURE MALFUNCTIONED W A UNSCHED LANDING L NO TEST CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF WHILE CLIMING THROUGH 31,000 FT, CREW NOTICED THAT CABIN ALTITUDE READING 9,500 FT. A/C DESCENTED TO 14,000 FT. CREW DONNED OXYGEN MASKS, AS PER QRC FOR RAPID DEPRESSURIZATION & PROCEEDED TO SELECT MANUAL CONTROL ON PRESUURIZATION PANEL & OUTFLOW VALVE TO CLOSE. CABIN ALTITUDE IND READ BELOW SEA LEVEL & PRESSURE DIFFERENTIAL WENT TO 8.4 PSI CAUSING DISCOMFORT ON EARS FOR EVERYONE. A/C WAS CLEARED TO 10,000 FT. & UNSCHEDULED PRESSURIZATION CHECKLIST COMPLETED TO REDUCE CABIN PRESSURE: FLT RETURNED UNPRESSURIZED & LANDED W/O INCIDENT. MAINT PERFORMED OPAL TEST OF PRESSURE CONTROL SYS AS PER MM 21-31-00 WITH NO FAULTS FOUND. 2L72 4F4 FRTA16WE E2EA 20020410001262002041000126NM 2002 4 10 CA020321003 120020321G575185740004003 STIFFENER DHAV DHC8 DHC8* NM AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THREE SKIN STIFFENERS LOCATED AT STA Y485.000 P/N 85740036-102, STA 447.00, P/N 85740030-102 AND AT STA 419.00, P/N 85740024-102 WERE FOUND TO BE CRACKED ON AFT MOST RIVET HOLE. N.B. PHOTOS ATTACHED. PART CYCLES, TSN, TSO ARE ALL UNKNOWN. 2H72 4T RTA13NM 20020410001272002041000127EU 2002 4 10 CA020321004 120020319G672060102RS1MT33CA BEARING SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A3 41560NE T/R SPYDER ROUGH W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN AIRCRAFT SHUTDOWN AFTER LANDING, A ODD CLICKING NOISE WAS HEARD COMINGFROM TAIL ROTOR AREA.INVESTIGATION UPON DISASSEMBLY FOUND TAIL ROTOR SWASHPLATE BEARING ROUGH. REPLACED ASSEMBLY. 1G71 3U3 U H9EU E5NE 20020503000122002050300012EU 2002 5 3 CA020322002 120020306G67201053176201 SLEEVE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL T/R PITCH CHANGEROUGH W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING MAINTENANCE TO REPLACE RUDDER BELLOWS BETWEEN SUBJECT SLIDING SLEEVE WAS FOUND TO BE VOID OF GREASE AND THE DUPLEX BEARINGS WERE DRY AND "RATTLING" WHEN SPAN. BASE MAINTENANCE STAFF WERE UNAWARE OF THE PRESENCE OF A NEEDLE POINT GREASE FITTING ON THE SLEEVE TO FACILITATE LUBRICATION. STAFF INFORMED ME THEY WERE INSTRUCTED BY THE LAST PERMANENT SUPERVISOR ON PROCEDURES FOR INSPECTION, CLEANING AND LUBRICATING SPLINES BUT WERE UNAWARE OF REQUIREMENTS TO LUBE BEARINGS. (C.A.M.P. CODE 672046 LUBE T/R SLIDING SLEEVE OPS 2,3,4.) 1G72 3U3 U H3EU E4CE 20020410001282002041000128EU 2002 4 10 CA020322003 220020304G7260IPC726120 CAGE BOEING727 727100 1384036NM RROYCETAY TAY65154 EU SHAFT BEARING FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) THE NR 3 CSD/GEN TRIPPED, FOLLOWED BY LOW ENGINE OIL PRESSURE WHICH RESULTED IN AN IFSD DUE TO LACK OF OIL AND PRESSURE. GROUND MAINTENANCE ADDED 6 LITERS/QTS OF OIL TO THE ENGINE AND TOPPED OFF THE CSD. THERE WERE NO REPORTED NOR ANY SIGNS OF EXTERNAL LEAKAGE. ON LOW POWER ENGINE RUN, CSD OIL LEVEL DROPPED. DEBRIS FOUND ON CHIP DETECTORS AND EXCESSIVE OIL IN G/BOX. INITIAL EXAMINATION PRIOR TO STRIP FOUND THAT THE GENERATOR SPUR GEARSHAFT REAR ROLLER BEARING CAGE AND ROLLERS FAILED. 2L73 4F4 FRTA3WE E25NE 20020410001322002041000132CE 2002 4 10 CA020322004 120020312G551207326012 FITTING CESSNA206 TU206C 2073334CE CONT O520 TSIO520C 17040SO HORIZONTAL STAB SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RIVETS THAT ATTACH FITTING TO FORWARD SPAR WERE SHEARED. MOST RIVETS, 10 IN ALL, SHOWED SIGNS OF RINGS AROUND SHANKS AT FITTING/SKIN SEAM. ONE RIVETS WAS SHEARED IN HALF. THERE WERE NO EXTERNAL SIGNS OF ANY PROBLEMS. THE STABILIZER IN QUESTION CAME IN FOR SKINS TO BE REPLACED. HAVING RECOLLECTED A PREVIOUS SDR ON THIS MATTER, WE DECIDED TO CHANGE ALL THE RIVETS 'JUST CAUSE' IN CASE THERE WAS A PROBLEM. THE RINGS AROUND THE SHANKS OF THE NON-SHEARED RIVETS MAY BE FROM WHEN THE RIVETS WERE ORIGINALLY INSTALLED. THEY MAY HAVE SOME STRESSES IMPOSED ON THEM. I CAN'T TELL JUST BY LOOKING AT THEM. 1H71 3O3 O A4CE E8CE 20020513000092002051300009SO 2002 5 13 CA020322005 120020321G55317105907 ANGLE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION THE RT VERTICAL STABILIZER FORWARD SPAR ATTACH TO FUSELAGE BULKHEAD, FOUND THE RT DRAG ANGLE CRACKED. 1L72 3O3 O A20SO E14EA 20020918000012002091800001SW 2002 9 18 CA020322006 120020307G2730 CONTROL CABLE BBAVIA7 7ECA 21101NNSW LYC O235 O235K2C 41505EA ELEVATOR FRAYED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING ACCEPTANCE INSPECTION BEFORE ADDITION TO FLEET, THE TRIM CABLES WERE FOUND TO BE CHAFING ON THE TOP ELEVATOR CABLE. THESE CABLES RUN IN CLOSE PROXIMITY TO ONE ANOTHER AND IT APPEARS THAT THE ELEVATOR CABLE WAS RUN OVER THE TRIM CABLES RATHER THAN UNDER, AND CHAFING RESULTED.ONE TRIM CABLE WAS FRAYED AND THE OTHER HAD A WORN AREA WITHOUT BROKEN WIRES. THE ELEVAOR CABLE HAD ONE BROKEN WIRE.THE DEFECT APPEARS TO HAVE EXISTED SINCE AIRCRAFT MANUFACTURE. 1H71 3O3 O A759 E223 20020410001332002041000133CE 2002 4 10 CA020322007 120020307G3232508202085 ACTUATOR BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA MLG FAILED W O OTHER N FALSE WARNING CRCRUISE 1 CA (CAN) AFTER TAKEOFF GEAR WAS SELECTED UP, BUT SHOWED A RED LIGHT IN GEAR HANDLE. GEAR WAS CYCLED WITH SAME RESULTS. GEAR WAS THEN SELECTED DOWN AND AIRCRAFT CONTINUED TO DESTINATION. CREW THEN NOTICED THAT THE NOSE GEAR DOWN LIGHT WAS NOT LIT. AIRCRAFT DID 2 FLYOVERS TO CONFIRM GEAR WAS DOWN. AIRCRAFT LANDED SAFELY. MAINTENANCE FOUND FAULTY UP POSITION SWITCH. NOSE GEAR IN DOWN POSITION WAS NOT FULLY DOWN. NOSE GEAR ACTUATOREND PLAY FOUND TO BE OUT OF LIMITS. REPLACED UP POSITION SWITCH AND NOSE GEAR ACTUATOR, RIGGED GEAR, AND RETURNED AIRCRAFT TO SERVICE. 1L72 3T4 T A14CE E4EA 20020430000012002043000001SW 2002 4 30 CA020322009 120020319G2810 VENT LINE BELL 206 206B 1181511SW ALLSN 250C 250C20J 03013GL FUEL CELL OBSTRUCTED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING SCHEDULED 100 HOUR ANNUAL & 12 MONTH INSPECTION. PROCEEDED TO CHECK OP OF LOW FUEL WARNING SYS. REMOVED FUEL LINE GOING TO AIRFRAME FUEL FILTER AND ATTACHED LONG FUEL LINE SO WE COULD DRAIN FUEL CELL VIA A/C FUEL BOOST PUMPS. WE PUT A/C POWER ON AND NOTED A/C HAD 80 GALLONS OF FUEL. APPLIED POWER TO A/C FUEL BOOST PUMPS AND STARTED TO DRAIN THE FUEL SYS. NOTED THAT FUEL INDICATOR HAD NOT MOVED OFF ITS INDICATED 80 GALLONS, EVEN THOUGH LARGE AMOUNT OF FUEL HAD BEEN REMOVED FROM A/C. REMOVED FUEL CAP AND FOUND THAT RUBBER FUEL CELL HAD COLLAPSED AND OBSTRUCTED THE VENT LINE. 1G71 3U3 U H2SW E4CE 20020410001342002041000134NE 2002 4 10 CA020322010 220020215G85205999 ROLLER NAMER T6 HARVARDMK4 1922828GL PWA R1340 S3H1 52016NE ENGINE GALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PN 5999 ROLLER STARTED GALLING. LEFT SMALL STEEL FLAKES ON OIL SCREEN WHICH WERE FOUND AND IDENTIFIED DURING INSPECTION. ENGINE NOSE CASE REMOVED, AND CAM RING PN 11768 REMOVED FOR RECONDITIONING.ALL 5999 ROLLERS REPLACED AS A PRECAUTION.IF PROBLEM HAD BEEN FOUND LATER, SERIOUS DAMAGE TO ENGINE WOULD HAVE RESULTED. 1L71 3R3 R EXPA1L71E143 20020410001352002041000135EA 2002 4 10 CA020322012 120020318G274070608 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE HORIZ STAB TRIM FAILED W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA (CAN) WHILE AT THE GATE, STAB TRIM PERFORMED UNCOMMANDED FULL NOSE UP TO FULL NOSE DOWN MOVEMENT. 'STAB CH 2 INOP' STATUS MESSAGE APPEARED. DISCONNECTED STAB TRIM. STAB TRIM RE-ENGAGED SEVERAL TIMES ON ITS OWN. INSTALLED SERVICEABLE HSTCU. OPS CHECKS OF STAB/YAW SYSTEM IAW 27-41-00. 2L72 4F4 FRTA21EA E15NE 20020430000022002043000002EA 2002 4 30 CA020322013 120020318G499038004883 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE APU BAY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) FLIGHT CAREW REPORTED SMOKE AND OIL SMELL IN COCKPIT AND CABIN. EMERGENCY DECLARED AND AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE STARTED APU ON GROUND AND UPON TRANSFER OF BLEEDS TO APU, SMOKE FILLED THE CABIN AND COCKPIT. ALSO, APU OIL PRESSURE CAUTION MESSAGE APPEARED. APU DEFERRED AND THEN LATER REPLACED. FOUND THAT OIL PRESSURE RELIEF VALVE BOSS CRACKED. THIS SAME UNIT WAS PREVIOUSLY REPAIRED BY ALIENCE AVIATOIN FOR THE SAME PROBLEM. RECORDS SHOW NO REPORTED EGT OVERTEMP CONDITIONS. APU REPLACED AND AIRCRAFT RETURNED IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020410001362002041000136EA 2002 4 10 CA020322014 120020318G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 1505114730 (CAN) CLIMBING THROUGH FL240 THE RIGHT COCKPIT SIDE WINDOW CRACKED. SIDE WINDOW REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020410001372002041000137EA 2002 4 10 CA020322015 120020320G3213601R85001103 STRUT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 22055 (CAN) DURING INSPECTION, MAINTENANCE FOUND LT MAIN LANDING GEAR CRACKED. MAIN LANDING GEAR REMOVED AND REPLACED. 2L72 4F4 FRTA21EA E15NE 20020410001382002041000138EA 2002 4 10 CA020322016 120020320G3510380270260 LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE OBSERVER OXYGEN RUPTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) OXYGEN LINE AT OBSERVER MASK RUPTURED. MAINTENANCE REPLACED LINE AND SERVICED THE O2 SYSTEM. LEAK CHECK CARRIED OUT. 2L72 4F4 FRTA21EA E15NE 20020410001392002041000139EU 2002 4 10 CA020325002 120020321G27409443019112 SWITCH 527401202 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL STAB TRIM FAILED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) PILOT REURNED FROM FLIGHT,LANDED AND WAS TAXIING TO HANGER WHEN HE TRIED TO CENTER HIS HORIZONTAL STAB. TRIM.,USING PILOT'SSWITCH ON CONTROL COLUMN. SELECTING "UP" TRIM,THE INDICATOR SHOWED NO MOVEMENT.SO HE USED THE CO'PILOTS SWITCH AND STAB WAS ABLE TO CENTER. INVESTIGATION REVEALED THAT THE PILOTS STAB TRIM SWITCH HAD NO CONTINUITY WHEN SELECTED TO THE "UP" POSITION,AN INTERNAL MALFUNCTION.A NEW SWITCH WAS INSTALLED AND SYSTEM FUNCTIONAL TESTS WERE NORMAL. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020410001402002041000140CE 2002 4 10 CA020325003 120020204G8011 BEARING PM1201 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL STARTER MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 80098702 (CAN) PILOT OF AIRCRAFT FOUND "A PART" BENEATH THE COWLING. COWLINGS WERE REMOVED & ENGINE INSPECTED FOR "MISSING PARTS". REAR SUPPORT BEARING (ROLLER TYPE) FOUND MISSING ON LAMAIR STARTER. PILOT REPORTED FURTHER THAT STARTER WAS STILL ENGAGED TO FLYWHEEL AT THIS TIME. LOSS OF REAR BEARING CAUSED STARTER SHAFT TO DROP OUT OF ALIGNMENT WITH CRANKSHAFT AND LOCKED BENDIX GEAR ONTO FLYWHEEL. SARTER REPLACED WITH SERVICEABLE UNIT. OLD UNIT B.E.R. SCRAP. 1H71 3O3 ONT3A12 E274 5 NP910 20020410001412002041000141CE 2002 4 10 CA020325004 120020318G3211 PIVOT CESSNA172 172RG 2072438CE MLG UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) INSTALLATION OF UNAPPROVED PARTS AS DEFINED BY APPENDIX D - REPORTING UNAPPROVED PARTS USING THE SDR SYSTEM. PARAGRAPH (2)(C). LANDING GEAR PIVOTS DISCOVERED WHICH HAD MATERIAL REMOVED IN ORDER TO ADDRESS THE ISSUES RAISED BY AD 2000-06-06 C IN CONTRAVENTION OF CESSNA APPROVED PRACTICES. 1H71 3O 3A17 20020417000822002041700082CE 2002 4 17 CA020325006 120020317G3230 FUSEABLE PLUG CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO MCAULY3AF32C3AF32C505 GL EMER BLOWDOWN OPEN W B EMER. DESCENT HR ELECT. POWER LOSS-50 PC PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) NORTHWEST OF CALGARY (CYYC)APPROX. 15 MINS AFTER TAKEOFF, A/C SUFFERED TOTAL ELECT. FAILURE: EMERG DESCENT INITIATED. ATC INFORMED. EMERG DECLARED, & PILOT ALTERED COURSE FOR RED DEER, ALBERTS (CYQF). LDG GEAR COULD NOT BE LOWERED IN NORMAL MANNER BECAUSE ELECT. POWER IS REQD TO OPERATE UP/DOWN SELECTOR VALVE. EMERG GEAR EXTENSION NOT SUCCESSFUL OWING TO CIRCUMSTANCES STILL UNDER INVEST.. DECISION MADE TO CARRY ON TO EDMONTON INTERNATIONAL (CYEG) BECAUSE OF SUPERIOR EMERG SRVCS. PILOT MADE CONTACT WITH MAINT PERSONNEL & AFTER DISCUSSION A/C COMMITTED TO LDG - WHEELS UP - ALONGSIDE RWY 20, WHICH COMPLETED W/O SERIOUS DAMAGE TO A/C. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020417000832002041700083CE 2002 4 17 CA020325007 120020322G3260 LANDING GEAR MTSBSIMU2 MU2B60 5780460CE NLG FALSE INDICATIONW O OTHER N FALSE WARNING LDLANDING 1 CA (CAN) AFTER TAKE OFF THE CREW SELECTED GEAR UP, THE GEAR CAME UP AS USUAL BUT THE NOSE GEAR GREEN LIGHT DID NOT GO OUT. THE CREW SELECTED GEAR DOWN BUT GEAR REMAINED UP. NOTE THE NOSE GEAR SWITCH CONTROLS THE ELECTRICS FOR THE GEAR EXTENSION / RETRACTION CREW ATTEMPTED TO PUT GEAR DOWN MANUALLY BUT THE FORWARD GEAR DOORS WOULD NOT RELEASE. NOTE THE AIRCRAFT WENT THROUGH SLUSH ON THE RUNWAY BEFORE DEPARTURECREW LANDED AIRCRAFT WITH GEAR UP.ONCE MAINTENANCE PUT AIRCRAFT ON JACKS AND GOT GEAR DOWN WE COULD NOT DUPLICATE THE SNAG. FURTHER INVESTIGATION REQUIRED 1H72 3T RTA10SW 20020411000012002041100001NM 2002 4 11 CA020325008 120020323G7500652244146 DUCT BOEING727 727243 138408DNM PWA JT8 JT8D9A 52048NE NR 2 ENGINE RUPTURED W CD ABORTED TAKEOFF RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA (CAN) NR 2 ENGINE FAILED ON TAKEOFF WITH AN AUTO PACK TRIP. AFTER ABORTED TAKEOFF THE A/C RETURNED TO THE GATE IN AND SUBSEQUENT INSPECTION REVEALED A RUPTURED 13TH STAGE SADDLE DUCT.NEW DUCT INSTALLED ENGINE GROUND RUN SATISFACTORY AND A/C RELEASED FOR SERVICE. 2L73 4F4 FRTA3WE E2EA 20020411000022002041100002EU 2002 4 11 CA020326001 120020321G2910704A33690004 BELT SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE HYD SYSTEM DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) HYDRAULIC BELT WAS STARTING TO DEBOND NEAR THE DIRECTION OF ROTATION ARROW NEAR THE BONDED JOINT. THE TTSN OF THE BELT BY THE MANUFACTURE IS 600 HOURS. WE HAVE FOUND THAT THE OCCURRENCE OF DEBONDING IS HAPPENING TOO OFTEN, SO OUR INSPECTION OF THE BELT IS MORE OFTEN SINCE WE DO NOT WANT A BELT FAILURE. 1G71 3U3 U H9EU E19EU 20020411000032002041100003NM 2002 4 11 CA020326002 120020323G7932AS3209015016 PACKING 3032324 DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE SCAV TUBE DETERIORATED W C ABORTED TAKEOFF KJ FLUID LOSS WARNING INDICATION TOTAKEOFF 1 CA NA (CAN) ON TAKE-OFF ROLL, LOW OIL PRESSURE CAUTION LIGHT FLICKERED.TAKE-OFF ABORTED.SECOND ATTEMPT WAS MADE OBSERVING PRESSURE GAUGE AND OIL PRESSURE CAUTION LIGHT FLICKERED AGAIN AND OIL PRESSURE PHYSICALLY CONFIRMED TO BE LOW BY GAUGE. TAKE OFF ABORTED AGAIN AND AIRCRAFT RETURNED TO GATE. UPON INVESTIGATION, MAINTENANCE FOUND OIL QAUNTITY LOW, AND NR 3,4,5 BEARING SCAVENGE TUBES LEAKING. O-RINGS WERE REPLACED AND ENGINE GROUND RUN. TEST FLIGHT WAS ALSO CARRIED OUT AND NO LEAKS WERE OBSERVED. L/H ENGINE WAS STARTED AT -25 DUE TO FAILURE OF ENGINE PRE-HEAT SYSTEM, SUSPECT PROBLEM OCCURED DUE TO COLD TEMPERATURE START. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020503000172002050300017EU 2002 5 3 CA020326003 120020307G32205322012072 DRAG LINK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG BROKEN W O OTHER D INFLIGHT SEPARATION APAPPROACH 1 CA (CAN) ON APPROACH PILOT HEARD A LOAD BANG A FEW SECONDS LATER A SECOND LOUD BANG WAS HEARD. THE NOSE GEAR EXTENDED AND GEAR DOWN AND LOCKED LIGHT CAME ON AS WELL AS NOSE GEAR UNSAFE LIGHT. PILOT SLOWED AIRCRAFT DOWN TO GEAR EXTENDED SPEED SELECTED GEAR DOWN. LANDED WITHOUT FURTHER PROBLEM. ON INSPECTION DRAG LINK BROKE BELOW ATTACH POINT FOR HYDRAULIC ACTUATOR. REPLACED DRAG LINK AND SWUNG GEAR. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020411000042002041100004SO 2002 4 11 CA020326004 120020314G21208124402 TUBE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA AIR DISTRIBUTIONSEPARATED W B EMER. DESCENT W INADEQUATE Q C CRCRUISE 1 CA 10123 (CAN) - THE FORWARD RUBBER TUBE ON THE FRESH AIR TUBE BECAME DISCONNECTED IN FLIGHT.- UPON INSPECTION, THE TUBE WAS CLEANED WITH MEK AND RECONNECTED THEN THE SYSTEM WAS TESTED SERVICEABLE. 1L72 3T4 T A8EA E4EA 20020411000052002041100005NE 2002 4 11 CA020326005 220020318G8530399359 CYLINDER HEAD DHAV DHC3 DHC3 2800202EA PWA R1340 S3H1G 52016NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE CYLINDER CRACKED ON TOP OF HEAD. 1H71 3R3 R A815 E142 20020411000062002041100006NE 2002 4 11 CA020326006 220020306G7230M04622AB MODULE BOEING757 757* NM RROYCERB211 RB211535E4B3 NE NR 2 ENG COMP FAILED W E ENGINE SHUTDOWN WM INADEQUATE Q C OVER TEMP CLCLIMB 1 CA 24500 (CAN) AIRCRAFT A/C0125 HAD 3 RAPID VIOLENT VIBRATIONS FELT APPROXIMATELY 2 MINUTES AFTER TAKEOFF. NR 2 ENGINE EGT MAXED OUT AT 903 C. NR 2 ENGINE THROTTLE RETARDED AND EGT REMAINED SOMEWHAT HIGH. ENGINE NR 2 SHUTDOWN SUCCESSFULLY. NO OTHER ABNORMAL INDICATION. ENGINE NR 2 HAD PREVIOUSLY EXPERIENCE A COMPRESSOR STALL ON TAKEOFF AT APPROXIMATELY 1000 AGL AND OVERTEMP TO 903C FOR 2.5 SEC REDUCED POWER TO STOP OVERTEMP AND ENGINE PARAMETERS RETURNED TO NORMAL, FULL POWER TAKEOFF WITH TAI ON OAT 49F, EVENT RECORDED ON MARCH 2, 2002. 2L72 4F4 FRTA2NM E12EU 20020503000182002050300018EA 2002 5 3 CA020326007 120020307G2710 CONTROL CABLE CNDAIRCL604 CL604 1900301EA RT WING AILERON FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION FOUND RT WING OUTBOARD AILERON CONTROL CABLE RUBBING AGAINST TOP AILERON FUEL SYNC TRANSMITTER LINK. FURTHER DETAIL INSPECTION DISCOVERED AILERON DUAL SYNC TRANSMITTER LEVER INSTECTED APPROX 180 DEG. OUT OF NORMAL POS. PERFORMED VISUAL INSPECTION OF RT WING OUTBOARD CONTROL CABLE PER M/M 20-40-00 NO DISCREPANCY FOUND. DETAIL INSPECTION OF AILERON DUAL SYNCHRO LEVER, FOUND SMALL GROOVE OF 0.010 ON EDGE OF LINK. INSPECTED SURROUNDING STRUCTURE FOR ABNORMALITIES, NO DISCREPANCY FOUND. ADJUSTED AILERON DUAL SYNCHRO TRANSMITTER PER M/M 22-11-11. SECURED AILERON DUAL SYNCHRO TRANSDUCER LINK PER M/M 22-11-11. 2L72 4F RTA21EA 20020411000072002041100007NE 2002 4 11 CA020326008 120020326G6320S613520670042 HOUSING SKRSKY S613520600 SKRSKYS61 S61A 814210CNE M/R GEARBOX CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 23186 A14891 (CAN) 6 CRACKS WERE NOTED ON AFT END OF OUTER FLANGE UNDERNEATH STUD HOLES. 2 OF CRACKS ARE UNDER STUD HOLES, WHICH WERE NOT INST WITH STUDS (PRE-TAPPED FOR HEAVY RING GEAR; CURRENTLY PLUGGED). CRACKS ARE ABOUT 0.18-0.27 INCHES LONG MEASU RED FROM CRACK CENTER.IT APPEARED THAT CRACKS RESULTED FROM OVER TAPPING OF STUD HOLES. EXAMINATION OF OF STUD HOLES SHOWED THAT THREADS ARE TAPPED BEYOND DRXXL DEPTH, WITH 4 FLUTE MARKS (WHICH APPEARS TO BE FROM TAPPING TOOL) SHOWN AT BOTTOM OF STUD HOLES. ALL 6 HOLES WITH CRACKS HAVE SAME FLUTE MARKS.THE DEPTH OF TAPPED HOLES HAVE AVERAGE READING OF 1.33 IN. ACCORDING TO SIKORSKY B/P, STUD HOLE IS TAPPED 0.375-16 UNC-3B X 1.18 DEEP PER MXX-S-8879.MAIN GEAR B 2G72 4U H2EA 20020503000192002050300019EA 2002 5 3 CA020326009 120020326G275021515065 ARM CNDAIRCL215 CL2151A10 1900320EA MASS BALANCE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SMALL CRACK FOUND IN RADIUS OF THE BASE OF THE MASS BALANCE ARM. 2H72 4R RTA14EA 20020513000112002051300011EU 2002 5 13 CA020326010 120020325G3213AN427 BOLT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG AXLE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DUE TO PREVIOUS EXPERIENCE REMOVED LEFT AND RIGHT AXLE BOLTS EVEN THOUGH AIRCRAFT WAS POST S/B 32-006 AND DID NOT REQUIRE REMOVAL. BOLT WAS FOUND TO BE WORN AND STEPPED EVEN THOUGH AIRCRAFT WAS LOW TIME.AS BEFORE THERE IS NO REQUIREMENT TO REMOVE THIS BOLT FOR INSPECTION! 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020503000202002050300020SO 2002 5 3 CA020326011 120020319G55524A314003 HINGE EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA ELEVATOR CRACKED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA 1826118261 (CAN) THE PILOT REPORTED INTEMITTENT ELEVATOR CONTROL ABNORMALITY. INSPECTION REVEALED THAT THE RT OUTBOARD ELEVATOR HINGE POINT WAS CRACKED. THE EFFECTED PARTS WHERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A21SO E4EA 20020513000122002051300012CE 2002 5 13 CA020326012 120020325G53115042002857 FRAME BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1572415724 (CAN) DURING AIRFRAME INSPECTION SMOKING RIVETS WHERE DETECTED ON THE AIRCRAFT FUSELAGE. INVESTIGATION REVEALED THAT THE FUSELAGE FRAME AT FLIGHT STATION 207.00 WAS CRACKED. THE FUSELAGE FRAME IS BEING REPLACED IN ACCORDANCE WITH THE MANUFACTURER'S RECOMMENDATIONS 1L72 3T4 T A14CE E4EA 20020513000132002051300013SO 2002 5 13 CA020327002 120020321G57116205600 SPAR PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA LT & RT WING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PLATES TO BOTH THE LEFT & RIGHT ATTACHMENT OF AFT WING SPAR TO FUSELAGE FOUND BADLY CORRODED AND NECESSITATED REPLACEMENT.THIS WILL CAUSE DISSIMILAR METAL. THE PLATES ARE RIVETED TO THE AFT SPAR. NEW PLATES ORDERED. ATTACHED PHOTO SHOWS CONDITION. THE ALUMINUM AFT SPAR INSPECTED FOR CONDITION OF CORROSION AND DETERMINDED SERVICEABLE. ADEQUATE CLEANING AND CORROSION TREATMENT APPLY. 1L71 3O3 O 2A13 E286 20020411000082002041100008SO 2002 4 11 CA020327003 120020321G55406354600 RUDDER PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA VERTICAL STAB CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION INSPECTED RUDDER & CONTROL SYSTEM FOUND CORROSION ON THE HORN ASSEMBLY ON THE STEEL PART. RUDDER REMOVED. HORN DERIVETED. PART SANDBLASTED. INSPECTED FOR CONDITION. FOUND SERVICEABLE CONSIDERING THIS SITUATION THE OWNER WILL BE ADVISED.THIS IS AN IMPORTANT AREA TO INSPECT. 1L71 3O3 O 2A13 E286 20020503000212002050300021EU 2002 5 3 CA020327004 120020320G2917 PRESSURE SWITCH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HYD SYSTEM FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) AFTER TAKEOFF, REPORTED THE HYDRAULIC PUMP SEEMED TO RUN LONGER THAN NORMAL, AND THAT THE UNDER FLOOR HEATER WAS NOT FUNCTIONING. INVESTIGATION REVEALED THAT THE HYDRALIC SYSTEM PRESSURE SWITCH WAS INTERMITTENT, CAUSING THE HYDRAULIC PUMP TO RUN UNTILL THE THERMAL SWITCH SHUT IT OFF, AND ALSO DISABLEING THE UNDER FLOOR HEATER. THE SWITCH WAS REPLACED WITH NEW, AND THE SYSTEM FUNCTIONS NORMALLY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020411000092002041100009SO 2002 4 11 CA020327005 120020321G5751 BALANCE WEIGHT PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA LT & RT AILERON CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AILERON LEFT AND RIGHT BALANCE WEIGHT ASSY FOUND BADLY CORRODED. PART REMOVED SANDBLASTED STEEL PART INSPECTED FOUND SERVICEABLE.ADEQUATE TREATMENT PRFORMED BEFORE REASSEMBLED.THIS IS CONSIDERED VERY IMPORTANT IF NO ACTION TAKEN WILL CAUSE LOST OF CONTROLS FLUTTERING AILERON.SUGGEST THAT PIPER OWNER'S OF PA28 SERIES BE ADVISED AS SOON AS POSSIBLE DUE TO THE FACT OF OLD AGE OF THE AIRCRAFT.AWD WILL SUPPORT THIS SITUATION. 1L71 3O3 O 2A13 E286 20020411000102002041100010EU 2002 4 11 CA020327007 120020315G6710V51313842CR764 BELLOWS BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL DUST BOOT FROZEN W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) WATER HAD FROZEN IN DUST BOOT AND RESTRICTED MOVEMENT OF LONGITUDINAL CONTROL ROD. BELOW HYDRAULIC PACK, ICE REMOVED, THAWED, DRIED OUT AND LIGHTLY SPRAYED WITH METHYL ALCOHOL TO REMOVE ANY FURTHER MOISTURE. 1G72 3U3 U H3EU E4CE 20020503000222002050300022CE 2002 5 3 CA020327008 120020322G32421338931CGNGC STATOR BFGOODRICH 215286 CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE BRAKE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2108 (CAN) WHILE CARRYING OUT A COMPANY DIRECTED INSPECTION, NR 1 STATOR DISC WAS FOUND CRACKED THROUGH, THE OTHER WAS CRACKED IN SEVERAL PLACES. 1L72 4F4 F A22CE E1NE 20020411000112002041100011NM 2002 4 11 CA020328001 120020325G3210651952031 SPACER BOEING727 727223 1384074NM PWA JT8 JT8D15 52051NE MLG MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING LINE MAINT IMPACT DAMAGE NOTICED ON LOWER SEGMENT CLEVIS ASSY. SIDE STRUT HAD BEEN OVERHAULED. THE AIRCRAFT JACKED & UPON INVESTIGATION. IT FOUND THAT EXCESSIVE PLAY BETWEEN CLEVIS ASSY & LOWER SEGMENT OF SIDE STRUT. LOWER SEGMENT REMOVED & FWDED TO REPAIR STATION FOR REVIEW & REPAIR. INVESTIGATION. BY REPAIR FACILITY FOUND THAT SPACER & WASHER WERE MISSING. 2L73 4F4 F A3WE E2EA 20020411000122002041100012EU 2002 4 11 CA020328002 120020315G2742D5598123320000 FITTING AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE HORIZONTAL STAB FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PLAY AT TRIMMABLE HORIZONTAL STABILIZER (THS) REAR ATTACH FITTINGS. THS REAR ATTTACH FITTINGS HAVE PLAY BETWEEN BUSHINGS AND THS LT AND RT AFT ATTACH FITTING BORES. 2L72 4F4 FRTA28NM E29NE 20020411000132002041100013EU 2002 4 11 CA020328003 120020309G291041010029 POWER UNIT AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE HYD SYSTEM FAILED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE AFTER APPROXIMATELY 1.5 HOURS IN FLIGHT, YELLOW HYDRAULIC FLUID LEVEL WENT LOW LEVEL. AIRCRAFT DIVERTED AND LANDED IN WINNIPEG. POWER TRANSFER UNIT (PTU) REPLACED. OPERATION CHECKED SERVICEABLE AS PER AIRCRAFT MAINTENANCE MANUAL REFERENCE 29-23-41-870-051. 2L72 4F4 FRTA28NM E29NE 20020411000142002041100014EA 2002 4 11 CA020328007 120020316G2742AC94A0855 SWITCH CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE STAB TRIM FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STABILIZER TRIM AND MACH TRIM TRIPPED OFF IN FLIGHT, WOULD NOT RE-ENGAGE. REPLACED CAPTAINS STAB TRIM DISCONNECT SWITCH, FUNCTIONAL TEST CARRIED OUT. AIRCRAFT FOUND SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020411000152002041100015NM 2002 4 11 CA020328009 120020320G3246BACB30MT826 TIE BOLT BOEING757 757236 1384971NM RROYCERB211 RB211535E43754555NE MLG WHEEL SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A "RAMP 1 CHECK" ONE TIE BOLT WAS FOUND BROKEN ON NR 6 MAIN WHEEL ASSY. MAINTENANCE REPLACED THE MAIN WHEEL ASSY.I.A.W. MM 33-45-01. 2L72 4F4 FRTA2NM E12EU 20020411000162002041100016CE 2002 4 11 CA020328011 120020315G3232 ACTUATOR BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA MLG WORN W K NONE O OTHER ININSP/MAINT 1 CA 10000 (CAN) AT ROUTINE END PLAY CHECK, FOUND EXCESS END PLAY AFTER ONLY 1004 CYCLES.ACTUATOR REPLACED. 1L72 3T4 T A14CE E4EA 20020411000182002041100018SO 2002 4 11 CA020401002 120020328G2430VR15283B VOLT REGULATOR PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE LT GENERATOR FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) LEFT GENERATOR SYSTEM FAILED DURING CLIMB. 1L72 3T4 TRTA8EA E4EA 20020918000022002091800002SO 2002 9 18 CA020401003 220020325G8520628752 CONNECTING ROD BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO LT ENGINE FAILED W A UNSCHED LANDING KEYFLUID LOSS VIBRATION/BUFFET ENGINE STOPPAGE CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN A CRUISE CONFIGURATION WHEN A SEVERE VIBRATION, NOISE, AND OIL LEAK WAS OBSERVED FROM THE LEFT HAND ENGINE OF THE AIRCRAFT.AIRCRAFT ENGINE WAS SHUT DOWN, PROP FEATHERED, AND THE AIRCRAFT MADE A SAFE LANDING. INITIAL EXTERNAL EXAMINATION OF THE FAILED ENGINE REVEALED A LARGE HOLE IN THE TOP FRONT OF THE ENGINE CASE THAT WASCAUSED BY A MASSIVE FAILURE OF THE NR 5 (FRONT INBOARD) CYLINDER CONNECTING ROD. ONCE THE CONNECTING ROD HAD BROKEN, THE REMAINING ASSOCIATED PIECES OF IT DESTROYED THE AFFECTED CYLINDER AND ENGINE CASE. PIECES OF THE REMAINING CONNECTING ROD WERE ATTACHED TO THE PISTON AND THE CRANKSHAFT. THE ENGINE WILL BE ANALYISED FOR THE CAUSE OF THE FAILURE. 1L72 3O3 ORT3A16 3E1 20020411000192002041100019SO 2002 4 11 CA020401006 220020325G8520628752 CONNECTING ROD BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO ENGINE BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN A CRUISE CONFIGURATION WHEN A SEVERE VIBRATION,NOISE, AND OIL LEAK WAS OBSERVED FROM THE LEFT HAND ENGINE OF THE AIRCRAFT.AIRCRAFT ENGINE WAS SHUT DOWN, PROP FEATHERED, AND THE AIRCRAFT MADE A SAFE LANDING. INITIAL XTERNAL EXAMINATION OF THE FAILED ENGINE REVEALED A LARGE HOLE IN THE TOP FRONT OF THE ENGINE CASE THAT WAS CAUSED BY A MASSIVE FAILURE OF THE NR 5 (FRONT INBOARD) CYLINDER CONNECTING ROD.ONCE THE CONNECTING ROD HAD BROKEN, THE REMAINING ASSOCIATED PIECES OF IT DESTROYED THE AFFECTED CYLINDER AND ENGINE CASE. PIECES OF THE REMAINING CONNECTING ROD WERE ATTACHED TO THE PISTON AND THE CRANKSHAFT. THE ENGINE WILL BE ANALYISED FOR THE CAUSE OF THE FAILURE. 1L72 3O3 ORT3A16 3E1 20020411000202002041100020EU 2002 4 11 CA020402001 120020323G3230 SELECTOR SWITCH AMD FALCONFALCON20 2730103EU GE CF700 CF7002D2 30010NE MLG FAILED W L ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 CA (CAN) ON MAR 23,2002 DURING LDG PHASE IN WILMINGTON, OHIO (KILN) PILOT INITIATED DEPLOYMENT OF LDG GEAR. COCKPIT INDICATOR SHOWED 3 RED LIGHTS IDENTIFYING FWD GEAR DOOR LATCH UNLOCKED & NO GREEN LIGHTS TO CONFIRM THAT GEAR DOORS WERE FULLY OPENED & GEAR DOWN & LOCKED. THE CAUSE OF THE MALFUNCTION WAS IDENTIFIED BY OUR CONTRACTEDAMO AS MOISTURE WITHIN THE GEAR DOOR MICRO-SWITCHES, WHICH PREVENTED THE SELECTOR SOLENOID VALVE TO OPEN AND CONSEQUENTLY THE LANDING GEAR DID NOT RELEASE. ALL SWITCHES WERE INSPECTED AND RE-SEALED. 2L72 4F4 FRTA7EU E7EA 20020503000232002050300023NM 2002 5 3 CA020402002 120020402G5270654583042 WIRE BOEING737 7372H4 138448CNM PWA JT8 JT8D9A 52048NE DOOR WARNING BROKEN W A UNSCHED LANDING P NO WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF OUT OF YWG, A/C WOULD NOT PRESSURIZE. NON NORMAL AUTO-FAIL CHECKLIST EXECUTED BUT DID NOT CORRECT PROBLEM. A/C LEVELED OFF AT 9,000 FT AND RETURN TO BASE. LANDED IN YWG W/O INCIDENT. MAINTENANCE INSPECTION DISCOVERED E/E SERVICE DOOR OPEN AND DOOR WARNING LIGHT UNSERVICABLE. MAINT FOUND BROKEN WIRE TERMINAL ON E/E DOOR WARNING SWITCH. WIRE REPLACED IAW MM 52-71-00 AND GROUND CHECKED SERVICEABLE. SERVICE DOOR CLOSED AND RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020417000842002041700084NE 2002 4 17 CA020402007 220020320G8500NAR7B18 CARBURETOR DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE ENGINE MALFUNCTIONED W D RETURN TO BLOCK Y ENGINE STOPPAGE TXTAXI/GRND HDL 1 CA (CAN) (AIRCRAFT ON FLOATS) DURING TAXI OUT FOR TAKE OFF, ENGINE STARTED TO POP AND BACKFIRE WHICH CREATED ENGINE FAILURE. CARB REPLACED AND IS CURRENTLY BEING INVESTIGATED. (NOTE: RT MAGNETO ALSO REPLACED) 1H71 3R3 R A806 5E1 20020411000232002041100023NM 2002 4 11 CA020403001 120020329G323065445815 ISOLATION VALVE BOEING737 737204 1384458NM PWA JT8 JT8D15 52051NE MLG LEAKING W O OTHER K FLUID LOSS APAPPROACH 1 CA (CAN) A/C ON ROUTINE FLT ON APPROACH PLANNED FLAPS FOR LDG & SELECTED FLAPS ON SCHEDULE. AFTER FLT CREW SELECTED FLAP TO 25 DEGS, MASTER CAUTION HYDRAULIC WARNING LIGHT FLASHED. AT TIME CREW NOTICED 'A' SYS HYDRAULIC QUANTITY READING ZERO - HYDRAULIC PRESSURE HELD STEADY AT 300 PSI. CREW ELECTED TO LAND A/C WITH FLAPS AT 25 - LDG UNEVENTFUL.MAINT INSP FOUND HYDRAULIC LEAK IN LT MLG WHEEL WELL- MLG MANUAL ISOLATION VALVE. MAINT REPLACED VALVE, & REPLENISHED SYS 'A' HYDRAULICS. LEAK CHECK PERFORMED AS PER MM 32-32-111 & MAINT FOUND NR 1 ENGINE DRIVEN PUMP HAD NO PRESSURE: MAINT REPLACED PUMP,&CARRIEDOUT LEAK CHECK AS PER MM 29-11-31, NO FAULT 2L72 4F4 F A16WE E2EA 20020411000242002041100024CE 2002 4 11 CA020403002 120020326G3244114800115 TIRE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA NLG UNBONDED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) AIRCRAFT DEPARTED PRINCE GEORGE,PILOTS FELT VIBRATION THRU AIRFRAME. AS IT DID NOT DIMINISH THEY ELECTED TO RETURN. MAINTENANCE INSPECTED AIRCRAFT AND WITH NO VISIBLE DEFECTS THE AIRCRAFT WAS TEST FLOWN. NO NOTICEABLE VIBRATION WAS FELT AND AIRCRAFT RETURNED TO SERVICE. NEXT DAY ON ROLL OUT PILOTS FELT VIBRATION AND ABORTED TAKEOFF. AIRCRAFT WAS AGAIN INSPECTED AND TEST FLOWN.ONLY IF AIRCRAFT WAS ON LONG HIGH SPEED ROLLCUT DID DEFECT REOCCUR. THE NOSE WHEEL WAS DISASSEMBLED AND THE BALANCE WEIGHT ON THE INNER PORTION OF THE TIRE WAS FOUND UNBONDED. THE TIRE WAS REPLACED AND A SATISFACTORY TEST FLIGHT COMPLETED. 2L72 4T4 TRTA24CE E4EA 20020503000252002050300025EU 2002 5 3 CA020403003 120020325G5280SD3101059XA BOSS STBROSSD3 SD360 8100606EU PWA PT6 PT6A65AR 52043NE NLG DOOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ROUTINE INSPECTION REVEALED EXTRA PLAY IN NOSE GEAR DOORS. FURTHER INVESTIGATION SHOWED THAT 4 BOLTS HAD SHEARED. THIS WAS LIKELY DUE TO THE FACT THAT THE BOSS HAD SEIZED ON THE TUBE THAT GOES THROUGH IT. THE INTERNAL SURFACE OFTHE BOSS WAS HIGHLY CORRODED. THERE IS NO SCHEDULED MAINTENANCE FOR THIS AREA. NO GREASE NIPPLE IS PROVIDED FOR LUBRICATION AND TO KEEP MOISTURE OUT. 2H72 4T4 T A41EU E4EA 20020411000252002041100025SO 2002 4 11 CA020403004 120020320G214084251003 PUMP PIPER PA34 PA34220T 7103420SO CONT O360 TSIO360KB 17025SO MCAULY3AF32C3AF32C508 GL HEATER LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WHILE CARRYING AT AD 2001-17-13 (JANAERO SOLENOID/SHUTOFF VALVE LEAK CHECK) THE HEATER FUEL PUMP WAS FOUND TO BE LEAKING OUT OF THE POWER WIRE GROMMET. THIS PUMP IS UNDER THE CENTRE FLOOR BOARD IN THE CABIN AND ALTHOUGH THERE IS A DRAIN UNDER THE PUMP FUEL WAS RUNNING ALONG THE BELLY SKIN INSIDE THE AIRCRAFT. 1L72 3O3 O A7SO E9CE 5 CP22EA 20020411000262002041100026SO 2002 4 11 CA020403005 120020401G6120 DRIVE UNIT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE3Y HCE3YR2A GL PROP GOVERNOR BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA (CAN) A/C DEPARTED AT APPROX 02:00 ZULU ON APR 2 ON IFR FLT TO VANCOUVER. DURING INITIAL STAGE OF CLIMB, RT ENGINE RPM BEGAN TO FLUCTUATE & OVERSPEED. PILOTS TRIED TO CONTROL IT WITH THROTTLE & PROPELLER CONTROLS BUT WHERE UNSUCCESSFUL & CHOOSE TO FEATHER ENGINE & RETURN TO PENTICTON. UPON INSPECTION MAINT CREW DISCOVERED THAT DRIVE ON PROP GOVERNOR BROKEN. GOVERNOR HAS APPROX 800 HRS SINCE OVERHAUL. GOVERNOR REMOVED FROM ENGINE & OVERHAULED GOVERNOR INSTALLED. A/C GROUND RUN & FOUND ACCEPTABLE FOR RETURN TO SERVICE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020417000882002041700088CE 2002 4 17 CA020403006 120020320G52101014300291 LATCH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA AIRSTAIR DOOR FAILED W BG EMER. DESCENT O2 MASK DEPLOYED D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF CALGARY (CYYC), CLIMBING THROUGH 14,000 FEET, THE CREW AND PASSENGERS HEARD A LOUD BANG, THEN THE CABIN AIRSTAIR DOOR DROPPED OPEN. THE CREW DECLARED AN EMERGENCY TO ATC, INSTITUTED AN EMERGENCY DESCENT AND TURNED BACK FOR CALGARY WHERE THEY LANDED WITHOUT FURTHER INCIDENT. THE CAUSE OF THIS DOOR FAILURE IS NOT FULLY KNOWN AT THIS TIME, BUT IT DOES APPEAR THAT THE FORWARD UPPER LATCH HOOK ASSEMBLY FAILED. REPORTS ON THE EXACT CAUSE WILL FOLLOW AFTER INVESTIGATION. 1L72 4T4 T A24CE E4EA 20020503000262002050300026NM 2002 5 3 CA020403007 120020327G2421 DRIVE SHAFT LUCAS 31708001A DHAV DHC8 DHC8* NM AC GENERATOR FAILED W O OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 CA 326 (CAN) DRIVE SHAFT SPINS FREE. INTERNAL SPLINES OF THE ROTOR AND EXTERNAL SPLINES OF THE DRIVE SHAFT WORN OUT (FAILED) . PROBABLE CAUSE IS OIL ORIFICE IN THE ROTOR PLUGGED WITH VARNISH PREVENTING LUBRICATION OF ROTOR AND DRIVE SHAFT SPLINES. 2H72 4T RTA13NM 20020411000272002041100027SW 2002 4 11 CA020403008 120020321G5320206033110189 STIFFENER BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16300 (CAN) CRACKED VERTICAL STIFFENER. CUTOUT IN HORIZONTAL STIFFENER WAS TOO SMALL WHICH PUT PRESSURE ON VERTICAL STIFFENER CAUSING IT TO CRACK. 1G71 3U3 U H2SW E4CE 20020411000282002041100028SW 2002 4 11 CA020403009 120020326G63206871064 RING BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL M/R GEARBOX CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BALANCE RING WAS PARTIALLY CRACKED. (MAIN GEARBOX TORQUE GEAR "BALANCE RING" FOUND CRACKED) 1G71 3U3 U H2SW E4CE 20020411000292002041100029NM 2002 4 11 CA020404001 120020328G3211654581945 GUSSET BOEING737 7372H4 138448CNM PWA JT8 JT8D9A 52048NE NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MAINTENANCE INSPECTION - SERVICE CHECK DURING REGULAR SCHEDULED MAINTENANCE, ENGINEER FOUND NOSE LANDING GEAR UPPER SUPPORT AT ACTUATOR ATTACH BRACKETS CRACKED. MAINTENANCE REPLACED UPPER DRAG BRACE, GUSSET AND 'T' EXTUSION FOR NOSE LANDING GEAR ACTUATOR. NDT INSPECTION OF EXPOSED STRUCTURE AND SUPPORT FITTING CARRIED OUT WITH NO DEFECTS NOTED. AIRCRAFT RETURNED BACK TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020411000302002041100030EU 2002 4 11 CA020404002 120020402G3297622800200 WIRE BAG JETSTMJETSTM3101 1500215EU GARRTTTPE331TPE33110UG 01514WP ROTOL R333 R333482F12 GL MLG BROKEN W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA (CAN) ON APPROACH THE PILOT NOTICED THAT THE NOSE GEAR WAS NOT INDICATING DOWN AND LOCKED. AFTER CYCLING THE GEAR WITH NO CHANGE IN THE INDICATION, A FLY PAST WAS CARRIED OUT TO DETERMINE THE GEAR STATUS. AFTER DECIDING THAT THE GEAR WAS LIKELY DOWN AND LOCKED A LANDING WAS ATTEMPTED WITH ERS ON STANDBY. THE LANDING WAS SUCCESSFUL.ON INVESTIGATION A WIRE WAS FOUND TO BE BROKEN ABOUT 12 INCHES FROM THE SWITCH. 2L72 4T4 TRTA21EU E4WE 6 CP61GL 20020411000312002041100031NM 2002 4 11 CA020405001 120020330G3211 STRUCTURE BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SCHEDULED MAINTENANCE;DURING REGULAR SCHEDULED MAINITENANCE INSPECTION, MAINTENANCE ENGINEER SUSPECTED A CRACK AT THE NOSE LANDING GEAR ACTUATOR ATTACH SUPPORT BRACKET (FORWARD SIDE UPPER R/H SIDE). NDT CALLED IN AND 3/8 INCH CRACK CONFIRMED BY HFEC METHOD IAW 51-00-00.MAINTENANCE REPLACED NLG TEE P/N: 65-45819-551 BELOW WL207 AT BLO.OO, STN 259.5 IAW BOEING DRAWING 65-45819 REV.G. AIRCRAFT LANDING GEAR SYSTEM GROUND CHECKED SERVICEABLE.AIRCRAFT RETURNED BACK TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020417000972002041700097CE 2002 4 17 CA020405003 120020327G282011892000029 LINE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FUEL TRANSFER CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) THE L/H FUEL CROSS TRANSFER TUBE WAS FOUND CHAFED THROUGH AND SEEPING FUEL. THE WEAR MARK ON THE TUBE MEASURED APPROXIMATELY 5/16 INCH IN LENGTH X 1/8 INCH IN WIDTH. REF: IPC 28-20-00. WEAR OCCURRED FROM THE WIRE BUNDLE COVERING OF THE GEAR UPLOCK MICROSWITCH. THE BUNDLE WAS SECURED CLEAR AFTER FUEL TUBE REPLACEMENT. SUGGEST OPARATORS CHECK THIS AREA. THE FUEL TUBE WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020411000322002041100032SO 2002 4 11 CA020405005 120020326G3246AN620A BOLT PIPER PA42 PA42 7104202SO PWA PT6 PT6A41 52043EA MGL WHEEL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MAIN WHEEL ASSEMBLY TIRE REPLACEMENT, THREE TIE BOLTS OUT OF EIGHT SHEARED WHEN RECOMMENDED TORQUE WAS APPLIED. PRIOR TO ASSEMBLY ALL BOLTS WERE VISUALLY INSPETED AND NO EVIDENCE OF CRACKS WERE NOTED. ALL EIGHT BOLTS WERE REPLACED. 1L72 4T4 T A23SO E4EA 20020503000462002050300046NE 2002 5 3 CA020405027 220020331G7230LK69554 TUBE LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE P3 AIR BROKEN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) WHILE CLIMBING THROUGH FLT LEVEL 290 , NR 2 ENGINE POWER WENT DOWN TO IDLE POWER ONLY. ABNORMAL CHECK LIST CARRIED OUT WITH NO SUCCESS. A/C RETURNED TO YMX. NO THROTTLE RESPONSE AT ALL. MAINT REPLACED THE FUEL FLOW REGULATOR IN ACCORDANCE WITH MM. FOUND TO BE SERVICEABLE. VERIFICATION FLT CARRIED OUT&POWER WENT TO IDLE PAST FLT LEVEL 240 AND EVERYTHING WENT BACK TO NORMAL WHEN POWER APPLIED AT FLT LEVEL 180. AFTER INSPECTION, MAINT FOUND ALTITUDE SWITCH NOT WITHIN LIMIT WITH TEST NR 1 AND REPLACED IT 2L73 4F4 F A23WE E12EU 20020417001192002041700119EU 2002 4 17 CA020405028 120020331G76034261212 THROTTLE CABLE AIRBUS310 A310 EU GE CF6 CF680C2* GL NR 2 ENGINE CONTAMINATED W K NONE E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) ENGINE NR 2 THROTTLE JAMMED IN DESCENT , IN IDLE POSITION. MAINTENANCE FOUND THE THROTTLE CONTROL CABLE ASSEMBLY WATER SOAKED AND ALSO FOUND THE ELASTOMER SLEEVE RIPPED OPENED. BOTH PARTS WERE REPLACED ; THE THROTTLE CONTROL CABLE ASSY.REPLACED I.A.W. MM 76-11-41 AND THE ELASTOMER SLEEVE , I.A.W. SB A310-76-2012.A VERIFICATION FLIGHT WAS CARRIED SERVICEABLE. 2L72 4F4 FRTA35EU E23EA 20020503000472002050300047SW 2002 5 3 CA020408001 120020308G7332209062608001 VENT BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA FUEL PRESSURE CLOGGED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) FUEL PRESSURE FLUCTUATED, FUEL PRESSURE TRANSMITTER PORT AND VENT FOUND ALMOST CLOGGED BY MUDDY SUBSTANCE. 1G71 4U4 U H4SW E22EA 20020503000482002050300048EA 2002 5 3 CA020408002 220020319G7321 SEAL BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA FUEL CONTROL LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) MANUAL FCU LEAKS AT CONTROL SHAFT SEAL, INTERCONNECT SIDE. 1G71 4U4 U H4SW E22EA 20020503000492002050300049SW 2002 5 3 CA020408003 120020308G7714209075326 CONTROL BOX BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA RPM WARNING CORRODED W A UNSCHED LANDING N FALSE WARNING HOHOVERING 1 CA (CAN) WHILE HOVERING OVER WATER ALL KINDS OF WARNING LIGHTS AND HORNS CAME ON. PARAMETERS LOOKED NORMAL, AIRCRAFT WAS FLOWN TO THE CLOSEST AIRPORT, RPM BOX WAS OPENED AND FOUND CORRODED, WAS SUBSEQUENTLY REPLACED. 1G71 4U4 U H4SW E22EA 20020503000502002050300050SW 2002 5 3 CA020408004 120020307G28222050606063 PUMP BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA FUEL BOOST FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) IN FLIGHT, FUEL PRESSURE FLUCTUATED AND WENT TO ZERO ON LT FUEL PUMP, CIRCUIT BREAKER POPPED. 1G71 4U4 U H4SW E22EA 20020503000512002050300051GL 2002 5 3 CA020408005 220020402G72406870992 COMBUSTION LINER BELL 206 206L 1181522SW ALLSN 250C 250C20B 03013GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE PERFORMANCE DETERIORATED, POWER CHECK CARRIED OUT, ENGINE DID NOT MEET SPECIFICATIONS. VISUAL INSPECTION REVEALED A CRACK IN LT ARMPIT OF THE OUTER COMBUSTION CAN. THE CAN WAS REPLACED. 1G71 3U3 U H2SW E4CE 20020503000922002050300092SW 2002 5 3 CA020408006 120020311G321322041 AXLE BBAVIA7 7GCBC 1220601SW LYC O320 O320A2B 41508EA MLG SHEARED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA (CAN) DURING THE TAKEOFF RUN ON ICE THE AIRCRAFT CROSSED OVER SOME SMALL SNOWMOBILE TRACKS. WHEN THE AIRCRAFT BECAME AIRBORNE THE RIGHT SKI SEPARATED. THE SKI, STILL ATTACHED BY THE SAFETY WIRE, FLAILED AROUND CAUSING SUBSTANTIAL DAMAGE TO THE BELLY AND RT STRUTS. EVENTUALLY THE FORWARD SAFETY WIRE FAILED AND THEN SWUNG AROUND TO BECOME LODGED BEHIND THE LT SKI, BUT NOT BEFORE STRIKING THE REAR FUSELAGE AND DAMAGING THE FABRIC AND REAR BULKHEADS. SUBSTANTIAL AIRCRAFT DAMAGE UPON LANDING AND RESULTING GROUND LOOP. 1H71 3O3 ONCA759 E274 20020503000942002050300094EA 2002 5 3 CA020408007 120020321G2910200809271 LINE CNDAIRCL600 CL600* EA HYD SYSTEM RUPTURED W K NONE K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) AFTER LANDING, HYDRAULIC FLUID NOTICED STEAMING FROM NR 3 BRAKE UNIT AND DRIPPING FROM NR 3 & 4 BRAKE UNIT. LEAK CHECK REVEALED FLUID LOSS FROM NR 4 (RT OUTBOARD) BRAKE UNIT PIPE 1/8 INCH FORWARD OF BANJO FITTING LOCATED ON TOP OF BRAKE. IMPROVEMENTS IN THAT SECTION OF LINE TO GET AWAY FROM RIGID PIPE IN SUCH A HARSH ENVIRONMENT OF VIBRATION. ALSO NEW REPLACEMENT LINES NEED TO BE REFORMED TO FIT APPLICATION CORRECTLY AND BANJO DOES NOT SIT PERFECTLY FLAT ON BRAKE UNIT WHICH INDUCES A TORSIONAL STRESS ON THE LINE TO BANJO JOINT. SUPPORTING THE BANJO DURING BOLT MOVEMENT IS CRITICAL. OCCURRENCES IN THIS EXACT AREA ARE NOT UNCOMMON. 2L72 4F RTA21EA 20020503000952002050300095EU 2002 5 3 CA020408008 120020318G3250Z4242170001 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA NLG STEERING BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CA (CAN) A STUDENT PILOT REPORTED EXCESSIVE MOVEMENT IN THE NOSE GEAR STEERING SYSTEM. A MAINTENANCE CHECK REVEALED THAT THE LT NOSE GEAR STEERING SPRING WAS BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM COIL DISTANCE SETTING ON THE L/H & R/H SPRINGS. THE PROBLEM MAY BE RELATED TO NOT HAVING THE AIRCRAFT ROLLING BEFORE STEERING THE AIRCRAFT LEFT OR RIGHT. 1L71 3O3 O0 A76EU 1E10 20020503000962002050300096EU 2002 5 3 CA020408009 120020319G7810L24266701320 STRUT ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA EXHAUST MANIFOLDBROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION THE EXHAUST STAY STRUT WAS FOUND BROKEN AT THE THREADED PART OF THE EYE END. A NEW STRUT AND EYE END ASSEMBLY WAS INSTALLED AND POSITIONED FOR PROPER FIT. THIS EYE END IS SECURED BY THE UPPER RIGHT HAND NUT THAT ALSO SECURES THE FUEL INJECTION SERVO. IF THE NUT HAD LOOSENED OFF THE EYE END COULD HAVE SWUNG DOWN AND INTERFERED WITH THROTTLE MOVEMENT.IT IS RECOMMENDED THAT THE NUT BE CHECKED FOR SECURITY EVERY INSPECTION AND THE STRUT ASSEMBLY BE INSTALLED WITH THE MINIMUM AMOUNT OF TENSION. 1L71 3O3 O0 A76EU 1E10 20020503000982002050300098EU 2002 5 3 CA020408011 120020325G324216402201 DISK BNORM BN2 BN2B27 7080227EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL BRAKE FAILED W O OTHER O OTHER LDLANDING 1 CA (CAN) BRAKE DISC FAILED. THE DAY OF THE FAILURE HAD SLUSH ON THE TAXI WAY, IT GOT IN AROUND THE DISC AREA. MAY BE A PART OF THE FAILURE IS DUE TO THERMAL SHOCK COOLING (HOT DISC, COLD SLUSH). 1H72 3O3 O A17EU E295 5 CP920 20020503001032002050300103EA 2002 5 3 CA020408012 120020402G7830CN6241242005 VANE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF34* NE LT ENGINE T/R MISINSTALLED W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED LDLANDING 1 CA (CAN) DURING CUSTOMER ACCEPTANCE FLT, UPON TOUCH DOWN & AFTER APPLICAITON OF FULL THRUST REVERSER POWER, A/C VEERED TO RT APPROX. 30 TO 40 DEGS FROM RWY HEADING. CORRECTIVE ACTION TO STOW THRUST REVERSERS & CONTROL DIRECTIONAL CONTROL USING RUDDER. INVESTIGATION REVEALED THAT THRUST REVERSER OF LT ENGINE INCORRECTLY INSTALLED. THRUST REVERSER CASCADE VANES WERE NOT POSED AT APPROPRIATE LOCATION FOR LT ENGINE. 2L72 4F4 FRTA21EA E15NE 20020417001202002041700120WP 2002 4 17 CA020408013 120020402G25201103080100 CONTROL BOX LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE PAX SEAT FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) SEAT ELECTRONIC BOX POSITIONED AT ROW 25 DE , STARTED SMOKING. THE SEB WAS DICONNECTED BY THE CREW. MAINTENANCE REPLACED THE UNIT. 2L73 4F4 F A23WE E12EU 20020503001052002050300105 2002 5 3 CA020408014 420020313G3420 GYRO CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL COCKPIT FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CLCLIMB 1 CA (CAN) TAKEOFF RUNWAY CLIMBING THROUGH 4,500 FT. THE PILOT REPORTED A COMPLETE AVIONICS FAILURE, AND THEN A RETURN TO NORMAL OPERATION. CONDUCTING AN I.F.R. APPROACH TO RUNWAY. THE PILOT REPORTED AN ERRATIC HSI CDI. TOWER GRANTED A CONTACT APPROACH. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE INSTALLED A SERVICEABLE HSI AND CARRIED OUT EXHAUSTIVE TROUBLE SHOOTING TEST FLIGHT BUT, COULD NOT DUPLICATE THE CONDITIONS REPORTED BY THE PILOT. THE AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020503001062002050300106EA 2002 5 3 CA020408015 120020408G5610601R330339 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) ENROUTE AT 33,000 FEET, THE LEFT WINDSHIELD SHATTERED. FLIGHT DIVERTED TO JFK.WINDSHIELD REPLACED AND AIRCRAFT RETURNED IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020503001072002050300107EA 2002 5 3 CA020408016 120020329G33209906813004 CONTROLLER CNDAIRCL604 CL604 1900301EA CABIN FAILED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA 01110012333 (CAN) IT HAS BEEN FOUND DURING DEVELOPMENT OF A CABIN MANAGEMENT SYSTEM. IT DID NOT MEET THE MANUFACTURER'S SPECIFICATIONS. THE UNIT IS USED TO SWITCH CABIN LIGHTS. THE SPECIFICATION WAS MENTIONING CAPACITY FOR MAX CONTINUOUS RATING OF 7.5 AMPS, THE CONTROLLED CURRENT MEASURED 6.5 AMPS FOR THE CABIN LIGHTS WHICH IS WITHIN SPECS. DURING GROUND TESTING THE SWITCHING UNIT FAILED AND GENERATED A LOT OF SMOKE IN THE CABIN. AFTER INVESTIGATION, WITHIN THE UNIT IT WAS FOUND THAT THE PRINTED CIRCUIT BOARDS WERE BURNED. 2L72 4F RTA21EA 20020417001212002041700121NM 2002 4 17 CA020408017 120020405G324626015711 WHEEL BOEING737 737297 1384480NM PWA JT8 JT8D9A 52048NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLIGHT CREW REPORTED ON TAXI THE AIRCRAFT SEEMED TO REQUIRE MORE POWER THAN NORMAL - AIRCRAFT DEPARTED WITHOUT INCIDENT.ON NEXT LANDING THE CREW NOTICED THE SAME AND REPORTED TO YLW MAINTENANCE. INSPECTION FOUND THE MAIN BRAKE ON NR 2 MAIN WHEEL ASSEMBLY SEIZED AND THE NR 2 TIRE RIM CRACKED/DETACHED FROM ASSEMBLY. MAINTENANCE REPLACED THE MAIN WHEEL ASSY, P/N: 2601571-1, THE NR 2 MAIN GEAR BRAKE ASSY. MAIN LANDING GEAR SYSTEM AND AIRCRAFT GROUND CHECKED SERVICEABLE - AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020503001142002050300114NE 2002 5 3 CA020409001 320020324G6114PRP0119026 O-RING DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU HOFMANHOV352HOV352F NE PROPELLER FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) PROP REPLACED ON AIRCRAFT AFTER TROUBLESHOOTING PROPELLER CONTROL SYSTEM AND INSPECTING OIL PUMP AND LINES. NO DEFECTS FOUND IN PUMP, LINES OR WITH GOVERNOR ASSY. REPLACING PROP SOLVED PROBLEM. DISASSEMBLY REVEALED DAMAGED SEAL IN FRONT OF PITCH CHANGE PISTON CAUSING OIL PRESSURE TO BUILD UP ON BACKSIDE OF PISTON, AND FORCING PROP TO COARSE PITCH. THIS OIL PRESSURE WAS GREATER THAN RETURN SPRING PRESSURE AND THE HUB HAS NO DUMP PROVISION IN THIS AREA TO ALLOW OIL TO RETURN TO THE ENGINE. 1L71 3O3 ONTTA4CH E00051EN5 CTP5BO 20020918000032002091800003SW 2002 9 18 CA020409003 120020322G6730 ACTUATOR BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE ROTARY SEIZED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ROTARY ACTUATOR SEIZED AND HAS NO SCHEDULED MAINTENANCE OR CHECK INTERVAL. 1G71 4U4 U H4SW E22EA 20020417001222002041700122CE 2002 4 17 CA020410001 120020408G3230903610373 DOWNLOCK SWITCH BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA MLG OPEN W O OTHER O OTHER DEDESCENT 1 CA (CAN) DURING DESCENT APPROACH FOR LANDING, PILOTS SELECTED GEAR DOWN AND RECEIVED A DOWN LOCK INDICATION FOR NOSE GEAR AND LT MAIN GEAR, NO DOWN LOCK INDICATION FOR RT MAIN GEAR. WITH THROTTLES AT FLIGHT IDLE THERE WAS NO GEAR HORN, NO IN TRANSIT LIGHT. PILOTS RESELECTED GEAR SEVERAL TIMES WITH THE SAME RESULTS. IT WAS DETERMINED BY MAINTENANCE THAT THE GEAR PROBLEM WAS INDICATION ONLY. THE PILOTS HAD TOWER CONFIRM THAT THE RT GEAR WAS DOWN AND LANDED WITHOUT INCIDENT. INVESTIGATION BY MAINTENANCE FOUND THE DOWNLOCK SWITCH CONTACTS RESPONSIBLE FOR INDICATION HAD FAILED, (OPEN CIRCUIT). 1L72 3T4 TRT3A20 E4EA 20020503001202002050300120CE 2002 5 3 CA020410002 120020410G2710ASABOVE BELLCRANK BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA AILERON MISMANUFACTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION THAT REQUIRED REMOVAL IT WAS NOTICED THAT THE HOLE IN THE OUTPUT ARM (AILERON PUSHROD ATTACH POINT) HAD BEEN INCORRECTLY DRILLED TO 5/16 INCH INSTEAD OF 1/4 INCH. THIS ALLOWED LOST MOTION BETWEEN THE PUSHROD AND BELLCRANK. THE BORE OF THE HOLE SHOWED PRIMER EXISTING FROM MANUFACTURE. MANUFACTURER WAS CONTACTED AND WILL BE SHOWN THE DEFECT AND IT WAS HINTED THAT THIS PROBLEM HAD BEEN SEEN BEFORE. 1L72 3T4 TRT3A20 E4EA 20020503001222002050300122EA 2002 5 3 CA020410003 120020409G2820700246C HOUSING DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA VALVE BODY CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) INSPECTED FUEL LEAK IN BELLY TANKS. FOUND AFT MOTIVE FLOW VALVE LEAKING DUE TO CRACKED BODY. HIGH TORQUE (50 FOOT LBS.) USED TO ASSEMBLE UNIT. 1H72 3T4 TRTA9EA E4EA 20020503001412002050300141SW 2002 5 3 CA020411001 120020408G52102724044010 SKIN SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP PAX DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON ROUTINE DAILY INSPECTION A CRACK WAS DISCOVERED IN LOWER FWD CORNER OF PASSENGER DOOR, EMMINATING FROM RIVET HOLES IN CORNER BRACKET WHERE IT SPLICES TO LOWER FRAME CHANNEL. CRACK CONTINUED 1.5 IN ALONG EDGE OF THE BRACKET & ALSO UNDER DOOR'S OUTER SKIN. DOOR REMVD&SKIN LIFTED FROM CORNER TO FIND THAT CRACK CONTINUED ALONG ATTACHMENT FLANGE FOR 3.5 IN. NEW -12 CORNER BRACKET FITTED THAT IS FACTORY UPGRADED TO THICKER MATERIAL. WEB OF OLD CORNER BRACKET IS DEFORMED IN AREA OF CRACK AS IF SOMETHING HAS BEEN CAUGHT BETWEEN DOOR & FRAME IN PAST. 2L72 4T4 TRTA8SW E4WE 20020506000012002050600001NE 2002 5 6 CA020411002 220020323G73102193340 LINE CNDAIRCL600 CL600* EA LYC ALF502ALF502L 41580NE FUEL CONTROL CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, CREW RECEIVED LT ENGINE FIRE WARNING. WARNING WENT OUT AFTER ENGINE THROTTLED BACK, BUT THEN ITT BEGAN CLIMBING. CREW SHUTDOWN ENGINE AND PERFORMED SINGLE ENGINE LANDING. SUBSEQUENT INSPECTION REVEALED THAT FUEL LINE BETWEEN FLOW DIVIDER AND MANIFOLD CRACKED AT BRAZED JOINT CAUSING FUEL TO LEAK AND SUBSEQUENTLY FIRE THAT BURNED THROUGH EXHAUST NOZZLE. ENGINE REMOVED AND REPLACED. 2L72 4F4 FRTA21EA E6NE 20020506000022002050600002NM 2002 5 6 CA020411003 120020320G291082920010169 LINE DHAV DHC8 DHC8315 2809010NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE HYD SYSTEM CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) -DURING APPROACH PILOT SELECT GEAR DOWN. THEN PILOT NOTICE MANY CAUTION LIGHTS: SPOILER, ISOVALVE, STEERING AND HYD TANK NR 2 LEVEL EMPTY. BUT GEAR LOCK DOWN OK 3 GREEN LIGHTS. AIRCRAFT LAND NORMALLY AND SAFELY. MAINTENANCE FOUND ALUMINIUM HYDRAULIC LINE FOR LANDING GEAR DOWN PRESSURE CRACK IN A RADIUS (LINE IS IN THE WING TO FUSELAGE BOX)(CRACK LOOKED LIKE A FATIGUE CRACK). LINE REPLACED SYSTEM SERVICED, NO MORE LEAK. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020506000102002050600010NE 2002 5 6 CA020411004 120020221G6320 LOCK SKRSKYS61 S61N 8142104NE GE CT58 CT581401 30011NE M/R GEARBOX LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AT FREEWHEEL CHANGE LOCKS WERE LOOSE. GEARS WERE REPLACED FOR FURTHER INSPECTION IN SHOP. PARTS WERE REMOVED FROM MAIN GEARBOX. 2G72 4U4 U 1H15 1E3 20020506000112002050600011 2002 5 6 CA020411005 420020313G6113055032111 BULKHEAD CESSNA 055032111 CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL SPINNER CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) SECOND PART FAILURE IN THE SAME AREA HEARD REPORTS OF THIS PART FAILING FROM OTHER OPERATORS. SPINNER AND AFT BULKHEAD HAVE A VERY POOR FIT. 1H71 3O3 ONT3A12 E274 5 NP910 20020506000132002050600013CE 2002 5 6 CA020411007 120020402G272003101965 SPRING CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA RUDDER DISCONNECTED W K NONE O OTHER ININSP/MAINT 1 CA 14032 (CAN) DURING THE PRE-FLIGHT INSPECTION, THE FLIGHT INSTRUCTOR NOTICED A COMPLETE DEFLEXION OF THE RUDDER CONTROL (TOWARDS THE RIGHT) WHEN THE NOSEWHEEL WAS CENTERED. AS WELL, THE PEDALS WERE NOT EVEN. DURING MAINTENANCE, NOTICED THAT THE FRONT PART OF THE SPRING WAS UNHOOKED. INSPECTED THE AFFECTED PARTS AND REPLACED THE SPRING, EVEN THOUGH IT WAS NOT BROKEN. 1H71 3O3 ONT3A12 E274 20020506000142002050600014CE 2002 5 6 CA020411008 120020402G551004320041 BRACKET CESSNA 043200161 CESSNA150 A150K 2071824CE CONT O200 O200A 17020SO HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BRACKET WAS FOUND TO BE CRACKED. AIRCRAFT IS BEING REBUILT AFTER AN ACCIDENT. 1H71 3O3 O 3A19 E252 20020513000152002051300015NE 2002 5 13 CA020411009 320020224G6197L195A12KU1C22 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE ZONE 521 CHAFED W A UNSCHED LANDING BB SMOKE/FUMES/ODORS/SPARKS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) AFTER DEPARTURE, CREW NOTICED FAINT ODOUR AND SAW AUTOFEATHER CB WAS POPPED. ELECTED TO RETURN AND DURING DECENT ODOUR INCREASED ACCOMPANIED BY SMOKE. DEPLOYED AND DONNED O2 MASKS. WENT THRU EMERGENCY PROC: SMOKE DISSIPATED, UNEVENTFULL LANDING. DURING MAINT INSPECTION, WIRES BEHIND AUTOFEATHER SWITCH GOING TO PRINTED CCT BOARD WERE FOUND MELTED. PCB ALSO HAD BURNED SOLDER TRACKS. TRACING WIRES OUT TO ENGINE NACELLES RT HAD NO DEFECTS BUT IN ZONE 521 BEHIND LT ENGINE WIRES FOR AUTOFEATHER SYS AND KU1C22 FOR LDG LIGHT SYS HAD CHAFED TOGETHER ENOUGH TO SHORT. ALLOWED 35 AMPS FROM LIGHTING TO ENTER 5 AMP AUTOFEATHER SYS. A TOTAL OF 21 WIRES WHERE REPLACED AND REROUTED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020506000152002050600015WP 2002 5 6 CA020411010 120020409G2612356680900 FIRE LOOP CVAC 580 580 2422806WP ALLSN 501D 501D13 03004GL NR 2 ENGINE OUT OF POSITION W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) NR 2 ENGINE ZONE 1 FIRE ALARM WARNING AND BELL SOUNDED ENROUTE YYC YVR. ENGINE SHUT DOWN FOLLOWING EMERGENCY PROCEDURE. MAINTENANCE CONTACTED VIA RADIO AND WAS ADVISED TO LAND IN YLW. LANDING UNEVENTFUL NO EMERGENCY DECLARED. MAINTENANCE FOUND AND REPOSITIONED FIRE WIRE, AND GROUND TESTED SERVICEABLE. A/C RELEASED FOR FURTHER FLIGHT TO YVR.NEXT DAY FIRE WIRE REPLACED AS A PRECAUTION. 2L72 4T4 TRT E282 20020506000162002050600016EA 2002 5 6 CA020412001 120020409G2782 ACTUATOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LE FLAPS FAILED W B EMER. DESCENT F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) "FLAP FAIL" WHEN FLAPS WERE SELECTED TO 8 DEG DURING APPROACH. EMERGENCY DECLARED AND LANDED. SYSTEM WOULD NOT RESET. FERRIED A/C , R&R'D LT INBD FLAP NR 1 AND 2 ACTUATORS FOR FAILING THEIR TORQUE CHECK. "FLAP FAIL" AT ZERO DEG AT 205 KNOTS ON DESCENT TO CVG. RT OUTBOARD FLAP PANEL TWISTED. RT FLEXSHAFT NR 4 TWISTED OFF WHERE IT ENTERS SWAGE ON INBOARD SIDE OF NR 4 RT ACTUATOR. R&R'D ALL 5 RT FLEXSHAFT, R&R'D RT OUTBOARD FLAP PANEL, R&R'D RT NR 3 AND 4 ACTUATORS. RIGGED SYSTEM, FECU POTS, OHMED AND MEGGED BPSU HARNESS. RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020506000172002050600017EA 2002 5 6 CA020412002 120020409G2721601R5122623 CONTROL PANEL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RUDDER TRIM FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA 1317610769 (CAN) CREW REPORTED THAT RUDDER TRIM INPUT (NOSE RIGHT) WAS APPLIED BUT, WHEN TRIM SWITCH WAS RELEASED, THE AIRCRAFT CONTINUED TO YAW PROGRESSIVELY MORE. THE RUDDER TRIM INDICATOR CONFIRMED THAT TRIM WAS STILL BEING APPLIED. THE TRIM SWITCH WAS THEN MOVED TO THE 'NOSE LEFT' DIRECTION AND, AFTER SEVERAL ATTEMPTS, THE YAW WAS ARRESTED. MAINTENANCE REPLACED THE RUDDER TRIM PANEL AND THE PROBLEM HAS NOT BEEN REPORTED SINCE. AIRCRAFT BACK IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020506000182002050600018EA 2002 5 6 CA020412003 120020409G5610NP1393225 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA (CAN) DURING DESCENT FOR APPROACH, THE LT SIDE WINDOW CRACKED. WINDOW REPLACED AND AIRCRAFT RETURNED IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020506000192002050600019EA 2002 5 6 CA020412006 120020409G5610601R350339 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) DURING CRUISE CAPTAIN'S FRONT WINDSCREEN PLY CRACKED. EMERGENCY DESCENT AND LANDING MADE AT NEAREST AIRPORT AFTER CAPTAIN'S WINDSCREEN PLY SHATTERED DURING CRUISE. AIRCRAFT MADE SAFE LANDING. WINDSCREEN REPLACED. 2L72 4F4 FRTA21EA E15NE 20020506000202002050600020EA 2002 5 6 CA020412008 120020409G274170607 CONTROL UNIT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE HORIZONTAL STAB FAILED W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA (CAN) "AFTER T/O MACH TRIM & STAB TRIM CAUTION MESSAGES ILLUMINATED. DECLARED EMERGENCY AND LANDED. "PERFORMED OPS CHECK. NO DEFECTS FOUND. RESET PER FIM AND OPS CHECKED GOOD. RETURNED TO SERVICE. 2ND FLT "AFTER T/O MACH TRIM & STAB TRIM CAUTION MSGS ILLUMINATED. WOULD NOT RESET. DECLARED EMERGENCY AND LANDED BACK AT TUL. "SENT ROAD CREW FROM CVG. COULD NOT DUPLICATE PROBLEM. R&R'D HSTCU & MCU AS PRECAUTIONARY MEASURE: FOUND BOTH LEFT & RIGHT HORIZONTAL STAB VISORS CRACKED. R&R'D VISORS. ON FERRY FLT BACK AFTER ABOVE MAINT ACTION PROBLEM DID NOT REOCCUR. 2L72 4F4 FRTA21EA E15NE 20020506000212002050600021EA 2002 5 6 CA020412009 120020409G2432 CONNECTOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE APU BAT CHARGER DAMAGED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA 13192 (CAN) APU BATTERY CHARGER CONNECTOR P12PA BURNED. REPLACED CONNECTOR PINS, CHARGER AND BATTERY. ALL TESTS SATISFACTORY. 2L72 4F4 FRTA21EA E15NE 20020506000222002050600022EA 2002 5 6 CA020412010 120020404G5730601R10004 SKIN CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE ACCESS HOLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 10461 (CAN) CRACKS FOUND ON THE WIND LOWER CENTRE WING PLANK ACCESS HOLE 540FB, BETWEEN WS 127.25 AND 148.19 ACCESS PANEL. 2L72 4F4 FRTA21EA E15NE 20020506000232002050600023EA 2002 5 6 CA020412011 120020404G5320601R3111357 FLOOR SUPPORT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND AT LONGITUDINAL FLOOR SUPPORT LT AND RT BL9. 2L72 4F4 FRTA21EA E15NE 20020506000242002050600024SW 2002 5 6 CA020412012 120020406G6330 BUSHING BELL BELL 206 206L 1181522SW ALLSN 250C 250C20R2 GL STOP MOUNT WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TRANSMISSION STOP MOUNT HAS WORN BUSHINGS. REPLACED. 1G71 3U3 U H2SW E4CE 20020506000252002050600025NM 2002 5 6 CA020412013 120020408G5230 HINGE PIN BOEING 727260 BOEING727 727260 NM PWA JT8 JT8D17 52049NE CARGO DOOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA 22759 (CAN) DURING B CHECK INSPECTION, MAIN CARGO DOOR HINGE PIN WAS FOUND MIGRATING AFT APROX. 6 INCHES. HINGE PIN REPOSITIONED AND SAFETIED. 2L73 4F4 FRTA3WE E2EA 20020513000162002051300016CE 2002 5 13 CA020415001 120020408G3233993880081 ACTUATOR BEECH 99 99 1154002CE PWA PT6 PT6A28 EA LT MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AIRCRAFT DEPARTED BASE AND THE GEAR WOULD NOT RETRACT WHEN THE GEAR HANDLE WAS SELECTED UP. AIRCRAFT RETURNED TO TO BASE. GEAR ACTUATOR WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. 1L72 3T4 T A14CE E4EA 20020506000262002050600026NM 2002 5 6 CA020415002 120020326G291082950010307 LINE DHAV DHC8 DHC8* NM HYD SYSTEM LEAKING W L ABORTED APPROACH K FLUID LOSS NRNOT REPORTED 1 CA 28712 (CAN) ON SELECTION OF FLAPS NR 1 HYD PRESSURE CAUTION LIGHT ILLUMINATED AND STANDBY AND MAIN PRESSURES WENT TO ZERO. FLAPS STOPPED AT 4 DEGREES. RUNWAY LENGTH IN YSB NOT SUFFICIENT DIVERTED TO YYB. 2H72 4T RTA13NM 20020506000272002050600027EA 2002 5 6 CA020416002 120020411G2750C6CT10461 ROD DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A27 52043EA TE FLAP CONTROL LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER COMPLETING AD CF-80-03 & SB6/390 THE TRIM ROD WAS BEING ADJUSTED AT INSTALLATION WHEN IT WAS FOUND THAT THE FORWARD SWAG WAS ALLOWING THE ROD END FITTING TO ROTATE. THE ROD WAS REPLACED. 1H72 3T4 TRTA9EA E4EA 20020506000282002050600028CE 2002 5 6 CA020416003 120020415G334068417066530 LENS CESSNA500 550 2076604CE PWA 530 PW530A NE NAV LIGHT MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON WALKAROUND AFTER A FLIGHT A CREW MEMBER NOTICED THE RT NAV LIGHT LENS COVER MISSING. REPLACED WITH NEW AND CONTINUED FLIGHT TO HOME BASE. 1L72 4F4 F A22CE E00053EN 20020506000292002050600029EA 2002 5 6 CA020416004 220020416G7322 FLOAT FRCHLDM62 M62A3 3371618EA FCD 6440 6440C5 26003EA CARBURETOR DAMAGED W A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AIRCRAFT SUFFERED SIGNIFICANT DAMAGE DUE TO A FORCED LANDING CAUSED BY ENGINE POWER FAILURE. ENGINE CEASED TO RUN DUE TO AN OVER-RICH MIXTURE CONDITION CAUSED BY A CARB. FLOAT WITH A HOLE IN IT. 1L71 3I3 I A724 E216 20020506000302002050600030CE 2002 5 6 CA020416005 120020415G2440 CONNECTOR CESSNA500 550 2076604CE PWA 530 PW530A NE EXTERNAL POWER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILOTS REPORTED THAT THEY COULD NOT START EITHER ENGINE USING EXTERNAL POWER BUT ENGINES STARTED FINE USING BATTERY POWER. MAIN POWER CABLES AND GROUND CABLE FOUND LOOSE AT GPU CONNECTOR. BOTH THE CONNECTOR STUDS AND THE POWER CABLE ENDS BURNED AND MELTED. PARTS REPLACED AS REQUIRED. 1L72 4F4 F A22CE E00053EN 20020506000312002050600031EU 2002 5 6 CA020416006 120020412G27502F11645 TORQUE TUBE BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU TE FLAP CONTROL SHEARED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) THE EMERGENCY FLAP HANDLE FAILED AT 3 DEGREES. THE TORQUE TUBE WAS FOUND SHEARED AT THE UPPER CRANK ADAPTER FITTING JUST BELOW THE FLOORBOARD. THE TORQUE TUBE WAS REPLACED AND THE SYSTEM WAS TESTED SERVICEABLE. 2L72 3T4 T A24EU A196 20020506000322002050600032EU 2002 5 6 CA020417002 120020417G24345243212137 SHAFT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NR 2 GENERATOR SHEARED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) CREW LOST NR 2 GENERATOR IN FLIGHT. AIRCRAFT RETURNED TO BASE AND THE SHAFT WAS FOUND SHEARED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020506000332002050600033CE 2002 5 6 CA020417003 120020401G32332327100506 ACTUATOR LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP MLG LEAKING W O OTHER K FLUID LOSS DEDESCENT 1 CA (CAN) ON GEAR EXTENSION, 3 GREENS, 1 UNSAFE ON RT SIDE. ON RETRACTION, NO GREENS LIGHTS, THREE UNSAFE. TWO MORE EXTENSIONS CARRIED OUT WITH SAME RESULT. GEAR EXTENDED AS PER EMERGENCY CHECK LIST(BLOWN DOWN). GEAR SWING CARRIED OUT ON JACKS, FOUND RT GEAR ACTUATOR LEAKING INTENALLY, REPLACED ACTUATOR. CHECKED SERVICEABLE. 2L72 4F4 F A10CE E6WE 20020506000342002050600034EA 2002 5 6 CA020417004 220020312G72303018389 SPACER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COMPRESSOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 11300 (CAN) AT ROUTINE ENGINE INSPECTION OF COMPRESSOR FIRST STAGE, FIRST STAGE DISK MADE SCRAPING NOISE AND JAMMED WHEN ROTATED. VISUAL INSPECTION FOUND FIRST STAGE SPACER HEAVILY RUBBED WITH LEADING EDGE METAL PIECES CURLED OUTWARD FROM INERTIAL FORCE. ENGINE REMOVED FOR REPAIR. 1L72 4T4 T A24CE E4EA 20020506000352002050600035CE 2002 5 6 CA020418001 120020416G2730MS276416 BEARING LEAR 45 45LEAR 5170805CE ELEVATOR HINGE SHIFTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRING OUT INSPECTION ON THE ELEVATOR, FOUND EXCESSIVE PLAY ON RT ELEVATOR. UPON FUTHER INSPECTION FOUND OUTBOARD HINGE BEARING HAD SHIFTED CAUSING ELEVATOR TO BIND. THIS CAUSED WEAR ON THE CENTER HINGE PICK-UP, PUSH-ROD AND DISCONNECT ASSY. 2L72 4F RTT00008WI 20020506000362002050600036CE 2002 5 6 CA020418002 120020416G5210 BEARING LEAR 45 45LEAR 5170805CE DOOR HANDLE BC MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) LOWER DOOR HANDLE BELLCRANK BEARING FOUND NOT SECURED DURING INSPECTION. 2L72 4F RTT00008WI 20020506000372002050600037NE 2002 5 6 CA020418003 220020418G7261 FILTER PWA PT6T PT6T3B 52045NE ENGINE UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) 2 OIL FILTERS WERE FOUND INSTALLED IN GEARBOX. FILTERS ARE NOT GENUINE, NOT APPROVED AND WERE NEVER RELEASED UNDER THE ENGINE / GEARBOX TYPE DESIGN. THE FILTER SHOWS AN IC NUMBER WHILE IT SHOULD INDICATE THE VENDOR P/N AND THE FILTERING CAPACITY. THE SEATING FLANGE DOES NOT MATCH THE ORIGINAL DESIGN SINCE IT IS BUILD FROM 2 ALUMINUM PIECES THAT ARE SPOT WELDED TOGETHER. PWC HAS PLACED THIS PART IN QUARANTINE FOR 21 DAYS. 4 U E22EA 20020918000042002091800004CE 2002 9 18 CA020418004 120020408G57533516505084 RIB BEECH 95 D95A 1153408CE LYC O360 IO360B1B 41514EA RT TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE RIB WAS CRACKED AND BROKEN IN THE NOSE AREA AND THE FORWARD ANCHOR NUT FOR THE FLAP ACTUATOR ATTACH BRACKET WAS BROKEN. WITH THE FLAPS UP THE AME STEPED ON THE FLAP WALKWAY AND A LOUD NOISE WAS HEARD. HE APPLIED UP AND DOWN LOADS TO THE FLAP AT THE TRAILING EDGE AND THE ACTUATOR ATTACH BRACKET FORWARD ANCHOR NUT AND A PORTION OF THE RIB PULLED THROUGH THE SKIN. THE RIB AND BRACKET WERE REPLACED WITH FACTORY NEW PARTS AND THE SKIN WAS REPAIRED WITH A FLUSH PATCH USING STANDARD SHEET METAL PRACTICES. 1L72 3O3 O 3A16 1E10 20020513000172002051300017NM 2002 5 13 CA020418005 120020416G2432BACC18W7 CIRCUIT BREAKER BOEING737 7372A3 138448ANM PWA JT8 JT8D9A 52048NE BATTERY CHARGER OVERHEATED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) A/C ON GROUND AND ALL PAX BOARDED WHEN F/A INFORMED CAPTAIN SMOKE COMING FROM FLOOR VENTS AT ROW 1. AT SAME TIME CREW NOTICED SMOKE ON FLIGHT DECK. STAIRS WERE STILL ATTACHED TO A/C AND DOORS OPEN. CAPTAIN INFORMED F/A TO DEPLANE PAX. GROUND SUPPORT, MAINT CONTROL WAS NOTIFIED. FIRE TRUCKS RESPONDED. MAINT ISOLATED VARIOUS ELECT. SYS EVENTUALLY FINDING CAUSE. NORMAL EQUIP COOLING FAN CCT BREAKER POPPED (FAN OVERHEATING); MEL 21-27-1 ISSD. BATTERY CHARGER CCT BREAKER POPPED - BATTERY CHARGER OVER HEATED; UNIT REPLACED. A/C SYSS GROUND CHECKED SERVICEABLE AND A/C RETURNED TO SERVICE WITH NO FURTHER INCIDENTS. 2L72 4F4 F A16WE E2EA 20020513000182002051300018CE 2002 5 13 CA020419001 120020419G32421338932CHNGD STATOR BFGOODRICH 215286 CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE BRAKE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2899 (CAN) DISASSEMBLED BRAKE UNIT AFTER 488 LANDINGS FOUND 1 STATOR DISC CRACKED ALMOST ALL THE WAY THROUGH, AND 2ND STATOR WITH SMALLER CRACKS. 1L72 4F4 F A22CE E1NE 20020513000192002051300019SO 2002 5 13 CA020422001 120020422G3220NAS464P427 BOLT PIPER 8628003 PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE DRAG LINK SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SCHEDULED INSPECTION OF THE AIRCRAFT NOSE LANDING GEAR REVEALED THAT THE DRAG LINK ATTACH BOLT WAS PARTIALLY BACKED OUT ON BOTH SIDES. FURTHER INVESTIGATION CONFIRMED THAT THE BOLT HAD SHEARED IN SERVICE AND WAS WORKING ITS WAY OUT. 1L72 3O3 O A19S0 E286 5 CP25EA 20020513000202002051300020GL 2002 5 13 CA020422002 220020422G725023059694 SHAFT CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL LP TURBINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OF THE LPT ASSEMBLY IT WAS DISCOVERED THAT THE LPT SHAFT HAD A SEVERE RUB AND HEAT DISCOLORATION ON THE OUTSIDE DIAMETER, LOCATED IN THE AREA OF THE HPT SLEEVE ALSO RUBBED AT FOUR LOCATION. THE SLEEVE IS ASSEMBLED INSIDE THE HPT SHAFT. THIS UNUSUAL CONDITION WAS NOTED FOR THE FIRST TIME AT RRC, THE LP SHAFT IS A CRITICAL PART. NO VIBRATION WAS REPORTED FROM THE LAST CUSTOMER, ENGINE CAE 330085 IS A LOANER ENGINE. THE LPT SHAFT, HPT SHAFT AND HPT SHAFT SLEEVE HAVE BEEN RETURNED TO INDIANAPOLIS FOR INVESTIGATION. 2L72 4J4 FRTT00007WITE6CH 20020513000212002051300021CE 2002 5 13 CA020422003 120020307G3211S21381 BOLT CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MLG SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE ATTEMPTING TO REMOVE THE LT MLG LEG TO FACILITATE A REPAIR TO AN ADJACENT AREA, IT WAS DETERMINED THAT THE MAIN ATTACH BOLT WAS SOMEHOW SEPARATED AS INSTALLED THROUGH THE INBOARD SUPPORT AND THE GEAR LEG. EVENTUAL REMOVAL OF THE BOLT REVEALED THAT IT HAD BEEN SHEARED AND WAS SOMEWHAT SIEZED BUT ALSO HELD IN PLACE BY THE NATURAL LOAD OF THE GEAR AS INSTALLED IN THE SUPPORTS. THE AIRCRAFT WAS INSPECTED FURTHER AND NO RELATED DAMAGE WAS FOUND. THE BOLT WAS REPLACED AND THE AIRCRAFT WAS RELEASED TO SERVICE. AIRCRAFT TOTAL TIME WAS 15945.7 HOURS WITH NO RECORD FOUND OF PREVIOUS REPLACEMENT. 1H71 3O3 ONT3A12 E274 20020918000052002091800005CE 2002 9 18 CA020422004 120020411G53141149800227 KEEL BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FUSELAGE WORN W K NONE O OTHER ININSP/MAINT 1 CA 1379913799 (CAN) DURING INVESTIGATION OF A DC LOAD SHARE PROBLEM BETWEEN BOTH GENERATOR FOUND FOUR WIRES CHAFFED IN THE LT NACELLE ON THE OUTBOARD KEEL WEB ASSY. THE DAMMAGE ON THE KEEL WEB WAS DUE TO ELECTRICAL ARCING BETWEEN THE WIRE AND THE KEEL WEB ASSY. NO PROTECTION WAS FOUND ON THE WIRE BUNDLE AND ON THE KEEL WEB. THE BIGGER WIRE IS 6 GAGE AND TRANSMIT THE CURRENT FROM THE LT GEN BUS TO TRIPLE FEED BUS WIRE. THE THREE OTHER CHAFFED WIRE WAS , AVIONIC BUS WIRE, THE STBY FUEL PUMP WIRE, AND THE FORWARD AIR CONDITIONNING BLOWER WIRE. IN ALL CASE NO CIRCUIT BREAKER OR CURRENT LIMITTER OPENED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020513000222002051300022NM 2002 5 13 CA020422005 120020418G32462601913 BOLT BOEING727 727260 NM PWA JT8 JT8D17 52049NE WHEEL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SERVICE CHECK, NR 2 MAIN WHEEL TIRE FOUND DEEPLY CUT AND ONE TIE BOLT BROKEN ON MAIN WHEEL HUB ASSY. NR 2 MAIN WHEEL ASSY REPLACED PER MM. MAIN WHEEL ASSY TSO: 472.9 HRS. CSO: 354 CYCLES MAIN WHEEL ASSY TO BE SENT TO OVERHAUL FACILITY FOR TEAR DOWN REPORT FOR PROBABLE CAUSE OF BROKEN TIE BOLT.FURTHER REPORTS TO FOLLOW. 2L73 4F4 FRTA3WE E2EA 20020507001112002050700111NM 2002 5 7 CA020422006 120020415G5523657378414 STRUCTURE BOEING 657378414 BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE ELEVATOR DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA BN126 (CAN) DURING REGULAR SCHEDULED MAINTENANCE INSPECTION (AD:02-01-01)THE RT ELEVATOR FAILED THE TAB HINGE FREEPLAY CHECK AT THE NR 2 ELEVATOR TAB HINGE POSITION - SUSPECTED CRACK AT ELEVATOR REAR SPAR. EDDY CURRENT INSPECTION CARRIED OUT ON RT ELEVATOR REAR SPAR - TWO CRACKS DETECTED AT THE OUTBOARD OF HINGE. RT ELEVATOR REPLACED IAW MM.27-313-11, AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020513000232002051300023EA 2002 5 13 CA020422007 220020417G852076786 GEAR PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA CRANKSHAFT BROKEN W A UNSCHED LANDING RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB, RT ENGINE SUDDENLY LOST POWER AND FEATHERED. CREW RETURNED FOR LANDING. MAINT CREW DISPATCHED AND REPLACED ENGINE WITH OVERHAULED ENGINE. A/C RETURNED TO SERVICE. THE REAR CASE OF FAILED ENGINE REMOVED, CRANKGEAR FOUND TO HAVE FAILED. IT APPEARS TO HAVE LOST ONE TOOTH, WHICH WOULD HAVE MISS TIMED ENGINE, THEN REMAINING TEETH WERE SUBSEQUENTLY ALL REMOVED, RESULTING IN ALL ACCESSORIES BEING DISCONNECTED FROM CRANKSHAFT. MATING GEARS WERE ALL INTACT AND SUSTAINED ONLY VERY MINOR COLLATERAL DAMAGE. ALL OF ACCESSORIES WERE FOUND TO BE SERVICEABLE WHEN REMOVED AND NOT A FACTOR IN FAILURE. 1L72 3O3 O A20SO E14EA 20020513000242002051300024WP 2002 5 13 CA020422008 220020228G723031071102 IMPELLER GARRTTTPE331TPE33111U 01514WP COMPRESSOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CUSTOMER REPORTED LOUD SQUEALING NOISE COMING FROM ENGINE. ENGINE WAS REMOVED. TEARDOWN REVEALED THAT REWORKED IMPELLER HAD A PIECE BROKEN OUT OF ONE VANE. 4 T E4WE 20020513000252002051300025 2002 5 13 CA020423001 420020418G6122F624Z GOVERNOR HARTZL HCE3YR2ATF PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL PROPELLER FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA DJ8047 (CAN) ON TAKE-OFF THE CREW REPORTED THAT THE LT ENGINE EXPERIENCED A POWER LOSS AS NOTED BY A REDUCED MANIFOLD PRESSURE AND RPM. VISUAL INSPECTION OF THE ENGINE, FUEL SYSTEM, IGNITION SYSTEM, INDUCTION SYSTEM, AND COMPRESSION CHECK DID NOT REVEAL ANY OBVIOUS CAUSE. THE PROBLEM COULD NOT BE DUPLICATED WITH EXTENSIVE GROUND RUNS. THE PROPELLER GOVENOR WAS SUSPECT AND WAS REPLACED. THE AIRCRAFT COMPLETED A LOCAL CHECK FLIGHT WITH NO FAULTS AND ALL ENGINE PARAMETERS WITHIN NORMAL OPERATING RANGE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020513000262002051300026 2002 5 13 CA020424001 420020423G34226226136002 GYRO BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE COCKPIT MALFUNCTIONED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) ON DEPARTURE GOT YELLOW HEADING FLAG, WHICH WAS CLEARED, HAPPENED AGAIN AT TOC, CLEARED. IN CRUISE GOT RED HEADING ON NR 1 SYSTEM, SWITCHED TO HDG ALL ON NR 2 REVERSION PANEL. RETURNED TO YYC. MAINTENANCE REPLACED THE NR 1 DIRECTIONAL GYRO, TESTED THE SYSTEM SERVICABLE AND RETURNED THE AIRCRAFT TO SERVICE. 2L72 4T4 TRTA24CE E26NE 20020513000272002051300027EU 2002 5 13 CA020424002 120020321G6220704A33633208 BEARING SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE MAIN ROTOR DELAMINATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON POST FLIGHT INSPECTION IT WAS FOUND THAT THE OUTBOARD ENDS OF THE SHPERICAL THRUST BEARINGS HAD BECOME DELAMINATED BEYOND SERVICEABLE LIMITS. THIS WAS DETERMINED BY INSERTING A FEELING GAUGE INTO THE VISIBLE CRACK IN THE ELASTOMER. PARTS WERE REPLACED WITH NEW ONES, NO FURTHER ACTION REQUIRED. 1G71 3U3 UNCH9EU E19EU 20020513000282002051300028NM 2002 5 13 CA020424003 120020418G291082950010303 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 31038 (CAN) DURING SERVICE CHECK HYDRAULIC LEAK FOUND. TRACED TO LINE IN RT WING ROLL SPOILER SYSTEM. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000292002051300029NM 2002 5 13 CA020424004 120020423G2913570717 SHAFT DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD PUMP SHEARED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 22720 (CAN) NR 1 ENGINE DRIVEN HYDRAULIC PUMP FAILED IN FLIGHT, SHEARING SHAFT ASSEMBLY IN TWO. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000302002051300030NM 2002 5 13 CA020424005 120020416G326082410306001 CIRCUIT CARD DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA 31584 (CAN) AFTER FLIGHT WAS AIRBORNE, CREW HAD A NOSEGEAR UNSAFE LIGHT IN GEAR SELECTOR HANDLE. GEAR CYCLED, NOSE GEAR LIGHT WENT OUT, BUT THEN RT MLG SHOWED DOWN AND LOCKED INDICATION ALTHOUGH GEAR WAS UP. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000312002051300031GL 2002 5 13 CA020425001 220020404G74126899093 EXCITER BOLKMS105 BO105C 5626005EU ALLSN 250C 250C20B 03013GL ENGINE FAILED W D RETURN TO BLOCK HL ELECT. POWER LOSS-50 PC NO TEST TXTAXI/GRND HDL 1 CA (CAN) NO LIGHT OFF DUE TO FAULTY PART. CAN CAUSE A REAL PROBLEM IN REMOTE AREA. 1G72 3U3 U H3EU E4CE 20020513000322002051300032CE 2002 5 13 CA020425003 120020404G554005310081 RUDDER HORN CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL TAIL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13329 (CAN) DURING ROUTINE INSPECTION THE RUDDER HORN ASSY AT THE AREA WERE THE HORN STRIKES THE RUDDER STOPS HAD BEEN DAMAGED. WE BELIEVE BY GUSTY WINDS WITHOUT THE RUDDER LOCK ON. THE RUDDER STOP SCREW HAD ACTUALLY ROLLED THE ALUMINIUM BACK ON THE HORN WHICH MADE FOR A HAZARDOUS SITUATION DUE TO THE FACT THAT THE STOP SCREW COULD HAVE JAMED OVER THE ROLLED ALUM.THE RUDDER HORN AND RIB ASSY. HAVE BEEN REPLACED WITH NEW UNITS. NO DAMAGE WAS FOUNDS IN THE STOP ATTACHEMENT AREA. 1H71 3O3 ONT3A12 E274 5 NP910 20020513000332002051300033NM 2002 5 13 CA020425004 120020424G291082950010273 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FLUID LEAK NOTED FROM LT WHEEL WELL UPON ARRIVAL. TRACED TO LT LIFT DUMP PRESSURE LINE CRACKED AT RADIUS. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000342002051300034NM 2002 5 13 CA020425005 120020404G5230 LINK DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE CARGO DOOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 28011 (CAN) CARGO DOOR WILL NOT CLOSE. HANDLE LINK ASSEMBLY DISCOVERED BROKEN. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000352002051300035NE 2002 5 13 CA020425006 220020401G7530MS274081N SWITCH DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE HBOV BLEED BENT W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) OVER TORQUE ON LT ENGINE WITH BLEEDS SELECTED ON. SUSPECT LEFT BLEED SELECTED TO HBOV FOR TAKEOFF. LT BLEED SWITCH BENT AND NOT STOPPING AT DETENT. OVERTORQUE FOR APPROX. ONE SECOND. SWITCH REPLACED AND FDR READOUT WITHIN LIMITS. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000362002051300036NE 2002 5 13 CA020425008 220020330G7200 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 FAILED W EC ENGINE SHUTDOWN ABORTED TAKEOFF ERJVIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 2796915774 (CAN) ON TAKEOFF ROLE AS POWER WAS APPLIED, NOISE HEARD FROM NR 2 ENGINE. TORQUE ROLLBACK TO 50 PERCENT AND ENGINE VIBRATION. ENGINE SHUTDOWN DUE TO INTERNAL FAILURE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020513000372002051300037EU 2002 5 13 CA020426001 120020422G7933 INDICATOR PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL ENG OIL TEMP MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT, PILOTS NOTICED QUICK RISE OF OIL TEMP, POWER WAS THEN REDUCED WHICH LOWERED THE OIL TEMP SHORTLY AFTER, NEW RISE IN OIL TEMP (LIMITS EXCEEDED), RISE AND FALL OF OIL PRESSURE (WITHIN LIMITS). PILOTS DECLARED EMERGENCY AND LANDED SAFELY. AFTER TROUBLESHOOTING, PROBLEM FOUND TO BE IN THE INDICATION SYSTEM. CONTACTS CLEANED AT THE FIREWALL CONNECTOR AND CONNECTOR SECURED. ENGINE STARTED TO VERIFY PROPER OPERATION OF THE INDICATION SYSTEM. DURING START, UNCOMMANDED ACCELERATION OCCURED. DATA RETRIEVED FROM ECTM PROCESSOR REVEALED NO LIMITS EXCEEDED. FCU REPLACED. ENGINE OPERATE NORMALLY. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020513000822002051300082NE 2002 5 13 CA020426003 220020424G7261626447 REGULATOR VALVE BOEING727 72725C 138400HNM PWA JT8 JT8D7B 52053NE NR 1 ENGINE FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) NR 1 ENGINE OIL PRESS RED LINED DURING T/O CLIMB. THROTTLE RETARDED TO IDLE, OIL PRESS BELOW RED LINE. A/C RETURNED TO BASE.OIL PRESS RELIEF/REGULATING VALVE REPLACED. ( O-RING FOUND DAMAGED, COMPLETE ASSY REPLACED) 2L73 4F4 F A3WE E2EA 20020513000832002051300083NM 2002 5 13 CA020426004 120020403G3520119001302 LATCH BOEING737 737275 1384485NM PWA JT8 JT8D17 52049NE OXYGEN SYSTEM FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) CABIN OXYGEN PSUS NR 9 RT AND NR 14 RT, NO FLOW FOUND DURING FUNCTIONAL TEST. BOTH UNITS ARE FROM THE SAME BATCH NR. BATCH NR 99795 REPLACED LATCH ASEMBLIES. 2L72 4F4 F A16WE E2EA 20020513000852002051300085WP 2002 5 13 CA020426005 120020420G7110NAS1335S3S09 PIN 1607740115 LKHEED1011 1011385114 WP RROYCERB211 RB21122B02 54555NE GLOVE FAIRING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING WALK AROUND , FOUND NR 3 ENGINE GLOVE FAIRING ADRIFT. GLOVE FAIRING FOUND RETAINED BY TWO LANYARD AND PIP PIN NOT IN PLACE FOR SECURITY. THE PIN WAS FOUND CORRODED AND THE PIN LOCKING MECHANISM WAS JAMMED DUE TO CORROSION. .IT WAS NOT POSSIBLE TO USE THE PIN FOR LOCKING THE GLOVE FAIRING IN PLACE. THE AIRCRAFT WAS RELEASED UNDER CDL 54-51. THE PIN WAS LATER REPLACED. 2L73 4F4 F A23WE E12EU 20020513000872002051300087NM 2002 5 13 CA020426006 120020420G2120 SMOKE BOEING757 75723A 1384967NM RROYCERB211 RB211535E43754555NE COCKPIT DETECTED W O OTHER RB PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) CROSSING TOP THURDERSTORM, APPLIED MAX CONTINUOUS FOR 30 SEC. SPEED DROP TO M.72 AT FL 360. SMELL OF OIL BURNED FOR 3 MINS ALL PARAMETERS NORMAL ACTION TAKEN LMWS 51130 ITEM 1,2 BVCU BITE CHECK, MCD'S INSPECTED ON BOTH ENGINE. BOTH ENGINE TEST C/O AS PER MM 71-00-00 TEST 6 VIBRATION SURVEY, TEST II, ACC/DLC, TEST 13 T/O POWER BOTH ENGINE GENERAL EXTERNAL INSPECTION C/O CHECK SERVICEABLE RII C/O BY TA114. THE DFDR WAS SENT, WAS REPLACED AND SENT FOR ANALYSIS. WAITING FOR RESULTS. 2L72 4F4 FRTA2NM E12EU 20020513000892002051300089CE 2002 5 13 CA020429001 120020423G5524 BRACKET CESSNA750 750 2076810CE ALLSN AE3007AE3007C GL ELEVATOR HINGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COMPLIED WITH CESSNA CUSTOMER LETTER NO 0423 DATED APRIL 23, 02. (INSPECTION OF LT AND RT ELEVATOR INBD HINGE BRACKETS) ONE BRACKET HAS TWO SURFACES: INBD AND OUTB.FOUND LEFT ELEVATOR INBD HINGE BRACKET CRACKED. INBD CRACK DIMENSION :. 062 INCH OUTB CRACK DIMENSION : .125 INCH, RT ELEVATOR INBD HINGE BRACKET CRACKED. INBDNONE OUTB CRACK DIMENSION: .180 INCH. ACTION: RE-INSPECT IN 100 HRS 2L72 4J4 FRTT00007WITE6CH 20020513000922002051300092NM 2002 5 13 CA020429002 120020426G32462601913 TIE BOLT BOEING727 727260 NM PWA JT8 JT8D17 52049NE MAIN WHEEL SHEARED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AIRCRAFT SERVICE CHECK FOUND NR 3 MAIN WHEEL ASSEMBLY WITH ONE SHEARED TIE BOLT NR 3 MAIN WHEEL ASSEMBLY. REPLACED IAW MM 32-45-1. MAIN WHEEL ASSEMBLY TO BE SENT TO OVERHAUL FACILITY FOR INVESTIGATION AND TEAR DOWN REPORT. FURTHER REPORT(S) TO FOLLOW. PROCEDURES FOR REPLACEMENT OF ALL TIE BOLTS WITH NEW AT OVERHAUL AND TRACKING OF THESE BOLTS IS UNDER REVIEW AT THIS TIME. 2L73 4F4 FRTA3WE E2EA 20020513000972002051300097NM 2002 5 13 CA020429003 120020429G2150 A/C PACK BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE AIR CON SYS SMOKE W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKOFF, F/A NOTIFIED CREW BOTH SMOKE DETECTORS HAD ACTIVATED AND THERE WAS A SMELL OF SMOKE IN THE CABIN. AIRCRAFT IMMEDIATELY RETURNED TO YYC AND DID AN OVERWEIGHT LANDING - MAINTENANCE INSPECTION FOUND CAUSE OF ODOUR FRON LEFT HAND AIR CONDITIONING PACK - SYSTEM DECONTAMINATED IAW MM. 21-00-01. AIR CONDITIONING SYSTEM GROUND CHECKED SERVICEABLE - AIRCRAFT RETUNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020513001032002051300103WP 2002 5 13 CA020429004 120020419G32331535927111 ACTUATOR LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE MLG FAILED W O OTHER D INFLIGHT SEPARATION APAPPROACH 1 CA (CAN) WHEN LOWERING THE LANDING GEAR CONTROL LEVER A LOUD BAG WAS HEARD, LT GEAR CONFIRMED DOWN AND LOCK WITH THE OVERWING GEAR POP-UP INDICATOR AND AIRCRAFT LANDED SAFELY. UPON INVESTIGATION ON THE GROUND, THE F/E REPORTED A COMPLETE FRACTURE OF THE LT MLG RETRACT ACTUATOR AND A BROKEN JURY BRACE. GEAR DOOR FOUND DAMAGED ALSO AND WAS REPLACED, GEAR SWING PERFORM AND AIRCRAFT SERVICEABLE. THE DAMAGED PARTS WERE SENT TO LOCKHEED FOR ANALYSIS. 2L73 4F4 F A23WE E12EU 20020513001052002051300105EA 2002 5 13 CA020430001 220020421G7310500991 FUEL FILTER AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A6 52043EA HARTZLHCB5M HCB5MA3 GL FIREWALL LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WHILE DE-INHIBITING ENGINE FCU, FUEL FOUND LEAKING FROM FIREWALL MOUNTED FUEL FILTER AT BASE OF CANISTER O-RING. FILTER CANISTER REMOVED, NEW FILTER ELEMENT AND O-RING WERE INSTALLED, FILTER ASSY TORQUED IAW AT-802 MM AND PRESSURE TESTED SERVICEABLE. A/C GROUND RUN FOR APPROX 2 HRS OVER ONE WEEK PERIOD. DURING TEST FLT PILOT NOTED FUEL SMELL IN COCKPIT. A/C RETURNED TO BASE. FUEL PRESSURE CHECK ACCOMPLISHED AND FUEL FOUND LEAKING FROM CANISTER TO BASE O-RING LOCATION. FILTER CANISTER SECURING BOLT LOCK WIRE REMOVED AND TORQUE CHECK WAS COMPLETED. 1L71 3T3 TNCA19SW E4EA 6 CP44GL 20020513001072002051300107EA 2002 5 13 CA020430002 220020408G8530LW16740 EXHAUST VALVE PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE3Y HCE3YR2A GL NR 6 CYLINDER SEPARATED W E ENGINE SHUTDOWN RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET APAPPROACH 1 CA (CAN) UPON FINAL THE PILOT NOTICED THE RT ENGINE STARTED TO RUN ROUGH & MAP CLIMB WITH A CHT DECREASE. WHEN THE POWER WAS REDUCED TO IDLE AT LANDING THE ENGINE STOPPED. THE PILOT RESTARTED THE ENGINE & TAXIED IN, BUT NOTICED THE RT ENGINE TO BE RUNNING ROUGH. UPON INSPECTION THE NR 6 CYLINDER EXHAUST VALVE WAS MISSING. DAMAGE TO THE PISTON AND CYLINDER HEAD HAD OCCURRED. THE ENGINE WAS REMOVED FOR OVERHAUL. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020513001082002051300108CE 2002 5 13 CA020430003 120020410G571207221981 RIB CESSNA182 182 2072702CE CONT O470 O470* 17026SO MCAULYD3A34 D3A34C401 GL RT WING FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT WING STA 172.00 - DURING INSTALATION OF AUXILIARY WING TANKS, AN INSPECTION ACCESS HOLE WAS CUT IN LOWER RING SKIN AT STA. 169.00 SURVEILLANCE INSPECTON OF THE WING RIB AT STA 172.00 REVEALED AN EXTENSIVE COMPRESSION FAILURE ALONG THE ENTIRE LENGTH OF PART UPPER RETURN FLANGE & WEB SECTION.- THERE WERE NO VISIBLE SIGNS OF EXTERNAL DAMAGE TO WING UPPER OR LOWER SKIN. 1H71 3O3 ONT3A13 E273 5 CP47GL 20020513001092002051300109WP 2002 5 13 CA020430004 120020318G6720369H75319 TORQUE TUBE 369A7500501 HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL T/R PEDAL CRACKED W C ABORTED TAKEOFF F FLT CONT AFFECTED TOTAKEOFF 1 CA (CAN) -PILOT NOTICED LOSS OF T/R AUTHORITY WITH A SPONGY FEEL JUST AS HE WAS PULLING INTO A HOVER. HELICOPTER WAS LANDED AND SHUTDOWN.- T/R PEDAL ASSEMBLY WAS FOUND CRACKED ALMOST 360 DEGREES.- CRACK ORIGINATED FROM UNDER 369A7511 FITTING WHERE THE ATTACH HOLE IS LOCATED. 1G71 3U3 U H3WE E4CE 20020513001102002051300110WP 2002 5 13 CA020430005 120020222G6310369D25351 SPRAG CLUTCH HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL MAIN ROTOR BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON THE 300 HOUR INSPECTION OF THE SPRAG ASSEMBLY IT WAS FOUND THAT ONE OF THE SPRAGS WAS BROKEN. THE BREAK WAS AT THE FAR END OF THE SPRAG WHERE THE PROFILE CHANGES. 1G71 3U3 U H3WE E4CE 20020514000012002051400001CE 2002 5 14 CA020430006 120020328G2435 BEARING LUCAS 6608458005 LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP STARTER GEN FAILED W O OTHER E VIBRATION/BUFFET CRCRUISE 1 CA 991168 (CAN) BEARINGS ROUGH AND NOISY. 2L72 4F4 FRTT00008WIE6WE 20020514000022002051400002SW 2002 5 14 CA020430007 120020410G2435 SHAFT 23032018 BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL STARTER GEN WORN W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 11754 (CAN) GENERATOR FAILED. GENERATOR INSPECTED, FOUND AFT SHAFT WORN.THIS PORTION OF SHAFT ENGAGES TO THE COMMUTATOR. 1G71 3U3 U H2SW E4CE 20020507001122002050700112GL 2002 5 7 CA020430008 220020410G7323206062708007 TORQUE TUBE BENDIX 23065121 BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL FUEL CONTROL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 17314 (CAN) THE TORQUE TUBE P/N 206-062-708-007 WAS FOUND CRACKED IN THE SHEAR AREA. THE CAUSE OF THE CRACKS WERE DETERMINED TO BE CAUSED BY THE GOVERNOR BECAUSE THE ARM WAS EXTREMELY HARD TO MOVE. NO COMPLAINTS FROM PILOT TO INDICATE A N2 PROBLEM. BOTH PARTS REPLACED. 1G71 3U3 U H2SW E4CE 20020514000032002051400003NE 2002 5 14 CA020430009 220020410G73217257255 FUEL CONTROL SKRSKYS61 S61N 8142104NE GE CT58 CT581401 30011NE ENGINE FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) AT 3.9 HOURS AFTER ENGINE INSTALLATION THE ENGINE PARTIALLY DECELERATED IN FLIGHT. THE ENGINE RESPONDED TO EMERGENCY THROTTLE AND WAS LANDED SAFELY. FUEL CONTROL WAS REPLACED. 2G72 4U4 U 1H15 1E3 20020514000042002051400004EA 2002 5 14 CA020430010 120020326G3246901230602 FITTING DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE MLG FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CORROSION AND STRESS CRACK DEVELOPED ON TAPER HOLE OF THE SPREADER ATTACH FITTING RT FLOAT TOWARD SPREADER ATTCH P/N 901-23060-2 WAS REMOVED AND QUARANTINED. REPLACEMENT PART SI 901-23060-2 WAS INSTALLED AS PER STC SF-97-2. 1H71 3R3 R A806 5E1 20020507001132002050700113SW 2002 5 7 CA020430011 120020327G6320214040118001 BEARING BELL 212040263107BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE MAIN ROTOR G/B FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA A124 (CAN) INFLIGHT ILLUMINATION OF TRANSMISSION OIL PRESSURE LIGHT, CONFIRMED BY VISUAL INDICATION OF LOW OIL PRESSURE INDICATION (40PSI). EMERGENCY PROCEDURES INITIATED, PRESSURE INDICATION WENT TO ZERO AFTER A FURTHER 6 MINS OF FLIGHT. EMERGENCY LANDING CARRIED OUT TO NEARBY SEA VESSEL. TRANSMISSION/DRIVE TRAIN SEIZED FOLLOWING ENGINE SHUT DOWN AND APPLICATION OF ROTOR BRAKE. TEARDOWN INSPECTION OF TRANSMISSION 26-APR-02 AT HELIPRO FACILITY IN LANGLEY BC IDENTIFIED FAILURE OF QUILL ASSY AND QTY.2 LOWER PLANETARY GEAR BEARING WHICH WERE SEIZED. 1G71 4U4 U H4SW E22EA 20020514000052002051400005EU 2002 5 14 CA020430012 120020425G26123001230117530014FIRE LOOP ISRAEL1125 ASTRASPX 4500205EU GARRTTTFE731TFE73140 29001NE RT ENGINE INTERMITTENT W FE ACTIVATE FIRE EXT. ENGINE SHUTDOWN N FALSE WARNING DEDESCENT 1 CA (CAN) WHILE ON DESCENT CREW HAD FIRE INDICATION RT ENGINE. EMERGENCY PROCEDURES INITIATED WHERE BOTH FIRE BOTTLES WERE BLOWN TO EXTINGUISH POSSIBLE FIRE AND ENGINE SHUT DOWN. LIGHT WENT OUT. LANDED WITH CRASH TRUCKS STANDING BY UNEVENTFULL. DURING TAXI IN, LIGHT CAME BACK ON, CREW SHUT DOWN AND EVACUATED AIRCRAFT. INSPECTION REVEALED NO FIRE. TROUBLESHOOTING FOUND FIRE LOOP INTERMITTENT. NEW LOOP ORDERED AND INSTALLED. 2L72 4F4 FRTA16NM E1NM 20020514000062002051400006EU 2002 5 14 CA020430013 120020401G5210 HANDLE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PAX DOOR FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) DURING CLOSING OF DOOR THE HANDLE BROKE IN HALF.THIS IS THE 3RD ONE BROKEN. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020731001112002073100111EU 2002 7 31 CA020501001 120020409G5210SWF653150214P3H STRUT SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE PAX DOOR FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GAS STRUTS FAIL TO HOLD DOOR OPEN. 1G71 3U3 U H9EU E19EU 20020731001122002073100112SW 2002 7 31 CA020501002 120020411G63302090313441 FITTING BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE M/R TRANSMISSIONCRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND AT BOTTOM OF BEAM (FITTING HOUSING) WHERE 5TH MOUNT IS HOUSED, 3/4 INCH LONG. BELL MAINTENANCE MANUAL SPECIFIES NO CRACKS IN THIS AREA. 1G71 4U4 U H1SW E17EA 20020514000072002051400007EU 2002 5 14 CA020501003 120020417G79311103P0954 SWITCH ISRAEL1125 ASTRASPX 4500205EU GARRTTTFE731TFE73140 29001NE OIL PRESSURE MALFUNCTIONED W O OTHER N FALSE WARNING TXTAXI/GRND HDL 1 CA (CAN) ON SHUTDOWN, LT ENGINE LOW OIL PRESSURE ANNUNCIATOR LIGHT DID NOT COME ON. INDICATOR LIGHT TEST FOUND SERVICEABLE. PRESSURE CHECKING OF SWITCH WITH NITROGEN FOUND ANNUNCIATOR COMING ON AT 60 PSI AND OFF AT 51 PSI AS MARKED ON SWITCH. SWITCH ASSY REINSTALLED AND GROUND RUN FUCNTION. LEAK CHECKED SERVICEABLE. NEW SWITCH ORDERED FOR ANY RECURRANCE (279.3 HRS & 142 CYCLES).8 FLTS LATER, THE RT ENGINE LOW OIL PRESSURE LIGHT DID NOT COME ON WHEN ENGINE SHUTDOWN. INDICATOR LIGHTS TEST WORKED OKAY. RT LOW OIL PRESSURE SWITCH REPLACED WITH NEW (297.0 HRS & 150 CYCLES). FUNCTION AND LEAK CHECKED SERVICEABLE. 2L72 4F4 FRTA16NM E1NM 20020507001142002050700114WP 2002 5 7 CA020501009 120020413G5610 WINDSHIELD SIERRACIN 1634896101 LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE COCKPIT FAILED W O OTHER O OTHER CRCRUISE 1 CA 3923LR (CAN) CAPTAIN WINDSHIELD HAD MAJOR DELAMINATION IN FLIGHT . THE CREW PROCEDURES WERE CARRIED OUT BY PULLING THE CIRCUIT BREAKER TO DEACTIVATE THE WINDSHIELD HEAT SYSTEM. MAINTENANCE REPLACED THE WINDSHIELD AND ALSO REPLACED THEWINDSHIELD HEAT CONTROL UNIT. 2L73 4F4 F A23WE E12EU 20020514000082002051400008CE 2002 5 14 CA020501011 120020220G554204330106 SKIN CESSNA 043301015 CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SKIN CRACKED AT UPPER LIGHTNING HOLE. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020514000092002051400009EA 2002 5 14 CA020501013 220020401G7414M3100 IMPULSE COUPLING 4372 ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 97020756 (CAN) AS A RESULT OF 2 RECENT CATASTROPHIC MAGNETO IMPULSE COUPLING FAILURES ON OTHER AIRCRAFT IN OUR FLEET THAT RESULTED IN ENGINES BEING REPLACED, THIS MAGNETO WAS REMOVED AND INSPECTED FOR CONDITION OF THE IMPULSE COUPLING. ONE OF THE TWO PAWLS AND IT'S ATTACHMENT RIVET WAS FOUND TO BE EXTREMELY LOOSE AND HAD WORN THE PAWL MOUNTING BACKING PLATE AT THE RIVET ATTACHMENT AREA. A NEW IMPULSE COUPLING WAS INSTALLED AND THE MAGNETO RETURNED TO SERVICE. 1L71 3O3 O0 A76EU 1E10 20020514000102002051400010EA 2002 5 14 CA020501014 220020328G7414M3100 IMPULSE COUPLING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MAGNETO BROKEN W D RETURN TO BLOCK D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA (CAN) DURING AN ENGINE START, AN UNUSUAL NOISE WAS HEARD COMING FROM THE ENGINE. INVESTIGATION BY MAINTENANCE PERSONNEL REVEALED THAT THE LT MAGNETO HAD FAILED AND THAT IT'S IMPULSE COUPLING HAD COME APART. THE PARTS MISSING FROM THE IMPULSE COUPLING ENTERED INTO THE ENGINE AND CAUSED CONSIDERABLE DAMAGE TO THE MAGNETO AND ENGINE. THE ENGINE HAD TO BE REPLACED AS A RESULT OF THE DAMAGE AND RESULTING OIL SYSTEM CONTAMINATION. THE FAILED IMPULSE COUPLING HAD 882.0 HOURS TIME SINCE NEW. NO DEFECTS WERE NOTED DURING THE LAST 500 HOUR INTERNAL INSPECTION (SLICK SB 2-80C) COMPLETED 389.7 HOURS PREVIOUS TO FAILURE. 1L71 3O3 O0 A76EU 1E10 20020514000112002051400011NE 2002 5 14 CA020501015 220020419G7310LK30233 LINE AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE FUEL SYSTEM DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 41123 (CAN) WHILE THE AIRCRAFT WAS IN FOR AN ENGINE CHANGE , FOUND ON NR 1 ENGINE , THAT THE FUEL TUBE ASSY LINE DISCONNECT TO HP PUMP WAS DENTED. ONCE REMOVED, FOR REPLACEMENT , NOTICED THAT THE FERRULE, THE FERRULE SEAL CARRIERS WERE WORN AND PITTED AND ALSO THE CONNECTOR HAD 2 GROOVES AND WERE ALSO PITTED. 1L72 4F4 FRTA46NM E39NE 20020514000122002051400012NM 2002 5 14 CA020502001 120020430G28213038454 FILTER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUEL SYSTEM CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) APPROX 1/2 HR INTO FLT, FLT CREW NOTICED "IMPENDING FUEL BYPASS" WARNING LIGHT ILLUMINATED ON RT ENGINE. A/C RETURNED TO MAINT BASE. INSPECTION OF LOW PRESSURE FILTER REVEALED CONTAMINATION OF SMALL PARTICLES OF PRC & HARDENED SEALANT. THESE ORIGINATED FROM FUEL TANK ACCESS PANELS. INSP OF HIGH PRESSURE FILTER SHOWED NO SIGNS OF CONTAMINATION. A/C HAD RECENTLY UNDERGONE MAINT IN FUEL TANKS. FUEL TANKS WERE CLEANED PRIOR TO CLOSING OF THE TANK PANELS. FUEL FILTER ON LT ENGINE CHANGED AS PRECAUTIONARY MEASURE: CONTAMINATION OBSERVED ON LOW PRESSURE FILTER TO LESSER DEG. FILTERS WERE WELL WITHIN ALLOWABLE TIME IN SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020514000132002051400013NE 2002 5 14 CA020502002 320020502G6111SFA13SIOA1 BLADE CNDAIRCL215 CL2156B11415 EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A DAILY INSPECTION, A CRACK ON A PROP BLADE APPROX 5 LONG, NO REPORT FROM THE PILOT AND NO SIGN OF IMPACT WAS FOUND DURING THE VISUAL INSPECTION. IT WAS REPORTED THAT A FEW DAYS BEFORE PAINT STARTED PEELING OFF FROM THAT BLADE AND KEPT PROGRESSING EACH DAY UNTIL A CRACK WAS FOUND. FURTHER INVESTIGATION REVEAL AFTER TAB TEST INSPECTION SOME DELAMINATION AROUND THE CRACK. 2H72 4T4 TRTA14EA E20NE 6 CP7NE 20020514000142002051400014CE 2002 5 14 CA020502003 120020407G7120 TUBE BEECH 18 3TM 1151046CE PWA R985 R985AN14B 52008NE MOUNT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 15292 (CAN) DURING INITIAL INSPECTION OF AIRCRAFT COMPLETED AD CF-63-08 WAS INSPECTED AND FOUND TO BE BROKEN AS ATTACHED INDICATES. FURTHER INVESTIGATION SHOWED THAT A PREVIOUS CRACK HAD JUST BEEN WELDED SHUT. THIS CRACK WELDED HAD CRACKED AGAIN AND GONE UNNOTICED. 1L72 3R3 R A765 5E1 20020514000152002051400015 2002 5 14 CA020502004 420020427G8300 FITTING BOEING737 737297 1384480NM PWA JT8 JT8D9A 52048NE NR 1 ENGINE G/B MISSING W EA ENGINE SHUTDOWN UNSCHED LANDING JYKWARNING INDICATION ENGINE STOPPAGE FLUID LOSS CRCRUISE 1 CA (CAN) ENROUTE PILOT NOTICED THE OIL QUANTITY WAS AT ZERO ON THE NR 1 ENGINE - BOTH OIL PRESSURE AND OIL TEMPERATURE WERE NORMAL. SHORTLY THERE AFTER THE OIL PRESSURE STARTED TO FLUCTUATE AND THE OIL PRESSURE WARNING LIGHT ILLUMINATED.FLIGHT CREW SHUTDOWN NR 1 ENGINE. AIRCRAFT DIVERTED AND PERFORMED AN ABNORMAL LANDING - AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION REVEALED THE BANJO FITTING BLOWN OUT FROM THE GEARBOX CAUSING THE OIL LEAK.MAINTENANCE REPLACED THE GEARBOX, GROUND CHECKED THE ENGINE AS SERVICEABLE - NO LEAKS TO REPORT.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020514000162002051400016EA 2002 5 14 CA020502005 220020405G7414M3100 IMPULSE COUPLING 4372 ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MAGNETO FAILED W D RETURN TO BLOCK D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA 96010043 (CAN) THE LT MAGNETO FAILED DURING ENGINE START UP. MAGNETO IMPULSE COUPLING HAD COME APART AND LOOSE PIECES FROM COUPLING CAUSED MAJOR DAMAGE TO MAGNETO AND ENGINE. ENGINE REPLACED AND A/C RETURNED TO SERVICE. 1L71 3O3 O0 A76EU 1E10 20020507001162002050700116EA 2002 5 7 CA020502007 120020411G499049100011 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE APU BAY FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) AIR TURN BACK, AIRCRAFT CABIN FILLED WITH SMOKE, RETURN TO ST-LOUIS. AIRCRAFT DEPARTED WITH THE APU UNDER MEL DUE TO LOW OIL QUANTITY & APU SHUTDOWN (APU FAILURE) OIL FROM THE APU WENT IN THE LT PACK CAUSING THE SMOKE. REPLACED THE APU AND THE PACK. 2L72 4F4 FRTA21EA E15NE 20020514000172002051400017EA 2002 5 14 CA020502008 120020413G27501104SD1002011 CONTROL CABLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE LT TE FLAP ACT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) FLAPS FAIL MESSAGE ON EICAS AFTER TAKEOFF WITH FLAPS SELECTED AT 8, AIR TURN BACK. REPLACED FLEX CABLE ACTUATOR BETWEEN NR 1 AND 2 ACTUATORS ON THE LT SIDE. 2L72 4F4 FRTA21EA E15NE 20020514000182002051400018NM 2002 5 14 CA020502012 120020323G2780285T004953 CONTROL UNIT BOEING767 767383 1385214NM GE CF6 CF680C2B6F 30025NE LE SLATS FAILED W O OTHER F FLT CONT AFFECTED TOTAKEOFF 1 CA (CAN) FLAP DISAGREE MESSAGE ON EICAS WHEN FLAP SELECTED TO RETRACT FROM 5 DEGREE TO 1 DEGREE ON TAKEOFF. ALTERNATE TE FLAP EXTENSION USED FOR LANDING. FOUND TO BE THE FSEU AT FAULT (FLAP SLAT CONTROL UNIT). REPLACED ELECT FLAP SLAT UNIT. 2L72 4F4 FRTA1NM E13NE 20020514000192002051400019 2002 5 14 CA020502014 420020417G2200285T0015116 ASYMMETRY SWITCH BOEING767 767333 1385301NM PWA 4060 PW4060 52119NE AUTOFLIGHT SYS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AT 400 FEET AFTER TAKEOFF CREW REPORTED AN AILERON LOCKOUT MESSAGE, RUDDER RATIO MESSAGE AND NONE OF THE 3 AUTOPILOTS COULD BE ENGAGED. AIRCRAFT RETURNED TO AIRPORT.BOTH LT AND RT STABILIZER TRIM/ELEVATOR ASYMMETRY MODULES (SAM) REPLACED AS PER AMM 27-09-00.SYSTEM TESTED SERVICEABLE.CHECK FLIGHT CARRIED OUT AND NO FAULT FOUND. 2L72 4F4 FRTA1NM E24NE 20020514000202002051400020NM 2002 5 14 CA020502018 120020404G561058935722 WINDOW BOEING737 737275 1384485NM PWA JT8 JT8D17 52049NE COCKPIT FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON GROUND FOUND FIRST OFFICER NR 4 WINDOW SHATTERED. RELACED NR 4 WINDOW. 2L72 4F4 F A16WE E2EA 20020507001212002050700121NM 2002 5 7 CA020502019 120020401G3150285T03855 MODULE BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE AURAL WARNING FAILED W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) REJECTED TAKEOFF AT 120 KNOTS DUE TO CONFIGURATION WARNING (FIRE WARNING BELL). NO OTHER INDICATIONS OF ANY FAULTS, FOUND TO BE THE AURAL WARNING BELL/CHIME MODULE AT FAULT. REPLACED THE AURAL WARNING BELL/CHIME MODULE. 2L72 4F4 FRTA1NM E3NE 20020514000212002051400021EA 2002 5 14 CA020502023 120020502G2820CC670622581 LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF34* NE FUEL SENSE LEAKING W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE AT FL330, BOTH FUEL PUMPS ON- INTERMITTENTLY AT FIRST, AND THEN PERMANENTLY. RT MAIN EJECTOR FLICKERING YELLOW ON SYNMOPTIC PAGE. FUEL BALANCE REMAINED OK BUT 65-70 KG IN CENTRE TANK. CENTRE TANK WAS ACCESSED AND THE SENSE LINE FROM RT MAIN EJECTOR TO LP SWITCH FOUND TO HAVE BROKEN AT THE FERRULE (AT PRESSURE SWITCH END OF PIPE), ALLOWING FUEL TO LEAK FROM THE EJECTOR INTO THE CENTRE TANK. REPLACEMENT PIPE WAS FITTED AND THE AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020514000232002051400023EA 2002 5 14 CA020502025 120020426G2820CC670622581 LINE CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF34* NE FUEL SENSE BROKEN W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) WHILE ON DESCENT, THE R MAIN EJECTOR CAUTION MESSAGE BECAME APPARENT TO THE CREW. AT THE POINT OF SHUTDOWN, THERE WAS 80 LBS OF FUEL IN THE CENTRE TANK.MAINTENANCE FOUND THE RT MAIN EJECTOR PRESSURE SWITCH SENSE LINE (CC670-62258-1) TO BE BROKEN JUST AT THE FERRULE GOING INTO THE "B" NUT. AFTER OBTAINING THE APPROPRIATE AUTHORIZATION, THE AIRCRAFT WAS FERRIED FOR INSTALLATIION OF A REPLACEMENT PART. 2L72 4F4 FRTA21EA E15NE 20020514000242002051400024EA 2002 5 14 CA020502026 120020428G5610NP1393215 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W BA EMER. DESCENT UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) PILOT'S SIDE WINDOW CRACKED IN FLIGHT. 2L72 4F4 FRTA21EA E15NE 20020514000252002051400025CE 2002 5 14 CA020502027 120020429G2720666000178 SERVO CESSNA560 560XL 2076702CE PWA 545 PW545A NE RUDDER MALFUNCTIONED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING A PHASE INSPECTION, THE AUTO-PILOT SERVO CABLE AND THE SECONDARY RUDDER CABLE WERE FOUND CROSSING EACH OTHER BETWEEN THE LOWER AFT RUDDER SECTOR AND PULLEYS AT THE 63 PERCENT VERTICAL SPAR IN ZONE 340.THE AUTO-PILOT SERVO CABLE HAS BEEN RE-ROUTED AS PER MAINTENANCE MANUAL. 2L72 4F4 FRTA22CE E00059EN 20020514000262002051400026SO 2002 5 14 CA020503002 120020403G57513564016 DOUBLER PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA MCAULY3D36C B3D36C424 GL AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING AN UNSCHEDULED MAINTENANCE EVENT (AILERON ADJUSTMENT), WE DISCOERED THAT THE LT AILERON OUTBOARD DOUBLER WAS CRACKED ON THE INBOARD TOP CORNER. THE CRACK WAS 1 INCH LONG. 1L71 3O3 O 2A13 1E10 5 CP58GL 20020612000082002061200008SO 2002 6 12 CA020503003 120020326G7810MVT69183200 COUPLING PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA MCAULY3DF36CB3DF36C526 GL EXHAUST PIPE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING TOUBLESHOOTING OF HIGHER THAN NORMAL E.G.T. INDICATION, (CAUSED BY MAGNETO), THE RT EXHAUST PIPE COUPLING AT THE TRANSITION WAS FOUND LOOSE. COUPLING P/N MVT69183-200 WAS REMOVED FOR DETAILED INSPECTION, A CRACK APPROXIMATELY 1.5 INCHES LONG WAS DETECTED IN THE LOWER FLAT SURFACE OF THE MIDDLE SEGMENT. 1L72 3O3 O A20SO E14EA 5 C 20020514000272002051400027CE 2002 5 14 CA020503004 120020409G532004102362 STIFFENER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11095 (CAN) PART FAILED IN THE CUT-OUT OF THE LOAD-BEARING MEMBER. 1H71 3O3 ONT3A19 E223 20020612000092002061200009EA 2002 6 12 CA020503005 220020411G8520LW13820 CRANKCASE BEECH 23 C23 1151242CE LYC O360 O360A4K 41514EA ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING A 50 HOUR INSPECTION, AN OIL LEAK WAS NOTED ON THE CRANKCASE HOUSING. FURTHER INSPECTION REVEALED A CRACK ON THE FORWARD LEFT HAND PART OF THE CASE. 1L71 3O3 O A1CE E286 20020514000282002051400028EU 2002 5 14 CA020503006 120020429G5240F5348614400200 DOOR AIRBUS330 A330243 3930330EU RROYCERB211 RB211TRENT77 NE WATER SERVICE MISSING W O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA (CAN) POTABLE WATER SERVICE PANEL MISSING ON ARRIVAL IN YYZ. MAINTENANCE RELEASED THE AIRCRAFT IN ACCORDANCE WITH CDL 52-7. 2L72 4F4 FRTA46NM E39NE 20020612000172002061200017EU 2002 6 12 CA020507003 220020412G8500 ENGINE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU NACELLE FAILED W O OTHER ERYVIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE STOPPAGE ININSP/MAINT 1 CA (CAN) -PILOT REPORTED 'PROP NOT CYCLING DURING RUN-UP, ALL INDICATIONS NORMAL'.- LINEMAN ATTEMPTED RUN-UP & TRIED TO REACH MAX RPM'S & CYCLE PROP. ENGINE REPORTEDLY LOST POWER & LINEMAN INCREASED THROTTLE, HE KEPT DOING SO UNTIL ENGINE RAN ROUGH, AT WHICH POINT HE RETARDED THROTTLE. ENGINE SEIZED AT IDLE. LINEMAN SUBSEQUENTLY CONTACTED MTC CONTRACTOR & CALLED FOR HELP. COMPANY ENGINEER ARRIVED. AMO CONTRACTOR ARRIVED & PROCEEDED TO INSPECT THE ENGINE. NOSE CASE CHIP PLUG FOUND COVERED IN STEEL FILINGS, WITH VAST & EXCESSIVE QUANTITY OF BRASS, ALUMINUM & STEEL IN THE OIL FILTER. ENGINE REMOVED FOR TEARDOWN BY ROTECH RESARCH CANADA. 1L71 3O3 ONTTA4CH E00051EN 20020612000212002061200021SW 2002 6 12 CA020507008 120020417G32509937 SHOE GULSTM690TP 690 0141720SW GARRTTTPE331TPE3315251K NM NLG STEERING DIRTY W C ABORTED TAKEOFF O OTHER TOTAKEOFF 1 CA (CAN) ANTI-SHIMMY FRICTION SHOE HAD DIRT OR SAND IN IT THAT WAS CAUSING MORE DRAG THEN NECESSARY. SAND MAY HAVE BEEN PICKED UP IN PARKING AREA. AIRCRAFT WAS ATTEMPTING TO TAKEOFF, A STEERING CORRECTION WAS MADE AND STEERING COULD NOT BE CENTERED. AIRCRAFT WENT OFF RUNWAY INTO GRASS. AIRCRAFT SUFFERED NO DAMAGE. 1H72 3T4 T 2A4 E2WE 20020918000062002091800006EA 2002 9 18 CA020507016 120020502G5101C6TE105329 HINGE DHAV DHC6 DHC6 2802606EA MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) HINGE HALF - MISMANUFACTURED. PLEASE NOTE RMA RECEIVED TWO C6WFM1218-27 CLEATS FROM DIFFERENT SUPPLIERS, 1 MAY 4/01 FOR RMA INVENTROY AND 1 APRIL 23/02 FOR A WORK ORDER. BOTH CLEATS ARE MISMANUFACTURED. THE CLEAT FROM C6WFM1218-27 APRIL 23/02 IS LOT 0007 FROM BRAD. 1H72 3T RTA9EA 20020612000352002061200035SW 2002 6 12 CA020507018 120020425G275019023 CONTROL CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA TE FLAPS FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT AND RT FLAP UPPER CABLES FRAYED AT WING ROOT PULLEYS. 1H71 3O3 O A21CE E286 20020612000362002061200036EA 2002 6 12 CA020507019 120020422G571122840111 SPAR CAP ARONCA15 15AC 0191202EA CONT C145 C1452 17012SO WING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INTERGRANULAR CORROSION FOUND ON TOP SPAR CAP (ANGLE) BOTH WINGS. REQUIRED REPLACEMENT (FOUND AT ANNUAL INSPECTION). 1H71 3O3 O A802 E253 20020612000392002061200039EU 2002 6 12 CA020507022 120020421G61201530650012 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MUHBR MTV MTV3BC EU PROP CONTROL BROKEN W D RETURN TO BLOCK E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA (CAN) A STUDENT PILOT REPORTED TO MAINTENANCE THAT ON A GROUND RUN OF THE AIRCRAFT THAT THE PROPELLER WOULD NOT CYCLE WHEN THE CONTROL WAS PULLED OUT TO PUT THE PROP INTO COARSE PITCH. INVESTIGATION FOUND THAT THE PROP CONTROL FLAT SPRINGS THAT HOLD THE PROP CONTROL SYSTEM RIGID HAD BROKEN. THESE SPRINGS GO THROUGH MANY CYCLES AND BREAK WHEN THEY ARE STRESSED. NEW SPRINGS WERE INSTALLED WITH NO STRESS BETWEEN THE BRACKET AND THE SUPPORT, AND THE PROP FUNCTIONED PROPERLY ON THE RUN-UP. 1L71 3O3 O0 A76EU 1E10 5 CUSSR 20020612000502002061200050EU 2002 6 12 CA020508003 120020422G3250Z4242170001 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA NLG STEERING BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIED AND THE RT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSION. STUDENT REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON THE NOSE GEAR STEERING SPRINGS. 1L71 3O3 O0 A76EU 1E10 20020612000522002061200052EU 2002 6 12 CA020508004 120020423G3250Z4242170001 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA NLG STEERING BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIED AND THE RT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WASREPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSION. STUDENT REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON THE NOSE GEAR STEERING SPRINGS. 1L71 3O3 O0 A76EU 1E10 20020612000552002061200055EU 2002 6 12 CA020508005 120020419G3250Z4242170001 SPRING ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA NLG STEERING BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) UPON TAXI A STUDENT PILOT NOTICED AN EXCESSIVE AMOUNT OF PLAY IN THE NOSE STEERING SYSTEM. MAINTENANCE WAS NOTIFIED AND THE LT STEERING SPRING WAS FOUND TO BE BROKEN. THE SPRING WAS REPLACED USING THE MINIMUM SPACING FOR PRELOAD TENSION. STUDENTS WERE ONCE AGAIN REMINDED OF GETTING THE AIRCRAFT MOVING BEFORE TURNING THE NOSE WHEEL TO REDUCE STRESS ON THE NOSE GEAR STEERING SPRINGS. 1L71 3O3 O0 A76EU 1E10 20020612000952002061200095NM 2002 6 12 CA020508011 120020327G3320B0330211150 SOCKET DHAV DHC8 DHC8* NM PWA PW120 PW123 NE CABIN ARCED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) AURCRAFT CARRIED OUT AN AIR-RETURN WITH AN APPARENT BURNING SMELL IN THE CABIN. UPON ENGINEERING INVESTIGATION, THE BURNING SMELL WAS TRACED TO THE CABIN LHS NR 2 FLUROESCENT TUBE LAMP HOLDER P/N BV03302-11-150. THE LAMP HOLDER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. NO FURTHER DEFECT HAS BEEN REPORTED. 2H72 4T4 TRTA13NM E20NE 20020612000962002061200096NM 2002 6 12 CA020508012 120020501G32338300101 ACTUATOR DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE MLG CONTAMINATED W L ABORTED APPROACH RJ PARTIAL RPM/PWR LOSS WARNING INDICATION APAPPROACH 1 CA (CAN) DURING A FLT ON FINAL DESCENT LDG GEAR WAS SELECTED "DOWN". NLG FAILED TO EXTEND WITH BOTH DOOR & UNSAFE LIGHT ILLUMINATED. A MISSED APPROACH WAS CARRIED OUT BY FLT CREW WITH GEAR SELECTION NOT CHANGED. DURING MISSED APROACH, APPROX ONE MIN AFTER GEAR WAS SELECTED DOWN NLG EXTENDED & LOCKED DOWN WITH NO INPUT FROM FLT CREW.FROM GO-AROUND AIRCRAF T MADE ANOTHER APPROACH FOLLOWED BY A LDG W/O INCID.. SUBSEQUENT ENGINEERING INVEST. REVEALED THAT NLG ACTUATOR WAS UNSERVICEABLE DUE TO A CONTAMINANT BEING FOUND INTERNALLY IN ACTUATOR. ACTUATOR WAS REPLACED, GROUND RETRACTIONS CARRIED OUT SATISFACTORILY, & A/C WAS RT-SRV. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020612001082002061200108SO 2002 6 12 CA020508015 120020503G5730 SKIN PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE AIRCRAFT WAS STORED IN COLLINGWOOD SINCE NOVEMBER AND FLOWN TO TORONTO IN APRIL FOR ITS ANNUAL. UPON INSPECTION SECTION OF LOWER WING SKIN WAS PEELED BACK, ABOUT EIGHT INCHES, DUE TO SLIPSTREAM. THE INITIAL CRACK HAD BEEN STOP DRILLED.THIS SECTION IS POSSIBLY PRONE TO CRACKING AS A RESULT OF WING FLEXING DURING FLIGHT. THERE ARE OTHER CRACKS STOP DRILLED IN THIS AREA SO A MORE FREQUENT INSPECTION SHOULD BE INITIATED. 1L71 3O3 O A3SO 1E4 20020612001102002061200110EA 2002 6 12 CA020508016 220020507G85303813 STUD PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA CYLINDER BROKEN W E ENGINE SHUTDOWN EKJVIBRATION/BUFFET FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) MAY 7, 2002. THE AIRCRAFT DEPARTED YVR ON A NORMAL POSITIONING FLIGHT TO YYJ. ABOUT 15 MILES OUT OF YYJ, THE CREW NOTED A ROUGHNESS IN THE LT ENGINE FOLLOWED BY OIL COMING OUT OF THE COWLING, AND ELECTED TO PERFORM A PRECAUTIONARY SHUTDOWN. LANDED IN YYJ WITHOUT FURTHER INCIDENT. INVESTIGATION REVEALED THAT THE 3/8 INCH DIAMETER STUD P/N 38-13 AT THE 1:00 POSITION ON THE NR 2 CYLINDER HAD FAILED JUST BELOW THE CASE SURFACE UNDER THE CYLINDER MOUNTING FLANGE. LOSS OF THIS STUD CAUSED RAPID FAILURE OF THE OTHER 3 STUDS ON THE UPPER FLANGE OF THIS CYLINDER, UNSEATING THE BASE SEAL AND RELEASING OIL. THE LOWER STUDS WERE ALL INTACT AND HOLDING THE CYLINDER IN PLACE. 1L72 3O3 O A20SO E14EA 20020612001752002061200175NM 2002 6 12 CA020509012 120020310G3320338210 SOCKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA CABIN BURNED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) AFTER ENGINE START SMOKE IN REAR PART OF CABIN WAS REPORTED BY CABIN CREW. THE THIN WHITE SMOKE NEAR SIDEWALL AT ROW 20AC WAS ACCOMPANIED BY A SMELL LIKE BURNED PLASTIC. ON GROUND EMERGENCY WAS PERFORMED. EMERGENCY EVACUATION THROUGH FORWARD ENTRANCE DOOR WAS PERFORMED. LAMP HOLDER REPLACED AND AIRCRAFT RELEASED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN 20020612001792002061200179NM 2002 6 12 CA020509016 120020204G3260 SENSOR DHAV DHC8 DHC8* NM PWC 150 PW150A EA LANDING GEAR FAILED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT, GEAR DOWN SEQUENCE STARTED WITHOUT ANY PILOT INPUT. GEAR RETURNED TO UP POSITION AND NO FURTHER INCIDENT RESULTED. SPEED REDUCED TO 200 KIAS AND FLIGHT CONTINUED WITH AN UNEENTFUL LANDING.MAINTENANCE PERSONNEL CHECKED AND ADJUSTED ALL SENSORS. LANDING GEAR CYCLED SEVERAL TIMES AFTER ADJUSTMENT WITHOUT ANY REMARKS. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN 20020613000122002061300012SO 2002 6 13 CA020510016 220020427G8530654961C CYLINDER CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL ENGINE WORN W O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CA (CAN) ENGINE INDICATING SYS & PARAMETERS WERE OP NORMALLY.AT 164.1 HRS OF OP, A CYLINDER DIFFERENTIAL CHECK WAS CARRIED OUT. ALL CYLINDERS WERE FOUND TO BE IN 60/80 RANGE. A/C CONTINUED TO FLY & AT 260.6 HRS OF OP, A 2ND DIFFERENTIAL CHECK SHOWED READINGS OF LOW 50'S WITH ONE CYLINDER 24/80. 2 CYLINDERS SHOWED EXHAUST VALVE LEAKS. TCM WAS CONTACTED & ALL CYLINDERS WERE REMOED & SENT TO A REPAIR STATION FOR INVESTIGATION. THOSE CYLINDERS WERE REPAIRED & INSTALLED. A/C WAS GROUND RUN & TEST FLOWN, PRODUCING ADEQUATE POWER IN ALL FLT CONDITIONS. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20020613000152002061300015SO 2002 6 13 CA020510019 120020501G3233AN517A BOLT PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE LT MLG ACTUATOR SHEARED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH THE LANDING GEAR WAS SELECTED DOWN, THE RIGHT MAIN & NOSE GEAR LOCKED DOWN CORRECTLY BUT THE LEFT MAIN DID NOT. THE CREW THEN SELECTED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. UPON INSPECTION THE LEFT ACTUATOR UPPER BOLT WAS FOUND TO BE SHEARED. 1L72 3T4 TRTA8EA E4EA 20020613000162002061300016GL 2002 6 13 CA020510020 320020415G611031561 CLAMP BEECH 55 D55 1152730CE CONT O520 IO520C 17032SO MCAULY2AF34C2AF34C55 GL COUNTERWEIGHT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) COUNTERWEIGHT CLAMP FOUND TO BE CRACKED IN THE MIDDLE MID-WAY BETWEEN THE CLAMP RETAINING BOLTS. 1L72 3O3 O 3A16 E5CE 5 CP5EA 20020613000172002061300017NE 2002 6 13 CA020510021 220020430G74141021488 RETAINER BENDIX SF14RN8 DOUG DC4 C54EDC 3021528WP PWA R2000 R2000* 52023NE MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA 214343 (CAN) RETAINER FOR VERNIER DRIVE COUPLING WORN ON ITS FLATS, ALLOWING VERNIER TO SLIP AND THEREFORE (ENGINE) TIMING TO CHANGE. OVERHAUL SHOPS HAVE BEEN NOTIFIED. 2L74 4R4 R A762 5E5 20020613000182002061300018GL 2002 6 13 CA020510022 320020508G6110A0014B THRUST LINK UNIVAR108 1083 9230408NM LYC O435 O435C 41516EA HARTZLHC12X HC12X208 GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE PROPELLER WAS OVERHAULED ON JULY 18, 1996, WAS REMOVED FOR AD 97-18-02 WITH 42.4 HRS. TSO. ON JUNE 29, 1999 THE AD WAS COMPLETED AND THE PROPELLER INSTALLED ON JULY 2, 1999. ON APRIL 19, 2000 THE PROPELLER WAS REMOVED FROM THE AIRCRAFT WITH 88.3 HRS. TSO. UPON OUR DISASSEMBLY OF THE PROPELLER WE FOUND CORROSION IN ONE OF THE BEARINGS ON ONE SIDE OF THE PROPELLER, AND EXTREME CORROSION ON THE BEARING SURFACES AND THE INNER SURFACE OF THE CLAMP ASSEMBLY. BOTH OF THE BEARINGS AND THE ONE CLAMP REQUIRE REPLACEMENT. 1H71 3O3 O A767 E228 5 CP845 20020524000862002052400086NM 2002 5 24 CA020510025 120020509G2910DCS252840124 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM DAMAGED W O OTHER K FLUID LOSS LDLANDING 1 CA 29504 (CAN) NR 2 HYD ISOLATION VALVE CAUTION LIGHT CAME ON WHEN GEAR EXTENSION SELECTED. ALTERNATE GEAR EXTENSION CARRIED OUT. LANDED WITHOUT FURTHER EVENT. MAINTENANCE FOUND NLG ACTUATOR HYD PRESSURE LINE SPLIT 1INCH FROM ACTUATOR FITTING 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020613000232002061300023EU 2002 6 13 CA020514002 220020513G7322961215 NEEDLE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CARBURETOR WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE NUMBER 3 CARBURETOR NEEDLE POSITION WAS FOUND TO BE WORN TO 1/16 INCH 1L71 3O3 INTTA4CH EXPE3I 20020613000242002061300024EU 2002 6 13 CA020514003 220020510G7322961215 NEEDLE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU CARBURETOR WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NEEDLE POSTION 3 WAS FOUND TO BE WORN TO 3/32 AN INCH. 1L71 3O3 ONTTA4CH E00051EN 20020524000882002052400088SO 2002 5 24 CA020515003 220020506G7421URHB32E SPARK PLUG CONT IO520F CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL CYLINDER BROKEN W K NONE E VIBRATION/BUFFET CRCRUISE 1 CA 570567 (CAN) ENGINE DEVELOPED A KNOCK ON RETURN FLIGHT IN CRUISE. REELED LOWER SPARK PLUG ON NR 6 CYLINDER BROKEN FLUSH WITH THE OUTSIDE OF THE CYLINDER. REMAINDER OF SPARK PLUG WAS FOUND HANGING ON THE LEAD. SPARK PLUG WAS REPLACED. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020617000612002061700061CE 2002 6 17 CA020516011 120020516G5311 FRAME BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11484 (CAN) FUSELAGE RIGHT HAND FRAME AT STA 177.50, STRINGER 8 CRACKED. SHEET METAL REPAIR TO BE DONE PRIOR TO FURTHER FLIGHT. 1L72 4T4 T A24CE E4EA 20020617000862002061700086CE 2002 6 17 CA020517006 120020515G32604532303016001 CLEVIS LEAR 66323030043 LEAR 45 45LEAR 5170805CE MLG UPLOCK FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 0108 (CAN) AIRCRAFT ROLL ON TAKE-OFF. DURING CLIMB FLIGHT CREW SELECTED GEAR UP. MAIN LANDING DOOR CYCLES UP AND DOWN, UNTIL THE PILOT RE-SELECTED GEAR IN DOWN POSITION. AIRCRAFT CAME BACK LANDING AT IT'S MAINTENANCE BASE. MAINTENANCE PERSONNEL FOUND THAT THE LT FREE FALL CLEVIS CABLE ON THE UPLOCK ASSY HAD'NT RESET TO IT'S PROPER POSITION. CABLE WAS RESET AND FUNCTION CHECK SERVICEABLE ON GROUND. 2L72 4F RTT00008WI 20020617000922002061700092SO 2002 6 17 CA020521005 220020513G8530CL66P15 CYLINDER PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO ENGINE CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) STEEL BARREL CRACKED AROUND CIRCUMFERENCE JUST BELOW HEAD ATTACH AREA. 90 PERCENT. 1L72 3O3 O A7SO E9CE 20020617001092002061700109SO 2002 6 17 CA020522000 120020517G5312764028 PLATE PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA BULKHEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE BULKHEAD REINFORCEMENT PLATE (KIT P/N 764 028)WAS FOUND CRACKED AT AFT FUSELAGE STA 317.75 WITHIN THE SAME INSPECTION AREA OUTLINED ON PIPER SB 636A. THE REINFORCEMENT PLATE IS A PART OF PIPER KIT 764 028 INSTALLED UNDER AD96-12-12 WITH ABOUT 2000 HOURS SINCE INSTALLATION. 1L72 3O3 O A20SO E14EA 20020617001222002061700122CE 2002 6 17 CA020522006 120020521G32450923150 TUBE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA TIRE DEFECTIVE W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) FAILURE OF CENTER SEAM OF 600 X 6 - 6 PLY TIRE TUBE. THIS HAS OCCURED ON 2 OTHER SEPERATE OCCASIONS. SUPPLIER HAS BEEN NOTIFIED AND HAS INDICATED THAT HE WAS GOING TO CONTACT MICHELIN AND INQUIRE ABOUT THE PROBLEM. PICTURES OF DEFECT ARE ON FILE AND MAY BE E-MAILED IF REQUESTED. SUPPLIER HAS BEEN ASKED FOR CREDIT FOR THESE TIRE TUBES. 1H71 3O3 ONT3A12 E274 20020618000142002061800014CE 2002 6 18 CA020523017 120020516G32136960298 FORK CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BOTH BOW WHEEL FORKS HAVE TWO CRACKS EACH UP TO 1.5 INCHES LONG LOCATED ON THE AFT UPPER EDGE OF FORK. THE CRACKS ARE RUNNING FROM EDGE OF THE FORK FORWARD THE TWO 5/16 INCH REAR MOUNTING BOLT HOLES. ONE OF THE CRACK HAD GONE BEYOND THE HOLE. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20020618000192002061800019SW 2002 6 18 CA020524006 120020524G275019023 CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA RT & LT TE FLAPSFRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT AND RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS WITH 2ND NOTCH OF FLAP SELECTED. 1H71 3O3 O A21CE E286 20020618000262002061800026SO 2002 6 18 CA020527009 120020514G5330 SKIN PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1048010480 (CAN) PIPER SB 1045 ISSUED TO INSPECT FORWARD WING SPAR ATTACH BRACKETS. INSPECTION REVEALED CRACKING IN FUSELAGE STRUCTURE AND SKIN. REPAIRS CARRIED OUT AS PER SB AND PIPER SERVICE MANUAL AND AC 43-13-1B/2A FIG 4-16. ALL PARTS REQUIRED AS PER SB 1045 WERE AVAILABLE AT PIPER. 1L72 3O3 O A20SO E14EA 20020613000942002061300094CE 2002 6 13 CA020528003 120020211G243523078019 STARTER GEN BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE LT ENGINE CRACKED W O OTHER HJ ELECT. POWER LOSS-50 PC WARNING INDICATION APAPPROACH 1 CA (CAN) NR 1 GENERATOR SHUT DOWN IN FLIGHT. AFTER LANDING THE ENGINE WAS SHUTDOWN AND TRIED TO RE-START. STARTER WOULD NOT ENGAGE.INSPECTED LT STARTER GENERATOR, FOUND THAT THE COOLING FAN WHICH IS PART OF UNIT HAD ITS BLADES ALL CRACKED UP. SUSPECTED BEARING FAILURE. REPLACED STARTER GENERATOR, ENGINE RUNS CARRIED OUT AND CHECKED SERVICEABLE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020618001122002061800112CE 2002 6 18 CA020529003 120020514G5744122005311 HINGE CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO CONTROL SURFACE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND IN LOWER ATTACH FLANGE DURING SPECIAL INSPECTION PER CESSNA CONTINUED AIRWORTHINESS PROGRAM.THIS WAS LEFT HAND INBOARD HINGE. ALSO FOUND RIGHT HAND INBOARD HINGE CRACKED. OUTBOARD LEFT HAND HINGE HAD BEEN RECENTLY REPLACED. 1H71 3O3 O A4CE E5CE 20020806000712002080600071CE 2002 8 6 CA020529004 120020520G532050420014230 CHANNEL BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 20868 (CAN) FOUND CHANNEL CRACKED AT FORWARD O/B RADIUS AND AFT O/B RADIUS DURING SPECIAL CYCLE REPETETIVE INSPECTION. THE LEFT (OPPOSITE) CHANNEL WAS ALSO FOUND CRACKED IN THE AFT AREA. BEECH CONTACTED. PARTS BEING REPLACED. 1L72 3T4 T A14CE E4EA 20020730001292002073000129CE 2002 7 30 CA020529005 120020529G5230260120413 LATCH CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL CARGO POD DOOR LOOSE W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) WHILE ON A BIRD DOGGING MISSION OVER A FIRE. THE AIRCRAFT WAS IN A TURN OVER THE TARGET, A THUMP WAS HEARD, AN INITIAL SEVERE VIBRATION WAS FELT, ON CLIMBING TO ALTITUDE THE VIBRATION BECAME INTERMITTENT. THE AIRCRAFT RETURNED TO BASE, UPON ARRIVAL AT THE TANKER BASE IT WAS DISCOVERED THAT THE FORWARD CARGO POD DOOR HAD OPENED IN FLIGHT. THE AIRCRAFT WAS INSPECTED FOR DAMAGE, AND THE DOOR LATCHES WERE ADJUSTED TO ENSURE A POSITIVE LOCK. THE AIRCRAFT WAS RETURNED TO SERVICE. THE OTHER C208B AIRCRAFT WERE INSPECTED AND FOUND TO BE SERVICEABLE. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020618001212002061800121CE 2002 6 18 CA020530006 120020516G532005130633 BRACKET CESSNA172 172F 2072414CE CONT O300 O300C 17022SO PAX DOOR FRAME CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE BELLCRANK BRACKET P/N 0513063-3 IN THE BULKHEAD ASSEMBLY, FRONT DOOR POST WAS CRACKED. THE FORWARD FLANGE OF THE BRACKET WAS CRACKED. A NEW PART WAS INSTALLED USING THE EXISTING RIVET SIZE AND PATTERN. 1H71 3O3 ONT3A12 E253 20020531001262002053100126EU 2002 5 31 CA020530007 120020527G2910NAS161212 SEAL 114080003 AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG DOOR MANIF FAILED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) GREEN HYDRAULIC FLUID LEVEL FELL IN YELLOW RANGE. AIRCRAFT DIVERTED TO YYZ RESULTING IN AN OVERWEIGHT LANDING. SEAL FOUND LEAKING ON LANDING GEAR DOOR MANIFOLD ASSY. SEAL REPLACED AND SYSTEM LEAK CHECKED SERVICEABLE. OVERWEIGHT LANDING CHECK COMPLETED, NO FAULTS FOUND. 2L72 4F4 FRTA28NM E29NE 20020618001232002061800123CE 2002 6 18 CA020530008 120020522G27500512128 PULLEY BRACKET CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED LDLANDING 1 CA (CAN) WHEN SELECTING FLAPS FOR LANDING, LEFT FLAP WOULD NOT COME DOWN. AIR PRESSURE KEPT IT UP. PILOT SELECTED FLAPS UP, AND LANDED. 1H71 3O3 O 3A24 E5CE 20020618001242002061800124SO 2002 6 18 CA020530009 220020509G8520646255 PISTON CESSNA172 172B 2072406CE CONT O300 O300C 17022SO ENGINE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE RAN WELL NO VISIBLE PROBLEM. PIECE OF PISTON SKIRT BROKEN LOOSE HELD IN BY OIL RING AND CYLINDER CURVE ONLY. 1H71 3O3 ONT3A12 E253 20020618001262002061800126CE 2002 6 18 CA020530010 120020517G5751122005311 HINGE BRACKET CESSNA206 U206B 2073322CE CONT O520 IO520F 17032SO MCAULY2A34C D2A34C58 GL LT & RT AILERONSCRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AILERON BRACKETS WERE LOOSE ON SPAR AND IN SKIN ATTACH. UPON EXAMINATION FOUND BOTH BRACKETS CRACKED AT REAR AND BOTTOM FLANGES. IT APPEARS THAT THE BRACKETS HAD BEEN LOOSE PREVIOUSLY AND REPAIRED BY SUBSTITUING CHERRY MAX THROUGH BOTTOM SKIN WHICH DID NOT SOLVE PROBLEM. RT & LT AILERON HINGE BRACKETS P/N 1220053-11 & 1220053-18. 1H71 3O3 O A4CE E5CE 5 CP3EA 20020618001322002061800132SW 2002 6 18 CA020530014 120020516G2432206075295053 WIRE BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL BATTERY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OF BATTERY COMPARTMENT, THE POSITIVE BATTERY WIRE AT THE SOLONOID WAS FOUND BROKEN. 1G71 3U3 U H2SW E1GL 20020618001342002061800134EA 2002 6 18 CA020530016 220020525G7414 MAGNETO CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE CONTAMINATED W D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT RAN ROUGH WHEN RT MAG SELECTED. OIL CONTAMINATION WAS FOUND IN BREAKER COMPARTMENT. MAGNETO WAS REPLACED AND A/C GROUND RUNS COMPLETED. 1H71 3O3 ONT3A19 E223 20020613000952002061300095NE 2002 6 13 CA020531005 220020531G725071500171 ENGINE 71500171 BOEING737 737275 1384485NM PWA JT8 JT8D9A 52048NE NR 1 FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA P674234B (CAN) PRELIMINARY REPORT, NR 1 ENGINE SHUT DOWN , ENGINE STARTED ROUGH WITH VIBRATION , ANTI-SELECTED OFF WITH NO CHANGE,AIRCRAFT LANDED WITHOUT ANY INCIDENT. FOUND ENGINE TURBINE DAMAGED 2L72 4F4 F A16WE E2EA 20020613000962002061300096EU 2002 6 13 CA020604009 120020602G5220 DOOR FOKKER A20401411 FOKKERF28 F28MK1000 4990808EU RROYCESPEY SPEY55515 54521EU EMERGENCY EXIT SEPARATED W O OTHER D INFLIGHT SEPARATION LDLANDING 1 CA TARLH (CAN) LT EMERGENCY EXIT OPENED UPON LANDING INTO YYC. AIRCRAFT SWAPPED. RECTIFICATION THE OVER WING EXIT WAS INSPECTED WITH NO FAULTS FOUND. OVER CENTER SPRINGS WERE REPLACED AND DOOR WAS RIGGED AS PER THE MAINTENANCE MANUAL. THE FORCE REQUIRED TO OPEN THE DOOR WAS MEASURED TO ESTABLISH A GUIDELINE AS THE AIRCRAFT WILL BE INSPECTED EVERY MAINTENANCE OVER NIGHT UNTIL AN SIO IS ISSUED. 2L72 4F4 FRTA20EU E2EU 20020619001472002061900147SW 2002 6 19 CA020604010 120020530G750088027687 LINE GULSTM690TP 690A 0141722SW GARRTTTPE331TPE3315251K NM BLEED AIR BROKEN W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB THE AIRCRAFT WOULD NOT PRESSURIZE. THERE WAS A LOUD WHISTLING SOUND COMING FROM THE ENTRANCE DOOR AREA, INDICATING NO PRESSURIZATION. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION IT WAS NOTED THAT THE FLARE END OF ONE CONNECTION HAD PULLED THROUGH THE B-NUT. THE BLEED AIR LINE WAS REPLACED WITH A SERVICEABLE UNIT. AIRCRAFT WAS GROUND RUN BLEED AIR SYSTEM WAS LEAK CHECKED SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE. 1H72 3T4 T 2A4 E2WE 20020806000732002080600073CE 2002 8 6 CA020606003 120020416G7100 GEAR CESSNA180 180J 2072622CE CONT O470 O470S 17026SO MCAULY2A34C 2A34C203 GL CAMSHAFT WRONG PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) ENGINE WAS PUT TOGETHER WITH THE WRONG CAMSHAFT GEAR. THE ENGINE WOULD RUN BUT THE MAGNETO DROP WAS HIGH. ALSO IF YOU EXERCISED THE PROP AT ABOUT 1700 RPM THE ENGINE WOULD STALL OUT. THROTTLE RESPONSE AT LOWER RPMS WAS SLUGGISH AND WOULD MAKE THE ENGINE SPIT AND SPUTTER. HIGHER RPMS SEEMED NO PROBLEM. 1H71 3O3 O 5A6 E273 5 CP3EA 20020613000972002061300097NM 2002 6 13 CA020606006 120020527G2760ZRV873 RESTRICTOR VALVE DORNERDO32 DO328100 2996000NM PWA 119 PW119C NE HARTZLHDE6C HDE6C3B NE SPOILERS FAILED W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED LDLANDING 1 CA 90213160 (CAN) LEFT OUTBOARD GROUND SPOILER FAILED TO DEPLOY ON LANDING. REPACED R/H RESTRICTOR VALVE P/N ZRV 87-3, S/N 90213160 AND CHECK VALVE P/N ZCV 157-1, S/N 80356276. AIRCRAFT RETURNED TO SERVICE AND GROUND SPOILER SYSTEM CHECKED SERVICEABLE. ALL PARTS SENT TO VENDOR FOR TEAR DOWN REPORT AND EVALUATION. 2H72 4T4 TRTA45NM E20NE 6 CP34NE 20020619001702002061900170CE 2002 6 19 CA020606008 120020523G550007120487 ANGLE CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO TAILCONE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE ANGLE - TAILCONE REINFORCEMENT RT IN THE TAILCONE BULKHEAD ASSEMBLY WERE CRACKED. NEW PARTS 0712048-7 (LT) AND 0712048-6 (RT) WERE INSTALLED USING THE EXISTING RIVET SIZE AND PATTERN. 1H71 3O3 O 3A24 E5CE 20020619001712002061900171SO 2002 6 19 CA020606009 220020419G8520639195 COUNTERWEIGHT CONT 639134 CONT O520 IO520D 17032SO CRANKSHAFT SEPARATED W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA D995 (CAN) ROLLER RETAINING PLATE VIBRATED THROUGH SIDE OF COUNTERWEIGHT ALLOWING ROLLER TO FALL OUT. COUNTERWEIGHT THEN STRUCK CRANKCASE CAUSING NOISE. CRANKSHAFT CRACKED AT OPPOSITE BUSHING FROM OVERLOAD. CRANKCASE AND TWO PISTONS DESTROYED. 3 O E5CE 20020619001822002061900182 2002 6 19 CA020606017 420020603G6113055032111 BULKHEAD CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFT SPINNER BULKHEAD FAILED AT RADIUS OF FLANGE AT CUTOUT FOR PROPELLER. SPINNER DISTORTED AS RESULT OF THE BULKHEAD FAILURE. 1H71 3O3 ONT3A12 1E10 20020807000022002080700002CE 2002 8 7 CA020607002 120020526G3210804184200651 GUSSET BEECH 18 D18S 1151004CE PWA R985 R985AN14B 52008NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13460 (CAN) DURING INITIAL INSPECTION OF AIRCRAFT AD CF-63-08 INSPECTED AND LT INBOARD AND RT INBOARD LANDING GEAR CLUSTER VISUALLY CRACKED.BOTH CLUSTERS HAD BEEN CRACKED AND WERE WELDED SHUT. CRACKS WERE THRU WELD AND PROGRESSING ALONG GUSSETS AND THRU GUSSETS. 1L72 3R3 R A765 5E1 20020708000112002070800011SO 2002 7 8 CA020607006 120020530G5720 COVER PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE RT WING LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STAIN LEAKS WERE FOUND AT THE INBOARD MOST PANEL OF THE RIGHT WING HEADER TANK. THE PANEL IS UNDERNEATH THE WHEEL FAIRING DEFLECTOR. PANEL WAS REMOVED AND RESEALED. SEALER MIGHT HAVE BEEN SLIGHTLY DRY. 1L71 3O4 TRTA25SO E4EA 20020807000032002080700003CE 2002 8 7 CA020607008 120020516G2497 CONNECTOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL PROP DEICE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA 2360023600 (CAN) CESSNA SERVICE BULLETIN CAB00-11. THIS SERVICE BULLETIN, WHICH IS OPTIONAL, WAS OUT ON OUR AIRCRAFT AND A SEVERELY BURNT CONNECTOR WAS FOUND. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020918000082002091800008EA 2002 9 18 CA020607018 220020606G8500 ENGINE PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA RIGHT FLUCTUATES W EA ENGINE SHUTDOWN UNSCHED LANDING EYJVIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA (CAN) JUNE 6, 2002. DURING CRUISE FLIGHT BETWEEN YVR & YYJ, THE RT ENGINE FLUCTUATED SLIGHTLY AND LOST POWER, HOWEVER, THE R/H TACH SHOWED OVERSPEED AS THE CREW SHUT THE ENGINE DOWN. THE CREW CONTINUED TO VICTORIA AND LANDED. INVESTIGATION REVEALED THE ENGINE TO BE INTACT WITH NO O UTWARD SIGNS OF FAILURE, HOWEVER, DRIVE BETWEEN THE PROPELLER AND REAR CASE HAS BEEN AFFECTED. THE ENGINE WAS REPLACED WITH A SERVICEABLE ENGINE. THE ENGINE IS IN OUR SHOP AND SHOULD BE OPENED NEXT WEEK TO DETERMINE THE CAUSE OF THE POWER LOSS.ONCE DETERMINED, SUPPLEMENTAL DATA WILL BE SUPPLIED. 1L72 3O3 O A20SO E14EA 20020619002182002061900218EA 2002 6 19 CA020610004 220020521G7314LW15473 PUMP CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FUEL SYSTEM FAILED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) FOLLOWING THE SB OF THE CESSNA 01-73-01A, A NEW MECHANICAL FUEL PUMP WAS INSTALLED. WE BELIEVE THE PUMP WAS DEFECTIVE, BECAUSE IT WAS NOT POSSIBLE FOR US TO HAVE RPM HIGHER THAN 1900. MOREOVER, AT 1900 RPM, A REDUCTION IN FUEL FLOW WAS NOTICED. FOR NOW, WE INSTALLED THE OLD PUMP UNTIL THE NEW PUMP ARRIVES. 1H71 3O3 ONT3A12 1E10 20020619002242002061900224EU 2002 6 19 CA020610007 120020608G5524NB310077 HINGE BNORM BN2 BN2B21 7080221EU LYC O540 IO540K1B5 41532EA ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING POST FLIGHT WALKAROUND A CRACK WAS NOTICED IN THE ELEVATOR OUTBOARD-HINGE, INBOARD-BRACKET. THIS BRACKET IS THE SUBJECT OF A 100 HOUR REPETITIVE INSPECTION UNDER BN2/SB.259. THE PREVIOUS INSPECTION 90 HOURS EARLIER SHOWED NO PROBLEMS. THE CRACK EXTENDED FROM THE LOWER FORWARD CORNER TO THE LOWEST FORWARD RIVET ON THE DISTANCE PIECE.AS WELL UPON REMOVAL OF THE ELEVATOR THE RIVETS HOLDING THE DISTANCE PIECE ON THE OUTBOARD SIDE OF THE HINGE WERE FOUND PULLED THROUGH THE RIB. 1H72 3O3 O A17EU 1E4 20020807000052002080700005 2002 8 7 CA020610009 420020524G3421 GYRO CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA COCKPIT UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER INSTALLATION OF A NEW OVERHAULED GYRO HORIZON, IT HAD BEEN FOUND UNSERVICABE. THAT GYRO HAD BEEN OVERHAULED BY AERONEUF INSTRUMENTS LTEE APPROVAL 27-91 ON RELEASE NOTE 28017 DATED FEB. 05, 2002 1H71 3O3 ONT3A12 E274 20020807000062002080700006 2002 8 7 CA020610010 420020531G3421 GYRO CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA COCKPIT UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER INSTALLATION OF A NEW OVERHAULED GYRO HORIZON, IT HAD BEEN FOUND UNSERVICABE. THAT GYRO HAD BEEN OVERHAULED BY AERONEUF INSTRUMENTS LTEE APPROVAL 27-91 ON RELEASE NOTE 28244 DATED MAY 27, 2002. IT IS THE SECOND SDR SUBMIT FOR THE SAME PROBLEM. ON RECEIP OF THESE INSTRUMENTS, THE SHIPPING BOX WAS FOUND IN AN PERFECT SHAPE 1H71 3O3 ONT3A12 E274 20020807000072002080700007CE 2002 8 7 CA020611002 120020516G5751 RIB HELIO H395 H395A 4300206CE LYC O435 GO435C2B2 41516EA AILERON CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RIB LACING THAT SECURES FABRIC ONTO AILERON RIBS FOUND TO BE SERIOUS CHAFED ALONG RIB EDGES WHICH COULD LEAD TO FAILURE OF FABRIC SECURITY ONTO RIBS AND POTENTIAL AILERON FLUTTER, ON BOTH RIGHT AND LEFT AILERON ASSEMBLIES. 1H71 3O3 O 1A8 E228 20020708000132002070800013CE 2002 7 8 CA020611004 120020526G2410 BEARING DOFF10300E CESSNA172 R172K 2072431CE CONT O360 IO360KB 17025SO MCAULY2A34C 2A34C203 GL ALTERNATOR SEIZED W K NONE O OTHER ININSP/MAINT 1 CA 630601533 (CAN) ALTERNATOR FAILURE. REAR ROLLER BEARING SEIZED SHAFT CAUSING SHAFT TO SHEAR IMMEDIATELY AFT OF THE DRIVE ASSEMBLY.NO EVIDENCE OF OR ADEQUATE LUBRICANT IN AFFECTED BEARING. OTHER PARTS OF THE ALTERNATOR APPEARED IN GOOD CONDITION EXCEPT FOR THE BRUSHES WHICH WERE DAMAGED BY LOOSE ROLLERS AND DEBRIS FROM BEARING. 1H71 3O3 O 3A17 E1CE 5 CP3EA 20020807000082002080700008EA 2002 8 7 CA020611005 220020425G8500 CASE PIPER PA31 PA31325 7103105SO LYC O540 TIO540F2BD 41532EA ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON ENGINE BUILD-UP TO INSTALL THE PROP DEICE BRUSH BLOCK BRACKET ASSEMBLY. ONE OF THE BOLTS THAT GO THROUGH THE CASE HAD TO BE REMOVED. THE THREADS OF THE BOLT WERE MARKED UP. ON FURTHER INVESTIGATION IT WAS FOUND THAT THE BOLT HAD BOTTOMED OUT IN THE HELICOIL INSERT. TOO LONG OF A BOLT WAS USED. NEW HELICOIL WAS INSTALLED AND PROPER BOLT LENGTH WAS USED. 1L72 3O3 O A20SO E14EA 20020717001852002071700185SO 2002 7 17 CA020611006 220020603G8540632617 BEVEL GEAR CONT 646220A38 CESSNA337 337G 2075730CE CONT O360 IO360G 17025SO MCAULY2AF34CD2AF34C306 GL STARTER ADAPTER FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) - VACUUM PUMP DRIVE NOT TURNING.- INSPECTION REVEALS NO TEETH ON DRIVE BEVEL GEAR.- METAL CONTAMINANTS CONTAINED INSIDE STARTER ADAPTER.- TCM SB 01-5 ADDRESSES PROBLEM.- TCM WARRANTS FULL REPLACEMENT. 1H72 3O3 O A6CE E1CE 5 CP5EA 20020717002072002071700207EA 2002 7 17 CA020611007 220020514G74141052947 MAGNETO ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA RIGHT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE 500 HOUR INSPECTION OF THE MAGNETO, SMALL CRACKS (1/4 INCH OR SHORTER) WERE FOUND IN THE ROTOR HOUSING WHERE THE MAGNET PROTRUDES THRU AT THE CORNERS (8 LOCATIONS). WERE ADVISED THIS WAS NOT RARE AND IS COMMON TO THE O-540 ENGINE SERIES AND PREDOMINENTLY TO THE O-540 INSTALLED IN R44 AIRCRAFT. 1G71 3O3 O H11NM E295 20020807000092002080700009EA 2002 8 7 CA020611008 220020514G74141052947 ROTATING MAGNET BENDIX 106006163 ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA LT MAGNETO CRACKED W K NONE O OTHER ININSP/MAINT 1 CA C159918E (CAN) DURING A ROUTINE 500 HOUR INSPECTION OF THE MAGNETO, SMALL CRACKS (1/4 INCH OR SHORTER) WERE FOUND IN THE ROTOR HOUSING WHERE THE MAGNET PROTRUDES THROUGH. TECH REP WAS CONTACTED AND WE WERE ADVISED THAT ALTHOUGH NOT COMMON, THIS WAS NOT RARE AND IS COMMON TO THE O-540 ENGINE SERIES AND PREDOMINENTLY TO THE O-540 INSTALLED IN R44 AIRCRAFT. 1G71 3O3 O H11NM E295 20020708000142002070800014CE 2002 7 8 CA020612002 120020603G2910CM3690A60XXX HOSE CESSNA441 441 2076020CE HYD SYSTEM CHAFED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYDRAULIC FLUID LEAK, FROM BELLY THE MAIN LANDING GEAR RETRACTION LINE WAS RUBBING AGAINST A SCREW, THAT WAS HOLDING TWO CLAMPS AROUND TWO OTHER HYDRAULIC LINES UNDER THE RELAY BOX IN THE BELLY. 1L72 3T RTA28CE 20020708000152002070800015CE 2002 7 8 CA020612005 120020610G32128AO2195006 FITTING 8000 CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE MCAULY3AF34C3GFR34C703 GL LEFT STRUT ELONGATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING REINSTALLATION OF FLOATS, BOTH LT FORWARD STRUT ATTACH FITTINGS WERE NOTED TO HAVE ELONGATED BOLT HOLES. AT CLOSER EXAMINATION YOU COULD SEE THAT THE HOLES WERE NOT WORN ELONGATED BUT THE POUNDING FORCE OF LANDING HAD ACTUALLY DISTORTED THE METAL AND PUSHED IT AWAY. RIGHT SIDE FITTINGS INSPECTED FOR SIMILAR DAMAGE (NO FAULTS FOUND) AND FLOATS INSPECTED FOR OTHER SIGNS OF STRESS. PARTS REPLACED WITH NEW AND AIRCRAFT RETURNED TO SERVICE. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20020807000122002080700012GL 2002 8 7 CA020612008 120020611G7603 LEVER NAMER T6 HARVARDMK4 1922828GL PWA R1340 S3H1 52016NE TROTTLE BROKEN W O OTHER E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) PILOT RETURNED AIRCRAFT TO AIRPORT UNEVENTFULLY AFTER THROTTLE CONTROL GRIP BROKE OFF THROTTLE LEVER. PILOT WAS ABLE TO RETAIN CONTROL USING THE STUB OF LEVER REMAINING, HOWEVER SITUATION COULD HAVE BEEN VERY SERIOUS HAD THE LEVER BROKEN IN A DIFFERENT LOCATION.LEVER BROKE OFF DUE TO A WEAKNESS IN A DESIGN OF THE PART (NARROWED DOWN AREA), PROBABLY VIBRATION FATIGUE. 1L71 3R3 R EXPA1L71E143 20020708000162002070800016EA 2002 7 8 CA020613001 120020613G2750C3WF24 FITTING DHAV DHC3 DHC3 2800202EA PWA PT6 PT6A34 52043EA CENTER FOREFLAP WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PUSH PULL ROD ATTACH POINT ON THE FOREFLAP HAD PLAY. UPON INSPECTION WE FOUND THAT THE RIBS HOLDING THE BRACKET FOR THE PUSH PULL ROD WAS CRACKED AND HAD LOOSE RIVETS. 1H71 3R4 T A815 E4EA 20020708000172002070800017NM 2002 7 8 CA020613002 120020528G3233 ACTUATOR DHAV DHC8 DHC8* NM PWA PW120 PW123 NE MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) WHEN LANDING GEAR RETRACTION SELECTED LT MLG DID NOT LOCK UP, DOORS DID NOT CLOSE. UNCONFIRMED THAT THE DOORS INDICATED CLOSED, ALSO UNCONFIRMED THAT THE NOSE GEAR DOOR DID NOT CLOSE. SUBSEQUENT TEST FLIGHTS INDICATED DIFFERENT SCENARIOS WITH NLG SOMETIMES UNLOCKED SOMETIMES ALL OKAY. MLG WAS CONSISTENT IN THAT IT NEVER SHOWED LOCKED. RT MLG BEHAVED NORMALLY. UNABLE TO REPRODUCE THE FAULT ON THE GROUND/ON JACKS. THE RETRACTION ACTUATOR BRACKET WAS BROKEN CREATING THE PROBLEM. BRACKET REPLACED. AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 20020730001302002073000130 2002 7 30 CA020613004 420020612G2562 G SWITCH POINTER ELT FAILED W K NONE L NO TEST ININSP/MAINT 1 CA 408833 (CAN) WHILE IN THE SHOP FOR ANNUAL RECERTIFICATION IT WAS FOUND THAT THE ELT WOULD ACTIVATE WITH ANY SLIGHT BUMPING. UNIT WAS RETURNED TO THE MANUFACTURER FOR REPAIR. 20020708000202002070800020EU 2002 7 8 CA020614002 120020612G77005D3 DETECTOR BRAERO748 HS7482A 4231001EU RROYCEDART DART5342 EU ROTOL R4304 R2124304 EU NR 1 ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) AFTER DEPARTING FROM FORT SEVERN, THE NR 1 ENGINE OVERHEAT LIGHT CAME ON. THE PILOT SHUT DOWN AND FEATHERED THE ENGINE, CONTINUING TO MAIN BASE. MAINTENANCE CHECKED THE OVERHEAT DETECTOR AND FOUND TO BE GOING OFF EARLY. THE DETECTOR WAS REPLACED AND THE AIRCRAFT GROUND RUN AT MAX POWER FOR 4 MINUTES WITH NO FURTHER INDICATION.AIRCRAFT RETURNED TO SERVICE. 2L72 3T4 T A24EU A196 6 CP899 20020708000222002070800022CE 2002 7 8 CA020617002 120020613G5511 SPAR CESSNA172 172G 2072420CE LYC O320 O320E2D 41508EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A RECENT PAINT SHOP VISIT IT WAS DISCOVERED THAT A SIGNIFICANT NUMBER OF SERIOUS STRUCTURALLY DAMAGED AREAS WERE AHMMERED OUT WITH A DOLLY, NOT REINFORCED, AND EITHER FILLED IN WITH BODY PUTTY OR COERED OER WITH A PATCH. THE LEFT WING MAIN SPAR APPEARS TO HAVE BEEN STRAIGHTENED AND NOT REINFORCED. BLIND FASTENERS WERE USED TO ATTACH A PORTION OF THE LEADING EDGE CONTRARY TO THE MAINTENANCE MANUAL. THE HORIZONTAL STABILIZER SPAR WAS FOUND TO BE CRACKED AND BUNCKLED, ETC. ETC..... THE 'REPAIRS' APPEAR TO HAE BEEN DONE SOME 20 YEARS AGO. THE AIRCRAFT HAS BEEN REMOVED FROM THIS LOCATION AND WILL BE REPAIRED AT SOME UNKNOWN FACILITY. 1H71 3O3 ONT3A12 E274 20020708001372002070800137EA 2002 7 8 CA020617003 220020514G8520LW13865 CONNECTING ROD CESSNA182 182S 2072701CE LYC O540 IO540AB1A5 EA MCAULY3D36C B3D36C431 GL ENGINE BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) CONNECTING ROD APPEARS TO HAVE BROKEN 1 INCH OUT FROM CRANKSHAFT JOURNAL. THIS WRAPPED ITSELF AROUND UNTIL THE CONNECTING ROD CAP DEPARTED AND THE PIECES BROKE THE CASE 60 PERCENT OF THE WAY AROUND THE ENTIRE CASE AND DESTROYED THE CAMSHAFT AND JAMMED UP THE ENTIRE ENGINE. ENGINE WAS REMOVED AND SENT TO MANUFACTURER FOR ANALYSIS. 1H71 3O3 ONT3A13 1E4 5 C 20020708000252002070800025SO 2002 7 8 CA020617005 120020604G25107634700 BELLCRANK PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION, THE LOWER SEAT FORWARD RT BELLCRANK ASSEMBLY WAS FOUND DETACHED LEAVING THE SEAT BOTTOM ATTACHED IN ONLY 3 CORNERS. THE BELLCRANK WAS FOUND DETACHED IN 3 WELDS. THE WELDS WERE ONLY "TACK" WELDS. THE 3 OTHER BELLCRANKS HAVE WELDS NEARLY THE ENTIRE WAY AROUND THE TUBE. THIS APPEARS TO HAVE BEEN DONE ON MANUFACTURE. AS WELL, THERE SHOULD BE A SMALL GUSSET TO STRENGTHEN THE BELLCRANK THAT WAS ALSO MISSING. 1L71 3O3 O 2A13 E286 20020807000132002080700013SO 2002 8 7 CA020618002 120020606G78109907704 EXHAUST PIPE PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA ENGINE FAILED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) PIPE FAILED IN FLIGHT, UNIT REPAIRED AND RESTALLED TIME SHOWN ON PART IS T.T ON AIRCRAFT TIME ON PART IS UNKOWN. 1L71 3O3 O 2A13 E274 20020807000142002080700014CE 2002 8 7 CA020618005 120020613G2133 SOLENOID VALVE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA CABIN PRESSURE FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) A/C FAILED TO PRESSURIZE AFTER TAKEOFF. UPON RETURN TO BASE THE A/C STILL WOULD NOT PRESSURIZE ON "TEST" POSITION. MAINTENANCE DETERMINED THAT THE CABIN PRESSURE SAFTEY VALVE SOLENOID (DESIGNATOR E 105) WAS FAILED OPEN, NOT ALLOWING THE SAFTEY VALVE TO CLOSE AFTER TAKEOFF. THE SOLENOID VALVE WAS REPLACED AND THE A/C WAS TEST FLOWN WITH PRESURRIZATION SERVICEABLE. 1L72 3T4 TRT3A20 E4EA 20020708000412002070800041CE 2002 7 8 CA020619002 120020618G325205421011 SHAFT CESSNA 04425121 CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MLG DAMPENER SHEARED W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION LDLANDING 1 CA (CAN) INVESTIGATION OF A SEVERE NOSEWHEEL SHIMMY REPORT REVEALED THAT THE SHIMMY DAMPENER SHAFT HAD SHEARED. BOTH HALVES OF THE ASSEMBLY REMAINED ATTACHED BUT THE UNIT COULD NO LONGER FUNCTION AS DESIGNED. THE FAULTY UNIT WAS REMOVED FROM SERVICE AND REPLACED WITH A SERVICEABLE UNIT. CAUSE OF DEFECT IS UNKNOWN AT THIS TIME. 1H71 3O3 ONT3A12 1E10 20020708000422002070800042CE 2002 7 8 CA020619003 120020508G325205421011 SHAFT CESSNA 04425121 CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA SHIMMY DAMPENER SHEARED W O OTHER EJ VIBRATION/BUFFET WARNING INDICATION LDLANDING 1 CA (CAN) SEVERE NOSEWHEEL SHIMMY REPORTED AFTER LANDING. INSPECTION OF THE DEFECT BY MAINTENANCE REVEALED THAT THE SHAFT WAS SHEARED. THE DAMPENER UNIT REMAINED ATTACHED BUT IN TWO SEPARATE PARTS PREVENTING IT FROM FUNCTIONING AS DESIGNED. NO FURTHER DAMAGE WAS FOUND AND THE UNIT WAS REMOVED FROM SERVICE. A REPLACEMENT UNIT WAS INSTALLED. 1H71 3O3 ONT3A12 E274 20020708000432002070800043CE 2002 7 8 CA020619004 120020619G322104425037 FORK CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MLG STRUT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION WE TOOK A CLOSE LOOK AT THE OLEO ASSEMBLY BASED ON PREVIOUS FINDINGS OF LIKE PARTS. THE PRIMARY REASON FOR THIS DETAILED INSPECTION IS BASED UPON THE KNOWN HIGH TIME AND OPERATING ENVIRONMENT OF THESE UNITS. WE DETECTED A CRACK ON THE OUTER TOP SURFACE WHERE THE FORK CURVES. THE PART WAS REMOVED FROM SERVICE AND REPLACED WITH A SERVICEABLE UNIT. 1H71 3O3 ONT3A19 E223 20020708000442002070800044CE 2002 7 8 CA020619005 120020605G324095440265 STRUCTURE LEAR 24 24D 5170311CE GARRTTTFE731TFE73122B 01518WP BRAKE ASSY BROKEN W O OTHER O OTHER LDLANDING 1 CA (CAN) ON LANDING, A "TANG" ON THE WHEEL THAT ENGAGES WITH THE ROTATING BRAKE DISCS BROKE OFF. TIRE DID NOT DEFLATE. WHILE TAXIING, A RHYTHMIC SOUND COULD BE HEARD IN THE COCKPIT. 2L72 4J4 F A10CE E6WE 20020708000452002070800045CE 2002 7 8 CA020619006 120020610G533005135212 SKIN CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA 12312 (CAN) DURING A T.C. AUDIT INSPECTION INTERGRANULAR CORROSION WAS OBSERVED. THE AREA IS THE TOP SKIN FORWARD OF WINDSCREEN ON THE LEFT SIDE. THERE IS A HOLE APPROXIMATELY 1/2 INCH IN DIAMETER. AT THIS POINT, THERE IS ALSO "BUBBLING" OF THE PAINT ON THE RIGHT SIDE. THE PATTERN FOLLOWS THE TOP OF THE STEEL FIREWALL.AT THIS TIME THE TOTAL EXTENT OF THE DAMAGE OR IT'S CAUSE IS NOT KNOWN. 1H71 3O3 ONT3A12 E274 20020807000152002080700015SO 2002 8 7 CA020619012 220020611G8520653631 GEAR CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL CRANKSHAFT BROKEN W E ENGINE SHUTDOWN O OTHER TXTAXI/GRND HDL 1 CA (CAN) AT THE MOMENT OF ACCIDENT, THE MOTOR DID A "KICK BACK". TWO TEETH OF THE CRANKSHAFT GEAR THAT WERE IN CONTACT WITH THE STARTER CLUTCH SHAFT GEAR BECAME BROKEN AND FELL INTO THE OIL PAN. THIS MODEL OF THE STARTER CLUTCH CAN STICK IF IT IS TURNED COUNTER-CLOCKWISE OF THE HELIX THAT PUTS HEAVY PRESSURE ON THE TEETH OF THE CRANKSHAFT GEAR. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20020718000182002071800018EA 2002 7 18 CA020621004 220020612G8530 VALVE SEAT LYC O320 O320* 41508EA CYLINDER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INTAKE VALVE LEAKING 20/80 COMPRESSION. PROBLEM FOUND ON THE BENCH. THE CYLINDER HAD TO BE REMOVED, THE VALVE RE-SEATED AND THE CYLINDER RE-INSTALLED ON THE ENGINE. 3 O E274 20020708000482002070800048CE 2002 7 8 CA020621007 120020605G3232MS166251068 RETAINER CESSNA337 337G 2075730CE CONT O360 IO360D 17025SO MCAULY2AF34CD2AF34C310 GL MLG DOOR FAILED W B EMER. DESCENT J WARNING INDICATION DEDESCENT 1 CA (CAN) PILOT INBOUND FOR LANDING & SELECTED GEAR DOWN. REPORTED THAT GEAR DID NOT EXTEND & GEAR MOTOR CONTINUED RUNNING. BEGAN EMERGENCY EXTENSION OF GEAR WITH HAND PUMP BUT NO PRESSURE BUILDING ON HAND PUMP. SEVERAL PROCEEDURES WERE CARRIED OUT BY PILOT & GROUND CREW, WITH NO SUCCESS. ON FLY BY IT WAS NOTED NOSE GEAR EXTENDED & SEEMED LOCKED, BUT MAIN GEAR HALFWAY EXTENDED. PILOT FINALLY EXECUTED GEAR UP LDG. ON INSPECTION OF MLG, IT WAS FOUND THAT REAR LT MLG DOOR ACTUATOR CYLINDER SEPARATED FROM PISTON ROD. PILOT REPORTED THAT HYDRAULIC FLUID AT NORMAL LEVEL. 1H72 3O3 O A6CE E1CE 5 CP5EA 20020718000342002071800034CE 2002 7 18 CA020624003 120020617G532150440012655 FLOORBOARD BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA CABIN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 15696 (CAN) THE ENTRANCE FLOOR PANEL WAS FOUND CRACKED AT STATION 278.5. PANEL REPLACED AND NO FURTHER DAMAGE REPORTED 1L72 3T4 T A14CE E4EA 20020918000092002091800009NE 2002 9 18 CA020624005 220020508G7200 BLADE BEECH MU300 400BEECH CE PWA JT15 JT15D5 52112NE LT & RT ENGINES BIRD STRIKE W C ABORTED TAKEOFF CTYF.O.D. ENGINE CASE PENETRATION ENGINE STOPPAGE TOTAKEOFF 1 CA 400GJ RJ23 (CAN) THE FLIGHT WAS CLEARED FOR DEPARTURE BY AIR TRAFFIC CONTROL. THE FLIGHT CREW DID NOT OBSERVE ANY BIRDS ON OR AROUND THE RUNWAY, AND POWER WAS APPLIED FOR TAKEOFF. AS THE AIRSPEED INCREASED, THE CO-PILOT CALLED 'V1,' AND IMMEDIATELY ALERTED THE PILOT TO THE PRESENCE OF BIRDS. THE BIRDS IMPACTED THE AIRPLANE AND THE PILOT ABORTED THE TAKEOFF. THE AIRPLANE CAME TO A STOP ABOUT 100 FEET PRIOR TO THE DEPARTURE END OF THE RUNWAY. EXAMINATION OF THE AIRPLANE BY A FAA INSPECTOR REVEALED SUBSTANTIAL DAMAGE TO BOTH THE LT AND RT ENGINES. FURTHER EXAMINATION OF THE RT ENGINE REVEALED THAT A FAN BLADE SEPARATED AND PENETRATED THE ENGINE COWLING. A 2-INCH GAP WAS ALSO OBSERVED BETWEEN THE ENGINE AND THE FUSELAGE. 2H72 4F4 FRTA16SW E25EA 20020718000612002071800061GL 2002 7 18 CA020626003 320020625G6110B4426 SNAP RING CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL PROPELLER MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER RECEIVED FROM CUSTOMER AFTER LOSS OF SNAP RING. PROPELLER WAS DISMANTLED, BLADES DRESSED, PAINTED AND ASSEMBLED. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20020718000632002071800063GL 2002 7 18 CA020626004 320020625G6114C93C4904 HUB MCAULY3AF32C3AF32C93 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE HUB WAS FOUND CRACKED ON NR 3 BLADE SOCKET. ONE BLADE NUT WAS FOUND CRACKED. 5 CP22EA 20020718000692002071800069EU 2002 7 18 CA020626006 120020619G2731Z14244130000 CONTROL CABLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA ELEVATOR TRIM FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AS A RESULT OF THE DISCOVERY OF AN ALMOST COMPLETELY FAILED ELEVATOR TRIM CONTROL CABLE ON ANOTHER AIRCRAFT AND BROKEN WIRES IN A SECOND AIRCRAFT'S CABLE, THIS AIRCRAFT'S ELEVATOR TRIM CONTROL SYSTEM WAS INSPECTED TO DETEMINE THE CONDITION OF THE CABLES. IT WAS FOUND THAT THE FORWARD ELEATOR TRIM CABLE ASSEMBLY HAD THE ENDS OF 3 BROKEN WIRES PROTRUDING FROM THE OUTER WIRE BUNDLE. THE FORWARD CABLE ASSEMBLY WAS REPLACED WITH NEW. 1L71 3O3 O0 A76EU 1E10 20020718000922002071800092EA 2002 7 18 CA020626007 220020618G7414 BOOSTER ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA LT MAGNETO FAILED W D RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING A PRE-FLIGHT RUN-UP THE AIRCRAFT ENGINE LT MAGNETO DROP WAS 600 RPM. TROUBLESHOOTING SHOWED THAT THE CAUSE WAS A FAULT WITH THE SLICK-START MAGNETO BOOSTER. THE BOOSTER WAS REPLACED AND THE ENGINE GROUND RUN. THE MAGNETO DROPS WERE WITHIN LIMITS. 1L71 3O3 O0 A76EU 1E10 20020807000172002080700017EA 2002 8 7 CA020626008 220020619G7414 BOOSTER ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MAGNETO FAILED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) DURING A PRE-FLIGHT RUN-UP THE AIRCRAFT ENGINE LT MAGNETO DROP WAS 600 RPM. TROUBLESHOOTING SHOWED THAT THE CAUSE WAS A FAULT WITH THE SLICK-START MEGNETO BOOSTER. THE BOOSTER WAS REPLACED AND THE ENGINE GROUND RUN. THE MAGENTO DROPS WERE WITHIN LIMITS. 1L71 3O3 O0 A76EU 1E10 20020718000952002071800095NM 2002 7 18 CA020626012 120020624G6123311195401 WIRE HARNESS DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE CORRODED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA 99999 (CAN) ON TAKE-OFF ROLL AUTO FEATHER FAILED TO ARM , TAKE-OFF REJECTED AND AIRCRAFT RETURNED TO RAMP. MAIN ENGINE ELECTRICAL HARNESS CONNECTER PINS FOUND CORRODED , WIRING HARNESS REPLACED , AIRCRAFT RETURNED TO SERVICE . 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020718001022002071800102EA 2002 7 18 CA020626017 220020614G853074541 EXHAUST VALVE PIPER PA44 PA44180 7104402SO LYC O360 O360F1A6 41514EA HARTZLHCC2Y HCC2YR2 GL VALE FACE BURNED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA (CAN) ENGINE POWER LOSER DURING TAKEOFF. RT ENGINE COMPRESSION TEST REVEALED CYLINDER NR 3 EXHAUST VALVE FACE BURNT CAUSING AIR LEAKAGE. 1L72 3O3 O A19S0 E286 5 CP920 20020708001432002070800143NM 2002 7 8 CA020627004 120020626G7921 OIL COOLER DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE NR 2 ENGINE LEAKING W O OTHER JK WARNING INDICATION FLUID LOSS DEDESCENT 1 CA 28311 (CAN) NR 2 ENGINE OIL PRESSURE FELL TO 45 PSI ON DESCENT. NR 2 OIL COOLER FOUND LEAKING AND REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807000212002080700021CE 2002 8 7 CA020628002 120020627G32334377113 CAP BEECH 993880001 BEECH 99 99 1154002CE PWA PT6 PT6A28 EA NLG ACTUATOR CRACKED W O OTHER BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION APAPPROACH 1 CA 102 (CAN) PILOT SELECTED GEAR DOWN. GEAR CAME DOWN AND 3 GREEN WERE INDICATED. MOTOR KEEP RUNNING UNTIL C/B POPPED. AIRCRAFT LANDED WITHOUT INCIDENT. NOSE GEAR ACTUATOR REPLACED, GEAR SWINGS CARRIED OUT AND AIRCRAFT RELEASED TO SERVICE. END CAP FRACTURED. 1L72 3T4 T A14CE E4EA 20020718001212002071800121SO 2002 7 18 CA020702002 220020620G8530SA648044 PISTON CESSNA207 T207A 2073614CE CONT O520 TSIO520* 17040SO ENGINE DAMAGED W EA ENGINE SHUTDOWN UNSCHED LANDING BRJSMOKE/FUMES/ODORS/SPARKS PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER A SOUTH BOUND DEPARTURE FROM CYPY RUNWAY 03 AN ABNORMAL DROP IN MANIFOLD PRESSURE WAS NOTICED. THE P/C SWITCHED FUEL TANKS TO ENSURE THE CAUSE WAS NOT FUEL CONTAMINATION. THERE WAS NO IMPROVEMENT. ENGINE INDICATIONS WERE LOW OIL PRESSURE, HIGH OIL TEMP, HIGH CYLINDER TEMP, AND SMOKE COULD BE SEEN FROM THE COCKPIT. THE A/C WAS TURNED BACK TO CYPY RUNWAY 03. AFTER ENSURING SUFFICIENT ALTITUDE TO MAKE THE FIELD, ENGINE WAS SHUTDOWN TO ENSURE NO FURTHER DAMAGE. AIRCRAFT WAS LANDED WITHOUT INCIDENT AND ROLLED OFF THE RUNWAY, ON & OFF THE TAXIWAY AND ONTO THE APRON WHERE IT WAS PARKED. MAINTENANCE INSPECTION REVEALED NR 6 PISTON DAMAGED BEYOND ECONOMICAL REPAIR. PISTON REMOVED. 1H71 3O3 O A16CE E8CE 20020807000242002080700024NE 2002 8 7 CA020702007 220020627G7310 TUBE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FUEL MANIFOLD CONTAMINATED W K NONE C F.O.D. ININSP/MAINT 1 CA (CAN) WHILE PERFORMING A REMOVAL / INSTALLATION OF THE FUEL NOZZLES,A SMALL PIECE OF METAL DEBRIS WAS FOUND WITHIN THE INTERNAL PASSAGE OF ONE OF THE FUEL MANIFOLD TRANSFER TUBES. THE DEBRIS WAS LODGED WITHIN THE TUBE AND HAD TO BE EXTRACTED BY PUSHING IT THROUGH WITH A PUNCH. THE NOZZLES DID NOT SHOW ANY ABNORMAL CONDITION. A NEW TRANSFER TUBE WAS INSTALLED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020807000252002080700025EU 2002 8 7 CA020702008 120020623G3110 WARNING SYSTEM PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT FAILED W O OTHER P NO WARNING INDICATION NRNOT REPORTED 1 CA (CAN) PILOT REPORTED NO MASTER WARNING OR CAUTION LIGHTS WORKING ON A/C.THE SYSTEM SENDS POWER TO LIGHTS FROM CENTRAL ADVISORY & WARNING CONTROL UNIT & PLACES GROUND TO TURN LIGHTS ON. 14.62 VOLTS MEASURED FROM UNIT. AFTER CONSULTING WITH TECHNICAL REPRESENTATIVE FOR MANUFACTURER A NEW CONTROL UNIT ORDERED. AFTER IT INST LIGHTS FAILED TO WORK. WIRES FROM TB115-02 WERE REMOVED VOLTAGE WAS TESTED AGAIN & WHEN WIRES WERE INSTALLED THE SYS WORKED NORMAL. THE A/C DEPARTED ON FLT TO ANOTHER BASE SYS FAILED AGAIN AT BASE. BASE ENGINEER WAS INSTRUCTED TO REMOVE WIRES GOING OUT OF TB115-02 TO SEE IF PROBLEM WITH ONE OF 4 LIGHTS HOOKED UP TO IT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020718001272002071800127EU 2002 7 18 CA020703001 220020625G8520 PLUG HOACAUHK36R HK36R 4170002EU ROTAX 912 ROTAX912 55555EU CRANKSHAFT LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRANKSHAFT HAS PRESSED IN WELSH PLUG IN FORWARD SECTION. THIS PLUG WAS FOUND INSIDE CRANKCASE.THE FOD WAS LIMITED TO CYLINDERS AND UNDERSIDE OF PISTONS. 1K71 3O3 IRCG51EU EXPE3I 20020807000312002080700031EU 2002 8 7 CA020704005 120020624G2434 SLIP RING 524321215 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL NR 2 GENERATOR GROOVED W K NONE O OTHER ININSP/MAINT 1 CA 100389 (CAN) INSPECTED GEN NR 2 BRUSHES FOR WEAR DURING SCHEDULED 100 HR INSP. FOUND APPROX 50 PERCENT LIFE REMAINING ON MOD "C" BRUSHES, HOWEVER THE BRUSH SLIP RING CONTACT AREA WAS GROOVED. IAW AIRCRAFT MM IF THERE IS PITTING, GROOVES OR SCORING FOUND ON THE SLIP RING SURFACE THEN REPLACE THE GENERATOR. GENERATOR 2 REPLACED WITH NEW UNIT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020730001312002073000131WP 2002 7 30 CA020705004 120020618G33971103070110 DECODER LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE CABIN FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) WHILE PERFORMING READING LIGHT TEST, BURNING ODOR COMING FROM AREA AROUND SEAT ROWS 26 ABC TO 30 ABC NOTICED. ALL READING LIGHTS WERE WORKING AT TIME & SMELL VERY WEAK. AFTER MOMENT LIGHTS FROM ROW 27 ABC TO END WENT OUT. IN THAT AREA TECHNICIAN HEARD STATIC / CRACKLING SOUND JUST BEFORE LIGHTS WENT OUT & SMELL GOT STRONGER. OVERHEAD PANELS ABOVE ROWS 26,27,28&29 WERE DROPPED & ODOR EXTREMELY STRONG. NO EVIDENCE OF ANY MALFUNCTION, ARCHING OR BURN MARKS. SYS RESET & WHEN THAT DONE DECODER AT ROW 29 ABC (POS 28) STARTED TO SMOKE. POWER CUT IMMEDIATELY & APPEARED TO BE NO OUTSIDE DAMAGE TO SURROUNDING AREA. NO DAMAGE TO ANY OF CANNON PLUGS , WIRING OR CONNECTORS. 2L73 4F4 F A23WE E12EU 20020730001322002073000132WP 2002 7 30 CA020705006 120020622G3232269002119 ACTUATOR LKHEED1011 1011385114 WP RROYCERB211 RB21122B02 54555NE MLG DOOR CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FOUND LT MLG DOOR ACTUATOR CRACKED .250 INCHES AND LEAKING (CONFIRMED BY NDT), IN DOOR CLOSED POSITION. MAINTENANCE REPLACED THE ACTUATOR IAW AMM 32-33-01. 2L73 4F4 F A23WE E12EU 20020807000392002080700039WP 2002 8 7 CA020708003 120020625G324060028812 MODULE LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE BRAKE ASSY CRACKED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT(IN MANCHESTER) RETURNED TO RAMP DUE TO B HYD SYSTEM LEAK FROM LT BRAKE MODULE. MAINTENANCE DISCOVERED THAT THE UNIT WAS CRACKED 2.5 INCHES JUST OVER SYSTEM B BRAKE RETURN PORT LT AND REPLACED THE UNIT IAW AMM 32-44-01. 2L73 4F4 F A23WE E12EU 20020807001852002080700185EU 2002 8 7 CA020708009 120020613G254024E507009G01 WATER HEATER AIRBUS310 A310300 3930305EU GE CF6 CF680C2A5 NE LAVATORY FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) DURING THE C-08 CHECK, IT WAS DISCOVERED DURING THE OPERATIONAL TEST, THAT THE POTABLE WATER HEATERS, IN LAVATORY F, WERE MAKING THE C/B TRIP. THE 3 UNITS WERE REMOVED AND SENT TO THE AVIONICS SHOP. WHEN REMOVING THE TOP COVER OF ONE UNIT, WE FOUND A SOPPY SUBSTANCE AND THE 2 OTHER UNITS SHOULD NOTHING (NO DEPOSITS). WHEN THE BOTTOM COVERS WERE REMOVED, WE FOUND ALL 3 THERMOSTAT ASSEMBLIES (P/N 24D50703G03) AND IRCUIT BOARD (24D507078G03) ASSEMBLIES BURNED. P/N OF THE POTABLE WATER HEATER ASSEMBLIES: P/N 24E507009G01. S/N'S OF THE POTABLE WATER HEATER ASSEMBLIES; S/N GOS 02204, G6W 03813, GOS 03427 2L72 4F4 FRTA35EU E13NE 20020807001982002080700198CE 2002 8 7 CA020711001 120020704G249721039 RHEOSTAT OHMITE 21039 LEAR 35 35A 5170602CE GARRTTTFE731TFE7312 01518WP COCKPIT DAMAGED W HD DEACTIVATE SYST/CIRCUITSRETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) WITH THE AIRCRAFT POWERED UP AND AC INVERTER ON, FLIGHT CREW NOTICE SMOKE RISING FROM LT SIDEWALL PANEL. UPON FUTHER INSPECTION WITH SIDEWALL REMOVED. THREE WIRE BUNDLES THAT GO TO THREE DIFFERENT REHOSTAT WERE FOUND WITH SPIRAL WRAP AROUND THEN AND MELTED TO TWO OF THREE REHOSTATS. DUE TO THE CHANGE OF RESISTANCE IN THE REHOSTAT IN DIFFERENT POSITIONS AND ALSO BECAUSE IT IS SUCH A TIGHT AREA WERE THE WIRE COULD CHAFE THE PROBLEM WOULD NEVER HAPPENED. THE REOSTAT WERE REPLACED AND AIRCRAFT RETURN TO SERVICE. 2L72 4F4 F A10CE E6WE 20020807001992002080700199CE 2002 8 7 CA020711002 120020711G531055112402 DOOR FRAME CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FUSELAGE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) OUTBOARD DOOR SKIN HAS WORN THE DOOR FRAME LINTEL AT THE RADIUS INTO THE DOOR OPENING AS MUCH AS 50 PERCENT MATERIAL THICKNESS. 1L72 4F4 F A22CE E1NE 20020807002042002080700204 2002 8 7 CA020711004 420020708G3160 DISPLAY BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA PFD FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) DURING FIRST DEPARTURE OF THE DAY THE NR 1 PFD DISPLAY UNIT (DU) WOULD NOT DISPLAY (BLANK). THE DU WAS REPLACED. THE A/C FLEW WITH NIL PROBLEMS.ON CLIMB OUT ON THE NEXT FLIGHT THE CREW REPORTED SMOKE IN THE FLIGHT DECK. THE AIRCRAFT RETURNED. THE NR 2 PFD WAS BLANK ON ARRIVAL AND CB WAS OUT. BURNING SMELL WAS CONFIRMED TO BE FROM THE NR 2 PFD. THE PFD WAS REPLACED. TECH RECORDS SHOW THE NR 2 PFD WAS PREVIOUSLY REPLACED ON MAY 7/02 DUE TO BLUE LINE ON SCREEN. 2H72 4T4 TRTA13NM E00062EN 20020807002082002080700208EA 2002 8 7 CA020712003 220020708G7320 FADEC BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA FUEL CONTROL MALFUNCTIONED W C ABORTED TAKEOFF W INADEQUATE Q C TOTAKEOFF 1 CA (CAN) A POWER PLANT MESSAGE WAS RECEIVED DURING INITIAL ELECTRICAL POWER UP OF THE A/C. THE CODES WERE CLEARED AND THE ENGINE GROUND RUN. NO PROBLEM WAS EVIDENT AT THAT TIME. TAKE OFF WAS BEGUN, AND ABORTED AS THE INDICATED TORQUE WENT TO 112 PERCENT FOR 2 SECONDS. MAINTENENCE ACTIONS: FADEC TRIM COMPENSATOR RESISTANCE VALUES WERE CHECKED, AND FOUND OK. THE FADEC WAS THEN REPLACED. NO FURTHER PROBLEM WAS EXPERIENCED. THE AIRCRAFT WAS RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E00062EN 20020807002112002080700211EU 2002 8 7 CA020712005 120020711G3230C23199104 CONTROL VALVE AIRBUS310 A310300 3930305EU NLG DOOR LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING AN A-CHECK A HYDRAULIC OIL PUDDLE WAS FOUND IN FRONT OF NOSE GEAR. AFTER INVESTIGATION A PIN HOLE WAS FOUND ON THE RIGHT NLG DOOR ACTUATOR CONTOL VALVE. THE ACTUATOR, CONTOL VALVE ASSEMBLY WAS REPLACED AND A LEAK CHECK WAS CARRIED OUT WITH NO FUTHER LEAKS NOTICED. 2L72 4F RTA35EU 20020807002142002080700214EA 2002 8 7 CA020712006 220020708G7314AN4101 PUMP GRUMANTS2 TS2ACALFORST3951102WP WRIGHTR1820 982C9HE2 67020EA HAMSTD43D 43D51 NE FUEL UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) DURING CLIMB FROM THE WHITEHORSE AIRPORT, THE PILOT NOTED THAT THE FUEL PRESSURE ON THE NUMBER 2 ENGINE WAS FLUCTUATING. THE ELECTRIC BOOST PUMP WAS ACTIVATED TO STABILIZE THE FUEL PRESSURE. THE PILOT EJECTED THE RETARDANT LOAD AND RETURNED TO THE AIRPORT. MAINTENANCE REPLACED THE ENGINE DRIVEN FUEL PUMP WITH A SERVICEABLE UNIT. THE ENGINE WAS GROUND RUN AND LEAK CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2H72 4R4 R A25WE E259 6 CP8879 20020807002202002080700220EA 2002 8 7 CA020715003 120020712G5740 ATTACH ANGLE CNDAIRCL215 CL2151A10 1900320EA WING TO BODY CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND AT ATTACH FASTENER HOLE AT LOWER SPAR LOCATION DURING NDT REQUIRED BY AD 1997-07R2 WHOSE REQUIREMENTS ARE EVERY 415 FLIGHT HOURS OR 1500 WATER DROPS, WHICHEVER COMES FIRST. THIS AIRCRAFT HAD 1250 WATER DROPS SINCE THE LAST COMPLIANCE OF THIS AD. 2H72 4R RTA14EA 20020807002312002080700231EA 2002 8 7 CA020715004 120020708G2800 CONTROL PANEL CNDAIRCL600 CL6002C10 1390015EA GE CF34 CF348C1 NE REFUEL/DEFUEL FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) WHILE REFUELING USING THE COCKPIT REFUEL / DEFUEL PANEL, THE PANEL FAILED AND WAS FOLLOWED BY A STRONG ELECTRICAL SMELL. AIRPLANE DEPOWERED.COCKPIT REFUEL/DEFUEL PANEL REPLACED. AIRCRAFT RETURNED IN SERVICE. 2L72 4F4 FRTA21EA EOOO63EN 20020807002322002080700232EA 2002 8 7 CA020715005 120020710G5610NP1393226 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CLCLIMB 1 CA 2290317464 (CAN) CO-PILOT SIDE WINDOW CRACKED DURING FLIGHT AT 5000 FEET. DIVERTED FLIGHT TO KOLN, GERMANY.SIDE WINDOW REPLACED. AIRCRAFT RETURNED IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020807002352002080700235EU 2002 8 7 CA020715007 120020715G2797 WIRE HARNESS ISRAEL1124 1124 4500102EU CONTROL COLUMN CHAFED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) DURING INSPECTION, AN ELECTRICAL SHORT WAS NOTICED AT THE BASE OF THE PILOTS CONTROL COLUMN. WIRING BUNDLE RUNNING UP THE CONTROL COLUMN WAS CHAFING ON THE STRINGER TO WHICH THE CONTROL COLUMN IS MOUNTED. THE CO-PILOTS COLUMN WAS INSPECTED AND SIMILAR CHAFING WAS NOTICED. WIRING WAS REPAIRED AND RE-LOCATED TO INSURE CLEARANCE DURING MOVEMENT OF THE COLUMN. CARE MUST BE TAKEN WHEN SECURING THE WIRE BUNDLES TO INSURE CLEARANCE DURING MOVEMENT OF THE CONTROL COLUMNS. 2M72 4F A2SW 20020807002412002080700241NM 2002 8 7 CA020715010 120020328G3246314354 WHEEL DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE MLG FAILED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) NR 4 MAIN WHEEL FAILED DURING TAXI OUT IN BATHHURST (ZBF)FOR TAKE OFF.WHEEL WAS JUST INSTALLED AND HAD ZERO TIME ON WHEEL SINCE INSTALLATION. THE OUTER FLANGE SEPERATED FROM THE WHEEL.WHEEL HALF SENT TO GOODRICH FOR ANALYSE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020807002532002080700253EA 2002 8 7 CA020717001 120020715G5520KS4 BEARING DHAV DHC2 DHC2MK3 2800107EA PWA PT6 PT6A27 52043EA ELEVATOR DISINTEGRATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON INSPECTION FOUND THAT THE CENTER BEARING ON THE RT ELEVATOR WAS MISSING. 1H71 3T4 T A806 E4EA 20020819000052002081900005EU 2002 8 19 CA020717002 120020716G2131 CONTROLLER AIRBUS320 A320212 3930322EU CFMINTCFM56 CFM565A3 NE CABIN PRESSURE MALFUNCTIONED W B EMER. DESCENT J WARNING INDICATION CRCRUISE 1 CA (CAN) IN LEVEL FLIGHT, FL350, FELT PRESSURE CHANGE. ECAM INDICATION, CABIN CLIMB RATE OF 700 FPM. PRESSURE PAGE ACCESS TO ASSESS RATE RAPIDLY INCREASED TO 1100 FPM. EMERGENCY DESCENT INITIATED, CABIN RATE INCREASE TO 1500 FPM. EXCESS CABIN ALT ECAM ACTIVATED AND ACTIONED. DITCH BUTTON SELECTED ON THEN OFF AS OUTFLOW VALVE APPEARED IN NORMAL POSITION. PRESSURE SELECTED TO MANUAL AND VALVE CLOSED WHEN SELECTED. CABIN PRESSURE CONTROL REGAINED AT APPROX FL240. CABIN RATE WENT TO -2800 IN DESCENT. AIRCRAFT LEVELED AT 16 000, ALL SYSTEMS AND PRESSURE APPEARED NORMAL. FLIGHT CONTINUED ENROUTE TO YWG 2L72 4F4 FRTA28NM E29NE 20020730001332002073000133SW 2002 7 30 CA020718008 120020623G3213 SUPPORT BELL 205050403 BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA SKID TUBE BROKEN W O OTHER D INFLIGHT SEPARATION LDLANDING 1 CA (CAN) AFTER LANDING THE AIRCRAFT, THE PILOT HEARD A LOUD BANG. THE AIRCRAFT DID NOT MOVE AND THERE WAS NO INDICATON OF ANY MALFUNCTION ON THE INSTRUMENTS. THE PILOT OPENED THE CREW DOOR AND SAW THE RT SKID TUBE SLIPPED OUT TO THE RIGHT. INSPECTION REEALED THAT THE FORWARD CROSSTUBE HAD SNAPPED IN HALF AT THE RT SUPPORT POSITION. THE BROKEN CROSSTUBE WAS REMOVED AND A NEW CROSSTUBE WAS INSTALLED. 1G71 4U4 U H4SW E22EA 20020807002642002080700264CE 2002 8 7 CA020718009 120020624G553004311481 FITTING CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL VERTICAL STAB BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 10919 (CAN) ON PRE-FLIGHT INSPECTION THE PILOT NOTICED A CRACK ON THE LEFT VERTICAL FIN ATTACH BRACKET. WHEN MAINTENANCE REMOVED THE BRACKET IT WAS FOUND BROKEN THROUGH. THE BRACKET WAS REPLACED WITH NEW AND NEW HARDWARE USED. THE RIGHT BRACKET WAS REMOVED CLEANED AND INSPECTED NO FAULT FOUND REINSTALLED USING NEW HARDWARE. THE REMAINING AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO FAULTS FOUND. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020807002652002080700265EA 2002 8 7 CA020718010 120020628G5711 SPAR FOUND FBA FBA2C 3640102EA LYC O540 O540A1C5 41532EA CENTER WING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WING SPAR CENTRE SECTION LOWER FORWARD CAP ANGLE VERTICAL FLANGE LEG WHERE RIVETED TO SPAR WEB HAS 25 PERCENT LOSS OF THICKNESS IN SEVERAL AREAS PROBABLY DUE TO INTERGRANULAR STRESS CORROSION. NO STRUCTURES REPAIR MANUAL EXISTS FOR THICKNESS LIMITS. ANOTHER WING WAS CHECKED AND IT HAS MORE SEVERE CORROSION THICKNESS LOSS. CONSIDER THIS A SAFETY CONCERN ON THIS AGING AIRCRAFT. 1H71 3O3 O A7EA E295 20020807002702002080700270NE 2002 8 7 CA020719004 320020712G611053216 BEARING RACE AYRES S2 S2RNORMAL 7630202SO PWA R1340 R1340AN1 52016NE HAMSTD12D 12D* NE PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER WAS REPORTED TO BE STICKING, AND UPON TEARDOWN OF THE PROPELLER IT WAS NOTED THAT THE CAP RACE WAS CRACKED. AS A RESULT THE CWT SHAFT WAS WORN BEYOND USE. OTHER FINDINGS WERE TWO BROKEN CWT. PINS IN THE CWT BRACKET, ONE WORN CHAFING RING, AND WORN BARREL SUPPORT BLOCKS. ALL THE ABOVE PARTS WERE REPLACED, PROP WAS ASSEMBLED LOCKED, AND BALANCED. 1L71 3R3 RNCA3SW 5E2 5 CP257 20020807002712002080700271CE 2002 8 7 CA020719005 120020627G575395160000604 SKIN BEECH 55 95A55 1152704CE CONT O470 IO470L 17026SO MCAULY2AF36C2AF36C39 GL TE FLAP CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE COMPLETING A 100 HR INSPECTION THE LEADING EDGE SKIN OF FLAP WAS FOUND CRACKED AT ACTUATOR ATTACH POINT.CRACKS EXTENDED INBOARD & OUTBOARD APPROXIMATELY 1INCH FROM THE FORWARD ATTACHMENT HOLE FOR FLAP ACTUATOR. - CRACKS WERE DETECTED AFTER CLEANING FLAPS.- CRACKS WERE ONLY VISIBLE WHILE FLAPS EXTENDED.- CRACKS WERE VISIBLE BEST FROM BELOW LOOKING AFT. 1L72 3O3 O 3A16 3E1 5 CP911 20020807002722002080700272CE 2002 8 7 CA020719006 120020710G55419763000023 SPAR BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A PHASE 2 INSPECTION IT WAS NOTED THAT THE RUDDER SPAR WAS CRACKED APPROXIMATELY 1.3 INCH, WHERE THE CENTRE HINGE BRACKET ATTACHES. THE CRACK WAS RUNNING VERTICALLY ALONG THE LT NUT PLATE FOR ATTACHING THE HINGE BRACKET. UPON REMOVAL OF THE SPAR IT WAS FOUND THAT THE HINGE DOUBLER P/N 96-630000-307 WAS ALSO CRACKED IN THE SAME PLACE. 1L72 3T4 T A14CE E4EA 20020807002732002080700273EA 2002 8 7 CA020719007 220020704G852011F20022D3 CRANKSHAFT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA ENGINE CRACKED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) CRANKSHAFT CRACKED - PIECE FROM COUNTERWEIGHT BROKEN - MISALIGNMENT CAUSED CAMSHAFT TO SHEAR 2 VALVE FACES DAMAGED. 1L72 3O3 O A20SO E14EA 20020807002752002080700275CE 2002 8 7 CA020719009 120020612G7120J951358 MOUNT CESSNA414 414 2075908CE CONT O520 TSIO520N 17040SO MCAULY3AF32C3AF32C505 GL ENGINE DEFORMED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE MOUNTS FOUND DEFORMED AND SOFT ALLOWING FOR EXCESSIVE MOVEMENT OF ENGINE ON MOUNTS. 1L72 3O3 ORTA7CE E8CE 5 CP22EA 20020807002762002080700276SO 2002 8 7 CA020722001 120020718G32504025700402377 SCISSORS PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA MLG BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN DOING A WALK AROUND THE PILOT NOTICED THE NUT, PART OF THE BOLT AND THE FORWARD LUG OF THE SCISSOR LINK WAS MISSING. CORROSION ON THE FACE OF BREAK INDICATES PRIOR CRACKS AT BREAK LOCATION.INITIATED INSPECTION OF SCISSOR LINKS AND HARDWARE ON SAME AIRCRAFT TYPE IN FLEET. 1L72 3O3 O A20SO E14EA 20020812000132002081200013GL 2002 8 12 CA020722005 320020719G6110A2807 PIN HARTZL HCE3YR2ATF PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA HARTZLHCE3Y HCE3YR2A GL PROPELLER BROKEN W O OTHER O OTHER TXTAXI/GRND HDL 1 CA DJ11753A (CAN) CUSTOMER COMPLAINED THAT PROPELLER DURING FLT WOULD NOT GO ALL THE WAY OUT OF FEATHER, INTO LOW PITCH. WHILE ON GROUND TRIED TO MOVE PROP TO LATCH WITH PADDLE, BUT ONLY ABLE TO MOVE IT PART WAY. UPON OUR REMOVAL OF LOW PITCH STOP IT NOTED THAT A3205 L.P. SCREW TURNED OUT & JAMMED BETWEEN LP STOP&PITCH CHANGE ROD. CYLINDER THEN REMVD&BROKEN A2807 LATCH PIN FOUND LAYING IN PISTON. PINS WERE REPL, CYLINDER INST, & ANGLES WERE SET. UPON SETTING FEATHER ANGLES THEY WERE FOUND TO BE SHORT ON TRAVEL, HUB NUTS WERE LOOSENED BLADE TRAEL ADJUSTED,&NUTS TIGHTENED. ASSY OF PROP COMPLETED,&PROP RETURNED TO CUSTOMER. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020730001342002073000134NM 2002 7 30 CA020722007 120020708G3260 PROXIMITY SWITCH BOEING737 737210C 1384459NM PWA JT8 JT8D9A 52048NE NLG OUT OF ADJUST W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA (CAN) DEPARTING YZF THE NLG INTRANSIT LIGHT WOULD NOT EXTINGUISH AFTER GEAR UP SELECTED. MTCE OBSERVED A CONTAMINATED PROXIMITY SWITCH SENSOR, DEFECT REMAINED AFTER CLEANING. THE UPLOCK POXIMITY SWITH WAS REPLACED AND STRIKE PLATE ADJUSTED. AIRCRAFT WAS GROUND FUNCTION TESTED SERVICEABLE AND TEST FLOWN BEFORE RETURN TO SERVICE. 2L72 4F4 F A16WE E2EA 20020819000072002081900007SO 2002 8 19 CA020722012 120020711G6121582855 HOUSING LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE PROP VALVE FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) ENROUTE YUX FROM YUW NR 4 ENGINE WOULD NOT SYNC. PRECAUTIONARY ENGINE SHUTDOWN CARRIED OUT. MAINTENANCE REPLACED THE PROP VALVE HOSUING. THE AIRCRAFT WAS GROUND CHECKED SERVICEABLE BEFORE RETURN TO SERVICE. 2H74 4T4 T A1SO E282 6 CP906 20020812000182002081200018SW 2002 8 12 CA020722013 120020630G5711 SPAR BBAVIA7 7EC 2110120SW CONT C90 C9012F 17009SO WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ALL 4 SPARS REPLACED DUE TO SMALL CRACKS AT NAIL HOLES, EDGE OF PLYWOOD REINFORCING AS A PRECAUTIONARY MEASURE. NO LARGE CRACKS FOUND.4 NEW METAL SPARS INSTALLED. 1H71 3O3 O A759 E252 20020812000202002081200020CE 2002 8 12 CA020722015 120020626G5330AK172168 SKIN CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11000 (CAN) WHEN STEPPING ONTO FUSELAGE STEP, THE STEP HAD MORE 'GIVE' THAN NORMAL. WHEN STEP WAS UNBOLTED, CRACKS WERE SEEN IN THE FUSELAGE SKIN. ALL COMPANY 172S & 172RGS WERE CHECKED AND ALL HAD CRACKS DEVELOPING TO SOME DEGREE. IT SEEMS THAT THE INSTALLATION ISN'T STRONG ENOUGH AND AN EXTRA DOUBLER OUGHT TO BE INSTALLED UNDER THE MOUNTING NUTS. 1H71 3O3 ONT3A12 E274 5 NP910 20020823000842002082300084CE 2002 8 23 CA020724002 120020702G282436600 CHECK VALVE BEECH 100 B100 1152919CE GARRTTTPE331TPE331625 WP FUEL SYSTEM OPEN W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FOLLOWING A FLIGHT WHILE UTILIZING THE AUXILIARY RESOURCES, A CHECK VALVE STAYED PARTIALLY OPEN. THE MAIN RESERVOIR TRANSFERRED TO THE AUXILIARY AND THE FUEL (TOO FULL) EXITED BY THE VENT AND LEAKED TO THE GROUND. THE PILOT ACTIVATED THE BOOST PUMP WITH AUXILIARY TRANSFER AND THE PROBLEM WAS RESOLVED. 1L72 4T4 T A14CE E2WE 20020823000872002082300087SW 2002 8 23 CA020724005 120020625G2820 LINE MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA FUEL DIST CORRODED W K NONE BK SMOKE/FUMES/ODORS/SPARKS FLUID LOSS ININSP/MAINT 1 CA (CAN) - DURING ANNUAL INSPECTION, FOUND FUEL ODOR IN CABIN AND FUEL STAIN ON LOWER FUSELAGE AREA. CABIN SIDE PANEL REMOVED FOR INSPECTION AND FOUND BOTH RIGID FUEL LINE FROM WING FUEL TANK TO AIRCRAFT FUEL STRAINER CORRODED AND LEAKING FUEL. NEW RIGID FUEL LINE INSTALLED. 1L71 3O3 O 2A3 1E10 20020812000362002081200036CE 2002 8 12 CA020724010 120020723G322204425037 FORK CESSNA 044250413 CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA STRUT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WITH THE PAINT CLEANED AWAY FROM THE UPPER OUTSIDE RADIUS OF THE FORK, THE TECHNICIAN WAS ABLE TO DETECT THE CRACK WITH A GOOD LIGHT AND 10 X MAGNIFIER. THE CRACK RUNS HORIZONTALLY AND IS ABOUT 1-2 INCHES LONG. THE DEFECTIVE PART HAS BEEN REMOVED FROM SERVICE AND REPLACED WITH A FACTORY NEW PART. 1H71 3O3 ONT3A19 E223 20020730001352002073000135NM 2002 7 30 CA020724012 120020722G2910NAS16126 O-RING DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM CUT W D RETURN TO BLOCK JK WARNING INDICATION FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) DURING TAXI AIRCRAFT LOST NR 1 HYDRAULIC PRESSURE, AND QUANITY WENT TO ZERO. O-RING REPLACED AT UNION AT RUDDER PRESSURE REGULATOR. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020730001362002073000136EA 2002 7 30 CA020725002 120020529G2910 LINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE HYDRAULIC SYSTEMFAILED W O OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 CA (CAN) LOSS OF SYS 1 HYDRAULIC FLUID DURING FLIGHT. PIN HOLE FOUND ON PUMP RETURN LINE. RETURN LINE REPLACED 2L72 4F4 FRTA21EA E15NE 20020812000462002081200046NE 2002 8 12 CA020725003 220020725G8500K60516 PIN DHAV DHC3 DHC3 2800202EA WSK ASZ62 ASZ62IRM18 NE NR 9 CYLINDER FRACTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE PIN FRACTURED IN THE AREA OF THE PIN THE RUNS INSIDE THE LINK ROD BUSHING. THE FRACTURE APPEARS TO HAVE ORIGINATED INSIDE THE CASTING AS A RESULT OF A FLAW IN THE CASTING OR FROM AN INCLUSION OR SOME OTHER INHERENT DISCREPANCY IN THE CASTING.THE EDGES OF THE FRACTURED PIN SHAVED THE BRASS LINK ROD BUSHING ALMOST TO THE LINK ROD PARENT MATERIAL AND CONTAMINATED THE ENTIRE ENGINE WITH BRASS.THE PIN IS BEING FORWARDED TO THE MANUFACTURER FOR FURTHER INVESTIGATION. 1H71 3R3 R A815 E10NE 20020830002332002083000233NM 2002 8 30 CA020725004 120020604G3040 WINDSHIELD BOEING737 7372T7 1384482NM PWA JT8 JT8D17A 52049NE COCKPIT ARCED W K NONE B SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA 91121H1125 (CAN) FIRST OFFICER NR 1 WINDSHIELD ARCING, UPPER MID SECTION DISCOLOURED BY WIRING LEADS REPLACED WINDSHIELD 2L72 4F4 FRTA16WE E2EA 20020819000372002081900037EA 2002 8 19 CA020725005 120020719G2420764510 PLUNGER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ADG ARM UNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE VALIDATION OF AMM TASK 24-23-01-720-803 IAW BOMBARDIER ENGINEERING TDS 601R-0566, WE DAMAGE THE ADG BACK PLATE AND BLADE LOCK PLUNGER OCCURRED. THE DAMAGE OF THE ADG WAS CAUSED BY AN IMPROPERLY CRIMPED LOCK TABFROM THE FACTORYLOCATED BETWEEN THE SELF LOCKING NUT AND THE BLADE LOCK PLUNGER OF THE ADG. DURING THE TESTING THE SELF LOCKING NUT SLACKENED OFF ALLOWING THE ENGAGEMENT LENGTH OF THE PIN TO INCREASE. THE PROTRUDING PIN IMPACTED THE ADG WHILE THE ADG WAS ROTATING. 2L72 4F4 FRTA21EA E15NE 20020812000472002081200047SO 2002 8 12 CA020725006 120020707G8011641368 BEARING PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO MCAULY3AF34C3AF34C503 GL STARTER SHAFT BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA (CAN) ON A TRAINING FLIGHT IN CRUISE PILOTS OBSERVED LOW OIL PRESSURE LIGHT ILLUMINATION ON THE LT ENGINE AND NO OIL PRESSURE ON THE GAUGE. THE PROPELLER FEATHERED ON ITS OWN DUE TO NO OIL PRESSURE. ENGINE WAS SHUT DOWN ACCORDING TO THE EMERGENCY PROCEDURES AND THE AIRCRAFT RETURNED AND LANDED AT THE AIRPORT OF DEPARTURE WITHOUT INCIDENT. UPON INSPECTION IT WASFOUND THAT A NEEDLE BEARING FROM THE STARTER CLUTCH ASSEMBLY HAD MADE ITS WAY TO THE OIL PUMP GEARS AND SUBSEQUENTLY JAMMING THE GEARS SHEARING THE PUMP DRIVE MAKING THE PUMP INOPERATIVE. 1L72 3O3 O A7SO E9CE 5 CP22EA 20020730001372002073000137EA 2002 7 30 CA020725007 120020604G5610 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT CRACKED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) CAPTAIN,S WINDSHIELD CRACKED ON DESCENT. WINDSHIELD REPLACED 2L72 4F4 FRTA21EA E15NE 20020812000542002081200054CE 2002 8 12 CA020725013 120020717G53115042006653 FRAME BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TWO CRACKS STARED FROM THE RADIUS OF THE LOWER FLANGE. THE FORWARD CRACKED ENDED AT LIGHTNING HOLE WHILE THE OTHER CRACK ENDED BEHIND THE AFT LIGHTNING HOLE. IPL 53-10-10-37 1L72 4T4 T A24CE E4EA 20020812000632002081200063 2002 8 12 CA020725014 420020613G3417HG480B13 ADC BOEING737 737217 1384464NM PWA JT8 JT8D17 52049NE AUTO FLIGHT FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CRCRUISE 1 CA (CAN) AUTOPILOT ENGAGED IN CRUISE,UNABLE TO UNFREEZE MANUALLY,LEFT WING LEVEL TO A SLIGHT RIGHT BANK. AILERON CONTOL LOST-FROZEN TILL AUTO PILOT RELEASED.CENTRAL AIR DATA COMPUTER REPLACED P/N HG480B13 S/N P-529 2L72 4F4 F A16WE E2EA 20020819000592002081900059CE 2002 8 19 CA020726005 120020724G2610302158 FIRE DETECTOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL RT ENGINE MALFUNCTIONED W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) CREW REPORTED A RIGHT ENGINE FIRE LIGHT IN FLIGHT.THE WARNING LIGHT ILLUMINATED, WENT OUT FOR A BRIEF PERIOD AND THEN CAME ON AGAIN. THERE WAS NO PHYSICAL EVIDENCE OF A FIRE AND ALL ENGINE PARAMETERS WERE NORMAL. THE ENGINE WAS SHUT DOWN AND THE FIRE BOTTLE DISCHARGED. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTION DETERMINED THAT THE AFT LOWER FIRE DETECTOR WAS DEFECTIVE. TIME ON PART UNKNOWN. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020823000892002082300089CE 2002 8 23 CA020726008 120020618G76035038901229 THROTTLE CABLE BEECH 58 58 1152740CE CONT O520 IO520C 17032SO ENGINE BROKEN W EA ENGINE SHUTDOWN UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) APPROXIMATELY 6 INCHES FROM ENGINE END THROTTLE CABLE BROKE. REPLACED THROTTLE CABLE. 1L72 3O3 O 3A16 E5CE 20020812000772002081200077NE 2002 8 12 CA020726011 220020716G8530K60516 PIN DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE ENGINE BROKEN W O OTHER D INFLIGHT SEPARATION APAPPROACH 1 CA (CAN) - ENGINE MAKING CLICKING SOUND SIMILAR TO EXCESSIVE VALVE CLEARANCES. OIL SCREEN INSPECTED AND BRASS PARTICLES FOUND. VALVE CLEARANCES ADJUSTED AND OIL SYSTEM FLUSHED. ENGINE GROUND RUN AND ENGINE NOISE STILL EXISTED. SPARK PLUGS PULLED AND EXAMINED AND NR 9 CYLINDER WAS DETERMINED TO BE BURNING OIL. CYLINDERS REMOVED AND BROKEN WRIST PIN FOUND. 1H71 3R3 R A815 5E2 6 CP719 20020819000632002081900063SW 2002 8 19 CA020726017 120020701G6210 BLADE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE MAIN ROTOR BENT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE LT WING TIP OF A CL-415 WATER BOMBER CONTACTED THE FORWARD ROTOR BLADE OF THE 205. THE 205 WAS PARKED AND TIED DOWN. THE CL-415 WAS DESCRIBED AS TRAVELLING AT A "SLOW TAXI SPEED". ONE BLADE SUSTAINED MINOR DAMAGE (REPAIRABLE) AT TIP. NO OTHER DAMAGE WAS FOUND WITH A VISUAL INSPECTION. BELL HELICOPTER PRODUCT SUPPORT ISSUED A LETTER STATING A VISUAL INSPECTION WAS ALL THAT WAS REQUIRED. THE DAMAGED BLADE WAS REPLACED. DURING THE TRACK AND BALANCE PROCEDURE LATERAL BALANCE COULD NOT BE REDUCED BELOW 0.80 IPS. AS A PRECAUTION THE M/R HEAD, M/R MA5, TRANSMISSION AND ALL TXSM MOUNTS WERE REPLACED. AIRCRAFT WAS EASILY BALANCED. SUSPECTED BENT MAST. 1G71 4U4 U H1SW E17EA 20020819000642002081900064EA 2002 8 19 CA020726019 220020703G732204500704 BUTTERFLY VALVE CESSNA 04500522 CESSNA150 152 2071835CE LYC O235 O235C2C 41505EA MCAULY1A103 1A103TCM GL CARBURETOR SEPARATED W A UNSCHED LANDING RB PARTIAL RPM/PWR LOSS SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA (CAN) THE SEAL FOR THE BUTTERFLY VALVE IN THE CARBURETOR AIR BOX (FOR CARBURETOR HEAT) SEPARATED AND WAS SUCKED UP INTO THE CARBURETOR. THIS CAUSED THE ENGINE TO LOSE PERFORMANCE WHICH MADE THE PILOT RETURN FOR A LANDING. TOWER REPORTED SMOKE (LIKELY FROM A RICH MIXTURE) TAILING THE AIRCRAFT. UNEVENTFUL LANDING. AIRCRAFT REMOVED FROM SERVICE. NOW REPAIRED AND BACK ON LINE. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020819000652002081900065CE 2002 8 19 CA020726020 120020711G273103103625 SCREW CESSNA 12601481 CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL ACTUATOR BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) DURING CRUISE FLIGHT THE TRIM TAB ON THE HORIZONTAL STABILIZER STARTED TO FLUTTER CAUSING VIBRATION IN THE CONTROL COLUMN. TRIM MECHANISM JAMMED IN THE FULL NOSE UP SETTING. PILOT WAS FORCED TO OVERRIDE TRIM SETTING WITH CONTROL INPUTS AND LAND ON A NEARBY LAKE.SUBSEQUENT INSPECTION REVEALED THE SCREW ASSEMBLY BROKEN IN HALF AT THE START OF THE THREADED SECTION. AMO DIRECTOR OF MAINTENANCE STATES VERY UNUSUAL FAILURE. BROKEN PART IS BEING HELD FOR INSPECTION IF REQUIRED. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020807001272002080700127WP 2002 8 7 CA020729001 120020719G5510369D2363312 TIP CAP HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL HORIZONTAL STAB CRACKED W O OTHER D INFLIGHT SEPARATION DEDESCENT 1 CA (CAN) WHILE IN A STEEP DESCENT THE PILOT OBSERVED THE RIGHT HAND TIP CAP (WINGLET) GO PAST HIM AND HIT THE GROUND IN THE LANDING / WORKSITE. THE AIRCRAFT WAS LESS THAN 300 FEET AGL. THE AIRCRAFT CONTINUED DESCENT AND MADE A NORMAL POWER ON LANDING. RECOVERY AND INSPECTION OF THE FAILED PART INDICATE VERY RECENT CRACKING AT THE FORWARD EDGE AIRFLOW OF THE ATTACHED WINGLET CAUSED TEARING OF THE REMAINDER OF THE STRUCTURE. THERE IS NO INDICATION OF A BIRD OR OTHER ITEM CONTACTING THE WINGLET. 1G71 3U3 U H3WE E4CE 20020819000662002081900066SW 2002 8 19 CA020729002 120020711G6240 INDICATOR BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE MAIN ROTOR FAILED W B EMER. DESCENT O OTHER HOHOVERING 1 CA (CAN) FROM REPORTS: THE AIRCRAFT WAS HOVERING WITH A WATER BUCKET OVER A FIRE. ROTOR SPEED DECAYED AND PILOT MADE A FORCED LANDING IN A CLEARING. THE AIRCRAFT LANDED VERY HARD AND ROLLED ON TO ITS RIGHT SIDE. PILOT CRAWLED OUT AND SUSTAINED MINOR INJURIES. THE AIRCRAFT WILL MOST LIKELY BE DECLARED A "WRITE OFF". CAUSE IS UNKNOWN AND THE T.S.B. IS CURRENTLY INVESTIGATING THE INCIDENT. OTTAWA T.C.C. (PMI) WAS INFORMED VERBALLY FRIDAY, JULY 12, 2002. 1G71 4U4 U H1SW E17EA 20020812001072002081200107GL 2002 8 12 CA020729003 320020717G6111 BLADE CESSNA140 140 2071602CE CONT C85 C8512 17008SO MCAULY1B90 1B90* GL PROPELLER CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. EXTRA WORK REQUIRED TO REMOVE CORROSION CARRIED OUT: AN OVERHAUL. AS PER MCCAULEY MANUAL 730720 1H71 3O3 ONCA768 E233 5 NP842 20020823000902002082300090GL 2002 8 23 CA020729004 120020716G55402055450300 HINGE BRACKET DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO VERTICAL STAB CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) CRACK FOUND ON BOTTOM LEFT WELD OF SUPPORT BRACKET. 1L71 3O3 ONTTA4CH E7SO 20020823000922002082300092SO 2002 8 23 CA020729005 120020703G528042059007 HINGE PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE MLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED 100 HOUR EVENT NR 2 LANDING GEAR INSPECTION, CRACK FOUND ON LEFT HAND FORWARD MAIN LANDING GEAR OUTBOARD DOOR HINGE. CAUSE DETERMINED TO BE FATIGUE. 1L72 3T4 TRTA8EA E4EA 20020819000702002081900070CE 2002 8 19 CA020729006 120020711G321265D1 COVER CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO FLOAT DEPARTED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) UPON LIFTING OFF THE WATER THE RT FLOAT HATCH - DEPARTED THE FLOAT - CREASING RT FUSELAGE SKIN AHEAD OF BULKHEAD AT STATION 108.0 AND HIT RT LEADING EDGE OF HORIZONTAL STABILIZER. 1H71 3O3 O 3A24 E5CE 20020812001092002081200109EA 2002 8 12 CA020729008 220020716G7322RSA5AD1 SERVO CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA FUEL CONTROL FAILED W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION LDLANDING 1 CA (CAN) PILOT REPORTED THAT THE ENGINE QUIT WHEN LANDING AND THROTTLE PULLED TO FULL IDLE. GROUND RUN CONFIRMED PROBLEM. MIXTURE CONTROL ADJUSTED TO GET PROPER RISE AT IDLE CUT-OFF - RUN UP AND FULL IDLE OPERATION NOW NORMAL. 1H71 3O3 ONT3A12 1E10 20020823000932002082300093CE 2002 8 23 CA020729009 120020627G32304013004 BRUSHES BEECH 100 B100 1152919CE MLG MOTOR FAILED W L ABORTED APPROACH R PARTIAL RPM/PWR LOSS APAPPROACH 1 CA (CAN) WHILE LANDING GEAR WAS BEING EXTENDED DURING AN APPROACH, LANDING GEAR DID NOT COME OUT AFTER A FEW TRIES (GEAR UP, GEAR DOWN), IT DID FINALLY EXTEND. THE AIRCRAFT WAS CHECKED AND IT SEEMED THAT THE ENGINE WAS FORCING DURING RETRACTION. THE BRUSHES WERE CHECKED AND 2 OUT OF 4 WERE FOUND FAILED. THESE WERE REPLACED. A FEW MORE RETRACTIONS WERE TRIED AND EVERYTHING RETURNED TO NORMAL. 1L72 4T A14CE 20020819000872002081900087CE 2002 8 19 CA020729011 120020716G3246C30057 WHEEL CESSNA150 150L 2071826CE CONT O200 O200A 17020SO MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON INSEPCTION IT WAS DISCOVERED THAT THE HUB WAS CRACKED IN THE AREA OF THE GREASE SEAL RETAINING RING. THE CRACK IS ONLY ABOUT 3/8 INCH LONG AND TRAVELS PARALLEL TO THE RETAINING RING GROOVE JUST BELOW IT. HUB WAS REPLACED. 1H71 3O3 O 3A19 E252 20020822000322002082200032EU 2002 8 22 CA020729014 120020614G56109598110112 WINDOW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING REMOVAL OF THE MAIN RT WINDSCREEN, IT WAS NOTICED THAT ONE OF LOWER SECTION SCREW ATTACHMENT LUGS ON THE RT SIDE WINDOW WAS CRACKED. THE SIDE WINDOW REQUIRED REPLACMENT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020822000372002082200037SW 2002 8 22 CA020730005 120020716G5711 SPAR BBAVIA7 7AC 2110102SW CONT A65 A658 17003SO RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WING SPARS, RIGHT FRONT WING WITH SMALL CRACKS FROM NAIL HOLES VARIOUS LOCATIONS. RIGHT REAR SPAR WITH CRACK FROM TIP DAMAGE PREVIOUS.BOTH SPARS REPLACED. 1H71 3O3 O A759 E205 20020822000382002082200038CE 2002 8 22 CA020730006 120020729G2434ES4145 ROTOR FORD DOFF10300J CESSNA177 177B 2073708CE LYC O360 O360A1F6 41514EA MCAULY2D34C B2D34C211 GL SLIP RINGS OUT OF TOLERANCEW A UNSCHED LANDING H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 CA A154280 (CAN) NEW ROTOR WAS INSTALLED AT OVERHAUL. AFTER 374 HRS, UNIT FAILED TO PRODUCE OUTPUT. ON DISASSEMBLY AND INSPECTION, ONE BRUSH WAS FOUND COMPLETELY WORN OUT, AND THE BRUSH SHUNT BRAIDED LEAD WAS CHAFED IN TWO. FOUND THAT THE SLIP RINGS ON THE ROTOR WERE OUT OF CONCENTRICITY BY 0.005 OF AN INCH TIR. THIS CONDITION WOULD CAUSE RAPID BRUSH WEAR. WHEN THE NEW ROTOR WAS INSTALLED, THE WORK ORDER DID NOT INDICATE THAT THE SLIP RINGS WERE INSPECTED FOR RUNOUT (TIR). THEY WERE EITHER OUT AT THAT TIME BUT IT WAS NOT DETECTED, OR THE SLIP RING ASSEMBLY HAS MOVED ON THE ROTOR SHAFT WHILE IN SERVICE. 1H71 3O3 O A13CE E286 5 CP7EA 20020812001102002081200110SO 2002 8 12 CA020731002 220020723G7414 LEAD CONT O470L CESSNA182 182A 2072704CE CONT O470 O470L 17026SO MAGNETO INTERMITTENT W K NONE O OTHER ININSP/MAINT 1 CA 671877L (CAN) DURING RUN-UP AFTER ANNUAL INSPECTION LT MAGNETO GROUNDED OUT. INSPECTION FOUND "P" LEAD INTERMITTENT. ON FLEXING RT "P" LEAD IT WAS ALSO FOUND TO BE INTERMITTENT. FURTHER EXAMINATION DISCLOSED DETERIORATED INSULATION CLOSE TO ENTRY TO MAGNETOS ALLOWING GROUNDING ON BRAIDED SHIELDING. 1H71 3O3 ONT3A13 E273 20020822000412002082200041EU 2002 8 22 CA020731003 120020723G7820 MUFFLER ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA ENGINE EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A FIRST 100 HOUR INSPECTION ON A NEW AIRCRAFT, THE NR 3 CYLINDER EXHAUST PIPE WAS FOUND TO BE CRACKED WHERE IT IS WELDED TO THE MUFFLER. THE CRACK WAS APPROXIMATELY 1.5 INCHES LONG AROUND THE CIRCUMFERENCE OF THE PIPE. THIS PIPE HAS A STRUT ATTACHED TO IT BRACING THE PIPE TO ONE OF THE INJECTOR SERVO MOUNTING STUDS. IT IS SUSPECTED THAT IF THE STRUT IS IMPROPERLY ADJUSTED THERE IS STRESS PUT ON THIS PIPE, AND WITH THE HEATING AND COOLING OF THE EXHAUST SYSTEM IT MAY PRODUCE CRACKING. 1L71 3O3 O0 A76EU 1E10 20020816001582002081600158NM 2002 8 16 CA020731013 120020709G2750BACP30K15 CONTROL CABLE BOEING737 7372T7 1384482NM PWA JT8 JT8D17 52049NE TE FLAPS FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 5 FLAP ACTUATOR ROLLER TRACK DISENGAGED AND WENT THROUGH THE INBOARD SIDE OF NR 5 FLAP FAIRING. NR 5 FLAP TRACK FITTING FOUND DAMAGED (SNAPPED) DUE BOOM CABLE BROKEN. CABLE, TRACK FITTING, PULLEYS, BOOM ASSY, AND CAM FOLLOWER GUARD ADJUSTED AS PER AMM. SYSTEM CERTIFIED AND CHECKED SERVICEABLE. 2L72 4F4 FRTA16WE E2EA 20020822000872002082200087CE 2002 8 22 CA020731014 120020624G2720NAS428H37 STOP CESSNA150 150J 2071820CE LYC O320 O320E2D 41508EA MCAULY1C172 1C172TM GL RUDDER MISSING W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) UPON COMPLETING INSPECTION OF RUDDER STOPS PER AD CF-2000-20, IT WAS FOUND THAT THE RUDDER STOPS WERE BOTH MISSING. THERE WERE NO HOLES IN THE TAILCONE SKIN WHERE THE STOPS SHOULD HAVE BEEN, BUT THE ANCHOR NUTS WERE RIVETS TO THE BULKHEAD. THIS SKIN WAS REPLACED (ACCORDING TO A WORK REPORT FOUND IN THE LOGBOOK) IN 1978 WHILE THE AIRCRAFT WAS IN MAJOR REPAIRED.OBVIOUSLY, THIS AIRCRAFT WAS FLOWN WITHOUT RUDDER STOPS FOR SOME 24 YEARS AND 1365 HOURS. 1H71 3O3 O 3A19 E274 5 NP910 20020822000912002082200091CE 2002 8 22 CA020731017 120020731G3220280X4 TUBE CESSNA305 305 2074001CE CONT O470 O47011 17026SO TAIL WHEEL ASSY SPLIT W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING SERVICING OF TAILWHEEL, A NEW TUBE WAS BEING INSTALLED. THE TUBE WAS INFLATED TO CHECK FOR LEAKS (STANDARD PROCEDURE) AND IT WAS NOTICED THAT THE SIDE OF THE TUBE STARTED TO SPLIT. 8 TUBES WERE PURCHASED AT THE SAME TIME. ALL OF THEM HAVE THE SAME DEFECT. THE TUBES ARE BEING RETURNED TO THE SUPPLIER FOR CREDIT. THE TUBES WERE PURCHASED IN JULY 2002. 1H71 3O3 O EXPA1H71E269 20021004000822002100400082NM 2002 10 4 CA020801001 120020714G2761684D1007 ACTUATOR BOEING767 767383 1385214NM GE CF6 CF680C2B6F 30025NE SPEED BRAKE SYS BINDING W O OTHER F FLT CONT AFFECTED CRCRUISE 1 CA (CAN) SPOILER LEVER FEELS TO HAVE MORE TENSION (BINDING) WHEN DEPLOYING AND RETRACTING. REPLACED SPEEDBRAKE MECHANISM AND TESTED PER AMM 27-62-04-002-114 2L72 4F4 FRTA1NM E13NE 20021004000832002100400083EU 2002 10 4 CA020801002 120020715G273031075217 SERVO AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE ELEVATOR FAILED W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) WHILE DOING OPEN PROCEDURES CALLED FOR MEL 27-93-01 A RB ELEVATOR SERVO FAILED. AIRCRAFT REMOVED FROM SERVICE FOR SERVO CHANGE. REPLACED RT BLUE ELEVATOR SERVO CONTROL AS PER AMM 27-34-51-400. OPERATION CHECKED SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20021004000872002100400087NM 2002 10 4 CA020801003 120020717G2710550030017 ACTUATOR BOEING767 767375 1385217NM GE CF6 CF680C2B6F 30025NE AILERON LOCKOUT FAILED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) RT AILERON LOCKED OUT DURING FLIGHT AFTER LEAVING YVR. RT LOCK OUT ACTUATOR REPLACED PER AMM 27-11-44 PG 1-12 OPERATION CHECKED SERVICEABLE 2L72 4F4 FRTA1NM E13NE 20020816001632002081600163CE 2002 8 16 CA020801011 120020725G7820 MUFFLER CESSNA206 U206D 2073342CE CONT O520 IO520F 17032SO MCAULY2A34C D2A34C58 GL RT EXHAUST PIPE SEPARATED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) THE MUFFLER INSTALLED MAY 27, 2002 SEPARATED AT THE BELL FLANGE (UPPER ATTACH POINT). THE TAILPIPE CLAMP REMAINED CONNECTED. THE MUFFLER WAS REMOVED AND REPLACED ON JULY 4, 2002 WITH A NEW OVERHAULED MUFFLER AND NEW ATTACHING HARDWARE. THE AIRCRAFT WAS RETURNED TO SERVICE. SEC 7 SUB SEC A AND B: PILOT ALERTED TOWER THAT THERE WAS SMOKE IN THE COCKPIT AND THAT HE WAS ABORTING HIS TRAFFIC PATTERN TO LAND. 1H71 3O3 O A4CE E5CE 5 CP3EA 20020822001002002082200100CE 2002 8 22 CA020801015 120020731G2435 ARMATURE CESSNA182 TR182 2072735CE LYC O540 O540L3C5 41532EA MCAULY2D34C B2D34C219 GL STARTER MOTOR SEPARATED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) PILOT REPORTED START ATTEMPT FAILED DUE TO EXCESSIVE ELECTRICAL DRAW AND STARTER MOTOR DID NOT TURN. STARTER REMOVED TO INSPECT AND FOUND COMMUTATOR COMPLETELY DISINTEGRATED ALONG WITH THE BRUSH BLOCKS AND HOLDER ASSY. THE CONNECTING WIRES TO THE ARMATURE WERE FOUND SEVERELY STRESSED AND BROKEN WITH THE APPEARANCE THAT THE STARTER HAD EXPERIENCED EXCESSIVE ROTATIONAL SPEED. ADVISED THAT PREVIOUS PILOT HAD INDICATED A PROBLEM WITH THE BENDIX DRIVE FAILING TO DISENGAGE PROPERLY ON THE PREVIOUS START. 1H71 3O3 O 3A13 E295 5 CP7EA 20020822001072002082200107EA 2002 8 22 CA020806003 220020722G741410357584 GEAR 101630052 ROBSINR22 R22BETA 7640110NM LYC O360 O360J2A 41514EA MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 CA C059701ER (CAN) - AXLE SHAFT AND WASHER FOUND LOOSE IN DISTRIBUTOR GEAR. 1G71 3O3 O H10WE E286 20020822001092002082200109CE 2002 8 22 CA020806004 120020803G29108A12000007 TUBE CESSNA208 208 2073702CE PWA PT6 PT6A114 52043NE MCAULY3AF34C3GFR34C703 GL HYD SYSTEM DEFORMED W O OTHER KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) OPERATOR PURCHASED A/C FROM COMMERCIAL OPERATOR & INHERITED PERSISTENT & ELUSIVE HYD LEAK. AFTER TROUBLESHOOTING, SOURCE ISOLATED TO TWO B-NUTS NOT TIGHT. FITTINGS WERE NOT ACCESSIBLE. 5 CYCLES LATER NR 13 HYDRAULIC LINE FAILED ON GEAR RETRACTION EMPTYING HYDRAULIC SYS. A/C RETURNED FOR LANDING ON INFIELD GRASS WITH GEAR PARTIALLY RETRACTED. NO DAMAGE TO GEAR OR FLOATS WERE ENCOUNTERED. FAILED LINE SHOWED SIGNS OF SLEEVE COUPLING WORKING AGAINST FLAIR. IT APPEARS THAT WHEN B-NUT WAS CORRECTLY TORQUED IT WEAKENED FLAIR ENOUGH TO ALLOW THE AN819-5D COUPLING SLEEVE AND AN818-5D NUT TO SLIDE OVER THE END OF THE TUBE. 1H71 3T3 TNTA37CE E4EA 5 CP60GL 20020822001212002082200121EA 2002 8 22 CA020806013 220020801G855071664 IDLER GEAR PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA ENGINE BROKEN W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) DURING CLIMB OUT, THROUGH ABOUT 11,000 FT, LT ENGINE LOST POWER. CREW NOTED LOW FUEL PRESSURE ON LT ENGINE, SELECTED BOOST PUMP, AND REGAINED NORMAL ENGINE OPERATION. DIVERTED FOR A LANDING. LT FUEL PUMP WAS REMOVED AND FOUND TO BE FUNCTIONAL, THE PUMP DRIVE IN THE ENGINE WAS NOT ROTATING. THE REAR CASE WAS REMOVED AND THE IDLER GEAR WAS FOUND TO HAVE LOST 5 TEETH THUS DIS-ENGAGING THE FUEL PUMP DRIVE GEARSHAFT. GEAR WAS REPLACED WITH A SERVICEABLE GEAR, ALL OTHER GEARS AND PARTS INSPECTED AND FOUND SERVICEABLE AND THE ENGINE WAS RE-ASSEMBLED AND TESTED OK. 1L72 3O3 O A20SO E14EA 20020823000032002082300003NE 2002 8 23 CA020808003 220020723G851039487 CASE GRUMAVG21 G21A 3951204SO PWA R985 R985* 52008NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE MAINTENANCE A 3 INCH CRACK WAS FOUND IN THE FORWARD NOSE CASE STARTING JUST ABOVE THE OIL SUMP AND PROGRESSING UPWARD. THE ENGINE WAS REPLACED. 1H72 3R3 R TC654 5E1 20020823000042002082300004SO 2002 8 23 CA020808005 120020801G7700URHB32E LIGHT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA COCKPIT BURNED OUT W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) DURING A RUN UP, EXPERIENCED A LOSS OF RPM OF 200 CYCLES ON THE RT MOTOR. AFTER VERIFICATION, AN INDICATOR LIGHT WAS FOUND TO BE DEAD. 2 MONTHS AGO THE SAME PROBLEM HAPPENED WITH ANOTHER ENGINE. 1L72 3O3 O A20SO E14EA 20020823000052002082300005EA 2002 8 23 CA020808006 220020801G8530AEL19001 EXHAUST VALVE CESSNA172 172N 2072434CE LYC O320 O320D2G 41508EA ENGINE CYCLINDERBROKEN W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) AT CRUISING ALTITUDE, THE ENGINE LOST POWER. RPMS DROPPED TO 2000. INSPECTION OF NR 3 CYLINDER, FOUND NO COMPRESSION. THE EXHAUST VALVE WAS FOUND TO BE BROKEN, REPLACED THE CYLINDER. 1H71 3O3 ONT3A12 E274 20020823000112002082300011CE 2002 8 23 CA020812005 120020811G2731 PIN CESSNA CESSNA150 150M 2071830CE CONT O200 O200A 17020SO MCAULY1A102 1A102OCM GL SPUR GEAR MISSING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TWO PERMANENT PINS THAT HOLD THE SPUR GEAR TO THE ROTATING SHAFT OF THE TRIM TAB ACTUATOR HAD FALLEN OUT AND WENT MISSING. TRIM CONTROL WAS IMPOSSIBLE DUE TO SLIPPAGE OF THE SPUR GEAR IN THE SHAFT. ACTUATOR REPLACED WITH NEWLY OVERHAULED UNIT. 1H71 3O3 O 3A19 E252 5 NP918 20020823000162002082300016NM 2002 8 23 CA020813005 120020721G291082970010143 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 3613236132 (CAN) DURING WALK-AROUND FOUND HYDRAULIC LEAK NEAR NR 1 GEAR , INSPECTION FOUND NR 1 SPU PRESSURE LINE LEAKING . LINE REPLACED WITH TEMP FLEX LINE . AIRCRAFT RETURNED TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020823000232002082300023NM 2002 8 23 CA020813014 120020806G532065453132 STRINGER CLIP BOEING727 72725C 138400HNM FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING C3-CHECK FOUND STRINGER CLIP CRACKED AT BS 1030 AT STRINGER 4 RT. REMOVED AND REPLACED STRINGER CLIP WITH A NEW CLIP IAW 51-30-2. 2L73 4F A3WE 20020823000272002082300027SO 2002 8 23 CA020814005 120020809G8011 DRIVE GEAR PRESTOLITE MZ4204 PIPER PA38 PA38112 7103812SO LYC O235 O235L2C 41505EA STARTER MOTOR DISINTEGRATED W C ABORTED TAKEOFF E VIBRATION/BUFFET TOTAKEOFF 1 CA 8L000474 (CAN) ON TAKEOFF, PILOT REPORTED NOISE AND ABORTED. INSPECTION REVEALED DISINTEGRATION OF STARTER MOTOR BENDIX DRIVE GEAR AND FRONT STARTER BUSHING IN CONTACT WITH SPINNER BACKING PLATE. THE BENDIX APPARENTLY DID NOT DISENGAGE AFTER STARTUP AND THE ENGINE DROVE THE STARTER MOTOR TO FAILURE. APPEARS THE ARMATURE SEIZED ON ITS BEARINGS, THEN THE BENDIX TRYING TO STILL TURN THE MOTOR PUSHED THE ARMATURE FORWARD ALONG WITH THE NOSE BUSHING INTO THE PERIPHERY OF THE SPINNER BACKING PLATE AT WHICH POINT THE BENDIX GEAR DISINTEGRATED. 1L71 3O3 O A18SO E223 20020823000442002082300044NM 2002 8 23 CA020816004 120020808G2701AE66111 BEARING BOEING757 757236 1384971NM RROYCERB211 RB211535E43754555NE RUDDER SEIZED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) CREW REPORTING RUDDER PEDAL HARD TO MOVE ON GROUND. AFTER INVESTIGATION, MAINT FOUND A ROLLER BEARING SEIZED IN THE CAM ROLLER ARM ASSY. OF THE RUDDER FEEL CENTERING MECHANISM MAINTENANCE REPLACED THE ROLLER AND TESTED THE RUDDER PEDAL FORCES IAW AMM 27-21-00 P. 570. 2L72 4F4 FRTA2NM E12EU 20020823000452002082300045NM 2002 8 23 CA020819009 120020814G254014352004 DUMP VALVE BOEING BOEING737 7372Q9 138448MNM PWA JT8 JT8D9A 52048NE FWD LAVATORY LEAKING W A UNSCHED LANDING K FLUID LOSS CRCRUISE 1 CA (CAN) FORWARD LAVATORY FLUID BYPASSED DUMP VALVE ASSEMBLY INTO DRAIN MAINIFOLD AND LEAKED INTO THE SERVICE PANEL AREA. AIRCRAFT WAS AT 32,000 FT AT A TEMP OF -17C, OAT, WHEN THE ICE SHED FROM THE FWD LAV SERVICING PANEL AND CONTACTED THE RT INBOARD WING AND HORIZONTAL STAB AREA. SPECIAL INSPECTION CARRIED OUT IAW MM 55-10-201. FORWARD TOILET TANK DUMP VALVE FOUND AT FAULT. VALVE REPLACED AS PER MM 38-32-31. 2L72 4F4 F A16WE E2EA 20020823001942002082300194SO 2002 8 23 CA020820004 120020805G7160 INTAKE DUCT PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE AIR INTAKE DUCTS / INERTIA SEPERATORS WERE FOUND TO BE CRACKED PRETTY MUCH ALL OVER. PLEASE NOTE THAT THE PAIR OF AIR INTAKE DUCTS IS CRACKED. THEY ARE MADE OF FIBERGLASS. NEW INTAKES WERE ORDERED AND THE ENGINE AND ENGINE MOUNT HAVE BEEN REMOVED TO ALLOW REPLACEMENT. 1L71 3O4 TRTA25SO E4EA 20020830002342002083000234CE 2002 8 30 CA020820007 120020817G2121FN100 COOLING FAN CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL AIR DISTRIBUTIONFAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) AIRCRAFT RETURNED TO BASE DUE TO SMOKE AND ELECTRICAL SMELL IN COCKPIT. ALL AVIONICS EQUIPMENT, WIRING, LIGHTING, RHEOSTATS, INSPECTED SATISFACTORY. FAULT FOUND IN GPS COOLING FAN. THE FAN WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.NO FURTHER EVIDENCE OF SMOKE OR SMELLS IN COCKPIT OCCURRED. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020903000142002090300014SW 2002 9 3 CA020820011 120020819G291027810322511 TUBE FRCHLDSA227 SA227CC 3377522SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL HYD SYSTEM CRACKED W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA 15636 (CAN) SHORTLY AFTER DEPARTURE THE CREW NOTED ILLUMINATION OF THE RT HYDRAULIC LIGHT. A FEW SECONDS LATER THE LEFT HYDRAULIC LIGHT ILLUMINATED FOLLOWED BY A LOSS OF PRESSURE ON THE HYDRAULIC PRESSURE GAUGE. THE AIRCRAFT RETURNED TO BASE AND LANDED UNEVENTFULLY. MAINTENANCE INSPECTION OF THE AIRCRAFT DETERMINED A LEAK IN THE HYDRAULIC PRESSURE LINE BETWEEN THE FIREWALL AND THE RIGHT SHUTOFF VALVE. THE LINE HAD DEVELOPED A CRACK ADJACENT TO THE SLEEVE AT THE FLARED END OF THE RIGID LINE AT THE FIREWALL. THERE WAS NO EVIDENCE OF PREVIOUS CHAFING OR DAMAGE TO THE AFFECTED LINE. THE LINE WAS REPLACED 2L72 4T4 TRTA18SW E4WE 6 CP61GL 20020903000662002090300066CE 2002 9 3 CA020821002 120020821G71209090771S ISOLATION MOUNT BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL ENGINE DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A ROUTINE INSPECTION OF THE RT ENGINE. THE UPPER INBOARD VIBRATION ISOLATOR ENGINE MOUNT WAS FOUND TO BE DEBONDED, THE BACK HALF OF THE RUBBER WAS DEBONDED FROM THE METAL FACE PLATE. THE MOUNT WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A24CE E4EA 5 CSTC 20020903000712002090300071SO 2002 9 3 CA020821006 120020805G7170 BREATHER PIPER PA46 PA46500TP 7104622SO PWA PT6 PT6A42 52043NE ENGINE CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE BREATHER ACCESSORIES DRAIN MANIFOLD FOUND CHAFED THROUGH ABOUT 50 PERCENT OF THE TUBE WALL THICKNESS. BREATHER IS CHAFING ON CIRCUMFERENCE OF THE HOLE IT GOES THROUGH IN THE COWLING. THERE IS NO GROMMET, IT IS JUST A HOLE IN THE ALUMINUM SKIN WITH A TUBE GOING THROUGH IT WITH LITTLE CLEARANCE. THE TUBE IS NOT SUPPORTED AND VIBRATES. 1L71 3O4 TRTA25SO E4EA 20020903000812002090300081NM 2002 9 3 CA020823003 120020814G276165449617 HOUSING BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE SPOILER ACTUATORSPLIT W L ABORTED APPROACH KFJFLUID LOSS FLT CONT AFFECTED WARNING INDICATION APAPPROACH 1 CA (CAN) ON APPROACH CREW REPORTED COMPLETE LOSS OF HYD FLUID FROM 'A' SYS UPON SELECTION OF FLAPS & MLG. CREW CONDUCTED MISSED APPROACH & PROCEEDED TO COMPLETE 'LOSS OF SYS HYDRAULICS NON NORMAL CHECKLIST. CREW PERFORMED VISUAL APPROACH & LANDED A/C WITHOUT INCIDENT. MAINT INSPECTION REVEALED NR 1 OUTBOARD GROUND SPOILER ACTUATOR CASE HAD SPLIT RESULTING IN COMPLETE LOSS OF HYDRAULICS. MAINT ENGINEERS CHANGED ACTUATOR, AND ENGINE DRIVEN HYDRAULIC PUMPS & CHANGED / CHECKED ALL RELATED FILTERS FOR CONTAMINATION. SYS GROUND CHECKED SERVICEABLE & A/C RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020903001382002090300138NM 2002 9 3 CA020826004 120020819G27212828001009 CONTROL UNIT BOEING767 767338 1385151NM GE CF6 CF680C2B6F 30025NE RUDDER TRIM FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT REQUIRES LARGE AMOUNTS OF RIGHT RUDDER TRIM IN ORDER TO FLY STRAIGHT 250 KTS RANGE REQUIRES 2.5 UNITS OF RT RUDDER TRIM. 300 - 325 KTS REQUIRES 3.5 UNITS.BOTH LT INBD AILERON PCUS REPLACED AND RIGGED AS PER AMM 27-11-48 2L72 4F4 FRTA1NM E13NE 20020904000032002090400003EA 2002 9 4 CA020826010 120020822G3270C2UT473 TORQUE TUBE DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE WATER RUDDER CRACKED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) WATER RUDDER (TAIL WHEEL) TORQUE TUBE FOUND TO HAVE A SPIRAL CRACK ENCIRCLING THE VERTICAL PORTION OF THE TUBE. EXTERNALLY THE TUBE ASSEMBLY SHOWED NO MAJOR DEFECTS. INTERNALLY THE TUBE WAS SEVERLY CORRODED AT THE INTERFACE OF THE TUBE JOINT AND THE WELDED SPLINE SHAFT. THE SUBMITTER SUGGESTS THAT A INTERNAL CORROSION PREVENTATIVE COMPOUND BE APPLIED BEFORE THE UNIT IS PUT INTO SERVICE. 1H71 3R3 R A806 5E1 20021021000382002102100038EU 2002 10 21 CA020827002 120020825G79205007T08P01 TUBE AMD FALCONFALCON20 2730103EU GE CF700 CF7002D2 30010NE AFT FAN AREA CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUND AN OIL PRESSURE LINE CRACKED AT THE AFT FAN AREA BY METHOD OF NDT. A COMPANY DECISION IN CONDUCTING AN INSPECTION OF THE OIL PRESSURE LINES AT THE AFT FAN AREA BY METHOD OF NDT WAS INSTRUCTED TO OUR CONTRACTED APPROVED MAINTENANCE ORGANIZATIONS TO COMPLY WITH, ON ALL OUR FALCON 20 S ASAP. ENGINE WAS DISASSEMBLED FOR COMPLIANCE OF A 3000 HOUR HOT SECTION INSPECTION AND A 600 HOUR INSPECTION. THE INSPECTION OF THE OIL PRESSURE LINES ARE PRESSURE TESTED AT THE ENGINE OVERHAUL TIME PERIOD, IN THIS CASE AT EACH 5000 HOUR INTERVAL. PART WAS REPLACED WITH SERVICEABLE NDT'D PART. 2L72 4F4 FRTA7EU E7EA 20021021000392002102100039CE 2002 10 21 CA020827004 120020716G3251508201892 LINKAGE BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA NLG STEERING BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA 1402714027 (CAN) THE STEERING LINK WAS FOUND BROKEN 3/4 OF AN INCH FROM WERE IT ENTERS THE DUST BOOT. THE STEERING LINK WAS REPLACED AND THERE HAS BEEN NO FURTHER OCCURANCES 1L72 3T4 T A14CE E4EA 20020906001582002090600158SW 2002 9 6 CA020827008 120020731G6320206040662101 SUN GEAR BELL 206 206L 1181522SW ALLSN 250C 250C20B 03013GL M/R GEARBOX CRACKED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) CUSTOMER REPORTED TRANSMISSION TO BE MAKING METAL AT 185.1 SINCE OVERHAUL. TRANSMISSION RETURNED TO OUR FACILITY FOR TEARDOWN AND INSPECTION. ON TEARDOWN IT WAS FOUND THAT THE SUN GEAR HAD FAILED. THE SUN GEAR WAS INSTALLED NEW AT THE TIME OF OVERHAUL. 1G71 3U3 U H2SW E4CE 20020904000092002090400009CE 2002 9 4 CA020829002 120020828G2720626023248 CONTROL CABLE CESSNA650 650 2076802CE GARRTTTPE731TFE7313C WP RUDDER FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING PHASE "A" INSPECTION. MAINTENANCE PERSONNEL WHEN THROUGH THE TAIL CONE AREA TO COMPLETE A VISUAL INSPECTION. ON THE LT SIDE OF THE TAIL CONE TECHNICIAN DISCOVERED THE RUDDER LT OUTBOARD CABLE WAS FRAYED BETWEEN THE PULLEY AND THE SAFETY PIN. CABLE REPLACED & RIGGED RUDDER SYSTEM IAW C650 AMM 27-20-00. 2L72 4F4 F A9NM E6WE 20020904000102002090400010CE 2002 9 4 CA020829005 120020804G551007321011 BRACKET CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C* GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT LANDED IN ROUGH WATER, CAUSING THE BATTERY TO CRACK AT THE BATTERY POSTS. A COMPLETE INSPECTION OF THE AIRCRAFT WAS CARRIED OUT, AND THE CRACK IN THE REINFORCEMENT BRACKET WAS DISCOVERED. NO OTHER DEFECTS WERE FOUND. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20020910000182002091000018WP 2002 9 10 CA020829006 120020808G5710 STRUCTURE LKHEED188 188A 5262602WP ALLSN 501D 501D13 03004GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 54373 (CAN) CRACK ALONG EXISTING PATH FOUND. AIRCRAFT RETURNED TO MAINTENANCE BASE. CRACK IS OUTBOARD OF BL-165 19 INCHES 2L74 4T4 TRT4A22 E282 20020910000202002091000020NE 2002 9 10 CA020829008 220020819G7314 COUPLING BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE RT ENG FUEL PUMPWORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE INPUT DRIVE SPLINES OF THE ENGINE HIGH PRESSURE FUEL PUMP WERE FOUND TO BE VERY WORN, AND SLIPPAGE OCCURRED CAUSING FUEL STARVATION. 1L72 4T4 T A24CE E4EA 20020910000222002091000022EA 2002 9 10 CA020829010 220020814G7314RG9080J4A PUMP PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA RT ENGINE FUEL FAILED W D RETURN TO BLOCK YJ ENGINE STOPPAGE WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) WHILE TAXIING FOR TAKEOFF, THE RT ENGINE QUIT AFTER TURNING ON EMERGENCY PUMP. FUEL FLOW GAUGE SPIKED UP ON SECOND TRY AND DID THE SAME. FOUND ENGINE DRIVEN PUMP BYPASSING FUEL THRU AIR SIDE OF FUEL INJECTOR. E/D PUMP REPLACED AND OPERATION NORMAL. 1L72 3O3 O A20SO E14EA 20020910000252002091000025EU 2002 9 10 CA020829014 120020826G2823 SHUTOFF VALVE AIRBUS310 A310300 3930305EU GE CF6 CF680C2A5 NE NR 1 ENGINE FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) IN YQB, HAD TO SHUT NR 1 ENGINE DOWN WITH FIRE HANDLE SINCE MOVING THE HP FUEL LEVER NR 1 TO THE OFF POSITION. CLOSE THE HP FUEL VALVE. MAINTENANCE IN YQB, CHECKED THE FUEL SYSTEM FOR PROPER FUNCTION, IN ACCORDANCE WITH THE AMM 71-00-00, P.534 AND CHECKED SERVICEABLE. THE AIRCRAFT DEPARTED FOR YYZ. MAINTENANCE IN YYZ ALSO REPLACED FOR PRECAUTIONARY REASONS, THE NR 1 HP FUEL SOV SWITCH I.A.W 76-12-11, THE NR 1 ENG. FUEL SHUT OFF RELAY 27 KC I.A.W. THE ELECTRICAL STD. PRACTICE MANUAL 20-46-50 AND THE MAIN ENG. CONTROL I.A.W. THE AMM 73-21-01 P.401 2L72 4F4 FRTA35EU E13NE 20020910000262002091000026WP 2002 9 10 CA020829016 120020826G7830LJ37013 BLOCKER DOOR LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE THRUST REVERSER BENT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUND NR 1 ENGINE THRUST REVERSER BLOCKER DOOR AT THE 8 O`CLOCK POSITION, DAMAGED AND THE TRANSLATING SLEEVE NOT CLOSED PROPERLY (GAP TO LARGE). MAINTENANCE REPLACED THE BLOCKER DOOR I.A.W. AMM 78-31-16 AND THE TRANSLATING COWL RIGGED I.A.W. 78-30-00 P. 516, PARA E. 2L73 4F4 F A23WE E12EU 20020906001602002090600160WP 2002 9 6 CA020829017 120020818G21617638801 CONTROLLER LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE CABIN TEMP FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) THE AIRCRAFT WAS FLYING AND DIVERTED DUE TO NR 2 PACK UNABLE TO CONTROL IN MANUAL MODE WHILE THE AUTO MODE WAS UNDER MEL 21-21-01 CATC. MAINTENANCE REPLACED THE PACK CONTROLLER IAW AMM 21-62-01 2L73 4F4 F A23WE E12EU 20020918000122002091800012GL 2002 9 18 CA020830001 220020815G7323104100A13A8 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ENGINE FAILED W ED ENGINE SHUTDOWN RETURN TO BLOCK W INADEQUATE Q C TXTAXI/GRND HDL 1 CA (CAN) PILOT NOTICED GOVERNOR OVERSPEEDING BEYOND SET LIMITS AND SHUT DOWN ENGINE. 1G71 3U3 U H2SW E4CE 20020918000152002091800015NE 2002 9 18 CA020830004 220020729G8530CH91ER CYLINDER DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE ENGINE CRACKED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) THE AIRCRAFT WAS ON FLOATS MOVING A CAMP FROM ONE LOCATION TO ANOTHER WHEN THE ENGINE STARTED TO RUN VERY ROUGH. THE PILOT SWITCHED FUEL TANKS THINKING THAT IT MIGHT BE WATER AND ADDED CARB HEAT JUST IN CASE IT WAS CARB ICE. WHEN THAT DID NOT HELP HE LANDED ON A LAKE AND CALLED BACK TO BASE. MAINTENANCE STAFF WENT OUT AND FOUND NR 3 CYLINDER WAS CRACKED. CYLINDER WAS CHANGED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3R3 R A815 5E2 20020904000122002090400012CE 2002 9 4 CA020830006 120020802G24360560 SENSOR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL OVER VOLTAGE FAILED W HA DEACTIVATE SYST/CIRCUITSUNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 CA A121706 (CAN) HIGH VOLTAGE LIGHT CAME ON DURING FLIGHT. FLIGHT TERMINATED. OVER VOLTAGE SENSOR FAILED. RESULTED IN DAMAGE TO VOLTAGE REGULATOR AND BATTERY CONTACTOR. ELECTRICAL COMPONENTS REPLACED. 1H71 3O3 ONT3A12 E274 5 NP910 20020910000302002091000030EU 2002 9 10 CA020830010 220020719G853020330160 CYLINDER DHAV DHC2 DHC2MK2 2800106EA WSK PZL PZL3S 67204EU WSK US132 US132000A NE VALVE SEAT CRACKED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) ON A 100 HOUR INSPECTION, NR 2 & 7 CYLINDER HAD VERY LOW COMPRESSION. AFTER REMOVAL OF BOTH CYLINDERS IT WAS NOTICED THAT THE EXHAUST VALVE SEATS WERE CRACKED. THE CYLINDERS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3R3 R A806 E18EU 5 CP4NE 20020910000322002091000032CE 2002 9 10 CA020830012 120020806G3230M710501 MOTOR BEECH B300 B300B350C CE PWA PT6 PT6A60A 52043NE HYD POWERPACK MALFUNCTIONED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) ON FINAL APPROACH, MLG WOULD NOT RESPOND TO SELECTOR LEVER MOVEMENT. MLG SUBSEQUENTLY LOWERED USING EMERGENCY HAND PUMP. UNEVENTFUL LANDING CARRIED OUT. MAINTENANCE DETERMINED MLG MOTOR 60 AMP CIRCUIT BREAKER HAD OPENED. BREAKER IS LOCATED IN LT WING CENTRE SECTION LEADING EDGE. A/C PLACED ON JACKS, BREAKER RESET & GEAR RETRACTION TEST PERFORMED. GEAR RETRACTED NORMALLY & CYCLE COMPLETED WITHIN MAINT MANUAL TIME LIMITS, HOWEVER MOTOR REPLACED ON SUSPICION IT HAD CAUSED BREAKER TO OPEN. REPLACED MOTOR (0 TSO) CYCLED GEAR NOTICEABLY QUICKER & QUIETER THAN ORIGINAL MOTOR. 2L72 4T4 TRTA24CE E4EA 20020910000332002091000033CE 2002 9 10 CA020830013 120020820G781017540071 RISER CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUND CRACK JUST BELOW THE EXHAUST FLANGE WELD. CRACK HAD PROGRESSED HALF WAY AROUND THE BACK OF THE RISER ASSEMBLY. CRACK WAS FOUND DURING A REGULARLY SCHEDULED INSPECTION. CRACK HAD NOT BEEN VISIBLE AT THE PREVIOUS INSPECTION, SO CRACK DID PROGRESS QUITE QUICKLY. RISER ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT, WHILE ORIGINAL WAS SENT IN FOR CORE. 1H71 3O3 ONT3A12 E274 5 NP910 20020918000162002091800016EU 2002 9 18 CA020830014 120020520G79219696 MOTOR SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE OIL COOLER FAN WORN W O OTHER O OTHER LDLANDING 1 CA (CAN) ON SHUTDOWN PILOT HEARD FAN MAKING A DIFFERENT SOUND. ON INSPECTION OF FAN, IT WAS FOUND TO BE LOOSE. INDICATING WORN ARMATURE BEARING JOURNALS. AT THIS TIME A NEW DC MOTOR WAS INSTALLED. ON TEAR DOWN OF MOTOR IT WAS FOUND THAT IT NEEDED 2 NEW BEARING 4 NEW BUSHING 1 ARMATURE - WORN JOURNALS 1G71 3U3 U H9EU E00054EN 20020918000172002091800017CE 2002 9 18 CA020830016 120020809G7120075100123 MOUNT CESSNA180 180A 2072604CE CONT O470 O470K 17026SO MCAULY2A34C 2A34C66 GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 59044 (CAN) ENGINE MOUNT HAD BROKEN TUBE JUST ABOVE FISHMOUTH WELD 11 INCHES BELOW UPPER RT FUSELAGE ATTACH. 1H71 3O3 O 5A6 E273 5 CP3EA 20020910001032002091000103CE 2002 9 10 CA020903005 120020726G323050301008 SWITCH BEECH 100 B100 1152919CE MLG MOTOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) WHILE THE LANDING GEAR WAS BEING STRETCHED, THE LANDING GEAR STAYED DOWN AND THE AIRCRAFT RETURNED TO ITS BASE. SWITCH WAS FOUND BROKEN IN THE CONTROL RELAY IN THE GEAR MOTOR. THE SWITCH WAS REPLACED AND LANDING GEAR RETRACTIONS WERE PERFORMED. 1L72 4T A14CE 20020910001052002091000105CE 2002 9 10 CA020903007 120020830G3242AN37A BOLT CLEVELANDXXX30144 BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA BRAKE ASSY UNDERTORQUED W O OTHER WK INADEQUATE Q C FLUID LOSS LDLANDING 1 CA (CAN) AFTER LANDING, DISCOVERED BRAKE FLUID LEAKING FROM AFT CALIPER AFT PISTON BORE GUIDE BOLT, CAUSED BY BOLT BEING UNDER TORQUED. PISTON BORE GUIDE BOLT TIGHTENED TO 30 INCH POUNDS PER CLEVELAND MM. BRAKE RESEVOIR TOPPED OFF, BRAKES CHECKED SERVICEABLE. ALL GUIDE BOLTS THIS AIRCRAFT 8 TOTAL TORQUE CHECKED AND 5 OTHERS FOUND BELOW SPECIFIED TORQUE. 1L72 3T4 TRT3A20 E4EA 20020918000252002091800025CE 2002 9 18 CA020904001 120020515G5342043200115 SPAR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL STABILIZER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON REMOVAL OF BRACKET TO GAIN ACCESS TO NUT PLATES DISCOVERED THE REINFORCEMENT AND RT SPAR CRACKED ALONG BEND RADIUS UNDER THE BRACKET. CRACKS COULD NOT BE SEEN UNTIL BRACKET WAS REMOVED. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020918000272002091800027EU 2002 9 18 CA020904004 120020826G3246AH43208 WHEEL BAG JETSTMJETSTM3201 1500217EU GARRTTTPE331TPE33110 01514WP ROTOL R333 R333482F12 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE POST FLIGHT INSPECTION, A 6 INCH CRACK WAS NOTED, ALONG WHEEL FLANGE AT TIRE BEAD ATTACHMENT. ON DISASSEMBLE INSPECTION THE CRACK EXTENDING TO 7.51INCH ON THE INSIDE OF WHEEL FLANGE. NO VISIBLE DAMAGE NOTED ON INNER WHEEL HALF MATE. BUT WAS REMOVED AND SENT FOR NDI INSPECITON. 2L72 4T4 TRTA56EU E4WE 6 CP61GL 20020918000282002091800028EU 2002 9 18 CA020904005 120020827G24359408308803 BEARING 5243212142 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILATUS GIVES A 3000 HOUR LIFE TO NR 2 GEN DRIVE OUTER BEARING, BUT NOT TO INNER BEARING. DURING REPLACEMENT OF OUTER BEARING DUE TO T/X, FOUND INNER BEARING UNSERVICEABLE. IT IS NOW OUR POLICY TO REPLACE INNER BEARING AS WELL DURING OUTER BEARING REPLACEMENT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020912000182002091200018NM 2002 9 12 CA020904007 120020904G7500 ISOLATION VALVE BOEING737 737217 1384464NM PWA JT8 JT8D17A 52049NE BLEED SYSTEM MALFUNCTIONED W O OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 CA (CAN) BOTH ENGINE SURGING AT CRUISE, BLEED SURGING FROM 20PSI TO 52 PSI. NR 2 ENGINE SURGING CONSIDERABLY MORE ON DESCENT. 2L72 4F4 F A16WE E2EA 20020918000302002091800030NM 2002 9 18 CA020904009 120020823G27511812993 INDICATOR BOEING727 727225 1384077NM PWA JT8 JT8D15 52051NE TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) DURING APPROACH, PILOT OBSERVED A SPLIT FLAP INDICATION. AIRCRAFT LANDED WITHOUT INCIDENT. FLAP POSITIONING INDICATOR REPLACED AND CHECKED SERVICEABLE IAW MM 27-50-00. 4. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2L73 4F4 F A3WE E2EA 20020918000312002091800031SO 2002 9 18 CA020904010 120020820G57306206102 SKIN PIPER PA28 PA28180 7102808SO LYC O360 O360A4A 41514EA RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WINGS REMOVED FOR INSPECTION AFTER HARD LANDING WITH RT WING REMOVED FORWARD AND AFT WING WALKS UNDER UPPER WING SKINS INSPECTED AND CRACKS FOUND AT END RADIUS OF STAMPED STIFFENER SECTIONS. 1L71 3O3 O 2A13 E286 20020918000322002091800032EA 2002 9 18 CA020904011 220020820G7414M3100 RIVET SLICK 4372 ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA IMPULSE COUPLINGLOOSE W K NONE O OTHER ININSP/MAINT 1 CA 00031603 (CAN) AFTER TWO COMPLETE IMPULSE COUPLING FAILURES WHICH RESULTED IN THE ENGINES BEING REMOVED FOR REPAIR, IT WAS DECIDED THAT AT EVERY 100 HOUR INSPECTION THE LT MAGNETO WOULD BE REMOVED AND THE IMPULSE COUPLING INSPECTED. ON THIS IMPULSE COUPLING ONE PAWL RIVET WAS LOOSE AND COULD BE EASILY ROTATED. THE PAWL GAP WAS NOT BEYOND LIMITS IN ACCORDANCE WITH UNISON 4300/6300 SERIES MAINTENANCE AND OVERHAUL MANUAL L-1363 CHAPTER 3 SECTION 3.3.4B. THE IMPULSE COUPLING WAS REPLACED WITH A NEW ONE. THE 100 HOUR INSPECTION INTERVAL ON THE IMPULSE COUPLINGS WILL BE CONTINUED AS COMMON PRACTICE. 1L71 3O3 O0 A76EU 1E10 20020919000082002091900008EU 2002 9 19 CA020904012 320020828G6114A915B BEARING MUHBR ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA MUHBR MTV MTV9* EU PROP HUB WORN W K NONE O OTHER ININSP/MAINT 1 CA 94277 (CAN) T57006 PROPELLER REMOVED AT SCHEDULED 100 HOUR INSPECTION. DURING ROTATION OF PROP BY HAND AN OBJECT COULD BE HEARD TUMBLING AROUND INSIDE HUB. NOTE THAT JUST PRIOR TO REMOVAL OF THE PROP A REPORT WAS RECEIVED STATING THAT THE PROPELLER WOULD NOT RETAIN ITS SETTING AND WOULD KEEP UP BY 200 - 300 RPM . HUB BLADE BORES WORE ENOUGH FOR GREASE TO LEAK OUT OF PROP. BALL BEARING SEPARATORS WORE AND CAME OUT OF BEARINGS. BALLS WOULD THEN CONTACT EACH OTHER GIVING SOUND OF RATTLING. 1L71 3O3 O0 A76EU 1E10 5 CP24NE 20020918000602002091800060CE 2002 9 18 CA020905008 120020904G3244 TIRE CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL MAIN WHEEL DAMAGED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) AFTER TOWING AIRCRAFT OUT FOR DEPARTURE A BULGE WAS FOUND IN THE TIRE. THE WHEEL ASSEMBLEY WAS REPLACED WITH A OVERHAULED UNIT. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020918000662002091800066NE 2002 9 18 CA020906005 220020829G741445540613 SWITCH NAMER T6 HARVARDMK4 1922828GL PWA R1340 S3H1 52016NE MAGNETO BROKEN W K NONE O OTHER ININSP/MAINT 1 CA NONE (CAN) PILOT DISCOVERED FORWARD COCKPIT MAGNETO CONTROL SPINNING FREELY WITH NO APPARENT CONNECTION TO SWITCH. MAINTENANCE PERSONNEL DISCOVERED THAT INDICATED LEVER MECHANISM FOUND TO BE BROKEN AT WELD. LEVER NO LONGER ABLE TO TURN MAGNETO SWITCH. LEVER REPAIRED BY WELDING, AND RE-INSTALLED. 1L71 3R3 R EXPA1L71E143 20021009000062002100900006EA 2002 10 9 CA020909001 120020905G563085240076001 WINDOW DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE SERVICE DOOR CRACKED W O OTHER O OTHER CRCRUISE 1 CA (CAN) FLIGHT ATTENDANT COULD HEAR AIR LEAK FROM REAR AFT SERVICE DOOR DURING FLT. FOUND WINDOW CRACKED AROUND CIRCUMFERENCE OF WINDOW. BOLTS ALSO FOUND BADLY CORRODED. NEW WINDOW AND HARDWARE INSTALLED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021009000132002100900013EU 2002 10 9 CA020910007 120020909G3251Z4242390000 CONTROL CABLE ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA NLG STEERING BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) ON TAXI THE AIRCRAFT WOULD ONLY TURN IN ONE DIRECTION. IT WAS FOUND THAT THE RT STEERING CABLE HAD BROKEN AT THE FWD END AT THE LOOP AROUND THE BOLT. THE CABLE WAS REPLACED AND THE STEERING SPRING GAP WAS SET. ALL OTHER CABLES ON THE FLEET OF Z242L AIRCRAFT WERE INSPECTED WITH NO DEFECTS FOUND. 1L71 3O3 O0 A76EU 1E10 20021002000022002100200002NM 2002 10 2 CA020912010 120020830G5330 SKIN BOEING BOEING727 72725C 138400HNM PWA JT8 JT8D7B 52053NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 66295 (CAN) CRACK AT AFT CARGO DOOR CUTOUT SKIN, AFT LOWER CORNER AT FASTNER HOLES. 2L73 4F4 F A3WE E2EA 20021009000392002100900039GL 2002 10 9 CA020913006 320020912G611157A2202 BEARING HARTZLHCD4N3HCD4N3A GL PROPELLER BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AFTER TAKING THE PROPELLER APART, IT WAS NOTED THAT NR 2 BLADE THRUST BEARING WAS BROKEN INTO SEVERAL SMALL PIECES. AS A RESULT OF THIS BROKEN BEARING, THERE WAS SOME MINOR DAMAGE TO THE BLADE SHOULDERS. ONE BEARING WAS ALSO FOUND CORRODED ON THE OUTER SURFACE. BOTH OF THESE BEARING RACES WERE REPLACED, AND THE BLADE SHOULDER WAS REPAIRED, CHECKED ON THE OPTICAL COMPARATOR, MEASURED FOR DIMENSIONS, AND COLD ROLLED. THERE WAS ALSO ONE SET OF BEARINGS THAT CONTAINED A LARGE AMOUNT OF RESIDUE MAGNETISM, THIS WAS DEMAGNETIZED, AND REINSTALLED. 5 CSTC 20021009000462002100900046SW 2002 10 9 CA020913009 120020827G571171493 SPAR BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA WING CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CRACK FOUND IN THE FUEL CELL STIFFENER SPAR ON THE WING. 1H71 3O3 O A21CE E286 20021009000532002100900053EA 2002 10 9 CA020913012 120020905G5413C6W1512S141 LONGERON DHAV DHC6 DHC6 2802606EA PWA PT6 PT6A20 52043EA NR 2 NACELLE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 2 ENGINE NACELLE LONGERON CRACKED ON INBOARD SIDE. 1H72 3T3 TRTA9EA E4EA 20021021000442002102100044NE 2002 10 21 CA020916002 220020822G7322A3025U3 CARBURETOR DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE ENGINE FAILED W BA EMER. DESCENT UNSCHED LANDING RY PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CRCRUISE 1 CA (CAN) A/C TOOK OFF WITH A LOAD OF ABOUT 4,500 LBS. POWER ON T/O NORM. CLIMB POWER SELECTED AND A/C CLIMBED TO CRUISE ALTITUDE. A/C CLIMB SLUGGISH. ENG INSTRUMENTS NORM. AT CRUISE A/C SLUGGISH, ENG INSTRUMENTS NORM. AFTER 12 MIN, ENG QUIT W/O WARNING. LANDED ON SMALL LAKE. EMER PROCEDURES C/O & LANDED W/O INCIDENT. ON INVESTIGATION, FUEL SYS INSPECTED FOR CONTAMINATION. NO WATER OR CONTAMINATES FOUND, & SUFFICIENT FUEL TO CARB TO RUN ENGINE. CARB REMOVED & SERVICEABLE INSTALLED, ENG TEST RUN, & NO DEFECTS NOTED. CARB WAS INSTALLED ON THIS A/C HAD ALSO BEEN REPAIRED WITH TTSO/H 297.3 HRS. BEFORE CARB WAS REPAIRED IT WAS REMOVED FROM SERVICE DUE TO A VERY RICH MIXTURE & COULD NOT BE ADJUSTED. 1H71 3R3 R A806 5E1 20021009000622002100900062CE 2002 10 9 CA020916005 120020802G324633924925 WIRE ROPE CESSNA172 172D 2072410CE LYC O360 O360A1A 41514EA TIE RODS BROKEN W CD ABORTED TAKEOFF RETURN TO BLOCK D INFLIGHT SEPARATION TOTAKEOFF 1 CA (CAN) ON TAKEOFF RUN, AT APPROXIMATELY 2 FT OFF THE WATER, A/C SETTLED BACK DOWN DUE TO UNSTABLE AIR. A NOISE WAS HEARD AND THE A/C BECAME VERY UNSTABLE. ABORTED TAKEOFF. AS THE A/C SLOWED DOWN & THE LIFT DISSIPATED, THE LT WING SUDDENLY DIPPED DOWN AND CAME IN CONTACT WITH THE WATER CAUSING THE A/C TO VEIR LT ABRUPTLY, DISPLACING A CONSIDERABLE AMOUNT OF WATER, BUT MANAGE TO KEEP THE A/C FROM INVERTING. CAUSED ALL THE FITTING ON THE END OF THE FLOAT STRUTS TO FAIL. THE FINAL RESTING POSITION OF THE A/C WAS ENGINE POINTING UP, TAIL AND LT WING TIP PARTIALLY SUBMERGE. THE A/C WAS TOWED AND BEACHED. UPON INSPECTION, IT WAS FOUND THAT BOTH CROSS WIRES WERE BROKEN ALLOWING THE WING TO GO DOWN. 1H71 3O3 ONT3A12 E286 20021009000992002100900099EU 2002 10 9 CA020917005 120020911G2710TB1017012000 ROD END SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA RT AILERON BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON A SCHEDULED MAINTENANCE INSPECTION THE RT AILERON SWIVEL ROD END WAS FOUND STIFF. ON FURTHER INSPECTION THE BEARING RACE WAS FOUND BROKEN AND SOME OF THE BALL BEARINGS WERE MISSING. 1L71 3O3 ONTAS1EU E274 20021009001052002100900105EU 2002 10 9 CA020918003 120020915G32513790037108 METERING VALVE AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE NLG STEERING FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 00733 (CAN) AFTER LANDING AND JUST TURNING OFF RUNWAY, UNABLE TO STEER AIRCRAFT USING RUDDER PEDDLES OR TILLER. HYDRAULIC PRESSURE NORMAL. SELECTING RESERVE BRAKE AND STEERING ALSO NO HELP. AIRCRAFT TOWED TO GATE. REPLACED NLG STEERING METERING VALVE AS PER AMM 32-51-04 2L72 4F4 FRTA28NM E29NE 20021002000052002100200005EU 2002 10 2 CA020918005 120020916G2910SC47003 ACTUATOR SAMM AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE HYD SYSTEM FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 1434 (CAN) YELLOW HYDRAULIC SYSTEM LOST FLUID AND CABIN FILLED WITH SMOKE. YELLOW SYSTEM YAW DAMPER ACTUATOR FOUND LEAKING. YAW DAMPER CHANGED AS PER AMM. YAW DAMPER OPERATION CHECK CARRIED OUT AS PER AMM. 2L72 4F4 FRTA28NM E29NE 20021009001402002100900140NE 2002 10 9 CA020918011 220020909G8530358686 CYLINDER HEAD DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE HAMSTD23D 23D40 NE NR 9 CRACKED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) NR 9 CYLINDER HEAD SEPARATED BETWEEN SPARK PLUG HOLES 20 MINUTES AFTER TAKEOFF WHILE IN CRUISE FLIGHT. SERVICEABLE UNIT INSTALLED AND RESUMED FLIGHT. 1H71 3R3 R A815 5E2 6 CP719 20021009001422002100900142SO 2002 10 9 CA020919001 120020901G2120554901 CLAMP PIPER 8124402 PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA AIR DISTRIBUTIONLOOSE W B EMER. DESCENT W INADEQUATE Q C DEDESCENT 1 CA (CAN) DURING DESCENT, THE AIRCRAFT DEPRESSURISED. UPON INSPECTION, THE FORWARD CLAMP ON THE FRESH AIR TUBE WAS FOUND LOOSE AND THE TUBE WAS DISCONNECTED. THE FIBERGLASS ON THE EVAPORATOR BOX WAS THEN REINFORCED AND THE CLAMP REINSTALLED. 1L72 3T4 T A8EA E4EA 20021009001482002100900148EA 2002 10 9 CA020923001 120020801G2997 WIRE CNDAIRCL601 CL6013A 8070802EA GE CF34 CF343A 30015NE HYD POWER SHORTED W O OTHER BH SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA (CAN) DURING PREFLIGHT CHECKS, THE HYDRAULIC PUMPS WERE SELECTED ON AND THE COCKPIT LIGHTING DIMMED.A HEAVY CURRENT LOAD COULD BE HEARD COMING FROM THE GROUND POWER CART.HYD PUMP 3B C/B TRIPPED.TWO ATTEMPTS WERE MADE TO RESET THE C/B, EACH HAVING THE SAME EFFECT AS PREVIOUSLY NOTED BUT WOULD NOT RESET.SMOKE WAS NOTICED COMING FROM THE AVIONICS BAY AND POWER WAS REMOVED FROM THE A/C.INVESTIGATION REVEALED THE MAIN POWER FEED WIRE TO THE 3B HYD PUMP IN THE AVIONIC BAY AROUND STATION 281 HAD SHORTED TO A CLAMP THAT SECURED THAT WIRE BUNDLE 2L72 4F4 FRTA21EA E15NE 20021021000472002102100047EA 2002 10 21 CA020927004 220020924G75109091010017 TUBE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA INTAKE ANTI ICE CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) ENGINE ANTI-ICE INTAKE TUBES REPLACED AS PER BEECH SB 71-3142, WERE FOUND CRACKED (NOT SEPARATED) ATFIRST INSPECTION AFTER SB COMPLIANCE. 1L72 3T4 TRT3A20 E4EA 20021002000072002100200007CE 2002 10 2 CA020930001 120020927G21303001241 SEAL LEAR 35 35LEAR 5170600CE GARRTTTFE731TFE73122B 01518WP BLEED AIR DUCT CRACKED W O OTHER J WARNING INDICATION CRCRUISE 1 CA 17135 (CAN) LT BLEED AIR WARNING CAME ON AT FLIGHT LEVEL 41000. BLEED AIR SHUT-OFF & SWITCH SELECTED IN THE OFF POSITION LIGHT EXTINGUISHED. FOUND LEFT HAND PYLON BLEED AIR DUCT SEALS DRYED AND CRACKED. 2L72 4F4 F A10CE E6WE 20021029000172002102900017EU 2002 10 29 CA020930006 120020929G2170BAS16346416 DUCT 258VF1331 BRAERODH125 BAE125800A 1500285EU GARRTTTFE731TFE7315R 01518WP WATER SEPARATOR LEAKING W A UNSCHED LANDING DJ INFLIGHT SEPARATION WARNING INDICATION CLCLIMB 1 CA (CAN) DUCT FROM WATER SEPERATOR SOCK IN AFT EQUIPMENT BAY DISCONNECTED FROM SEPERATOR. CABIN DEPRESSURIZEDAND AIRCRAFT DECENDED AND RETURNED TO BASE. DUCTS AND CLAMPS WERE INSPECTED AND AFTER RE-INSTALLATION AIRCRAFT WAS RUN TO MAX DIFF ON RAMP USING APU. NO LEAKS NOTED AND AIRCRAFT WAS RETURNED TO SERVICE. 2L72 4F4 FRTA3EU E6WE 20021029000202002102900020CE 2002 10 29 CA021001003 120020930G5753652511585 RIB CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TE FLAPS WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RIB EXTENSIONS ON FLAP ASSY'S ON BOTH LT & RT FLAPS WERE WORN BY THE RIVETS HOLDING THE FLAP TRACKS ON THE WING. THE WEAR WAS AS MUCH AS 50 PERCENT MATERIAL THICKNESS.THESE 4 RIB EXTENSIONS WERE REPLACED. SIMILAR WEAR ON THE INBOARD & OUTBOARD RIB EXTENSIONS WERE WITHIN BLENDABLE LIMITS. 1L72 4F4 F A22CE E1NE 20021021000482002102100048CE 2002 10 21 CA021001006 120020925G304010138402517 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE HARTZLHCD4N3HCD4N3A GL COCKPIT OVERHEATED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) SHORTED AND OVERHEAT CONDITION ON LT WINDSHIELD GROUND TERMINAL CAUSING A HEAVY SMELL OF BURNED PLEXIGLASS TYPE OF ODOUR. PILOTS SWITCHED OFF LT WINDSHIELD ANTI-ICE AND SMOLDERING SUBSIDED. 1L72 4T4 T A24CE E4EA 5 CSTC 20021021000492002102100049CE 2002 10 21 CA021001007 120020930G3211664130667 BUSHING CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MLG CORRODED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) DURING PHASE 5 INSPECTION CORROSION WAS NOTICED AROUND THE TRUNNION INNER PINS.AFTER MUCH DIFFICULTY THE PINS WERE REMOVED AND CORROSION WAS FOUND ON THE INSIDE OF THE BUSHINGS,SEIZING THE PINS. THE PINS ARE STACKED TO THE TRUNNION AND BUSHING WITH ROLL PINS. THE GEAR IS REQUIRED TO BE REMOVED AT 25800 LANDINGS, BUT, THERE IS NO REQUIREMENT TO REMOVE AND INSPECT THE PINS. 1L72 4F4 F A22CE E1NE 20021021000512002102100051CE 2002 10 21 CA021001009 120020930G2497 TERMINAL BEECH 99 99 1154002CE PWA PT6 PT6A20 52043EA CIRCUIT BREAKER LOOSE W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA (CAN) ON DESCENT INTO FORT SMITH FROM FORT CHIPEWYAN, THE CREW NOTICED AN ELECTRICAL SMELL, FOLLOWED SHORTLY BY SMOKE.ALL ELECTRICAL POWER WAS TURNED OFF.ALL NON ESSENTIAL FUNCTIONS WERE TURNED OFF THEN POWER WAS TURNED BACK ON. THE SMELL REAPPEARED.POWER WAS RESTORED LONG ENOUGH TO LOWER GEAR AND MAKE RADIO CALLS THEN TURNED OFF FOR LANDING. ON INSPECTION, THE WIRE ATTACHED TO THE POWER SIDE OF THE WING DEICE LIGHT CIRCUIT BREAKER WAS LOOSE.THE BAD CONNECTION WAS CAUSING THE WIRE TO HEAT UP NEAR THE TERMINAL. 1L72 3T3 T A14CE E4EA 20021021000522002102100052SW 2002 10 21 CA021001012 120020925G2497J340 CONNECTOR SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP GCU PANEL CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE GCU PANEL CONNECTOR WIRES IN THE LT NACELLE WERE FOUND CHAFED APPROXIMATELY 1 INCH FROM THE CONNECTOR. SEVERAL WIRES HAD BEEN CHAFED BY A TOOL USED TO LOOSEN THE HYDRAULIC FILLER CAP WHICH IS LOCATED JUST FORWARD OF THE CONNECTOR. THE WIRES ARE PROTECTED IN THAT AREA WITH NYLON SPIRAL WRAP BUT BECAUSE OF THE SHALLOW ANGLE TO THE CONNECTOR THE TOOL COULD PENETRATE THE WRAP WHICH COULD THEN SPRING BACK AND COVER THE DAMAGE MAKING IT DIFFICULT TO NOTICE. 2L72 4T4 TRTA8SW E4WE 20021021000542002102100054WP 2002 10 21 CA021001013 120020926G351040193733 HOSE LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE OXYGEN SYSTEM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE 'MEDIUM PRESSURE OXYGEN HOSE ASSY AT THE OXYGEN CYLINDER HOOKUP PANEL, WAS FOUND TO DAMAGED. THIS FLEXIBLE BRAID LINE WAS FRAYED AT THE PANEL CONNECTION AND THE FLEXIBLE LINE INSIDE WAS CRACKED.9 OF THOSE LINES WERE ORDERED AOG. ALSO, FOR PRECAUTIONARY REASONS, THE 'LOW PRESSURE OXYGEN HOSES ASSY THAT CONNECTS TO THE CREW OXY. AND MICROPHONE SERVICE PANEL' WERE ALSO ORDERED AOG (9 LINES). A SPECIAL INSPECTION 1-35-003 REV 00, WAS RAISED FOR A FLEET CAMPAIGN INSPECTION. 2L73 4F4 F A23WE E12EU 20021021000562002102100056CE 2002 10 21 CA021002001 120020930G5312641201534 BULKHEAD CESSNA CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE FUSELAGE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHERE THE ELEVATOR TRIM CABLES PASS THROUGH THE CANTED BULKHEAD, THE RT CABLE WAS FOUND WEARING INTO THE LOWER CORNER OF THE HOLE & THE LT CABLE WAS JUST CLEAR BY ABOUT .020 INCH. 1L72 4F4 F A22CE E1NE 20021029000242002102900024WP 2002 10 29 CA021002008 120020825G7910369A8322 SEAL HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ENGINE OIL WAS DETECTED COMING THROUGH THE UPPER AFT RT INTERIOR PANEL AND GRAVITY LEAKAGE DOWN TO THE AIRCRAFT FLOOR. CONDITION ONLY EXISTED UNDER STEEP RT TURNS OF THE HELICOPTER. A/C RETURNED TO BASE AND UPON INVESTIGATION OF THIS SITUATION IT WAS DETERMINED THAT THE RUBBER OIL SEAL FROM THE ENGINE OIL FILLER SUPPORT TO ENGINE OIL TANK DEVELOPED A HOLE UNDER THE CLAMP AT THE TANK LOCATION. OIL TANK IS LOCATED AT THE UPPER RT (AFT FACING FORWARD) OF THE HELICOPTER. THAT EXPLAINED THE AREA OF LEAKAGE IN QUESTION. NEW SEAL WAS INSTALLED ANDTHE AIRCRAFT WAS GROUND RUN AND FLOWN WITH NO FURTHER LEAKAGE. DEFECT ENTRY WAS COMPLETED AS PER COMPANY MCM AND UNDER CARS 605.06 AND RECTIFIED PRIOR TO NEXT FLIGHT. 1G71 3U3 U H3WE E4CE 20021021001292002102100129SO 2002 10 21 CA021002011 120020826G5280 STRUCTURE PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA MLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14253 (CAN) LT OUTBOARD GEAR DOOR HAD A SMALL CRACK FRONT AND BACK OVER THE HINGE TO THE GEAR LEG. RT OUTBOARD GEAR DOOR HAD A SMALL CRACK FRONT OVER THE HINGE TO THE GEAR LEG. 1L72 3O3 O A20SO E14EA 20021021001302002102100130SO 2002 10 21 CA021002012 120020826G52804040522 RIB PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA MLG DOOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14253 (CAN) ON INSPECTION IT WAS NOTICED THAT WHERE THE OUTBOARD DOOR HINGE ATTACH TO THE OUTBOARD RIB, THE RIB WAS CRACKED. THE RIB WAS REPAIRED AND DOOR REINSTALLED. IF LEFT LONGER THE DOOR COULD HAVE JAM IN THE WHEEL WELL. 1L72 3O3 O A20SO E14EA 20021021001312002102100131SO 2002 10 21 CA021002013 120020826G57304472303 SKIN PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 14253 (CAN) ON INSPECTION IT WAS NOTICED THAT WHERE THE RT MAIN GEAR PUSHES TO THE UP POSITION, THE RIB HOLDING THE WHEEL STOP WAS CRACKED AND THE WING SKIN HOLDING THE RIB WAS ALSO CRACKED FROM THE MANY CYCLES. 1L72 3O3 O A20SO E14EA 20021021001322002102100132SO 2002 10 21 CA021002014 120020422G3232756265 SPRING OZONE O14529243 PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA DOOR ACTUATOR BROKEN W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) INBOARD GEAR DOOR OPENED IN FLIGHT AND AFTER LANDING WHEN MASTER WAS CLOSE OFF. THE DOOR CAME OPEN. THE SPRING IN THE DOOR ACTUATOR THAT PUSHES THE BALL LOCK WAS FOUND BROKEN. 1L72 3O3 O A20SO E14EA 20021021001332002102100133CE 2002 10 21 CA021002015 120020829G3260A4503M95 SWITCH BEECH 90 C90 1152913CE PWA PT6 PT6A28 EA MLG FAILED W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) THE HANDLE WOULD NOT WORK IN THE DOWN POSITION UNLESS THE HANDLE WAS TAPPED. A NEWLY OVERHAULED LANDING GEAR CONTROL WAS INSTALLED. IT WORKED FOR 229.5 HOURS AND 216 CYCLES BEFORE FAILING THE SAME WAY. AFTER REMOVING THE HANDLE THE DOWN SWITCH WAS NOT WORKING. THIS IS THE THIRD CONTROL WITH THE SAME PROBLEM IN 10 MONTHS 450 HOUR OF FLYING. 1L72 3T4 T 3A20 E4EA 20021021001342002102100134EU 2002 10 21 CA021003002 120020913G3242 LINER CLEVELAND 03024400 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BRAKE ASSY WORN W K NONE O OTHER ININSP/MAINT 1 CA 1122 (CAN) DURING INSPECTION FOUND 10 PERCENT OF BRAKE LININGS WORN BEYOND LIMITS STATED IN CLEVELAND BRAKE MANUAL. EVEN THOUGH LININGS ARE WORN OUT WEAR INDICATORS SHOW BRAKE ASSEMBLY AT HALF LIFE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021021001352002102100135EU 2002 10 21 CA021003003 120020913G32440213500 TIRE 0213500 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 1287W00244 (CAN) TIRE RUN FOR 46.0 HOURS TIRE WOULD LEAK 25 PERCENT PER DAY. TIRE LEAKS THROUGH SIDE WALL VENTS. THIS IS SECOND TIRE THIS WEEK TO DO THIS. SECOND TIRE HAD 413 HOURS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021021001362002102100136EU 2002 10 21 CA021003004 120020923G27409742001212 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL HORIZONTAL STAB FAILED W H DEACTIVATE SYST/CIRCUITS I FLT. ATTITUDE INST. APAPPROACH 1 CA (CAN) FLIGHT CREW EXPERIENCED UNCOMMANDED UP TRIM ON HORIZONTAL STAB TRIM. SYSTEM WAS DEACTIVATED USING TRIM INTERRUPT SWITCH, AND AIRCRAFT LANDED USING ACT. STAB TRIM. ON INVESTIGATION FAULTY RELAY FOUND (K22) RELAY REPLACED AND SYSTEM TESTED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021021001372002102100137EA 2002 10 21 CA021004006 220020924G75109091009913 TUBE BEECH 9091009913 BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA INTAKE ANTI ICE CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) ENGINE ANTI-ICE (INTAKE) TUBES REPLACED AS PER SB 71-3142 (BEECH) - NEW TUBES FOUND CRACKED (NOT SEPARATED) AT FIRST INSPECTION AFTER SB COMPLIANCE. 1L72 3T4 TRT3A20 E4EA 20021021001382002102100138CE 2002 10 21 CA021004007 120020915G3260S20881 DOWNLOCK SWITCH CESSNA337 337F 2075725CE CONT O360 IO360C 17025SO MCAULY2AF34CD2AF34C301 GL MLG BROKEN W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA (CAN) ONE WIRE THAT ATTACHES TO THE LT MLG DOWNLOCK SWITCH FRACTURED CAUSING NO 'GREEN' DOWN GEAR LIGHT TO ILLUMINATE AFTER GEAR WAS SELECTED DOWN. THE WIRES THAT ATTACH TO THE SWITCH ARE PERMANENTLY MOULDED AND APPROXIMATELY 18 GAUGE WHICH ARE QUITE THIN FOR THE APPLICATION. 1H72 3O3 O A6CE E1CE 5 CP5EA 20021021001392002102100139CE 2002 10 21 CA021004008 120021003G2842774000068 TRANSMITTER CESSNA185 A185E 2072818CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL FUEL QTY FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AT 1/4 FUEL LEVEL TRANSMITTER READS 7/8. NOTE: PROBLEM ONLY EXISTS WHEN TRANSMITTER IS IN FUEL. BENCH CHECK IN DRY CONDITION INDICATES CESSNA RESISTANCE SPEC'S AS NORMAL. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20021029001262002102900126EA 2002 10 29 CA021004009 220020916G8500TIO540J2BD ENGINE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) AFTER TAKEOFF PILOT REDUCED POWER TO CLIMB, NOTED UNUSUALLY LOW OIL PRESSURE, AFTER FURTHER REDUCINGPOWER TO CRUISE SETTING OIL PRESSURE STABILIZED AT BOTTOM OF GREEN ARC. PILOT COMPLETED FLIGHT (10M MINS) TO BASE. OIL TEMPS & CYLINDER HEAD TEMPS NORMAL. ENGINEER INSPECTED OIL PRESSURE RELIEF VALVE FOR FOD. FOUND SMALL METAL FOD UNDER SEAT. REMOVED & INSPECTED OIL FILTER, REVEALED METAL TRACES ABOVE NORMAL CONCENTRATIONS. ENGINE REMOVED FROM AIRFRAMES TO BE INSPECTED BY O/H FACILITY. 1L72 3O3 O A20SO E14EA 20021021001402002102100140SO 2002 10 21 CA021007003 120020930G55124015514 SKIN PIPER PA31 PA31 7103102SO LYC O540 TIO540J2BD 41532EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LEFT HORIZONTAL STABILIZER LEADING EDGE SKIN CRACKED APPROXIMATELY 13 INCHES. 1L72 3O3 O A20SO E14EA 20021021001422002102100142GL 2002 10 21 CA021007004 220020920G731068756320 LINE BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUEL SYSTEM CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AIRCRAFT LANDED NORMAL SHUTDOWN. FUEL WAS NOTICED DRIPPING FROM ENGINE PAN DRAIN. BOOST PUMPS TURNED ON TO CHECK FOR STATIC LEAKS. FOUND SUBJECT LINE DRIPPING FUEL AROUND 'B' NUT. NUT WAS CHECKED AND WAS TIGHT. LINE WAS REMOVED AND INSPECTED AND A CRACK WAS FOUND. CRACK RUNS ABOUT 1/3 OF THE CIRCUMFERENCE OF THE STEEL TUBE AT THE BASE OF THE FLARE. 1G71 3U3 U H2SW E4CE 20021021001432002102100143SW 2002 10 21 CA021007005 120020909G2810714931L FUEL TANK BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA CENTER CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CRACK IN LT INBOARD FUEL TANK UPPER SURFACE AT OUTBOARD END OF CENTER PREFORMED STIFFENER. - IN ALUMINUM SPAR WINGS. 1H71 3O3 O A21CE E286 20021021001472002102100147SO 2002 10 21 CA021007014 120020913G54107847502 RIB PIPER PA34 PA34200 7103405SO LYC O360 IO360C1E6 41514EA NACELLE DAMAGED W O OTHER O OTHER CLCLIMB 1 CA (CAN) PILOT ON A RETURN FLIGHT HOME EXPERIENCED A SLOWER THAN NORMAL LANDING GEAR RETRACTION. A VISUAL INSPECTION WAS CARRIED OUT. INSPECTION OF THE LEFT MAIN GEAR AREA REVEALED TWO RIB ASSEMBLIES DAMAGED. THEY WERE LOCATED ADJACENT TO EACH SIDE OF THE GEAR LEG, AT STATION 49.25 AND 69.24. THE AIRCRAFT WAS REMOVED FROM SERVICE. DURING THE GEAR REMOVAL, THE SUPPORT FITTING (AFT) WAS FOUND CRACKED AT THE LOWER OUTBOARD BOLT HOLE. PART NUMBER FOR THE RIB ASSEMBLIES WERE 78475-04 AND 78500-02. SUPPORT FITTING NUMBER WAS 67042-012. AIRCRAFT AIRFRAME HOURS WERE 7138.6. THE AIRCRAFT WAS TWO HOURS AWAY FROM A SCHEDULED 50 HOUR INSPECTION. THE RIB ASSEMBLIES AND SUPPORT FITTING REPLACEMENT WAS CARRIED OUT, AND LANDIN1L72 3O3 O A7SO 1E10 20021021001612002102100161NM 2002 10 21 CA021008004 120020930G27521502371 PIN BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA LT FLAP ACTUATOROUT OF POSITION W K NONE F FLT CONT AFFECTED ININSP/MAINT 1 CA (CAN) THE FLAP DRIVE CAUTION LIGHT ILLUMINATED DURING PUSHBACK. FLAPS DRIVE OK FROM 5 DEGREES, TO 35, EXTENDING.FLAP DRIVE LIGHT ILLUMINATED AGAIN, WHEN FLAPS WE RERAISED FROM 35 TO 5 DEGREES. FCU WAS RESET AND THE A/C FERRIED TO HOME BASE. MECHANICS FOUND ACCESS PANEL WAS FOUND DAMAGED, THE LT INBOARD FLAP TRAILING EDGE IS DAMAGED, DELAMINATED. THE MECHANICS ALSO FOUND PIN OUT OF POSITION, FROM THE OUTBOARD ACTUATOR. 2H72 4T4 TRTA13NM E00062EN 20021021001632002102100163NM 2002 10 21 CA021009022 120020620G3260464505 DOWNLOCK SENSOR BOMBDRDHC8 DHC8400 NM PWC 150 PW150A EA RT MLG FAILED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) LANDING GEAR FAILURE-LIGHT IN GEAR HANDLE CAME ON 4-5 TIMES INTERMITTENTLY DURING FLIGHT. THE PROBLEM WAS RECORDED 5 TIMES IN THE LAST 6 DAYS. WE EXTENDED THE GEARS IN GOOD TIME AND GOT NORMAL DOWN AND LOCKED INDICATION.1 MIN LATER WE GOT LIGHT IN GEAR HANDLE,RED, GREEN AND YELLOW ALTERNATING.ALTERNATE GEAR EXTENSION PROCEDURE USED. INVESTIGATION/ACTION FAULT CODES FROM PSEU - CODE RGDLKL FAULT PROX SENS OPEN FOUND . RH GEAR DOWNLOCK NR 1 SENSOR AND HARNESS ASSY REPLACED. AT FURTHER INVESTIGATION OF THE SENSOR AND HARNESS ASSY THE WIRES JUST BEHIND THESENSOR WAS FOUND OPEN WHEN MANIPULATING. 2H72 4T4 TRTA13NM E00062EN 20021029001422002102900142EA 2002 10 29 CA021009023 220021006G7322105009N TUBE CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA CARBURETOR SEPARATED W O OTHER E VIBRATION/BUFFET APAPPROACH 1 CA (CAN) INJECTION TUBE IN CARB BROKE LOOSE IN FLIGHT AND JAMED THROTTLE IN 2400 RPM RANGE. AIRCRAFT LANDED AT HIGH RATE OF SPEED AND MAIN TIRES WHERE BLOWN ON ROLL OUT. 1H71 3O3 ONT3A12 E274 20021029001432002102900143CE 2002 10 29 CA021009026 120021002G793183278 PRESSURE SWITCH CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE OIL FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILOT NOTICED LOW OIL PRESSURE LIGHT AND HOBBS METER HAD STOPPED. INVESTIGATION REVEALED THAT SWITCHP/N 83278 HAD FAILED INTERNALLY ALLOWING OIL TO COME UP THROUGH THE SWITCH AND CONNECTOR. 1H71 3O3 ONT3A12 1E10 20021029001442002102900144SO 2002 10 29 CA021009027 220021009G8550HD4C2 DRAIN LINE CESSNA207 207A 2073604CE CONT O520 IO520F 17032SO ENGINE FAILED W D RETURN TO BLOCK K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) OIL DRAIN PLUG FROM ENGINE O-RING WEARS OUT. METAL RUBBED AGAINST METAL UNTIL COLLAR WEARS OFF. THEN CENTER PIECE FELL OUT LEAVING A 1/2 INCH HOLE FOR THE OIL TO DRAIN. (IN FLIGHT). THIS DRAIN VARIES FROM ENGINE TO ENGINE TYPE. 1H71 3O3 O A16CE E5CE 20021022000072002102200007CE 2002 10 22 CA021010003 120020927G712005510171 MOUNT CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 10834 (CAN) ENGINE MOUNT ASSEMBLY CRACKED AT LOWER CROSS MEMBER RT SIDE. 1H71 3O3 ONT3A12 E274 5 NP910 20021030000052002103000005EA 2002 10 30 CA021010004 220020926G7414M3163 IMPULSE COUPLINGSLICK 4371 CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MAGNETO CRACKED W O OTHER R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA 00041882 (CAN) OUR MAINTENANCE SCHEDULE APPROVAL FOR 172R CALLS FOR MAG OVERHAUL AT 700 HOURS +/- 10 HOURS. AT 657.9 HR MAGS WERE CHANGED FOR ROUGH ENGINE (2-3 SEC) SNAG. AT OVERHAUL MAG IMPULSE COUPLINGS FOUND CRACKED AT HUB. 1H71 3O3 ONT3A12 1E10 20021022000082002102200008CE 2002 10 22 CA021010007 120020928G21107468331 SWITCH HAMSTD 73844315 CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP HARTZLHCB3T HCB3TN5 GL ACM SHORTED W BH EMER. DESCENT DEACTIVATE SYST/CIRCUITS BMJSMOKE/FUMES/ODORS/SPARKS OVER TEMP WARNING INDICATION CRCRUISE 1 CA 50797 (CAN) THERMAL SWITCH FAILED ON ACM COMPRESSOR DISCHARGE CAUSING AN AUTOMATIC SHUTOFF OF BOTH BLEED AIR TO AIR CYCLE MACHINE. EMERGENCY PRESSURIZATION AUTOMATICALLY TURN ON WITH ANNUNCIATOR LIGHT ON PANEL.HOT AIR FROM BLEED AIR AND SMOKE FROM DUST IN DUCT CAME INTO THE CABIN, THE PILOT DID AN EMERGENCY DESCENT AND SHUT THE EMERGENCY BLEED AIR AT SAFE ALTITUDE. THE SMOKE CLEARED AT ABOUT 5000'. SAFE LANDING WITH ANNUNCIATOR FOR EMERGENCY BLEED LIGHT STILL ON. ACM AND THERMAL SWITCH REPLACED. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20021030000072002103000007SO 2002 10 30 CA021010009 120020926G32318626305 BRACKET PIPER PA44 PA44180 7104402SO MLG DOOR BROKEN W O OTHER R PARTIAL RPM/PWR LOSS APAPPROACH 1 CA (CAN) NOSE GEAR RECYCLE FOUR TIMES BEFORE FULLY EXTENDED. NOSE GEAR INSPECTED AND FOUND RIGHT GEAR DOOR LINK ATTACHMENT BRACKET BROKEN. THE BROKEN BRACKET WAS STOPPING THE NOSE FROM GOING DOWN TO LOCK POSITION. 1L72 3O A19S0 20021028000782002102800078EA 2002 10 28 CA021015009 120021015G323282970014011 CASE DHAV DHC8 DHC8311 1386006EA PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE MLG DOOR ACT CRACKED W O OTHER KJ FLUID LOSS WARNING INDICATION APAPPROACH 1 CA 27316 (CAN) ON APPRAOCH, THE PILOT NOTED A NR 2 HYDRAULIC ISO VLV CAUTION LT. AND NR 2 HYDRAULIC QUANTITY REDUCED TO APPROXIMATELY 1 QUART. MAINTENANCE FOUND LT MLG REAR AND CENTER DOOR ACTUATOR HOUSING (CASTING) CRACKED NEAR THE UPPER ATTACHMENT FITTING. THE DOOR ACTUATOR WAS REPLACED AND ALL FURTHER CHECKS COMPLETED PRIOR TO RELEASE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20021030000142002103000014CE 2002 10 30 CA021015010 120021013G5740817841432SPS12 BOLT BEECH 100 B100 1152919CE WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OF WING AND BOLTS, IN CONJUNCTION WITH AD. DYE PENETRANT INSPECTION FOUND CRACK IN LOWER FORWARD LT WINGBOLT. CRACK FOUND ON BOLT SHAFT/FLANGE AREA. NO OTHER CRACKS FOUND DURING INSPECTION. BOLT REPLACED. ORIGINAL FAILED BOLT INSTALLED AUG. 1ST, 1996. TIME ON A/C 6776.0, CYCLES 5362. BOLT WAS INSPECTED ON A YEARLY BASIS. WITH NO CRACKS DETECTED PREVIOUS. 1L72 4T A14CE 20021030000242002103000024EU 2002 10 30 CA021016014 120020623G80129550147560 VALVE SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE STARTER FAILED W O OTHER YJ ENGINE STOPPAGE WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) ENGINE FAILED TO START. MAXIMUM NG ATTAINED - 40 PERCENT. START ELECTROVALVE REPLACED WITH AIRWORTHY PART, START CORRECT. 1G71 3U3 UNCH9EU E19EU 20021030000292002103000029NE 2002 10 30 CA021016019 220020716G7412ABG6766000 EXCITER SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) ENGINE START REVEALED REDUCED IGNITOR SPARKING. ONE HIGH ENERGY GENERATOR FOUND FAULTY, REMOVED UNSERVICEABLE. NEW PART INSTALLED. 1G71 3U3 U H9EU E19EU 20021030000302002103000030EU 2002 10 30 CA021016020 120020605G77140177555170 TACH GENERATOR SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE FAILED W O OTHER E VIBRATION/BUFFET TXTAXI/GRND HDL 1 CA (CAN) FAILURE OF THE TACH BOX CAUSED THE BLEED VALVE TO CLOSE ON ENGINE START-UP, STALLING THE COMPRESSOR.START WAS ABORTED. PART REPLACED WITH AIRWORTHY TACH BOX. 1G71 3U3 U H9EU E19EU 20021106001892002110600189CE 2002 11 6 CA021016030 120021008G3242AN4H214 BOLT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL BRAKE CALIPER BROKEN W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) UPON COMMENCING TAXI, BRAKES WERE TESTED BY PILOT AS PER CHECKLIST, AND CALIPER ASSEMBLY BOLTS FAILED AND ALLOWED PISTON TO OVER EXTEND AND CAUSE LOSS OF FLUID. BOLTS APPEAR TO HAVE BEEN FRACTURED FOURSOME TIME, DUE EITHER TO FATIGUE OR OVERTORQUING. BOLT MANUFACTURER UNKNOWN, BUT HEAD HAS SYMBOL. C-X-S 1H71 3O3 ONT3A12 E274 5 NP910 20021205000602002120500060CE 2002 12 5 CA021022004 120021022G2434 FAN FORD DOFF10300F CESSNA150 150M 2071830CE CONT O200 O200A 17020SO ALTERNATOR FRONTBROKEN W K NONE D INFLIGHT SEPARATION ININSP/MAINT 1 CA A150894 (CAN) ON VISUAL INSPECTION NOTICED COOLING FAN'S FINS BROKEN AND METAL STIFFENER BROKEN IN HALF, INSIDE THE ALTERNATOR CASE. 1H71 3O3 O 3A19 E252 20021205000612002120500061CE 2002 12 5 CA021022005 120020903G8011 STARTER CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE STUCK W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT. AFTER SENDING THE UNIT TO LAMAR FOR WARRANTY CONSIDERATION, AND TO DISCOVER WHAT WAS ACCTUALLY WRONG WITH THE UNIT, WE WERE INFORMED THE THE WARRANTY WILL NOT BE HONOURED. LAMAR DESCRIBED THAT THE UNIT WAS UN-ECONOMICAL TO REPAIR. THE UNIT HAD APPERENTLY BEEN OVERHEATED (AMATURE FAILURE.) THE STARTER WAS SUBJECTED TO 'IMPROPER STARTING TECHNIQUE. 1H71 3O3 ONT3A12 1E10 20021205000622002120500062CE 2002 12 5 CA021022007 120020924G8011PM2401 STARTER CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ENGINE SHORTED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILOT REPORTED DURING PRE-TAKE-OFF RUN-UP: 'OVERCHARGING DURING RUN UP, COMPLETE ELECTRICAL MALFUNCTION 30 SEC. THEN COMPLETE ELECTRICAL FAILURE BURNING SMELL (PALASTIC RUBBER). CYCLED MASTER NO EFFECT, SHUTDOWN.' STARTER FOUND BURNED UP AND SHORTED, STARTER REPLACED WITH NEW. ALSO ALTERNATOR WAS FOUND TO BE UN-SERVICEABLE. IT WAS CONCLUDED THAT THE STARTER HAD SHORTED DURING THE STARTING PROCESS, AND THE STARTER CONTACTOR WAS TEMPORARILY FUSED (STUCK CLOSED). THE ALTERNATOR ATTEMPTED TO RUN THE ELECTRICAL SYSTEM WITH STARTER SOLOENOID TEMPORARILY ENGAGED AND THE SHORTED STARTER IN THE CIRCUIT. THE AMMETER SHOWED A HEAVY DRAW AND THE ALTERNATOR EVENTUALLY QUIT. THE BATTERY ALSO SUFFERED SOME DAMAGE. 1H71 3O3 ONT3A12 1E10 20021205000632002120500063CE 2002 12 5 CA021022008 120021022G8011 STARTER CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STARTER NOT ENGAGING. STARTER REPLACED WITH SERVICEABLE UNIT. 1H71 3O3 ONT3A12 1E10 20021114000792002111400079NE 2002 11 14 CA021028008 220021027G8500 ENGINE GRUMAVG21 G21 3951202SO PWA R985 R985AN14B 52008NE NACELLE MAKING METAL W K NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 CA (CAN) PILOT NOTICED ENGINE RUNNING ROUGH ON LAST FLIGHT. PROCEEDED TO DO PERFORMANCE RUNS ON GROUND AND FOUND ENGINE WOULD NOT DEVELOP POWER. MAINTENANCE PULLED OIL SCREENS AND FOUND SEVERE METAL CONTAMINATION IN SUMP. CAUSE UNKNOWN AT THIS POINT. 1H72 3R3 R TC654 5E1 20021202001812002120200181EA 2002 12 2 CA021029012 120021024G5610 WINDSHIELD 60R330339 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE OUTER PANE CRACKED W K NONE O OTHER DEDESCENT 1 CA 99078H2836 (CAN) WHILE IN FLIGHT OUTER PANE OF L/H WINDSHIELD CRACKED. WINDSHIELD REPLACED. 2L72 4F4 FRTA21EA E15NE 20021206000082002120600008CE 2002 12 6 CA021030001 120021010G781017540071 RISER CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA EXHAUST CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) EXHAUST PORT MATING FLANGE ON RISER CRACKED THROUGH FLANGE AND ALONG LOWER EDGE OF WELD 5/8 OF CIRCUMFERENCE. REPLACED RISER ASSEMBLY. 1H71 3O3 ONT3A12 E274 20021206000132002120600013CE 2002 12 6 CA021031002 120021017G555104320049 BRACKET CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION OF STABILIZER BRACKET NUTPLATES AS PER AD 80-11-04, IT WAS NOTED THAT STEEL BRACKET ITSELF WAS CRACKED. AT REMOVAL, BOTH LEFT AND RIGHT TOP SIDES WERE CRACKED. THE FIN BOLTS TO THIS BRACKET, SO THE CRACKING COULD BE A RESULT OF STRESS ON THE FIN TO BRACKET ATTACH POINT DUE TO SPIN TRAINING. THIS IS THE SECOND BRACKET IN OUR FLEET OF 7 152'S TO BE FOUND CRACKED. 1H71 3O3 ONT3A19 E223 20021206000142002120600014SW 2002 12 6 CA021031004 120021022G2810714931R FUEL TANK BBAVIA8 8GCBC 1220803SW LYC O360 O360C2A 41514EA WING CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) ALUMINUM SPAR WINGS.- CRACK LOCATION ON WELD OF PREVIOUS REPAIR. 1H71 3O3 O A21CE E286 20021206000152002120600015SW 2002 12 6 CA021031005 120021023G272012364 CONTROL CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA RUDDER CONTROL FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT & RT RUDDER CABLES FRAYED AT PULLEYS - MINIMAL DEFLECTION AT PULLEY. - UNSURE AS TO WHY THEY ARE FRAYED. - REPLACING STAINLESS CABLES WITH GALVINIZED. 1H71 3O3 O A21CE E286 20021206000162002120600016SW 2002 12 6 CA021031006 120021022G275019023 CONTROL CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA WING FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABLE FRAYED AT WING ROOT ALUMINUM PULLEY.- NEW CABLE FABRICATED WITH GALVINIZED. - OLD CABLE WAS STAINLESS STEEL. 1H71 3O3 O A21CE E286 20021206000172002120600017SW 2002 12 6 CA021031007 120021022G272012364 CONTROL CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA RUDDER CONTROL FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT & RT RUDDER CABLES FRAYED AT PULLEY. MINIMAL DEFLECTION AT PULLEY. THEREFORE UNSURE AS TO WHY THEY ARE FRAYED. - REPLACING STAINLESS CABLES WITH GALVINIZED. 1H71 3O3 O A21CE E286 20021206000192002120600019SO 2002 12 6 CA021101002 120021018G571278500002 RIB PIPER PA34 PA34200 7103405SO LYC O360 LIO360C1E6 41515EA LT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING A SCHEDULED 1000 HOUR INSPECTION, THE RIB HAS BEEN FOUND CRACKED IN THE FORWARD BOTTOM CORNER. 1L72 3O3 O A7SO 1E10 20021206000202002120600020SO 2002 12 6 CA021101003 120021013G2730110K15001012 CONTROL CABLE EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA ELEVATOR FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT AFTT: 22782.0 HOURS. CABLE FOUND FRAYED DURING INSPECTION OF ELEVATOR CABLE SYSTEM AS PER AD 82-09-08R2 AND SB 110-027-064-R2 AND C2 INSP SHEET, HENCE NECESSITY OF DISCONNECTING CABLES FOR PROPER INSPECTION. PULLEY MS 20220A2 ALSO REPLACED AS SHOWING 'INDENT' PIN POINTS IN PULLEY'S GROOVE. CABLE AND PULLEY REPLACED. 1L72 4T4 T A21SO E4EA 20021206000212002120600021EU 2002 12 6 CA021101005 120021019G27529787320307 ACTUATOR PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAPS FAILED W A UNSCHED LANDING F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) THE PILOT SELECTED FLAPS IN PREPARATION FOR LANDING.THE AURAL WARNING AND FLAP CAUTION LIGHT ON THE CAWS PANEL WERE THEN OBSERVED BY THE PILOT. THE AIRCRAFT LANDED AND THE FLAPS WERE RESET ON THE GROUND.THIS SNAG OCCURRED AN ADDITIONAL TWO (2) TIMES THROUGHOUT THE DAY.WHEN THE AIRCRAFT RETURNED TO BASE, MAINTENANCE FOUND THAT THE OUTBOARD ACTUATORS WERE FROZEN AND WOULD NOT MOVE. A HEAT GUN WAS USED FOR APPROX. 60 SECONDS TO FREE THE ACTUATORS.THE ACTUATORS WE RESERVICED WITH NEW GREASE AND THE AIRCRAFT RELEASED FOR FLIGHT.THIS MAINTENANCE ACTION DID NOT RESOLVE THE PROBLEM SO NEW ACTUATORS WERE INSTALLED IN THE OUTBOARD POSITIONS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021206000222002120600022EU 2002 12 6 CA021101006 120021024G3233 SWITCH PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG ACTUATOR INDFAILED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) THE PILOT SELECTED THE GEAR DOWN DURING APPROACH. THE NOSE GEAR AND THE LT MAIN INDICATIONS SHOWED 'DOWN & LOCKED'. THE RT GEAR INDICATOR WAS SHOWING A 'GEAR UNSAFE' CONDITION. THE PILOT USED THE EMERGENCY GEAR PUMP TO INSURE THAT THE GEAR WAS INDEED DOWN AND LOCKED.THERE WAS NO MOVEMENT FROM THE HYDRAULIC HAND PUMP, SO THE GEAR WAS RETRACTED AND CYCLED AN ADDITIONAL FOUR (4) TIMES BEFORE THE GEAR SAFE INDICATION WAS ACHIEVED. WHEN THE AIRCRAFT RETURNED TO BASE, MAINTENANCE PERFORMED THE FUNCTION TEST OF THE LANDING GEAR & EMERGENCY EXTENSION SYSTEMS WITH NO DEFECTS OCCURRING.HOWEVER, WHEN THE RT GEAR 'DOWN INDICATION SWITCH' WAS COOLED TO APPROX. -15(C) THE SNAG COULD BE DUPLICATED.AN OVERHAULED GEAR AC1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021206000242002120600024CE 2002 12 6 CA021101011 120021031G2497650801127 WIRE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE MAIN ELECTRICAL SPLIT W K NONE O OTHER ININSP/MAINT 1 CA 12654 (CAN) DURING A PHASE 5 INSPECTION, A 10 GAUGE WIRE WAS FOUND TO HAVE SPLIT OPEN EXPOSING 2 INCHES OF BARE WIRE BEHIND THE LT CIRCUIT BREAKER PANEL. THIS WIRE TIES THE LT AND RT CIRCUIT BREAKER PANELS AT CB58 AND CB120 RESPECTIVELY. THE MATERIAL SPEC ON THE WIRE IS M81381/8. WHILE REMOVING IT FROM THE AIRCRAFT IT ALSO SPLIT OPEN IN OTHER AREAS WHEN FLEXED.THE WIRE WAS REPLACED WITH A DIFFERENT SPEC WIRE PER MAINTENANCE PRACTICES IN CHAPTER 20 OF THE CITATION WIRING DIAGRAM MANUAL. 1L72 4F4 F A22CE E1NE 20021206000252002120600025EA 2002 12 6 CA021104002 120021029G5610601R3303311 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT FAILED W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA 14074 (CAN) CAPTAIN'S SIDE WINDOW SHATTERED AT 23,000 FT. LANDING UNEVENTFUL. FERRIED AIRCRAFT FOR WINDOW REPLACEMENT. 2L72 4F4 FRTA21EA E15NE 20021113000562002111300056WP 2002 11 13 CA021104004 220021028G73108945682 LINE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ROTOL R321 R321482F8 GL FUEL SYSTEM CHAFED W EA ENGINE SHUTDOWN UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE RT ENGINE BEGAN TO LOOSE TORQUE WITHIN 5-10 SECONDS. ENGINE TEMP DROPPED TO 400 DEGREES IN 30 SECONDS. PROP FEATHERED AND ENGINE SHUTDOWNN PROCEDURES CARRIED OUT. AIRCRAFT LANDED AND MAINTENANCE CREW DISPATCHED FROM YVR. FUEL LINE CHAFED. 2L72 4T4 TRTA8SW E4WE 6 CP61GL 20021206000272002120600027SO 2002 12 6 CA021104007 120021027G2622 EXTINGUISHER EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA CABIN LOOSE W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AT LAST FLIGHT OF THE DAY, PILOT NOTICED PRESSURE VERY LOW ON REAR CABIN HAND FIRE EXTINGUISHER AND REPORTED SNAG. UPON REMOVAL, MAINTENANCE PERSONNEL FOUND UNIT VERY LIGHT, AND PRESSURE ZERO. THE Q.A.CHECKED: BOTTLE LOOSELY UNSCREWED FROM HEAD. NOTE: SEAL OF HANDLE: NOT BROKEN. PILOT SAID HE CHECKED IT OK ON HIS PREFLIGHT. EVIDENTLY UNIT HAS BEEN TEMPERED WITH. RECOMMENDATION: THAT THE NEXT OF THE BOTTLE BE DRILLED FOR SAFETY WIRING TO THE HEAD. 1L72 4T4 T A21SO E4EA 20021206000282002120600028CE 2002 12 6 CA021104010 120021016G302010191002211 HINGE BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE ICE BYPASS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 15310 (CAN) UPON INSPECTION IT WAS NOTED THAT THE DOOR ASSY BYPASS ICE VANE WAS RUBBING AGAINST THE COWLING. AFTER CLOSE INSPECTION IT WAS NOTED THAT THE HINGE HAD CRACKED FROM THE INBOARD END OUTBOARD ABOUT 3 INCH ALONG THE HINGE PIN. THE HINGE ASSEMBLY WAS REPLACED. 1L72 4T4 T A24CE E4EA 20021206000352002120600035SO 2002 12 6 CA021105007 120021030G2435200S6L118Q STARTER GEN EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL RT ENGINE FAILED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA (CAN) STARTER/GENERATOR SHAFT SHEARED WHILE MOTORING THE RT ENGINE FOR START. THE SHAFT BROKE AT 1/8 INCH BELOW THE SPLINE. INSTALLED NEW STARTER/GENERATOR ON RT ENGINE. GROUND RUN SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 1L72 4T4 T A21SO E4EA 6 CP15EA 20021206000362002120600036CE 2002 12 6 CA021105008 120021101G7120045100336 MOUNT CESSNA150 A152 2071836CE LYC O235 O235L2C 41505EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE MOUNT CRACKED AT RT TOP AT THE WELDED JOINT. 1H71 3O3 O 3A19 E223 20021206000372002120600037CE 2002 12 6 CA021105009 120021101G5511043200146 RIB CESSNA150 A152 2071836CE LYC O235 O235L2C 41505EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) L/H INBOARD LEADING EDGE RIB WAS FOUND CRACKED AT THE TOP REAR CORNER OF THE HORIZONTAL STABILIZER. 1H71 3O3 O 3A19 E223 20021206000382002120600038CE 2002 12 6 CA021105010 120021011G7602 SHAFT FACET 1048931 CESSNA182 182 2072702CE CONT O470 O470L 17026SO THROTTLE LOOSE W EA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA H114611 (CAN) CARBURETOR RUNNING LEAN AT ALTITUDE, THROTTLE SHAFT LOOSE, ENGINE RUNS POORLY WITH THIS CARBURETOR. TIME SINCE FACTORY OVERHAUL IS 542.1 HOURS. 1H71 3O3 ONT3A13 E273 20021206000392002120600039EU 2002 12 6 CA021105011 120021104G324206308400 PAD PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL RT MLG BRAKE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT WAS BEING TOWED FROM TERMINAL TO HANGER WHEN THE RT BRAKE SEIZED AND WHEEL WOULD NOT TURN.FURTHER INSPECTION REVEALED THAT THE RIVITS WERE SHEARED ON THE WEAR PADS ON THE OUTSIDE ROWS OF THE BRAKE ASSY. THE WEAR PIN INDICATOR WAS SHOWING AROUND 50 PERCENT WEAR. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021206000472002120600047NM 2002 12 6 CA021108002 120021025G2530 HEATER BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE GALLEY BURNED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE TROUBLE SHOOTING SEVERAL SNAGS REGARDING PROBLEMS FOR 'NO WATER IN FORWARD GALLEY HALF WAY THROUGH FLIGHT' WATER LINE RIBBON HEATER FOR WATER LINE ABOVE NOSE WHEEL WELL FOUND BURNED AND BADLY DAMAGED. 2L72 4F4 FRTA1NM E3NE 20021206000552002120600055GL 2002 12 6 CA021108008 320021107G61123E23604 HARNESS PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PROPELLER SHORTED W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) PROPELLER DE-ICE FAILURE INDICATION REPORTED. DEFECT WAS FOUND AS AN INTERMITTENT OPEN CIRCUIT ON ONE OF THE DEICE HARNESS LEADS. PART REPLACED WITH NEW. THIS DEFECT OCCURRED 106.2 HRS PREVIOUS,TWO DIFFERENT HARNESS ASSY WERE REPLACED AT THAT TIME. THE 4TH HARNESS WAS ALSO REPLACED AS A PREVENTATIVE MEASURE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021206000562002120600056EA 2002 12 6 CA021108009 220021011G741467542 BEARING PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA LEFT MAGNETO LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT ENGINE, LT MAGNETO. DAMAGE WAS DISCOVERED DURING ACCOMPLISHMENT OF AN UNRELATED AIRWORTHINESS DIRECTIVE KNOWN AS, AD2002-20-51. REMOVAL OF ALL ACCESSORIES ON THE ACCESSORIES HOUSING WAS REQUIRED, FOR THIS AD. WHEN THE MAGNETO WAS REMOVED THE MAGNETO GEAR RETAINER ASSY AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE COUPLING YET AGAIN.UPON FURTHER INSPECTION NO DAMAGE TO THE GEAR RETAINER ASSY AND BEARING WAS FOUND AND ASSEMBLY WAS REINSTALLED.ALSO THE BEARING RECESS WAS INSPECTED AND CHECKED O.K. 1L72 3O3 O 1A10 1E4 20021206000582002120600058EA 2002 12 6 CA021108010 220021025G741467542 BEARING PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA LEFT MAG RECESS LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT ENGINE, LT MAGNETO. DAMAGE WAS DISCOVERED DURING ACCOMPLISHMENT OF AN UNRELATED AD, REMOVAL OF ALL ACCESSORIES ON THE ACCESSORIES HOUSING WAS REQUIRED, FOR THIS AD. WHEN THE MAGNETO WAS REMOVED THE MAGNETO GEAR RETAINER ( ASSY AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE COUPLING. UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE SHAFT OF THE 'GEAR RETAINER ASSY AND BEARING WERE DAMAGED AND REQUIRED REPLACEMENT. 'GEAR RETAINER ASSY AND BEARING WAS REPLACED WITH NEW. ALSO THE BEARING RECESS WAS INSPECTED AND CHECKED O.K. MAGNETO WAS INSPECTED AND IT WAS FOUND THAT MAGNETO BEARING, SHAFT AND ARMATURE WAS DAMAGED BEYOND REPAIR. MAGNETO WAS ALSO REPLACED WITH SERVICEABLE MAGNETO. 1L72 3O3 O 1A10 1E4 20021206000702002120600070EA 2002 12 6 CA021108011 220021028G741467542 BEARING PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA LEFT MAG RECESS DESTROYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ENGINE, LT MAGNETO. DURING A 100 HR INSP, OIL FILTER OF LT ENGINE WAS SECTIONED AND INSPECTED. METAL WAS FOUND IN FILTER. SUCTION SCREEN WAS REMOVED AND INSP, PIECES OF A BEARING DISCOVERED. FURTHER DISASSEMBLY WAS REQUIRED. LT OR RT MAGNETO WAS SUSPECTED. ONCE LT MAGNETO WAS REMOVED, MAGNETO GEAR RETAINER ASSY, AND BEARING DROPPED OUT OF THE ENGINE WITH THE DRIVE COUPLING, DRIVE COUPLING NUT AND COTTER-PIN. GEAR RETAINER BEARING HAD COMPLETELY DESTROYED ITSELF. UPON FURTHER INSP, IT WAS DISCOVERED THAT THE SHAFT OF THE GEAR RETAINER ASSY WAS BADLY DAMAGED. THE BEARING RECESS WAS SERIOUSLY DAMAGED. MAGNETO WAS INSPECTED AND FOUND THE MAG BEARING SHAFT AND ARMATURE WAS DAMAGED BEYOND REPAIR. 1L72 3O3 O 1A10 1E4 20021206000732002120600073NE 2002 12 6 CA021108012 320021030G6110E3932 HUB BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE PROPELLER DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) UPON DISASSEMBLY, C792 BEARING WAS FOUND TO BE BROKEN CAUSING DAMAGE TO HUB RENDERING IT UNSERVICEABLE. UPON REMOVING PAINT FROM 3 BLADES, CRACKS WERE DISCOVERED IN THE SHANK AREA IN THE COMPOSITE MATERIAL. AS THIS DAMAGE IS NOT ADDRESSED IN THE O/H MANUAL,THESE BLADES HAVE BEEN FORWARDED TO THE MANUFACTURER FOR EVALUATION. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20021206000752002120600075CE 2002 12 6 CA021108013 120021105G561017360015 WINDSHIELD LEAR 45 45LEAR 5170805CE COCKPIT FAILED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA 617 (CAN) OUTER GLASS FACE PLY 0.12 INCH SHATTERED. 2L72 4F RTT00008WI 20021206000812002120600081EA 2002 12 6 CA021108016 220021030G8520LTIO540J2BD ENGINE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA RIGHT FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) ON CLIMB OUT OF YYC RT POWERPLANT BEGAN TO SURGE 300 TO 400 RPM. PILOT ADVISED TOWER AND RETURNED TO AIRPORT. NOTED THAT ONCE POWER WAS REDUCED POWERPLANT, THEN RAN NORMALLY. ONCE ON GROUND, ADDITIONAL ANTI ICE HOLES DRILLED IN BREATHER LINE AND 2 LBS PRESSURE ADDED TO PROP DOME. AIRCRAFT GROUND RUN & NO FAULTS FOUND, AIRCRAFT RELEASED FOR FURTHER FLIGHT. 1L72 3O3 O A20SO E14EA 20021202001822002120200182WP 2002 12 2 CA021108018 120021016G32331523042101 ACTUATOR LKHEED1011 1011385114 WP RROYCERB211 RB21122B02 54555NE LUG CRACKED W K NONE D INFLIGHT SEPARATION ININSP/MAINT 1 CA (CAN) WHILE PERFORMING A MLG RETRACTION TEST, AFTER REPLACEMENT OF ALL GEARS ON A/C, WE NOTICED AFTER A COUPLE RETRACTIONS, THAT THE MLG ACTUATOR PIN (P/N 1523042-101, REF IPC 32-11-03, ITEM 435) OF THE MLGRETRACT ACTUATOR ON THE R/H MLG WAS CRACKED. RETRACTION SPEED WAS NORMAL. AFTER REPLACEMENT OF THELOWER PIN (P/N 1523042-101, REF IPC 32-11-03, ITEM 435 AND REPLACED IAW AMM 32-11-27) AND MLG RETRACTACTUATOR (P/N 1523042-101, IPC 32-11-03, ITEM 405 AND REPLACED I.A.W AMM 32-33-01), ON THE NEXT RETRACTION, WE FOUND OUT THAT THEJURY BRACE ASSYWAS MAKING A SNAP SOUND AND THE LAST MOVEMENT OF THEACTUATOR WAS TOO FAST (NO SNUBBER ACTION). AFTER REPLACEMENT OF THE JURY BRACE RETRACT ACTUATOR(P/N 1523107-105, IPC 2L73 4F4 F A23WE E12EU 20021209000022002120900002 2002 12 9 CA021112005 420021030G8300996881 CLUTCH DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU HOFMANHOV352HOV352F NE GEARBOX SLIPPED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKE OFF, ON GO AROUND ENG SEEMED TO SURGE & SLIGHTLY OVERSPEED. STARTED AS AN INTERMITTENT CONDITION AND DURING A COUPLE WEEKS DEGRADED. STARTED SURGING SLIGHTLY IN CRUISE. PROP & GOV WERE REPLACED FOR TROUBLESHOOTING. NO CHANGE. ALL OIL SUPPLY LINES TO GOV CHECKED, OIL PUMP SUCTION CHECKED. NEW OIL COOLER INSTALLED. PROBLEM WENT AWAY FOR 1 WEEK. GEARBOX REMOVED, OIL TRANSFER SPIGOT CHECKED, OIL PUMP REMOVED AND CHECKED. NO PROBLEMS. ENG GROUND RUN AND RPM OF PROP CHECKED WITH TACH. ENG RPM SURGED HIGHER THAN PROP RPM WHEN THROTTLE ADVANCED RAPIDLY. OVERLOAD CLUTCH SLIPPING. CLUTCH REMOVED FROM GEARBOX. SLIPS AT 210 FT/LB. THRUST WASHER WORN BELOW LIMITS. CLUTCH REPLACED. RUN UP AND NO PROBLEMS. 1L71 3O3 ONTTA4CH E00051EN5 CTP5BO 20021209000042002120900004CE 2002 12 9 CA021112007 120021104G79203035890 LINE BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA ENGINE OIL GOUGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) INTERFERENCE OCCURRING BETWEEN OIL TRANSFER TUBE AND ANTI ICE FLEX LINE CAUSED TWO GOUGES IN OIL TRANSFER TUBE .015 INCH AND .017 INCH DEEP. WALL THICKNESS OF OIL TRANSFER TUBE IS .025 INCH. THE PROBLEM WAS DETECTED AT SCHEDULED INSPECTION. THE PROBABLE CAUSE WAS FAILURE TO ENSURE A DEQUATE SEPARATION BETWEEN THE OIL TUBE AND THE ANTI ICE FLEX LINE DURING INSTALATION OF THE FLEX LINE. 1L72 3T4 TRT3A20 E4EA 20030115000012003011500001GL 2003 1 15 CA021112009 120021112G6123 SWITCH AMTR AVRO LANCASTER10 GL PCKARD224 224 SO HAMSTD23E 23EX583 NE PROP FEATHERING FAILED W E ENGINE SHUTDOWN E VIBRATION/BUFFET CLCLIMB 1 CA (CAN) AFTER TAKE OFF, PILOT EXPERIENCED DIFFICULTY CONTROLLING NR 4 PROP RPM. AFTER INFLIGHT SHUT DOWN, PILOT UNABLE TO FEATHER NR 4 PROPELLER. UPON INSPECTION, NR 4 PROP FEATHERING SWITCH WAS FOUND TO HAVE FAILED INTERNALLY IN SUCH A MANNER THAT IT WAS TURNING THE PROP FEATHERING PUMP ON/OFF UNCOMMANDED. THIS SUBSEQUENTLY CAUSED THE RPM CONTROL DIFFICULTY WITH THE GOVERNOR. THE PROP FEATHERING PUMP MOTOR FAILED DUE TO OVER- EXTENDED USE, WHICH CAUSED THE PILOT AN INABILITY TO FEATHER THE ENGINE. BOTH COMPONENTS WERE REPLACED AND AIRCRAFT EXTENSIVELY TESTED PRIOR TO TEST FLIGHT. 2H74 4V4 VRCEXPA2M74EXP4V 6 CEXPP6C 20030114000782003011400078NE 2003 1 14 CA021113003 220021031G7250112000014 NOZZLE LYC T53 T5313B 41549NE 2ND GP UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) MILITARY PARTS FOUND INSTALLED ON ENGINE S/N LE-07616. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996 (US MILITARY). IT SHOULD BE 91547. (HONEYWELL OEM). ENGINE S/N LE-07616 OVERHAULED ON 31 MARCH 1993 AT ENGINE TSN:2979.051. 2ND GP NOZZLE P/N 1-120-000-14 S/N: AC102 2) SEAL HOUSING P/N 1-140-190-05 S/N: 01359M3) RETAINING RING P/N 1-100-890-03 4 U E17EA 20030114000792003011400079NE 2003 1 14 CA021113004 220021031G7250119005007 NOZZLE KAMAN K1200 K1200 05625F6SW LYC T53 T5317A 41549NE 1ST STAGE PT UNAPPROVED PART W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) MILITARY PART FOUND INSTALLED ON ENGINE S/N LE-81004. INSTALLED PART MANUFACTURER CODE NUMBER IS 81996, (US MILITARY) IT SHOULD BE 91547. (HONEYWELL OEM) ITEM INSTALLED 7TH MARCH 2001. 1G71 4F4 UNTTR7BO E17EA 20021209000072002120900007EA 2002 12 9 CA021113005 220021106G72003020807 CASE DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND IN CASE 6 O`CLOCK POSITION BY FUEL DUMP VALVE. 1H72 3T3 TRTA9EA E4EA 20021209000172002120900017EA 2002 12 9 CA021115001 120021107G2797 WIRE HARNESS CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE TE FLAPS FAILED W O OTHER N FALSE WARNING LDLANDING 1 CA 16666 (CAN) AFTER TAKE OFF, WHEN FLAPS WERE RETRACTED, STALL FAIL CAUTION MESSAGE APPEARED ACCOMPANIED BY HYD CAUTION FOR HYD PUMP 1B & 3B. STALL TAPE ON CAPTAINS & F/O'S PFD APPEAR TO RUN FULL LENGTH OF AIR SPEED INDICATOR. AIRCRAFT FERRIED FOR TROUBLESHOOTING. R&R FLAP POSITION TRANSMITTER WIRING HARNESS AND OPS CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20021209000192002120900019EA 2002 12 9 CA021115002 220021105G8550CH48108 OIL FILTER ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE SEPARATED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA CAN- OIL PRESSURE WAS FLUCTUATING ON START. PRESSURE RELIEF VALVE WAS INSPECTED & FOUND TWO PIECES OF 3/8 TO 1/2 INCH RUBBER (FROM THE OIL FILTER) WAS FOUND IN THE BAY & SEAT AREA. OIL FILTER REMOVED FOR INSPECTION, WAS SHOWING EVIDENCE OF RUBBER PART DETERIORATION. AIRWOLF OIL FILTER SYSTEM STC SH1252ME REMOVED & ORIGINAL OIL SCREEN & HOUSING WAS INSTALLED ON THE ENGINE. 1G71 3O3 O H10WE E274 20021209000612002120900061CE 2002 12 9 CA021115004 120021005G5410555211060 DOOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE RT ENG NACELLE SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) RT ENGINE ANTI-ICE VALVE REPLACED, INVESTIGATION SHOWS THAT INNER HALF OF LOWER COWLING FASTENERS NOT SECURED. AIRCRAFT DEPARTED YVR, CREW NOTICED A 'BANG' AND THEN A CONSTANT VIBRATION, GOING THROUGH 8,000 FT, CLIMBING OUT. CREW CONTINUED TO CLIMB THROUGH 15,000 FT, BEFORE DECLARING AN EMERGENCY AND RETURNING TO YVR AND COMPLETING A NORMAL LANDING ON RUNWAY 12. INVESTIGATION SHOWED RT LOWER ENGINE COWLING PARTIALLY DETACHED FROM AIRCRAFT AND SKIN KINKED AND BENT, AND FORWARD OUTER FASTENER HOLES TORN. 1L72 4F4 F A22CE E1NE 20021209000642002120900064SO 2002 12 9 CA021115006 120021113G55544A3441 ATTACH ANGLE EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA 1925719257 (CAN) DURING A SCHEDULED INSPECTION EVENT EXCESSIVE WEAR WAS NOTED AROUND THE BOLT HOLE OF THE UPPER RUDDER ATTACH BRACKET. THE RIVETS SECURING THE BUSHING BOSS IN THE BRACKET WERE ALSO WORKING.THE RUDDER ATTACH BRACKET ASSEMBLY PART NUMBER 4A-3441 WAS REPLACED. 1L72 4T4 T A21SO E4EA 20021209000662002120900066EU 2002 12 9 CA021115008 120021029G324223203500 DISK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BRAKE ASSY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON INSPECTION FOUND RT BRAKE ASSEMBLY TO HAVE A BROKEN ROTOR DISK. BRAKE ASSEMBLY REPLACED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021202001842002120200184CE 2002 12 2 CA021115009 120021105G326012700341 SQUAT SWITCH CESSNA210 210L 2073448CE CONT O520 IO520L 17032SO MCAULY3A32C D3A32C88 GL WIRING FAILED W K NONE R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 CA (CAN) PILOT SELECTED GEAR UP AFTER TAKEOFF AND GEAR MOTOR 'APPEARED' TO RUN ON, AND NO GEAR-UP INDICATION WAS NOTED. PILOT SELECTED GEAR DOWN AND GOT CORRECT INDICATION AND MOTOR STOPPED AS NORMAL. PILOT CONTINUED BACK TO HOME BASE WITH GEAR DOWN AND NO FURTHER INCIDENT. MAINTENANCE DISCOVERED BROKEN WIRE INTERMITTENTLY MAKING CONTACT IN NOSE SQUAT SWITCH. REPLACED SWITCH WITH NEW P/N 1270034-4 GEAR SWUNG - SYSTEM FOUND SATISFACTORY. 1H71 3O3 O 3A21 E5CE 5 CP21EA 20021209000692002120900069SO 2002 12 9 CA021115010 120021107G2434 BEARING GULSTMG159 G159 3952202SO RROYCEDART DART5298X 54507EU LT GENERATOR SHORTED W H DEACTIVATE SYST/CIRCUITS HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 CA (CAN) LT GENERATOR TRIPPED, PILOTS REPORTED AN UNDER VOLTAGE CONDITION.ACTION: LT GENERATOR REMOVED, UPON INSPECTION OF COMPONENT, GEARING ASSEMBLY PARTS HAD MIGRATED TO, AND SHORTED OUT A BRUSH HOLDDOWN SPRING TO THE GENERATOR CASE. 2L72 4T4 T 1A17 E297 20021209000792002120900079EU 2002 12 9 CA021115013 120021112G27529787320307 ACTUATOR PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL TE FLAPS FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE OF THE AIRCRAFT. THE FLAPS WERE SELECTED DOWN TO THE 40 DEGREE POSITION. DURING MOVEMENT OF THE FLAPS A 'GRINDING' NOISE WAS HEARD COMING FROM THE L/H INBOARD FLAP ACTUATOR. THE ACTUATOR BECAME VERY HOT AND WOULD CAUSE THE FLAPS TO STALL. THE AIRCRAFT HAD RETURNED FROM A TRIP APPROX. (1) HOUR PRIOR TO THE DEFECT OCCURRING. THE PILOT DIDNOT INCOUNTER ANY FAILURE OF THEFLAP SYSTEM DURING THE FLIGHT. A REPLACEMENT ACTUATOR WAS INSTALLE D AND NO FURTHER DEFECTS WERE NOTED.RECENT PROBLEMS WITH THIS AIRCRAFTS FLAP SYSTEM, WERE THE RESULT OF ACTUATORS FREEZING AT ALTITU DE. THIS IS OUR FIRST INCIDENT WHERE SUCH A FAILURE HAS OCCURRED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021209000802002120900080EU 2002 12 9 CA021115014 120021103G324223203500 DISK PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL BRAKE ASSY BROKEN W O OTHER O OTHER LDLANDING 1 CA (CAN) ON LANDING LT WHEEL BRAKE LOCKED UP AND SKIDDED TIRE. ON INSPECTION FOUND ROTOR DISK AND BROKEN INTO 2 PIECES AND JAMMED BRAKE ASSEMBLY. BRAKE ASSEMBLY AND TIRE REPLACED. ON INSPECTION OF R/H BRAKE ASSEMBLY, FOUND ONE ROTOR DISK ALSO BROKEN. BUT THIS ASSEMBLY STILL FUNCTION WITHOUT LOCK UP. REPLACED RT BRAKE ASSY. THIS IS THE 3RD DISK IN 5 DAYS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20021209000902002120900090SO 2002 12 9 CA021115023 120021115G57511710013 RIB PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA RT AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING 100 HOURS INSPECTION, FOUND RT AILERON INBOARD TRAILING EDGE RIB CRACKED AROUND BOTTOM MOUNTING NUT. UPON REMOVAL OF RIB, THE AILERON SPAR IS ALSO CRACKED AT SAME LOCATION. 1L72 3O3 O 1A10 E14EA 20030114000802003011400080CE 2003 1 14 CA021118003 120021113G323050450102 TORQUE TUBE CESSNA310 310L 2074230CE CONT O470 IO470VO 17026SO MLG CRACKED W A UNSCHED LANDING EN VIBRATION/BUFFET FALSE WARNING CLCLIMB 1 CA (CAN) ON T/O, A CLUNK HEARD NEAR END OF MLG TRAVEL DURING RETRACTION. NO DIFFERECE IN FLT CONTROL. PILOTS INFORMED RT MLG HANGING. MLG SELECTED DOWN STEEP BANKS & YAWS PERFORMED TO GET RT MLG LOCKED. NO DOWN & LOCKED IND EVIDENT, A/C LANDED UNEVENTFULLY. RT MLG NOT LOCKED, SIDE BRACE LOCK NOT OVER-CENTER AND DOWNLOCK SPRING BROKEN. JACKED A/C, RT TORQUE TUBE ASSY BROKEN AT OTBD PUSH-PULL TUBE ATTACH POINT. INVEST REVEALED A CRACK AT ATTACH POINT. THERE IS NO SPECIAL INSPECTION ON THIS PART OF MLG, DIFFICULT TO DETECT A CRACK WITHOUT REMOVING TORQUE TUBE FROM A/C. TORQUE TUBE AND RETRACTION SYSTEM TEARDOWN AND INSPECT REQUIRE INITIAL INSPECTIONS AT 10000 HOURS. A/C HAS ONLY 7621.4 HOURS SINCE NEW. 1L72 3O3 O 3A10 3E1 20021209001012002120900101CE 2002 12 9 CA021118004 120021113G326050410051 SPRING CESSNA310 310L 2074230CE CONT O470 IO470VO 17026SO RT MLG DOWNLOCK BROKEN W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) SUBSEQUENT TO THE RT MAIN GEAR FAILURE TO LOCK AND FINDING THE TORQUE TUBE CRACKED, THE DOWNLOCK SPRING WAS ALSO BROKEN. HAD THIS SPRING BEEN INTACT THE GEAR WOULD HAVE FREE-FALLEN DOWN AND LOCKED. THERE IS NO RIGGING OR ADJUSTMENT ON THESE SPRINGS. BOTH LT & RT SPRINGS WERE REPLACED NEW, THE RT FAILING AFTER 164.4 HOURS AND AGAIN AFTER 25.1 HOURS. ALL SPRINGS WERE FOUND TO BE OF THE SAME ORIGIN AND THE INTACT LT SPRING HAS BEEN REMOVED FROM THE AIRCRAFT.ALL SPRINGS HAVE BEEN SUPPLIED TO OUR PMI FOR FURTHER INVESTIGATION. 1L72 3O3 O 3A10 3E1 20021209001042002120900104CE 2002 12 9 CA021118007 120021118G2810051600918 TANK CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA MAIN FUEL CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HEADER TANK FOUND LEAKING. UPON REMOVAL, TANK HAS A 1 INCH CRACK ON TOP OF WELD AROUND BOTTOM AFT SIDE OF TANK. 1H71 3O3 ONT3A12 1E10 20021202001852002120200185CE 2002 12 2 CA021118008 120021107G7160TA8071 BAFFLE CONT O320E2D CESSNA172 172 2072402CE LYC O320 O320E2D 41508EA AIRBOX BAFFLE BROKEN W AD UNSCHED LANDING RETURN TO BLOCK R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) A PIECE OF BAFFLE BROKE OFF OF THE AIRBOX BAFFLE CONTROL. THE PIECE LOGGED IN THE CARBURETOR VENTURIRESULTING IN A RICH MIXTURE AND PARTIAL POWER LOSS. REPAIRS MADE BY AMO 98.91, OCTOBER 28/02. INCIDENT REPORTED AS POWER LOSS DUE TO CARB ICE - SUBSEQUENT RUN-UP REVEALED THE PROBLEM WAS NOT DUECARB ICE BUT RICH MIXTURE AND ROUGH RUNNING UNTIL LEAN - MAINTENANCE ARRANGED. 1H71 3O3 ONT3A12 E274 20021202001862002120200186CE 2002 12 2 CA021118009 120021116G2434C6115050201 ALTERNATOR CESSNA C6115050201 CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL ALTERNATOR W D RETURN TO BLOCK JL WARNING INDICATION NO TEST CRCRUISE 1 CA 2310 (CAN) PILOT REPORTED STANDBY ALTERNATOR INOP LIGHT CAME ON. THE SYSTEM WAS SHUT DOWN AND RETURN TO BASE. THE ALTERNATOR WAS FOUND TO BE UNSERVICABLE. A SEARCH OF THE AIRCRAFT RECORDS FOUND THAT THIS WAS T HE ORIGINAL ALTERNATOR. THERE IS NO T.B.O. PUT ON THIS UNIT FROM CESSNA. THE BASE PUT A 3000 HOUR TBO ON THE ALTERNATOR. 1H71 3T3 T A37CE E4EA 5 CP60GL 20021209001792002120900179CE 2002 12 9 CA021119008 120021025G3246704AC5225 FLYING WIRE CESSNA172 172G 2072420CE CONT O300 O300C 17022SO FLOAT BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) HARD LANDING ON GATINEAU RIVER - BROKE BOTH FLYING WIRES THAT ATTACH UPPER LT HAND AND LOWER RT HAND. THIS ALLOWED THE AIRPLANE TO GO DOWN ON RT WING TIP. THIS BROKEN THE ATTACH FITTINGS ON END OF REAR AND DIAGONAL STRUTS. 1H71 3O3 ONT3A12 E253 20021209001802002120900180CE 2002 12 9 CA021119009 120021108G5511043200146 RIB CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13643 (CAN) THE LT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER. 1H71 3O3 ONT3A19 E223 20021209001812002120900181CE 2002 12 9 CA021119010 120021108G551104320016 RIB CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13643 (CAN) THE RT INBOARD LEADING EDGE RIB CRACKED AT TOP REAR CORNER. 1H71 3O3 ONT3A19 E223 20021209001822002120900182SO 2002 12 9 CA021119011 220021101G8530654961 CYLINDER CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CONDUCTING A CYLINDER COMPRESSION TEST, THE FOLLOWING RESULTS WERE DISCOVERED:CYLINDER 1-40PSI, 2-45PSI, 3-0PSI, 4-0PSI,5-40PSI, 6-58PSITHE MEASURE OF THE CYLINDER BARRELS INDICATES THAT THEY SHOULD MEASURE '10 THOU OVERSIZE'. THE EXHAUST VALVES ARE ALL WORN, MOREOVER THE INTAKE VALVES ARE ALSO WORN AT THE NEEDLE SHAFT AND TOO THIN ATTHE BASE OF THE VALVE. 1H71 3O3 O 3A24 E5CE 20021209001832002120900183CE 2002 12 9 CA021119012 120021116G281007161249 FLAPPER VALVE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA LT FUEL CELL FAILED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) VALVE ASSEMBLY CENTER SECTION PIN AND SPRING FAILURE. THE FAILURE ALLOWED FUEL TO EXIT FUEL VENT SYSTEM. CORRECT BY REPLACING ENTIRE VALVE ASSEMBLY. 1H71 3O3 ONT3A12 E274 20030114000912003011400091SO 2003 1 14 CA021120001 220021114G8550C1650010202 SCREEN CESSNA414 414 2075908CE CONT O520 TSIO520N 17040SO MCAULY3AF32C3AF32C93 GL AIR/OIL SEP DESTROYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING OPERATION 1 INSPECT, NON FERROUS METAL FOUND IN LT OIL FILTER AND SCREEN. INSPECTED FILTER AGAIN IN 20 HOURS. IN LESS THAN 15 HOURS OIL WAS DRIPPING ONTO LT MLG. PAINT REMOVED FROM CRANKCASE FWD OF ALTERNATOR, CRACK WAS CONFIRMED BY DEVELOPER. ENG REMOVED FOR CRACK REPAIR AND SHOP NOTIFIED TO INSPECT FOR SOURCE OF CONTAM FOUND IN FILTER AFTER 14.6 HOURS. SHOP COULDN`T FIND SOURCE. RETURN LINE REMOVED FROM AIR/OIL SEPARATOR, METAL FOUND IN HOSE. SEPARATOR, REMOVED, & CUT APART. INSIDE SCREEN & HOLDER HAD VIBRATED APART & ALUMINUM GETTING TO CRANKCASE THROUGH RETURN LINE. PRESS HOSE TO BOOTS & PRESSURE FILTER HAD A LARGE AMOUNT OF METAL SCREEN PARTS TRAPPED INSIDE. 1L72 3O3 ORTA7CE E8CE 5 CP22EA 20021211000042002121100004GL 2002 12 11 CA021120005 320021112G6111T10282 BLADE SWRNGNSA226 SA226TC 8780404SW GARRTTTPE331TPE33110UA 01514WP HARTZLHCB3T HCB3TN5 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINEER NOTICED CRACKED TRAILING EDGE OF PROPELLER BLADE, FOUND DURING POST FLIGHT INSPECTION IN THE HANGER. 2L72 4T4 TRTA8SW E4WE 6 CP15EA 20021211000052002121100005CE 2002 12 11 CA021120006 120021110G3340 SWITCH CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL LANDING LIGHT FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA (CAN) SMOKE IN THE CABIN WAS DETERMINED TO BE FROM THE LANDING LIGHT SWITCH. SWITCH WAS SHUT-OFF BUT CONTINUED TO SMOKE. ONLY WAY TO STOP SMOKING WAS TO TURN OFF THE BATTERY MASTER AS THE CIRCUIT BREAKER IS OF A TYPE THAT CANNOT BE MANUALLY PULLED. NEW SWITCH AND CIRCUIT BREAKER WAS INSTALLED AFTER AIRCRAFT WIRING AND LANDING LIGHT CHECKED SERVICABLE. 1H71 3O3 ONT3A12 E274 5 NP910 20021211000082002121100008CE 2002 12 11 CA021121003 120021119G2701556575717 SHAFT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE CONTROL PED CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE CLAMP SCREW ON THE FLIGHT DIRECTOR MODE SELECTOR CONNECTOR PLUG RUBBED AGAINST THE AILERON TRIM CONTROL SHAFT ABOUT 3 INCHES FROM THE AFT END OF THE SHAFT. THE 1/4 INCH SOLID STEEL SHAFT WAS WORN TO .238 INCH DIAMETER AT THIS CONTACT POINT. 3/8 INCHES OF EXCESS SCREW WAS CUT OFF TO PREVENT FURTHER WEAR. A FLEET CAMPAIGN INSPECTION HAS BEEN INITIATED. 1L72 4F4 F A22CE E1NE 20021211000092002121100009SO 2002 12 11 CA021121004 120021117G32206716800 SPRING PIPER PA44 PA44180 7104402SO NLG BROKEN W O OTHER J WARNING INDICATION APAPPROACH 1 CA (CAN) A STUDENT PILOT SELECTED LANDING GEAR DOWN, WHEN IT WAS NOTICED THAT THE NOSE LANDING GEAR TOOK APPROX. 2 MIN. TO EXTEND. THE AIRCRAFT WAS LANDED SAFELY AND MAINTENANCE WAS NOTIFIED. IT WAS NOTICE THE NOSE LANDING GEAR DOWN ASSIST SPRINGS WERE POSITIONED DIFFERENTLY. FURTHER INVESTIGATION REVEALED THAT THE INNER SPRING WAS BROKEN AND WAS JAMMING THE OUTER SPRING, THUS RESULTING IN THE LENGTH OF TIME IT TOOK TO LOWER THE GEAR. IT IS SPECULATED THAT THE BUILD UP OF HYDRAULIC PRESSURE FINALLY PUSHED THE GEAR DOWN AND LOCKED. BOTH THE INNER AND OUTER SPRINGS WERE REPLACED NEW. IT IS BELIEVED THAT CYCLES AND FATIGUE CONTRIBUTED TO SPRING BREAKING. 1L72 3O A19S0 20021211000102002121100010CE 2002 12 11 CA021121005 120021030G71601099100299 DUCT BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA ENGINE INLET CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LOWER FWD ENGINE COWLING FOUND CRACKED. 1L72 3T4 TRT3A20 E4EA 20021211000122002121100012NE 2002 12 11 CA021121007 320021121G6114B70192 SETSCREW BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE PROPELLER CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) PROPELLER WAS REMOVED FOR A GREASE LEAK, WITH NO INDICATIONS OF LOOSE BLADES. UPON DISASSEMBLY BLADE PRELOAD SET SCREW WAS FOUND CRACKED AND ONCE CLEANED THE TIPS FELL OFF OF NR 2. BLADES WERE WITHIN THEIR BLADE PLAY LIMITS IN THE HUB PRIOR TO DISASSEMBLY. SEVERE WEAR WAS FOUND ON THE PRELOAD PLATES. PROCEEDED TO CHECK NEW SET SCREWS FROM STOCK, AND 21 OUT OF 24 WERE FOUND CRACKED VIA VISUAL INSPECTION USING A 10X MAGNIFYING GLASS. MANUFACTURER WAS NOTIFIED AND THEIR STOCK WAS CHECKED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20021211000142002121100014CE 2002 12 11 CA021122002 120020720G555107321014 BRACKET CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULY2A34C D2A34C58 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THE REINFORCEMENT BRACKETS WERE CRACKED. NEW PARTS 0732101-4 WERE INSTALLED. 1H71 3O3 O 3A24 E5CE 5 CP3EA 20021211000152002121100015CE 2002 12 11 CA021122003 120020920G531207120487 BULKHEAD CESSNA180 180H 2072618CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL TAIL CONE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, IT WAS DISCOVERED THAT THE ANGLE TAILCONE REINFORCEMENT LT IN THE TAILCONE BULKHEAD ASSEMBLY WAS CRACKED. 1H71 3O3 O 5A6 E273 5 CP3EA 20021211000162002121100016CE 2002 12 11 CA021122004 120021030G3211 TUBE BEECH 17 D17S 1150538CE PWA R985 R985AN1 52008NE MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) STRUCTURAL TUBE, 10CM IN LENGTH, FORMING UPPER SUPPORT FOR RT LANDING GEAR SLIDE TUBE FOUND CRACKED DURING PERFORMANCE OF UNRELATED MAINTENANCE. CRACK ORIGINATED FROM HOLE IN TUBE USED TO APPLY LINSE ED OIL TO INTERIOR OF TUBE. HOLE HAD BEEN PLUGGED WITH RIVET. CRACK 1.5CM IN LENGTH WAS EXTENDING AROUND THE CIRCUMFERENCE OF THE TUBE. TUBE WAS CUT FROM AIRCRAFT STRUCTURE AND NEW PIECE WELDED IN. 1Q71 3R3 R A649 5E1 20030114000972003011400097EA 2003 1 14 CA021122006 220021115G8530LW11633 CYLINDER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CYLINDER BARREL CRACKED, 2 INCHES LONG AT BOTTOM OF CYLINDER HEAD. 1H71 3O3 ONT3A19 E223 5 NP50GL 20021211000172002121100017CE 2002 12 11 CA021122008 120021122G2711556575717 SHAFT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE AILERON CONTROL DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DAMAGE WAS FOUND ON THE AILERON TRIM CONTROL SHAFT MIDWAY BETWEEN THE TRIM WHEEL AND CHAIN GEAR. THIS DAMAGE WAS FOUND WHILE CARRYING OUT AN IN HOUSE CAMPAIGN (851-018) TO LOOK FOR THIS TYPE OF DAMAGE TO THE SHAFT. THE DAMAGE WAS CAUSED BY THE CLAMPING SCREW ON THE 'SOURCE CONTROLLER' CONNECTOR PLUG. THE SCREW IS TO LONG AND CONTACTS THE TRIM SHAFT. DAMAGE WAS .004 OR AND INCH DEEP WITH A DRESSED OUT DEPTH OF .006 OF AN INCH AFTER REPAIR. 1L72 4F4 F A22CE E1NE 20021211000182002121100018NM 2002 12 11 CA021122009 120021007G3397320562 SPLICE DHAV DHC8 DHC8301 1386003NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE CABIN OVERHEATED W K NONE MB OVER TEMP SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) WHILE AIRCRAFT WAS IN HEAVY MAINTENANCE, TECHNICIANS DISCOVERED HEAT DAMAGE TO SEVERAL WIRING COMPONENTS FOR THE PASSENGER SERVICE UNIT READING LIGHTS, ON THE LT SIDE OF THE AIRCRAFT JUST AFT OF THE MAIN CABIN DOOR. WIRING SPLICES EXHIBITED SIGNS OF OVERHEATING, AND ADJACENT WIRING WAS HEAT DAMAGED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20030106002122003010600212SO 2003 1 6 CA021124001 220021121G7414103493505 MAGNETO CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO MCAULY2A34C C2A34C204 GL ENGINE DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE PREFORMING ROUTINE MAINTENANCE, IT WAS FOUND THAT THE LT MAGNETO COULD NOT BE TIMED. IT APPEARS THAT THE MAGNETO POINTS ARE NOT OPENING. MAGNETO REPLACED WITH OVERHAULED UNIT AND TIMED NORMALLY. GROUND RUN CHECKS ALL OK. 1H71 3O3 ONT3A13 E273 5 CP3EA 20030114001262003011400126EU 2003 1 14 CA021125001 120021109G7921RK35782A OIL COOLER BRAERO748 HS7482B 1500248EU RROYCEDART DART5342 EU ENGINE LEAKING W EC ENGINE SHUTDOWN ABORTED TAKEOFF KJ FLUID LOSS WARNING INDICATION TOTAKEOFF 1 CA (CAN) AIRCRAFT TOOKOFF FROM YZG FOR YUZ, AFTER TAKEOFF IN FLIGHT THE RT ENGINE OIL PRESSURE LIGHT CAME ON, OIL PRESSURE ZERO, PILOT SHUTDOWN ENGINE. ON ARRIVING TO YVP, INSPECTION WAS CARRIED OUT, AND RT OIL COOLER HONEYCOMB WAS LEAKING. RT OIL COOLER WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 2L72 3T4 T A24EU A196 20030114001272003011400127SO 2003 1 14 CA021125003 220021105G7310 SHIELD MOONEYM20 M20K 5870220SW CONT O520 TSIO520NB 17040SO FUEL DIST HEAD MISSING W BA EMER. DESCENT UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA 3055E (CAN) A/C ENROUTE AT FLIGHT LEVEL 210, DECLARED AN EMERGENCY. AIRCRAFT TURNED BACK. PILOT REPORTED ROUGH RUNNING ENGINE & MISFIRING BADLY A/C LANDED SAFELY. PILOTS EXPERIENCED POWER LOSS ON NR 3 CYLINDER FIRST & THEN ON BOTH NR 3 & 4 CYLINDERS. ENGINE IS EQUIPPED WITH CYLINDER HEAD TEMPERATURE PROBES FOR ALL CYLINDERS & COULD SEE 3 & 4 AS COLD CYLINDERS. BASED ON THE INVESTIGATION PILOTS ARE CONFIDENT PROBLEM WAS ICE CRYSTALS IN THE FUEL. FUEL IS FEED TO THE CYLINDERS FROM A DISTRIBUTION HEAD ON THE TOP OF ENGINE. A SHIELD THAT IS DESIGNED TO DEFLECT COLD AIR FROM THE DISTRIBUTION HEAD AND THE LINES COMING FROM IT, REQUIRED BY AN AD. 1L71 3O3 O 2A3 E8CE 20030114001302003011400130EU 2003 1 14 CA021125006 120020917G2435P6007052 BELL ASSY AUXILEC SNIAS 350 AS350B1 8680811EU TMECA ARRIELARRIEL1D NE STARTER GEN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 2383 (CAN) WHILE COMPETING A DAILY INSPECTION ON THE AIRCRAFT THE ENGINEER NOTICED A CRACK ON THE DRIVE END BELL ON THE STARTER GEN. 1G71 3U3 U H9EU E19EU 20030130000262003013000026EA 2003 1 30 CA021125009 320021113G6111M76AM PROPELLER SNSNCH76AM M76AM EA LEADING EDGE MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) PROPELLER WITH NO HISTORY SENT IN FOR OVERHAUL. - DURING LIQUID PENETRANT INSPECTION, FOUND SUSPICIOUS WELDING WITH EDDY CURRENT CONDUCTIVITY PROBE AS WELDED AREA MATCHED GOOD AREA. KELLERS ETCH SHOWED DISCOLOURATION AND CHROMIC ACID ANODIZING CONFIRMED WELDING HAD TAKEN PLACE. AS MOST PROP SHOPS DO NOT HAVE ANODIZE FACILITIES, THIS IS A TOUGH IMPROPER REPAIR TO LOCATE. 5 N1P210 20030114001352003011400135CE 2003 1 14 CA021125010 120021121G2720151350013 BRACKET CESSNA337 337A 2075704CE CONT O360 IO360C 17025SO MCAULY2AF34CD2AF34C59 GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK FOUND ON BOTH INBOARD RUDDER TORQUE TUBE MOUNTING BRACKETS. THE CRACK BEGAN AT THE AFT END OF THE BRACKET, EXTENDING FORWARD APPROXIMATELY 3-4 INCHES ON THE LT BRACKET AND 1/2 INCH FORWARD ON THE RT BRACKET. THE CRACK OCCURRED AT THE BEND RADIUS ON THE OUTER PIECE OF THE BRACKET. 1H72 3O3 O A6CE E1CE 5 CP5EA 20021211000202002121100020SO 2002 12 11 CA021125011 120021113G3210AN17651 BOLT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA MLG BROKEN W C ABORTED TAKEOFF D INFLIGHT SEPARATION TOTAKEOFF 1 CA (CAN) ON TAKEOFF, VIBRATION WAS NOTICED IN LT MAIN GEAR. INSPECTED MAIN GEAR (LT) LINK BOLT FOUND BROKEN, BOLT REPLACED. BEARING UP LOCK REPLACED. RETRACT GEAR CHECKED AND OK. CAUSE: TIGHT TURN ON GROUND WITH BRAKES APPLIED. 1L72 3O3 O A20SO E14EA 20021211000212002121100021CE 2002 12 11 CA021125012 120021125G30209091010017 DUCT BEECH 90 C90A 1152911CE PWA PT6 PT6A21 52043EA ANTI ICE SYS CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION THE RT ENGINE COWL WAS REMOVED AND THE FLEXIBLE TUBE THAT DELIVERS EXHAUST AIR TO HEAT THE ENGINE COWL INTAKE WAS DISCOVERED TO BE CRACKED. THE CRACK EXTENDED APPROXI MATELY 1/3 OF THE CIRCUMFERENCE OF THE TUBE. 1L72 3T4 TRT3A20 E4EA 20030114001462003011400146EU 2003 1 14 CA021127002 120021101G6123 PLATE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL PROPELLER DISLODGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PROPELLER WAS NOT IN THE FULL FEATHER POSITION. INSPECTION SHOWED THAT THERE WAS A GAP BETWEEN THE FEATHER STOP NUT AND THE REVERSE ADJUST SLEEVE. PROPELLER WAS REMOVED AND SENT TO PROPELLER OVERHAUL SHOP FOR REPAIR. ON DISASSEMBLY, THE PRELOAD PLATE WAS FOUND TO HAVE MOVED THUS PREVENTING THE PROPELLER TO GO INTO THE FULL FEATHER POSITION. SERVICE BULLETIN HC-SB-61-243 REV.1 INCORPORATED. PROPELLER REINSTALLED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030114001512003011400151EA 2003 1 14 CA021129004 120021117G2841 COMPUTER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE FUEL QTY IND INACCURATE W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AIRCRAFT OPERATING UNDER MEL 28-24-01-2 (XFLOW /APU FUEL PUMP INOP). ON TAKEOFF CREW NOTICED 600LB FUEL IMBALANCE. UNABLE TO TRANSFER FUEL FROM LT TO RT TANK USING GRAVITY FLOW. IMBALANCE INCREASED TO 2000LB IN STRAIGHT AND LEVEL DESPITE ALL EFFORTS. FUEL PUMP WAS REPLACED TO CLEAR THE MEL, BUT TROUBLESHOOTING REVEALED THAT FAULT CODES 701 & 702, (FAULTS IN BOTH CHANNEL 1 AND CHANNEL 2, WHICH MAY CAUSE ERRONEOUS FUEL SYSTEM INDICATION) WERE INDICATED, WHICH IS BELIEVED TO BE THE CAUSE OF THIS INCIDENT 2L72 4F4 FRTA21EA E15NE 20030114001712003011400171CE 2003 1 14 CA021203003 120021202G27509910554 MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE TE FLAPS INTERMITTENT W A UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION NRNOT REPORTED 1 CA (CAN) FLAPS WILL NOT RETRACT COMPLETELY. INVESTIGATION REVEALED A SNAPPED COUPLING ON THE RT FLAPACTUATOR SHAFT AT THE GEARBOX. FURTHER INVESTIGATION REVEALED THE RT FLAP MOTOR WAS INTERMITENT. SUSPECT THE FLAP MOTOR BRAKE WAS NOT RELEASING DURING FLAP OPERATION. 1L72 4F4 F A22CE E1NE 20030114001762003011400176 2003 1 14 CA021203007 420021202G6122180315 BEARING WOODWARD 8210007F PROP GOVERNOR FAILED W K NONE O OTHER ININSP/MAINT 1 CA 180626F (CAN) UPON DISASSEMBLY OF THIS GOVERNOR, IT WAS NOTED THAT ONE OF THE FOUR BEARING ASSEMBLIES HAD LOST ITS BALLS. BECAUSE THERE IS NO SCREEN IN THE BASE OF THIS GASKET, ANY OIL CONTAMINATES COULD CHANNEL BACK INTO THE ENGINE. THE GOVERNOR WAS COMPLETELY OVERHAULED, THE BEARINGS REPLACED, AND THE OWNER OF THE AIRCRAFT WAS ADVISED WHAT THE FINDINGS WERE. 20030106002152003010600215NM 2003 1 6 CA021203009 120021130G278265449617 ACTUATOR BOEING737 737284 138448RNM PWA JT8 JT8D9A 52048NE NR 1 SPOILER LEAKING W E ENGINE SHUTDOWN K FLUID LOSS TXTAXI/GRND HDL 1 CA (CAN) AFTER LANDING, FLIGHT CREW REPORTED THE AIRCRAFT LOST ALL SYSTEM "A" HYDRAULIC PRESSURE AND THE FLUID QUANTITY INDICATION READ ZERO.MAINTENANCE INSPECTION REFEALED THE NR 1 GROUND SPOILER OUTBOARD ACTUATOR ASSEMBLY WAS LEAKING - ACTUATOR CASING CRACKED. ACTUATOR REPLACED IAW MM 27-62-101 2L72 4F4 F A16WE E2EA 20030114001862003011400186CE 2003 1 14 CA021204005 120021204G2820 FUEL LINE CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO WING RUPTURED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WATER CONTAMINATION IN ALUMINIUM FUEL LINE CAUSE DETERIOTION OF THE LINE BY CORROSION AND RUPTURE BY FREEZING. THIS LINE IS LOCATED BETWEEN WING TIP TANK AND ELECTRIC TRANSFER PUMP LOCATED IN WING. 1H71 3O3 O A4CE E5CE 20030114001902003011400190EA 2003 1 14 CA021204008 220021119G7322105267 CARBURETOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE FAILED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA (CAN) LOSS OF CONTROL AT/ON TAKEOFF 200KM. CARBUETOR MALFUNCTION. 1H71 3O3 ONT3A19 E223 20030114001922003011400192EA 2003 1 14 CA021204010 220021120G853075772 PUSHROD TUBE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA NR 3 CYLINDER BROKEN W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WITH THE ENGINE COWLING REMOVED TO REPLACE UNSERVICEABLE LANDING LIGHT, OIL WAS NOTED AROUND THE NR 3 CYLINDER. INVESTIGATION SHOWED SHROUD WAS BROKEN APPROXIMATELY MIDWAY ALONG THE TUBE. AS THE CRACK WAS A RATHER SHARP BREAK THE PROBLEM WAS NOT FOUND UNTIL THE TUBE WAS MOVED (TWISTED) BY HAND. 1H71 3O3 ONT3A12 E274 20030106002172003010600217NM 2003 1 6 CA021206002 120021129G3230841005 PSEU ELDEC DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE INTERNAL FAULT W OA OTHER UNSCHED LANDING J WARNING INDICATION APAPPROACH 1 CA 289 (CAN) ON APPROACH CREW SELECTED GEAR DOWN, RECEIVED 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20030114002062003011400206GL 2003 1 14 CA021206005 120021203G56102056501100 CANOPY DIAMONDA20 DA20A1 2990000GL COCKPIT CRACKED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) A PREVIOUS CRACK THAT ORIGINATED IMMEDIATELY AFT OF THE PORT CANOPY LOCKING HANDLE HAD BEEN STOP-DRILLED. IN FLIGHT A CRACK ORIGINATED FROM THE STOP DRILL LOCATION AND PROPAGATED TO THE UPPER PORTION OF THE CANOPY.AN ELLIPTICAL SEGMENT APPROX. 12 INCHES X 6 INCHES OF THE UPPER SIDE OF THE CANOPY FELL INTO THE AIRCRAFT. THE NEW CRACK WAS NOT THE RESULT OF A BIRD STRIKE OR TURBULENCE ENCOUNTER. 1L71 3O NTTA4CH 20030106002182003010600218NM 2003 1 6 CA021210001 120021203G276165449617 ACTUATOR BOEING737 7372H4 138448CNM PWA JT8 JT8D9A 52048NE GROUND SPOILER LEAKING W ED ENGINE SHUTDOWN RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA 73030 (CAN) FLIGHT 178, CREW REPORTED "A" SYSTEM HYDRAULIC PRESSURE AND QTY WENT TO ZERO ON TAXI INTO YYC. LOW PRESSURE WARNING LIGHT ILLUMINATED FOR APPROXIMATELY 90 SECONDS - CREW SELECTED "A"' PUMPS OFF AND SHUTDOWN BOTH ENGINES. AIRCRAFT TOWED TO THE GATE. MAINTENANCE INSPECTION REVEALED THE NR 1 GROUND SPOILER ACTUATOR CASING WAS CRACKED AND LEAKING. MAINTENANCE REPLACED THE ACTUATOR, SYSTEM GROUND CHECKED SERVICEABLE - NO LEAKS AND RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20030114002302003011400230CE 2003 1 14 CA021210008 120021206G2434646655 GEAR CONT CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL ALTERNATOR CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) GEAR TEETH FOUND CORRODED ON ALTERNATOR DRIVE HUB. CORRESPONDING DRIVE RING INSIDE ENGINE CHECKED OK. 1L72 3O3 O A25CE E7CE 5 CP45GL 20030114002322003011400232EU 2003 1 14 CA021210009 120021210G2842NB571261 TRANSMITTER BNORM BN2 BN2B21 7080221EU LYC O540 IO540K1B5 41532EA FUEL QTY FLOAT WORN W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) FIBRE FUEL LEVEL FLOAT WORE ON RIB INSIDE FUEL TANK SENDING SMALL PARTICLES THROUGH ENTIRE FUEL SYSTEM. 1H72 3O3 O A17EU 1E4 20030106002192003010600219CE 2003 1 6 CA021211001 120021201G55419763000017 SPAR BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL RUDDER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16909 (CAN) THE RUDDER WAS REMOVED DUE TO A DAMAGED SKIN. WHEN THE SKIN WAS REMOVED THE UPPER SPAR WAS FOUND CRACKED AT THE HOLE FOR A NUT PLATE TO ATTACH TO. THIS NUT PLATE IS USED TO HOLD THE UPPER HINGE TO THE RUDDER. SPAR WAS REPLACED 1L72 3T4 T A14CE E4EA 6 CP15EA 20030106002212003010600221CE 2003 1 6 CA021212002 120021202G5753501600183 FLAP TRACK BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA HARTZLHCB3T HCB3TN3 GL RT WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 16964 (CAN) THE RT OUTBOARD FLAP, INBOARD FLAP TRACK WAS FOUND CRACKED NOTE YOU CANNOT SEE THIS WHEN THE FLAP IS INSTALLED ON THE AIRCRAFT 1L72 3T4 T A14CE E4EA 6 CP15EA 20030210000832003021000083NM 2003 2 10 CA021213001 120021205G242260B400232 STATIC INVERTER BOEING737 737275 1384485NM PWA JT8 JT8D17A 52049NE STATIC INVERTER W O OTHER O OTHER ININSP/MAINT 1 CA 067C2191 (CAN) DATE OF REMOVAL NOV 25/02 DATE OF ARRIVAL IN SHOP SNAG DESCRIPTIONWHEN CONDUCTING W/C 12010 ITEM 8 B737 DAILY CHECK,STNDBY PWR CHECK AC VOLT METER FULL DEFLECTING RIGHT 130 VOLTS. #1 AND 2 AUTO XFMR C/B POPPED AND CADC AC & 26VAC C/BS POPPED, UNABLE TO RESET CADC C/BS.COMPONENT INFORMATION U.N.I. 24-22-0107 (P/N60B40023-2)DESCRIPTION INVERTER, STBY 500VA FTN R0G0A0 (S/N 067C-2191) TSV LAST REPAIR2001-06-27 FINDINGSSNAG TEST FINDINGSFAULT CONFIRMED REPAIRED BY IMPROVING MISCELLANEOUS SOLDERING ON THE CIRCUITS RELATED TO OUTPUT VOLTAGE LEVELS. FAULT CONFIRMED:AT INPUT VOLTAGE OF 24VDC AND INPU T CURRENT 1.5A, NO LOAD APPLIED THE FOLLOWING OBSERVATION WAS MADE: OUTPUT VOLTAGE 155 VACWAITED TWO MINUTESVOLTAG2L72 4F4 F A16WE E2EA 20030115000032003011500003NM 2003 1 15 CA021213005 120021129G2422DH1030246 INVERTER DHAV DHC8 DHC8201 2809001NM PWA 120 PW123D 52152NE HAMSTD14SF 14SF7 NE ELECTRICAL FAILED W O OTHER BGHSMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE ELECT. POWER LOSS-50 PC CLCLIMB 1 CA (CAN) JUST AFTER THE A/C BECAME AIRBORNE, CREW NOTED A SMOKE ODOR IN THE COCKPIT. PRIMARY INVERTER, DC CIRCUIT BREAKER OPENED. THE AUX AND SECONDARY INVERTER DC CIRCUIT BREAKERS OPENED ALMOST IMMEDIATELY THEREAFTER. BOTH 400HZ BUSSES, AND 26 VAC BUSSES BECAME UNPOWERED, WITH THE ASSOCIATED LOSS OF SERVICES. THE PRIMARY INVERTOR FAILED, THE AUX INVERTOR WAS SELECTED TO THE LT BUSS AT THE TIME. WHEN THE PRIMARY INVERTOR FAILED, THE SHORT CIRCUIT INTERNAL TO THE INVERTOR, DRAGGED DOWN THE AUX INVERTOR, AND IT ALSO WENT OFF LINE. THE REMAINING SECONDARY INVERTOR WAS UNABLE TO HANDLE THE ELECTRICAL LOAD AND IT ALSO DROPPED OFF LINE. THE BUSS TIE CIRCUIT BREAKER, (3.5 AMP, CB 14) DID NOT OPEN. INVERTOR REPLACED2H72 4T4 TRTA13NM E20NE 6 CP7NE 20030115000042003011500004EU 2003 1 15 CA021213007 220021113G8520888364 CRANKCASE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912S3 EU HOFMANHOV352HOV352F NE ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CRANKCASE APPEARED TO BE LEAKING OIL ABOVE AND BETWEEN NR 1 AND 3 CYLINDERS. CLEANING AREA AND RUNNING SHOWED MORE OIL COMING FROM THIS AREA. ENGINE COOLING SHROUD WAS REMOVED AND REVEALED A 3 INCH CRACK IN CASE. CASE WAS REPLACED WITH NEW AND ENGINE RETURNED TO SERVICE. 1L71 3O3 ONTTA4CH E00051EN5 CTP5BO 20030115000082003011500008SO 2003 1 15 CA021217002 120021214G329747936002 WIRE PIPER PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE DOWNLOCK SWITCH BROKEN W L ABORTED APPROACH N FALSE WARNING APAPPROACH 1 CA (CAN) ON FINAL APPROACH, PILOTS SELECTED GEAR DOWN. THREE GREEN INDICATION LIGHTS WERE CONFIRMED. THE GEAR HANDLE WOULD NOT COME BACK TO NEUTRAL. THE CREW CONDUCTED A MISSED APPROACHED AND PROCEEDED TO FOLLOW THE APPROPRIATE CHECKLISTS. THE CREW FLEW OVER THE CONTROL TOWER FOR GEAR DOWN CONFIRMATION. THE AIRCRAFT LANDED SAFELY AND WAS TOWED OFF RUNWAY. MAINTENANCE CONFIRMED BROKEN WIRE ON LT MAIN GEAR DOWN SWITCH.THE WIRE WAS REPAIRED, GEAR SWING CARRIED OUT, AND SYSTEM TESTED OK. THE AIRCRAFT WAS RELEASED FOR SERVICE. 1L72 3T4 TRTA8EA E4EA 20030115000092003011500009GL 2003 1 15 CA021217003 120021215G56102056000902 SPRING DIAMON DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU CANOPY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE RT SIDE CANOPY SPRING FAILED AT THE LOWER ATTACH POINT. THIS TYPE OF FAILURE HAS BEEN ROUTINELY OCCURING AROUND 800-1000 HOURS OPERATION. 1L71 3O3 ONTTA4CH E00051EN 20030115000162003011500016EU 2003 1 15 CA021218001 120021213G324221577 BRAKE ASSY AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE NR 3 FIRE W D RETURN TO BLOCK A FLAME/FIRE TXTAXI/GRND HDL 1 CA (CAN) NR 3 WHEEL OBSERVED SMOKING AS AIRCRAFT TAXIED TO GATE. THEN FLAMES WERE OBSERVED COMMING FROM BETWEEN WHEEL HUB SPOKES. CREW LOG REPORT STATED MEDIUM BRAKING AND IDLE REVERSE SELECTED FOR LANDING. DUE INOPERATIVE REVERSER NR 2. AFTER AIRCRAFT STOPPED AT GATE A SMALL BRAKE FIRE OCCURED. A FIRE EXTINGUISHER WAS DEPLOYED UNTIL NO FURTHER FLAMES WERE VISIBLE. NR 3 BRAKE ASSY AND NR 3 TIRE ASSY REPLACED AND LANDING GEAR WASHED WITH LOW PRESSURE. 1L72 4F4 FRTA46NM E39NE 20030115000232003011500023CE 2003 1 15 CA021219005 120021218G5520115610010125 STRUCTURE BEECH BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 18850 (CAN) DURING INSPECTION, THE TRAILING EDGE SPLINE ON THE ELEVATORS WERE FOUND CRACKED AT SEVERAL LOCATIONS, THIS IS THE 5TH SDR REGARDING THESE SPLINES AND A TOTAL OF 7 SPLINES FOUND CRACKED. THE ELEVATORS WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. WE ARE CURRENTLY CONDUCTING A FLEET INSPECTION. 1L72 3T4 T A14CE E4EA 20030131000062003013100006NE 2003 1 31 CA030102004 220020406G8500 ENGINE PIPER PA31 PA31 7103102SO LYC O540 TIO540J2B NE HARTZLHCC4Y HCC4YR2 GL RIGHT MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA L505361A (CAN) EVENT NR 2 INSPECTION, FOUND RT ENGINE METAL PARTICLES IN OIL FILTER, BETWEEN 20-40 PARTICLES. ENGINE SERVICED WITH 15W50 OIL. AIRCRAFT GROUND RUN AND LEAK CHECKED. ONE HOUR TEST FLIGHT, OIL CHECKED AFTER FLIGHT. AT 523.6 HOURS, CUSTOMER DECIDE NOT TO FLY AIRCRAFT. SENT ENGINE FOR OVERHAUL. AFTER ENGINE OVERHAUL, FOUND THAT THE ENGINE CAMSHAFT LOBES WERE WEARING OUT CAUSING METAL PARTICLES IN THE ENGINE OIL. 1L72 3O3 O A20SO E14EA 5 CP52GL 20030131000072003013100007 2003 1 31 CA030102006 420020604G6122H210800 GOVERNOR PIPER PA31 PA31 7103102SO LYC O540 TIO540J2B NE HARTZLHCC4Y HCC4YR2 GL PROPELLER MALFUNCTIONED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) SLIGHT RPM HUNTING ON RT ENGINE AT CLIMB OUT POWER. PROP GOVERNORS WERE SWITCHED TO SEE IF PROBLEM WOULD MOVE. ENDED UP SENDING GOVERNOR OUT FOR REPAIR. 1L72 3O3 O A20SO E14EA 5 CP52GL 20030131000082003013100008GL 2003 1 31 CA030103001 320021210G6111A5270 BEARING MCAULY3AF32C3AF32C505 GL PROP ASSY DENTED W K NONE O OTHER ININSP/MAINT 1 CA 941261 (CAN) AFTER DISASSEMBLY OF THE PROPELLER IT WAS NOTED THAT ALL THREE BLADE THRUST BEARINGS WERE BADLY DENTED, BEYOND REUSE. THE BEARINGS, LUBRICANTS, AND BALLS WERE ALL REPLACED AND THE PROPELLER WAS ASSEMBLED. 5 CP22EA 20030131000122003013100012EA 2003 1 31 CA030103009 220021223G8530L2W12397 CYLINDER DIAMONDA40 DA40 GL LYC O360 IO360A1A 41514EA ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT IN FOR NORMAL MAINTENANCE. LOW COMPRESSION ON NR 2 CYLINDER. REMOVED CYLINDER. DISCOVERED PITTING ON BARREL. SURFACE AND INTAKE VALVE WARPED.CYLINDERS NR 1, 3 AND 4 REMOVED ALSO FOUND PITTING, LYCOMING FACTORY TO SUPPLY 4 NEW CYLINDER ASSEMBLIES. 1L71 3O3 ONTA47CE 1E10 20030131000132003013100013GL 2003 1 31 CA030103010 120021220G7810 EXHAUST PIPE DIAMONDA40 DA40 GL LYC O360 IO360A1A 41514EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT IN FOR NORMAL MAINTENANCE INSPECTION REVEALED EXHAUST PIPES CRACKED AT ALL FOUR EXHAUST FLANGES. 1L71 3O3 ONTA47CE 1E10 20030131000142003013100014CE 2003 1 31 CA030103011 120021223G575155240051 SKIN CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE LT AILERON CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TWO OF THE BALANCE WEIGHT ATTACHMENT SCREW HOLE HAD 1/2 INCH CRACKS STARTING FROM UNDER THE SCREW HEADS. 1L72 4F4 F A22CE E1NE 20030131000292003013100029CE 2003 1 31 CA030103017 120021205G532050110117 SUPPORT CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 17944 (CAN) INSPECTION REVEALED PILOT SEAT SUPPORT STRUCTURES CRACKED, GUSSET ASSY LT OUTBOARD, AND GUSSET ASSY LT INBOARD. INBOARD GUSSET CRACKED IN INBOARD FLANGE RADIUS ATTACHMENT TO FLOOR, OUTBOARD GUSSET CRACKED ON TOP SURFACE RUNNING THROUGH TWO ANCHOR NUTS, AND OUTBOARD RADIUS ON ATTACHMENT TO FLOOR, ILLUSTRATION REFERENCE 53-40-00, FIGURE 01. 1L72 3O3 O A7CE E8CE 5 CP22EA 20030115000682003011500068EA 2003 1 15 CA030103019 220021206G8520STD2209 BOLT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA CRANKSHAFT GEAR SHEARED W A UNSCHED LANDING RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA (CAN) PILOT WAS IN CRUISE FLIGHT WHEN HE FELT A SURGE IN POWER ON THE LT ENGINE AND SUDDEN LOSS OF RPM, ATTEMPTED TO SWITCH TANKS AND NOTHING HAPPENED, FEATHERED PROP AND SHUT ENGINE DOWN. PILOT FLEW TO AIRPORT AND LANDED SAFELY ON RT ENGINE. AN ENGINE RESTART WAS ATTEMPTED ON THE GROUND AND NOTHING HAPPENED. THE PROP WAS TURNED BY HAND AND NO COMPRESSION WAS FELT. THE REAR ACCESSORY SECTION WAS REMOVED AND FOUND CRANKSHAFT GEAR BOLT SHEARED AND GEAR TEETH BROKEN OFF. TOTAL TIME ON ENGINE 1100 HOURS, 400 HOURS SINCE BULK DISASSEMBLY AFTER PROP STIKE, 40 HOURS SINCE AD 02-20-51AND SB 554 AND 475B WAS C/W. 1L72 3O3 O A20SO E14EA 20030131000412003013100041NM 2003 1 31 CA030103022 120021126G242260B400232 STATIC INVERTER BOEING737 737275 1384485NM PWA JT8 JT8D17A 52049NE AC SYS MALFUNCTIONED W K NONE S AFFECT SYSTEMS ININSP/MAINT 1 CA (CAN) WHEN CONDUCTING AN EMERGENCY POWER CHECK THE AC VOLT METER WENT FULL DEFLECTION TO 130 VOLTS. NR 1 AND 2 AUTO TRANFORMER C/B POPPED AND CADC AC AND 26 VAC C/B'S POPPED. SHOP REPORT CONFIRMED THE FAULT THAT THE INVERTER WAS PUTTING OUT 155 VAC. THIS WAS BELIEVED TO BE DUE TO POOR SOLDER CONNECTIONS WITHIN THE INTERNAL CIRCUIT BOARDS. 2L72 4F4 F A16WE E2EA 20030131000992003013100099CE 2003 1 31 CA030106018 120020720G281004265126 STRAP CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA RT AFT FUEL TANKBROKEN W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) FUEL LEAK. RT WING. UPON REMOVAL OF THE FUEL TANK WING PANEL, DISCOVERED THE AFT FUEL TANK STRAP TO BE BROKEN. DUE TO THE BROKEN STRAP THE SCREEN ASSEMBLY HAD CHAFED THROUGH THE TOP OF THE FUEL TANK CAUSING A FUEL LEAK. FUEL TANK REPAIRED AT AN APPROVED REPAIR SHOP. NEW STRAP AND SCREEN ASSEMBLY INSTALLED CARRIED OUT FUEL TANK INSTALLATION AS PER CESSNA MAINTENANCE MANUAL AND ALL SYSTEM CHECKED SERVICEABLE AND AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3O3 ONT3A19 E223 20030131001072003013100107SO 2003 1 31 CA030107010 120020120G32206705403 TRUNNION PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA NLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION, NOSE GEAR TRUNION FOUND CRACKED AROUND UPPER RT ATTACHMENT. 1L71 3O3 O 2A13 1E10 20030131001092003013100109SO 2003 1 31 CA030107011 120020801G55201279004 STRUCTURE PIPER PA18 PA18 7101802SO LYC O320 O320A2B 41508EA ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT STABILIZER REAR TUBE WAS FOUND CRACKED INBOARD OF THE OUTBOARD ELEVATOR HINGE. 1H71 3O3 O 1A2 E274 20030131001102003013100110CE 2003 1 31 CA030107012 120021206G551104320016 RIB CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13957 (CAN) RT HORIZONTAL STAB RIB WAS FOUND CRACKED. 1H71 3O3 ONT3A19 E223 20030131001152003013100115EA 2003 1 31 CA030107013 220021220G8520 CRANKCASE PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA RT ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WHILE CONDUCTING A DAILY INSPECTION, IT WAS NOTED THAT THE RT ENGINE NACELLE WAS FULL OF OIL. WITH THE COWLING REMOVED AN INSPECTION OF THE ENGINE WAS CARRIED OUT. A CRACK WAS FOUND ON THE RIGHT SIDE OF THE CRANKCASE AT THE FORWARD CYLINDER, LOWER FORWARD STUD (FORWARD OF CYLINDER NR 2). 1L72 3O3 O A20SO E14EA 20030121002532003012100253NE 2003 1 21 CA030107017 220021221G7250 BLADE DOUG DC9 DC983 3022083WP PWA JT8 JT8D219 52053NE NR 1 TURBINE DAMAGED W A UNSCHED LANDING DR INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS CRCRUISE 1 CA 13140 (CAN) ON ROUTE TO YVR FROM YYZ AT 130 NM FROM YYC HEARD LOUD BANG, FOLLOWED BY NR 1 ENGINE EPR DROP TO ZERO N1-N2 SPEED DECREASING. ENGINE RETARDED TO IDLE. PARAMETERS WITHIN LIMITS. DIVERTED TO YYC. PRELIMINARY INSPECTION REVEALS DAMAGED TURBINE BLADES. ENGINE WILL BE SENT TO SHOP FOR INVESTIGATION AND REPAIR. 2L72 4F4 FRTA6WE E9NE 20030131001362003013100136SO 2003 1 31 CA030107018 120021224G21403716742 LINE PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360E 17025SO HEATER FUEL CORRODED W K NONE KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS ININSP/MAINT 1 CA (CAN) DURING A GROUND RUN FOR CALIBRATION OF AN UNRELATED SYSTEM THE ENGINEER NOTICED A STRONG FUEL SMELL IN THE CABIN. THE SOURCE WAS FOUND TO BE A CORRODED HEATER FUEL LINE AT APPROXIMATELY FS 165. THE CARPET AHEAD OF PASSENGER SEAT NR 6 WAS SOAKED WITH FUEL. 1L72 3O3 O A7SO E9CE 20030131001432003013100143GL 2003 1 31 CA030108001 220021212G7321 FUEL CONTROL BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL ENGINE MALFUNCTIONED W BA EMER. DESCENT UNSCHED LANDING FJ FLT CONT AFFECTED WARNING INDICATION DEDESCENT 1 CA (CAN) NORMAL TAKEOFF. AFTER REDUCING COLLECTIVE TO 70 PERCENT, TURBINE AND ROTOR RPM AT 105 PERCENT. BEEPED DOWN WITH NO RESPONSE, COLLECTIVE WAS LOWERED TO SLOW DOWN AND ROTOR RPM WAS NOW 115-120 PERCENT. PILOT ROLLED BACK THROTTLE TO DISENGAGE GOVERNOR, RPM REMAINED AT 115-120 PERCENT. THROTTLE WAS NOW AT FLIGHT IDLE WITH RPM AT 115-120 PERCENT. REDUCED AIRSPEED TO 60 MPH AND DESCENDED. AT APPROX. 300 FT, ENGINE SLOWED DOWN, FULL THROTTLE WAS APPLIED AND 100 PERCENT ROTOR RPM WAS REACHED & STABLE. ALL TEMPS AND RPMS WERE NORMAL, FLT WAS CONTINUED FOR 8 MINUTES BACK TO CAMP. ROTOR RPM WAS BETWEEN 115-120 PERCENT FOR 20-30 SECONDS. AFTER INSPECTING OIL LEVELS AND CHIP DETECTORS, CONTINUED FLT. 1G71 3U3 UNCH2SW E1GL 20030131001512003013100151SW 2003 1 31 CA030108004 120021203G281043122 ADAPTER MOONEYM20 M20C 5870208SW LYC O360 O360A1D 41514EA FUEL CAP CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION CORROSION WAS FOUND IN THE AREA OF THE ADAPTER FOR THE FUEL FILLER CAP WHERE THE O-RING SEALS AGAINST WATER ENTERING THE FUEL TANK. 1L71 3O3 O 2A3 E286 20030131001532003013100153NE 2003 1 31 CA030108006 220021206G7314AN4101 PUMP AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67 52043NE ENG DRIVEN FUEL LEAKING W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A FUEL LEAK WAS DETECTED DURING ANNUAL INSPECTION IN THE PLENUM CHAMBER AREA. IT WAS TRACED TO THE ENGINE DRIVEN FUEL PUMP. 1L71 3T4 TNCA19SW E26NE 20060612003552006061200355CE 2006 6 12 CA030108008 120021211G3110S18802 RHEOSTAT CESSNA172 172I 2072426CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL INSTRUMENT PANELFAILED W O OTHER O OTHER NRNOT REPORTED 1 CA THIS 'SDR' IS BEING RAISED BECAUSE OF AD 93-24-15 AND SEB92-33R1 REGARDING INSTRUCTIONS OF RHEOSTAT P/N RD-0015H-1600. WHEN AN AD IS ISSUED, AS THIS ONE WAS, REGARDING AN IMPROVED PART THE REGULATORY BODY SHOULD ENSURE PARTS CATALOGS OR MAINTENANCE MANUALS ARE CHANGED TO REFLECT THESE CHANGES. SHOULD THIS PART BE REQUIRED IN THE FUTURE, IT IS POSSIBLE FOR THE PART LISTED IN THE PARTS CATALOG BE ORDERED AND INSTRUCTED, WHICH WOULD INVALID THE AD ALAREADY ENTERED IN THE TECH LOGS AS BEING CARRIED OUT, THUS REINTRODUCING THE ORIGINAL PROBLEM BACK INTO THE AIRCRAFT. 1H71 3O3 ONT3A12 E274 5 NP910 20060612003562006061200356EU 2006 6 12 CA030108012 120021227G30109598901014 TIMER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL DE-ICE SYS ERRATIC W O OTHER J WARNING INDICATION CRCRUISE 1 CA 8 THIS DE-ICE TIMER WAS RECEIVED WITH AN "INSPECTED" TAG. AFTER INSTALLATION, THE SYSTEM FAILED AFTER 7.7HRS. INVESTIGATION REVEALED THAT THE TIMER WOULD "CHATTER" AND THE BOOT INFLATION SEQUENCE WOULD BECOME ERRATIC. THE TIMER WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20060619002442006061900244WP 2006 6 19 CA030108017 120021214G6420 TAIL ROTOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL DEPARTED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) AC WAS AT A HEIGHT OF 6-10 FT ABOVE GROUND TRAVELING AT 20MPH IN CROSSWIND. AT TIME OF PROBLEM, FAIR AMOUNT OF LT PEDAL WAS BEING USED. AC TRAVELED APPROX 30FT CROSSWIND WHEN LOUD BANG WAS HEARD BY PILOT FOLLOWED BY T/R ASSY FLYING PASSED PILOTS CHIN BUBBLE. PILOT ROLLED THROTTLE OFF TO STOP ROTATION OF AC, LANDED AC ON A NEARLY LEVEL OR FAIRLY LEVEL SPOT. AC HAD COMPLETED ONE HALF OF A REVOLUTION BY TIME PILOT GOT IT ON GROUND. NO FURTHER DAMAGE TO AC. WIND: SOUTH 20KMH. ELEVATION: 8000FT. TOTAL TIME: 13000HRS. TT ON TYPE: 6000HRS. PILOT OBSERVATION: IT APPEARS TO ME THAT THE T/R GEARBOX BLEW APART. AT NO TIME DID THE T/R COME IN CONTACT WITH THE GROUND OR SNOW. (TC NR 20030108017) 1G71 3U3 U H3WE E4CE 20030203000032003020300003SW 2003 2 3 CA030110003 120020718G323052002503 PIVOT ASSY MOONEYM20 M20M 5870222SW LYC O540 TIO540AF1A 41532EA MCAULY3D32C B3D32C417 GL LT MLG SEIZED W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) THE LT MLG HAD FAILED TO EXTEND. UPON EXAMINATION IT WAS FOUND THAT THE HINGE PIVOT POINT BETWEEN THE SHOCK STRUT AND GEAR LEG SPINDLE ASSEMBLY WAS SEIZED DUE TO A LACK OF LUBRICATION. THIS CAUSED THE MLG LEG TO RETRACT IMPROPERLY AND JAMMED IN THE WHEEL WELL. EXAMINATION ALSO REVEALED A LACK OF A GREASE FITTINGS FOR THE BEARING SURFACE. LUBRICATION OF THIS PIVOT POINT WAS EFFECTIVELY IMPOSSIBLE. THE SEIZURE RESULTED IN A GEAR UP LANDING. 1L71 3O3 ORT2A3 E14EA 5 CP58GL 20030203000152003020300015EU 2003 2 3 CA030112009 120021227G793111346AA TRANSMITTER AMD FALCONFALCON20 2730103EU GE CF700 CF7002D2 30010NE RT ENGINE OIL FALSE INDICATIONW CD ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TOTAKEOFF 1 CA (CAN) DURING TAKE-OFF ROLE THE PILOT IN COMMAND NOTICED OIL PRESSURE FLUCTUATION OF THE RT ENGINE. THE PILOT IN COMMAND INITIATED REJECTED TAKE-OFF. AT THIS TIME, THE FLIGHT CREW ADVISED ATC AND RETURNED TO THE MAINTENANCE FACILITY. OUR CONTRACTED AMO HAS DETERMINED THAT THE OIL PRESSURE TRANSMITTER IDENTIFIED AS AT FAULT, THEREFORE GIVING A FALSE OIL PRESSURE INDICATION TO THE FLIGHT CREW. THE OIL PRES SURE TRANSMITTER WAS REPLACED WITH A SERVICEABLE UNIT. THE AIRCRAFT WAS GROUND RUN SATISFACTORILY AND WAS RETURNED INTO SERVICE TO RESUME OPERATIONS. 2L72 4F4 FRTA7EU E7EA 20030203000192003020300019EA 2003 2 3 CA030113003 220021128G7530 LINE BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA RT ENG P3 SUPPLYBLOCKED W A UNSCHED LANDING RAJPARTIAL RPM/PWR LOSS FLAME/FIRE WARNING INDICATION CLCLIMB 1 CA PCE52432 (CAN) AFTER TAKEOFF IN THE CLIMB THROUGH 15,000 FT THE RT ENGINE EXPERIENCED THREE MAJOR SURGES WITH FLUCTUATIONS OF TORQUE, NG, ITT, AND FUEL FLOW ALONG WITH FLAMES SHOOTING FROM THE ENGINE EXHAUST. AFTER EXTENSIVE TROUBLESHOOTING THE ENGINE WAS DEEMED TO BE INTERNALLY AT FAULT. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED BACK TO SERVICE. THE ENGINE REMOVED WAS FOUND TO HAVE A PARTIAL BLOCKAGE OF THE P3 SUPPLY TUBE TO THE BLEED OFF VALVE. THE BLOCKAGE WAS CLEARED AND THE ENGINE RETESTED SATISFACTORY AT THE REPAIR FACILITY. 1L72 3T4 T A14CE E4EA 20060612003642006061200364WP 2006 6 12 CA030113012 120021214G2810 FUEL TANK LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE CONTAMINATED W O OTHER W INADEQUATE Q C CRCRUISE 1 CA TANK 2R INBD, QTY HIGHER THAN NORMAL WITH QTY SWITCH LIGHT LATCHED IN. FUEL QTY GAUGES OK. INBD QTY READS 4000 LBS, WITH TOTAL BELOW 7000LBS. PER FAULT ISOLATION AMM 28-27-00 P 107, REPLACED BOOST PUMP CHECK VALVES PER AMM 28-24-03 (NIL FIX). FUEL WAS STILL TRANSFERRING FROM OUTER INTO INNER TANK (GRAVITY FLOW). FAULT FOUND TO BE A PAPER TOWEL (FACE WIPE) LOGGED IN THE FWD FLAPPER CHECK VALVE OF THE TANK 2R INNER TANK/BOOST PUMP BOX. PAPER TOWEL REMOVED AND TANK 2R TRANSFER CHECKED SERVICEABLE PER AMM 28-27-00. 2L73 4F4 F A23WE E12EU 20030203000302003020300030CE 2003 2 3 CA030114005 120021231G2121115384007 BLOWER BEECH 99 99 1154002CE PWA PT6 PT6A28 EA COCKPIT FAILED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT WAS TAXING FROM TERMINAL TO RUNWAY WHEN SMOKE STARTED FILLING COCKPIT. ELECTRICAL COMPONENTS WERE TURNED OFF AND AIRCRAFT RETURNED TO TERMINAL. MAINTENANCE WAS CONTACTED AND FORWARD VENT BLOWER WAS REPLACED. GROUND CHECKED SERVICEABLE. 1L72 3T4 T A14CE E4EA 20030212000562003021200056CE 2003 2 12 CA030115002 120021205G37101U128006 PUMP CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL VACUUM SYSTEM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE SCHEDULED OPERATION NR 2 ENGINE OF THE AIRCRAFT. A CRACK WAS NOTED ON THE ENGINE ATTACH BRACKET OF THE INSTALLED VACUUM PUMP. UPON REMOVAL OF THE PUMP IT WAS DISCOVERED THAT THE ENTIRE ATTACH BRACKET WAS COMPLETELY SEPARATED FROM THE PUMP. FLIGHT CREW HAD NOT NOTED ANY FAILURE AND REPORTED THAT INSTRUMENT AIR PRESSURE WAS NORMAL WHILE IN FLIGHT. THE DAMAGED PUMP WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. 1H71 3O3 O A4CE E5CE 5 CP47GL 20060612003662006061200366GL 2006 6 12 CA030115007 220021223G7310AN21220D FITTING CVAC 340 340CVAC 242270AWP ALLSN 501D 501D22 03005GL HAMSTD54H 54H60 NE HOSE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA TWO HOSE ASSEMBLIES (390A20D4.8 AND 390A20D12.5) FROM A FUEL SUPPLY "Y" MANIFOLD WAS REMOVED AND ROUTED TO OUR INTERNAL OVERHAUL SHOP FOR REPLACEMENT OF THE HOSES. UPON DISASSEMBLY, IT WAS DISCOVERED THAT THREE OF THE FOUR FITTINGS (SOCKETS) (AN212-20D) WERE CORRODED AND CRACKED LONGITUDINALLY. ONE WAS CRACKED ON BOTH SIDES OF THE FITTING (ACTUALLY SPLIT IN TWO), THE OTHER TWO WERE CRACKED ON ONE SIDE ONLY WHERE THE FIRE SLEEVES COVER THE FITTINGS. IT WOULD APPEAR THAT THE FIRE SLEEVES TRAPPED MOISTURE AND THUS CORRODED THE FITTINGS. UNFORTUNATELY, THERE ARE NO PHOTOS AVAILABLE AS THE FITTINGS WERE DISCARDED ACCIDENTALLY. PLEASE REFER TO THE PICTURES FROM SDR 20030115004 FOR IDENTICAL PARTS AND CONSISTENT 2L72 4R4 T 6A6 E282 6 CP906 20060612003682006061200368EU 2006 6 12 CA030115009 120021209G5240A5247007020200 PANEL AIRBUS310 A310300 3930305EU GE CF6 CF680C2* GL MISSING W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CA UPON A/C ARRIVAL FROM FLIGHT, FOUND ON WALK AROUND 3 MISSING PANELS (PANELS 134ER; P/N A5247007020600, 134CR; P/N A5247007020200, 134DR; P/N A5247007020400). HOLDING BRACKETS THOSE PANELS WERE ALSO FOUND TO BE DAMAGED. NEW HOLDING BRACKETS WERE FABRICATED IAW SRM 51-72-10 AND PANELS INSTALLED IAW AMM 53-13-00. THESE PANELS ARE OFTEN HIT BY CARGO LOADING EQUIPMENT OR STEPPED ON BY THE CARGO HANDLERS. 2L72 4F4 FRTA35EU E23EA 20030203000362003020300036EA 2003 2 3 CA030116004 220021224G85205L13792 SEAL ZLIN 242 Z242L 9970204EU LYC O360 AEIO360A1B6 41514EA CRANKSHAFT BLOWN W A UNSCHED LANDING KRJFLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) FRONT CRANKSHAFT SEAL BLOWN OUT DUE TO FROZEN ENGINE VENT LINE CANISTER. VENT SYSTEM PURGED AND CLEANED CRANKSHAFT SEAL RESEATED. ENGINE RUN-UP AND OIL FILTERS SERVICEABLE (NO METAL). 1L71 3O3 O0 A76EU 1E10 20030213000052003021300005EU 2003 2 13 CA030121005 220021113G8530854116 EXHAUST VALVE ROTAX DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912S3 EU NR 1 CYLINDER BROKEN W A UNSCHED LANDING ERYVIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CLCLIMB 1 CA (CAN) EXHAUST VALVE IN NR 1 CYLINDER BROKEN AT AREA BETWEEN STEM AND HEAD OF VALVE. VALVE DROPPED INTO COMBUSTION AREA AND CAUSED PISTON DAMAGE AND EVENTUALLY ENGINE STOPPAGE. VISIBLE WEAR ON VALVE TRAIN COMPONENTS CONSISTENT WITH IMPROPER PURGING OF LIFTERS AS ADDRESSED BY SB-912-036. NO ENTRY IN ENGINE LOG BOOK TO SHOW COMPLIANCE TO SB-912-036 OR AD-113. AD WAS RELEASED 2 MONTHS BEFORE OCCURRANCE DATE. 1L71 3O3 ONTTA4CH E00051EN 20030210000902003021000090GL 2003 2 10 CA030122004 320021204G6114 PROPELLER MCAULY 3AF32C504C CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL PROPELLER W K NONE K FLUID LOSS ININSP/MAINT 1 CA 941261 (CAN) NUMBER 1 BLADE WAS LEAKING OIL FROM THE HUB. PROP WAS REMOVED AND SENT TO O/H SHOP. SEAL IN HUB WAS FOUND TO BE LEAKING. SEAL REPLACED -PROP WAS REINSTALLED. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20060612004212006061200421CE 2006 6 12 CA030122005 120021216G7931264600053 INDICATOR CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL OIL PRESSURE READS HIGH W C ABORTED TAKEOFF N FALSE WARNING TOTAKEOFF 1 CA 1095 AT HIGH RPM, THE OIL PRESSURE GAUGE WAS READING PAST THE RED LINE. ENGINE OIL PRESSURE WAS CHECKED USING EXTERNAL GAUGE FOUND TO BE WITHIN MANUFACTURES LIMITS. OIL PRESSURE GAUGE WAS REPLACED. THE OLD GAUGE WAS INSPECTED AND NOTHING COULD BE SEEN CAUSING THE PROBLEM. OIL PRESSURE LINE WAS CLEANED OUT AND NOTHING WAS FOUND IN IT OTHER THAN OIL. 1H71 3O3 ONT3A12 E274 5 NP910 20030213000282003021300028EA 2003 2 13 CA030128003 220021218G7322105267 CARBURETOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE MALFUNCTIONED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) ROUGH RUNNING ENGINE WAS NOTICED IN FLIGHT. PILOT THOUGHT IT WAS CARB ICE TRIED TO CLEAR IT OUT BY USING CARB HEAT. THIS DID NOT WORK, SO HE CAME BACK TO THE HANGER. AIRCRAFT WAS BROUGHT BACK INTO THE HANGER, ALL THE PLUGS WERE CLEANED. THEY WERE FULL OF LEAD, THE MAGNETO TIMING WAS CHECKED BUT IT WAS OKAY. AIRCRAFT WAS TAKEN OUTSIDE AND RAN UP, ENGINE WAS STILL RUNNING ROUGH SO IT WAS BROUGHT BACKIN AGAIN. ANOTHER CARB WAS INSTALLED AND AIRCRAFT WAS RUN UP AGAIN THIS TIME THE ENGINE RAN SMOOTH. CARB WAS SENT OUT FOR REPAIRS NOTHING OBVIOUS WAS FOUND AT THE ENGINE SHOP. ENGINE SHOP REPLACED THROTTLE SHAFT BUSHINGS. OTHER THAN THAT IT WAS IN GOOD SHAPE. 1H71 3O3 ONT3A19 E223 20030326000632003032600063 2003 3 26 CA030204012 420021128G23975136738 WIRE CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO MCAULYD3A34 D3A34C403 GL RADIO MASTER OVERHEATED W K NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA (CAN) LUG IMPROPERLY CRIMPED TO WIRE PA-6 AT RADIO MASTER SWITCH CAUSING AN OVERHEAT SITUATION WITH EVENTUAL SEPARATION OF WIRE FROM LUG. WIRE WAS ORIGINAL FROM CESSNA FACTORY INSTALLATION. 1H71 3O3 O 3A24 E5CE 5 CP47GL 20030213000512003021300051SO 2003 2 13 CA030205008 120020116G8120 HOUSING GARRTT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA TURBOCHARGER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA KHR0371 (CAN) DURING A DETAILED ENGINE INSPECTION, A CRACKED TURBOCHARGER HOUSING WAS DISCOVERED. POSSIBLE TURBOCHARGER BEARING WEAR ON INSPECTION WAS INVESTIGATED AND AFTER REMOVAL OF THE TURBO HEATBLANKET, A CRACK WAS FOUND IN THE TURBOCHARGER HOUSING INCLUDING HEAT DAMAGE TO THE BLANKET. AN OVERHAULED TURBOCHARGER AND NEW HEAT BLANKET WAS INSTALLED. 1L72 3O3 O A20SO E14EA 20030414000992003041400099EU 2003 4 14 CA030228003 120021212G32225322012200 GUIDE PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG FAILED W O OTHER D INFLIGHT SEPARATION LDLANDING 1 CA (CAN) LOUD UNUSUAL SOUND FROM NOSE GEAR WHEN SELECTED DOWN. - FOUND NOSE GEAR OLEO NOT EXTENDING COMPLETELY.- NOSE LANDING GEAR FORK RUBBED ON NOSE GEAR DOOR ACTUATING ROD. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030414001022003041400102CE 2003 4 14 CA030228008 120021015G534307900065 BRACKET CESSNA180 180 2072602CE CONT O470 O470K 17026SO LT MLG LEG CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION OUTER GEAR LEG BRACKET FOR LT MAIN GEAR WAS FOUND SEVERELY CORRODED. CORROSION HAD CAUSED SEVERE EXFOLIATION. SUSPECT CORROSION INDUCED FROM ENGINE EXHAUST ENTERING AREA. OUTSIDE COVER WAS NOT SEALED WHICH ALLOWED EXHAUST TO ENTER AND CAUSE CORROSION. PART REPLACED WITH NEW. 1H71 3O3 ONC5A6 E273 20030414001032003041400103CE 2003 4 14 CA030228009 120021015G575105238161 HINGE CESSNA180 180 2072602CE CONT O470 O470K 17026SO AILERON SEIZED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING INSPECTION AILERONS WERE ACTUATED FROM THE CONTROL COLUMN AND AILERON MOVEMENT WAS FOUND TO BE SPRINGY. VISUAL INSPECTION OF BOTH AILERONS CONFIRMED HINGE PINS WERE SEIZED AND NOT ALLOWING THE HINGE TO MOVE. NEW HINGES INSTALLED. 1H71 3O3 ONC5A6 E273 20030414001062003041400106NE 2003 4 14 CA030228014 220021203G85503034292 OIL FILTER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL ENGINE CLOGGED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) OIL PRESSURE FLUCTUATION IN FLIGHT. FOUND OIL FILTER PLUGGED WITH CARBON. OIL FILTER REPLACED. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030414001202003041400120CE 2003 4 14 CA030306001 120021215G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT FAILED W A UNSCHED LANDING D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) IN FLIGHT THE WINDOW SUDDENLY SHATTERED WITH A LOUD BANG. 1L72 4T4 T A24CE E4EA 20030409000232003040900023EU 2003 4 9 CA030312010 120020813G2750 CONTROL QUADRANT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FLAP SYSTEM FAILED W J DUMP FUEL A FLAME/FIRE CLCLIMB 1 CA (CAN) AFTER TAKEOFF THE PILOT SELECTED FLAPS UP. A FLAP WARNING LIGHT ILLUMINATED AND THE FLAPS DID NOT MOVE. (FLAPS REMAINED AT 15 DEGREES). THE PILOT RETURNED TO LAND AT THE AIRPORT WITHOUT INCIDENT. A FLAP RESET WAS CARRIED OUT ON THE GROUND SERVICEABLE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20030414000402003041400040CE 2003 4 14 CA030312013 120020110G575358250057 SKIN CESSNA441 441 2076020CE GARRTTTPE331TPE331* 01514WP HARTZLHCB3T HCB3TN5 GL TE FLAPS DELAMINATED W O OTHER O OTHER NRNOT REPORTED 1 CA (CAN) THE LT INBOARD FLAP WAS DISCOVERED PARTIALLY SEPARATED ON THE TOP SURFACE OF THE COMPOSITE STRUCTURE WHERE A NON CONFORMANT REPAIR (AS INDICATED IN THE APPLICABLE MANUAL) WAS CARRIED OUT. THIS REPAIR SEEMS TO HAVE BEEN DONE WITHOUT ANY DOCUMENTATION.THE RT INBOARD FLAP IS STARTING TO DELAMINATE. IT HAS NO TRACES OF WORK CARRIED OUT ON THE FLAP SURFACE. THE DELAMINATED SURFACE IS IN THE SAME LOCATION AS THE LT FLAP. 1L72 3T3 TRTA28CE E2WE 6 CP15EA 20030507001162003050700116EA 2003 5 7 CA030417006 120020625G5741 BUSHING CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE WING ATTAHCMENT LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MIGRATING BUSHINGS ON WING ATTACHMENT FITTINGS. 2L72 4F4 FRTA21EA E15NE 20030609001832003060900183EA 2003 6 9 CA030502002 220020816G74144371 MAGNETO CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE FAILED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) ROUGH RUNNING ENGINE DUE TO LT MAGNETO MALFUNCTION. INTERNAL DEFECTS, THEREFORE EXACT MALFUNCTION UNKNOWN. 1H71 3O3 ONT3A12 E274 5 NP910 20030506002552003050600255EA 2003 5 6 CA030505001 120020529G5610NP1393221 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT FAILED W O OTHER O OTHER APAPPROACH 1 CA (CAN) LT SIDE WINDOW SHATTERED IN FLIGHT. AIRCRAFT LANDED IN CINCINNATI WITHOUT FURTHER INCIDENT.WINDOW REPLACED, AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20030821000842003082100084SO 2003 8 21 CA030506003 220020623G8550646277 LIFTER CONT O470 IO470L 17026SO ENGINE WRONG PART W O OTHER W INADEQUATE Q C NRNOT REPORTED 1 CA 454939CS (CAN) A/C EXPERIENCED ENG OIL PRESS PROBLEM. TROUBLESHOT & CONSULTED WITH O/H SHOP, UNABLE TO RECTIFY OIL PRESSURE PROBLEM. ENGINE REMOVED/OVERHAULED & INSTALLED. ENG HAD OVER MAX OIL PRESSURE (100 PSI) AT HIGHER RPM SETTING, AT IDLE, OIL PRESSURE WOULD DROP BELOW NORMAL OPERATING RANGE AIRCRAFT WAS GROUNDED. AFFECTED ENGINES SENT TO ANOTHER OVERHAUL FACILITY FOR ANALYSIS AND REPAIR.ENGINE DISASSEMBLED, DISCOVERED 12 IMPROPER VALVE LIFTERS 646277 HAD BEEN INSTALLED. O/H SHOP CONFIRMED THIS WOULD CAUSE POOR OIL PRESSURE. ENGINE REPAIRED AND TESTED AFTER RE-ASSEMBLY, OIL PRESSURE READINGS WERE EXCELLENT. 3 O 3E1 20030617000752003061700075EA 2003 6 17 CA030526006 220020422G74144381 MAGNETO CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING RUN UP IGNITION SYSTEM CHECK REVEALED POWER LOST ON RT MAGNETO. UNIT REPLACED WITH SERVICEABLE MAGNETO AND GROUND RUN OK. UNIT SENT BACK FOR CREDIT THUS INTERNAL PROBLEM IS UNKNOWN AT THIS TIME. 1H71 3O3 ONT3A19 E223 20030703000532003070300053NE 2003 7 3 CA030526009 220020603G7414SKL32138AN PLUG C2N2181A DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE HARTZLHCB3R HCB3R304 GL MAGNETO SHORTED W AB UNSCHED LANDING EMER. DESCENT Y ENGINE STOPPAGE CRCRUISE 1 CA (CAN) THE ENGINE QUITE IN CRUISE AND THE PILOT MADE A DEAD STICK LANDING ONTO THE WATER. UPON INSPECTION FOUND THE SAFETY GROUNDING TAB IN THE FIREWALL PLUG APPEARED TO BE BROKEN OFF AND FELL ACROSS THECONTACT PINS, SHORTING OUT BOTH MAGS. NOT SURE BECAUSE THE PLUG WOULD HAVE TO BE DESTROYED TO GET IT APART. 1H71 3R3 R A806 5E1 5 CP28EA 20030703000232003070300023EU 2003 7 3 CA030602003 120020529G1430LN93556X32 BOLT BOLKMS105 BO105C 5626005EU ALLSN 250C 250C20B 03013GL HYD PACK INCORRECT W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE COMPLYING WITH FLEET CAMPAIGN NOTICE 351-73-20-12 IT WAS FOUND THAT THE BOLT CONNECTING THE TWO NR 2 GOVERNOR CABLES TO THE HYDRAULIC PACK WAS TOO SHORT ONLY ONE THREAD WAS SHOWING THROUGH THE ANCHOR NUT. A NEW BOLT WAS INSTALLED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1G72 3U3 U H3EU E4CE 20030703000012003070300001EU 2003 7 3 CA030605002 220021111G8530 EXHAUST VALVE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU NR 1 CYLINDER DESTROYED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 CA (CAN) EXHAUST VALVE ON NR 1 CYLINDER FAILED ON TAKEOFF CAUSING IT TO FALL INTO THE COMBUSTION CHAMBER WHERE IT CAME INTO CONTACT WITH PISTON AND INTAKE VALVE CAUSING EXTENSIVE DAMAGE TO CYLINDER WALL AND DESTROYING PISTON. ENGINE SEIZED CAUSING CONNECTING ROD TO TWIST AND CRACK. CYLINDER BASE FLANGE AT TOP OF ENGINE WAS ALSO DAMAGED LEAVING A HOLE IN ENGINE CASE JUST BEHIND NR 1 CYLINDER. 1L71 3O3 INTTA4CH EXPE3I 20030703000462003070300046SW 2003 7 3 CA030610003 120020301G6520209011710005 TUBE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE T/R GEARBOX CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE TUBE ASSEMBLY WAS REMOVED DURING A NORMAL INSPECTION AND FOUND TO HAVE EXCESSIVE WEAR ON THE SEAL JOURNAL. THE TUBE WAS SENT TO A REPAIR STATION TO HAVE THE JOURNAL REPLATED IAW TB 205-91-89. THE TUBE WAS INSPECTED BY MAGNETIC PARTICAL INSPECTION PRIOR TO REPLATING. A CRACK WAS DISCOVERED AND THE TUBE WAS RETURNED UNSERVICEABLE. THE TUBE ASSEMBLY IS MADE IN 3 SECTIONS WELDED TOGETHER. THE CENTER SECTION WAS CRACKED LONGITUDINALLY FROM WELD TO WELD APPROXIMATELY 19 INCHES. THE CRACK IS VERY STRAIGHT AND DEEP SUGGESTING A MANUFACTURING DEFECT. 1G71 4U4 U H1SW E17EA 20030821002112003082100211SW 2003 8 21 CA030722001 120020618G278019023 CONTROL CABLE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA TE FLAP FRAYED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABLE FOUND FRAYED AT THE PULLEY PN 12395.THE AREA TENDS TO BE A HIGH WEAR BECAUSE OF THE SIZE OF PULLEY AND IS MONITORED CLOSELY AT ALL INSPECTIONS. FAILURES HAVE OCCURED IN THE PAST WITH THIS COMPANY. 1H71 3O3 O A21CE E286 20030822000072003082200007NE 2003 8 22 CA030726001 220021007G8530 STUD DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE CYLINDER BROKEN W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA (CAN) CYLINDER FOUND LOOSE BECAUSE OF THE 6 STUDS PARTIALLY BROKEN. 6 STUDS REPAIRED AND NEW GASKET INSTALLED. 1H71 3R3 R A806 5E1 20030822000082003082200008CE 2003 8 22 CA030726003 120020618G7603C2995050101 THROTTLE CESSNA206 U206F 2073333CE CONT O550 IO550F 17042SO ENGINE CONTROL MALFUNCTIONED W O OTHER E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) NEW THROTTLE INSTALLED DUE TO MALFUNCTION. 1H71 3O3 O A4CE E3SO 20030822000092003082200009CE 2003 8 22 CA030726005 120021009G2434DOFF10300J ALTERNATOR CESSNA206 U206F 2073333CE CONT O550 IO550F 17042SO ENGINE FAILED W O OTHER H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA (CAN) LOSS OF ALTERNATOR POWER. ALTERNATOR OVERHAULED. 1H71 3O3 O A4CE E3SO 20030909000482003090900048SW 2003 9 9 CA030825004 120020715G2720315371 PEDAL BLANCA BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA MCAULY1A200 1A200* GL TOE BRAKE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A/C ARRIVED FOR SUMMER OPERATION. THE AME TOOK A QUICK LOOK THROUGH THE COCKPIT AND NOTICED THE RIGHT PEDAL SYSTEM LOOSE. ON FURTHER INSPECTION, HE NOTICED THE FORWARD RIGHT PEDAL BENT AND CRACKED ON THE RIGHT MOUNT SUPPORT. 1H71 3O3 O A21CE E286 5 NP874 20040126001072004012600107EA 2004 1 26 CA031103007 220021128G8530 ENGINE MOONEYM20 M20M 5870222SW LYC 0540 TIO540AF1B 41532EA MCAULY3D32C B3D32C417 GL MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUND METAL CONTAMINATION ON OIL FILTER ELEMENT. MFG LAB REPORTS METAL AREA MS 6274 STEEL LIKELY FROM CAMSHAFT AND AMS 4280 ALUMINUM FROM CRANKCASE. ENGINE WAS REMOVED AS PRECAUTIONARY INVESTIGATION DUE TO SIMILAR METAL CONTAMINATION AND REPAIR ABOUT 100 HOURS AGO. FURTHER DETAIL WILL BE SUBMITTED AFTER INVESTIGATION BY MFG. 1L71 3O3 ORT2A3 E14EA 5 CP58GL 20031126000862003112600086SW 2003 11 26 CA031106002 120021001G5302 SKIN BELL BELL 206 206B3 1181506SW TAILBOOM CRACKED W K NONE O OTHER ININSP/MAINT 1 CA BCJN07579 (CAN) 206B3 OWNED BY FOREIGN OPERATOR: WHILE ROUTINE WALK AROUND, OBSERVED FRACTURE OF THE LOWER SKIN ON THE RT, FORWARD OF THE T/R GEARBOX SUPPORT. 1G71 3U H2SW 20040107000152004010700015SW 2004 1 7 CA031110005 120020621G291070612J22OW234 LINE BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE HYD SYSTEM CHAFED W E ENGINE SHUTDOWN KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) DURING THE PRE-FLIGHT COCKPIT CHECKS WHILE THE AIRCRAFT WAS ON THE GROUND WITH ENGINES STARTED, THE PILOT NOTICED NR 2 HYDRAULIC PRESSURE LOSS. THE AIRCRAFT WAS SHUT DOWN FOR FURTHER INVESTIGATION. A HYDRAULIC LINE IN THE (HELL HOLE) WAS FOUND TO BE CHAFED BY A NEARBY BRAIDED LINE CAUSING FLUID LOSS AND THUS PRESSURE LOSS IN NR 2 HYDRAULIC SYSTEM. THE SUBJECT HYDRAULIC LINE WAS REPLACED WITH A NEW LINE AND THE BRAIDED LINE WAS CLAMPED TO PREVENT CONTACT WITH THE SURROUNDING LINES. THE AIRCRAFT HYDRAULIC SYSTEM WAS RE-FILLED AND THE AIRCRAFT GROUND RUN FOR LEAKS. NO LEAKS WERE FOUND AND THE SYSTEM PRESSURE WAS BACK TO NORMAL. 1G71 4U4 U H4SW E22EA 20040126001002004012600100SW 2004 1 26 CA031117011 120020909G6320 GEARBOX BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL MAIN ROTOR CONTAMINATED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA 11888 (CAN) ENGINE CHIP LIGHT ILLUMINATED DURING START. THE ENGINE WAS REMOVED AND SENT OUT FOR REPAIR. THE SUSPECTED CAUSE OF THE METAL CONTAMINATION WAS THE SPUR ADAPTER GEARSHAFT WHICH WAS A PMA PART OR THE 2.5 BEARING. 1G71 3U3 U H2SW E4CE 20040315000522004031500052NE 2004 3 15 CA040127009 220020217G7230758378 BLADE BOEING727 727225 1384077NM PWA JT8 JT8D9A 52048NE ENGINE FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 CA 665399 (CAN) SPARKS WERE REPORTED SEEN COMING FROM ENGINE EXHAUST AND VERIFIED WITH TEST RUNS. ENGINE WAS REMOVED FEB 17/2002 AND UNABLE TO IDENTIFY FAULT DURING INSPECTION. DURING THE SHOP INSPECTION, FAULT WAS IDENTIFIED AS SEPARATION OF AN 8TH STAGE STATOR BLADE. MFG IS LOOKING INTO INVESTIGATING CAUSE OF FAILURE. COMPONENT TSR = 3109.7, CSR = 1625 2L73 4F4 F A3WE E2EA 20040729000112004072900011SO 2004 7 29 CA040622004 220020506G8520 CRANKCASE CESSNA182 182J 2072722CE CONT O520 IO520D 17032SO MCAULY3A32C D3A32C90 GL ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) WHILE CONDUCTING PRE-FLIGHT CHECK, OIL DRIPS WHERE NOTICED. AFTER VERIFICATION BY AN AMO, IT WAS DETERMINED THAT THERE WAS A SMALL CRACK IN THE CRANKCASE. ENGINE DISASSEMBLED AND CRANKCASE WAS REPLACED. 1H71 3O3 ONT3A13 E5CE 5 CP21EA 20050419000562005041900056SO 2005 4 19 CA041213001 120020111G53307861901 SKIN PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360KB 17025SO WING MISMARKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) SKIN ASSY P/N 7861901 MATERIAL AND SKIN THICKNESS IDENTIFIED IN PIPER SENECA SERVICE MANUAL STRUCTURES SECTION FIG.4-9 NR 5 AS 2024-T3 0.032 1L72 3O3 O A7SO E9CE 20050419000802005041900080GL 2005 4 19 CA041214010 220020603G724023064570 COMBUSTION LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA CAE847080 (CAN) CRACK FOUND DURING REMOVAL FOR UNRELATED TURBINE CEB. NO CRACKS ALLOWED IN SUBJECT AREA. 1G71 3U3 UO H2SW E1GL 20060619001632006061900163CE 2006 6 19 CA051109004 120020713G3213508103237 TORQUE LINK BEECH 100 100BEECH 1152916CE PWA PT6 PT6A28 EA MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA UPON INSPECTION DISCOVERED MLG TORQUE LINKS CRACKED AT CENTER BOLT ATTACH POINTS. TORQUE LINKS SUBSEQUENTLY REPLACED. 1L72 3T4 T A14CE E4EA 20060705002452006070500245EA 2006 7 5 CA060208008 120020201G541173507217 LONGERON DHAV DHC6 DHC6300 2802606EA LT NACELLE FRACTURED W C ABORTED TAKEOFF FY FLT CONT AFFECTED ENGINE STOPPAGE TOTAKEOFF 1 CA 36395 (CAN) ON TAKE-OFF THE ENGINE TORQUE INDICATION OBSERVERED DROPPING OFF, ABORTED TAKE-OFF. OBSERVED LEFT ENGINE SAGGING IN THE COWLING. (TC# 20060208008) 1H72 3T RTA9EA 20060614001182006061400118NE 2006 6 14 CA060413004 220020221G73975003T78P04 WIRE HARNESS GE CT58 CT581401 30011NE ENGINE MISMANUFACTURED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA SIX NEW HARNESSES WERE SENT TO COLUMBIA HELICOPTERS FOR JET CAL TEST. ALL SIX FAILED. THIS WAS THE RESULT OF AN ENGINE NOT PASSING TEST ON THE TEST STAND AND THE FAULT WAS FOUND TO BE A NEW T5 HARNESS. AFTER THAT WE HAVE BEEN SENDING ALL NEW T5 HARNESS OUT FOR JET CAL BEFORE BEING INSTALLED ON AN ENGINE. 4 U 1E3 20021217000022002121700002EA 2002 12 17 DDER146D 220021125G8550LW13388 GASKET PIPER PA28 PA28236 7102815SO LYC O540 O540J3A5 41532EA ENG OIL FILTER DAMAGED B K NONE K FLUID LOSS ININSP/MAINT 1 WP018122Z482 288011033 FOUND OIL FILTER CONVERTER GASKET LEAKING. UPON REPLACEMENT IT WAS NOTICED TO BE DAMAGED. 1L71 3O3 O 2A13 E295 20020327001542002032700154CE 2002 3 27 DEBA2624D 120020315G2897 WIRE HARNESS CESSNA441 441 2076020CE GARRTTTPE331TPE331* 01514WP BOOST PUMP CHAFED D DEBAK NONE O OTHER ININSP/MAINT 1 CE032624D4209 4410122 FUEL BOOST PUMP WIRING IN THE WET WING AREA OF EACH WING, WAS CHAFED THROUGH THE INSULATION TO THE CENTER CONDUCTOR. THE WIRING, WHERE IT EXITS THE FEED THROUGH CONNETOR PLUG, INTO THE WET WING, AT THE INBOARD MOST RIB, IS CHAFING ON THE BOX THAT SURROUNDS THE BOOST PUMPS. 1L72 3T3 TRTA28CE E2WE 20020313001232002031300123NE 2002 3 13 ERAA077889 220020107G7230PT6T3B SEAL BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMPRESSOR LEAKING H ERAAO OTHER K FLUID LOSS NRNOT REPORTED 1 FS01412EH8992 33001 ENGINE HAS 2013.9 HRS SINCE OVERHAUL BY PRATT & WHITNEY. REMOVED FROM AIRCRAFT DUE TO HIGH OIL CONSUMPTION. USED 5QTS OF OIL IN 10.8 HRS; SUSPECTED COMP SEAL LEAK. RETURNING ON ERA REPAIR ORDER RW-887792 REQUESTING WARRANTY REPAIR DUE TO SUCH LOW TIME ON ENGINE. 1G72 4U4 U H4SW E22EA 20020313001242002031300124EU 2002 3 13 ERAA077890 120020110G63204638001001 TRANSMISSION BOLKMS105 BO105S 5626006EU MAIN ROTOR MAKING METAL H ERAAK NONE O OTHER ININSP/MAINT 1 FS01125EH4923 S562 TRANSMISSION IS MAKING METAL. HINGED SUPPORT BEARINGS FROZEN. ONE EACH SLIDING SLEEVE TO CONTROL LINK BRG MECHANICALLY DAMAGED. UPPER CENTER HOUSING SLIGHTLY CORRODED ONE PLANETARY AXLE BREAKING DOWN & ONE PLANETARY GEAR PITTED. ACTION TAKEN: DISASSEMBLED AS FAR AS NECESSARY FOR REPAIR. REPLACED ONE PLANETARY GEAR, ONE PLANETARY AXLE,ONE DOUBLE ROWED CAGE. REPLACED BOTH HINGED SUPPORT BRGS, ONE CONTROL LINK TO SLIDING SLEEVE BEARING. REPLACED LOCK PLATES, AND HARDWARE AS NECESSARY. REPAIRED I/A/W BO-105 REM 103 & M/M CHAPTER 41. COPY TO AEC. 1G72 3U H3EU 20020313001252002031300125EU 2002 3 13 ERAA077891 120020115G63204638001007 TRANSMISSION BOLKMS105 BO105S 5626006EU MAIN ROTOR MAKING METAL H ERAAK NONE O OTHER ININSP/MAINT 1 FS01 10465 TRANSMISSION IS MAKING METAL. ALL FOUR CONTROL ROD ASSY BRGS WORN BEYOND LIMITS. BOTH CENTROL LEVERS BRGS FROZEN. TWO CENTROL LEVER TO SLIDING SLEEVE BRGS FROZEN. TWO HINGED SUPPORT BRGS FROZEN. DUST SHIELD CLAMP RUSTED, TOP CASE TO OUTER CASE BOLTS MECHANICALLY DAMAGED. MAST ROLLER BEARING BREAKING DOWN. ROTOR MAST PITTED ON FLANGE & BORES. OIL COOLER BLOWER DRIVE BUSHING WORN. LT INPUT PINION BREAKING DOWN. RT INPUT PINION LUBRICATE TUBE HAS DAMAGED THREADS. RT INPUT PINION BREAKING DOWN. LT BEVEL GEAR BREAKING DOWN. LT INT SHAFT BRG MECHANICALLY DAMAGED. LT INT SHAFT ROLLER TRACK BREAKING DOWN. RT BEVEL GEAR BREAKING DOWN. 1G72 3U H3EU 20020313001262002031300126SW 2002 3 13 ERAA077892 120020116G2435230461030 ARMATURE BELL 412 412 1182202SW STARTER GEN WORN H ERAAK NONE O OTHER ININSP/MAINT 1 FS01168EH 33067 DRIVE END BEARING JOURNAL OUT OF LIMITS. 1G72 4U H4SW 20020313001272002031300127SW 2002 3 13 ERAA077893 120020116G2435230461030 ARMATURE BELL 412 412 1182202SW STARTER GEN MISSING H ERAAK NONE O OTHER ININSP/MAINT 1 FS01418EH BEARING JOURNAL BASE MISSING. 1G72 4U H4SW 20020313001282002031300128SW 2002 3 13 ERAA077896 120020117G7921209062502101 IMPELLER BELL 412 412 1182202SW COOLER BLOWER BENT H ERAAK NONE O OTHER ININSP/MAINT 1 FS01412EH7755 33001 IMPELLER BLADES ON OIL COOLER 1G72 4U H4SW 20020313001292002031300129EU 2002 3 13 ERAA077922 120020215G79316607190A SWITCH BOLKMS105 BO105S 5626006EU OIL PRESS WARN INOPERATIVE H ERAAK NONE O OTHER ININSP/MAINT 1 FS01128EH53 572 OIL PRESSURE WARNING SWITCH IS INOPERABLE. 1G72 3U H3EU 20020313001302002031300130SW 2002 3 13 ERAA077924 120020219G6320412040002103 HOUSING BELL 412 412 1182202SW TRANSMISSION BROKEN H ERAAK NONE O OTHER ININSP/MAINT 1 FS01422EH10475 33068 AUX JET HOUSING CRACKED, HOUSING BROKEN IN TWO PIECES. ACTION TAKEN: REMOVED TOP CASE AND UPPER PLANETARY INSTALLED NEW HOUSING AND GASKET. REINSTALLED UPPER PLANETARY AND TOP CASE ALL WORK IAW BHT CR&O 63. 1G72 4U H4SW 20020419000242002041900024EU 2002 4 19 ERAA078421 120020227G632023008021 HOUSING BOLKMS105 BO105S 5626006EU GEARBOX DEBONDED A ERAAK NONE W INADEQUATE Q C ININSP/MAINT 1 AL03149EH S705 (2) 1/4 X 28 STUDS PULLED FROM HOUSING. RETURNED FROM OVERHAUL. 1G72 3U H3EU 20020419000252002041900025EU 2002 4 19 ERAA078424 120020314G7900 COVER BOLKMS105 BO105S 5626006EU SUMP CORRODED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01134EH 635 SENT FOR REPAIR 11/2001 AND RETURNED 1/18/2002 AND COULD NOT BE USED ON THE AIRCRAFT DUE TO LINE OF CORROSION PITTS ON AFT SUMP COVER. 1G72 3U H3EU 20020423000312002042300031EU 2002 4 23 ERAA078446 120020320G2421230322111 ARMATURE BOLKMS105 BO105S 5626006EU GENERATOR ARCED H ERAAK NONE L NO TEST ININSP/MAINT 1 FS01128EH 572 EXCESSIVE ARCHING DURING TEST. WAS ISSUED TO AIRCRAFT BUT COULD NOT BE USED. 1G72 3U H3EU 20020423000322002042300032EU 2002 4 23 ERAA078447 120020326G78106879879 COLLECTOR RING BOLKMS105 BO105S 5626006EU EXHAUST GROOVED H ERAAK NONE W INADEQUATE Q C ININSP/MAINT 1 FS01134EH 635 EXHAUST COLLECTOR RETURNED FROM OVERHAUL AND ISSUED TO AIRCRAFT BUT COULD NOT BE INSTALLED DUE TO GROOVED .100 IN MOUNT AREA. 1G72 3U H3EU 20020423000332002042300033EU 2002 4 23 ERAA078450 120020403G78106879879 COLLECTOR RING BOLKMS105 BO105S 5626006EU EXHAUST MISOVERHAULED H ERAAK NONE W INADEQUATE Q C ININSP/MAINT 1 FS01134EH 635 EXHAUST COLLECTOR REC'D BACK 1-10-02 FROM OVERHAUL AND COULD NOT BE INSTALLED ON A/C ISSUED TO DUE TO TOP TURBINE MOUNT BEING DEBONDED. 1G72 3U H3EU 20020423000342002042300034GL 2002 4 23 ERAA078452 220020403G7320252466715H GOVERNOR ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED H ERAAK NONE L NO TEST ININSP/MAINT 1 FS01 12618 GOVERNOR DROOPING EXCESSIVELY, OUT OF SERVICE LIMITS. INTERNAL BEARINGS FOUND ROUGH / RATCHETY, DRIVESHAFT SPLINES WORN BEYOND LIMITS, DRIVE SLEEVE SPLINES WORN, GOVERNOR WEIGHTS WORN FLAT. 3 U E4CE 20020423000352002042300035GL 2002 4 23 ERAA078453 220020403G7320 DIAPHRAGM BOLKMS105 BO105A EU ALLSN 250C 250C20B 03013GL ENG GOVERNOR DEFORMED H ERAAO OTHER J WARNING INDICATION NRNOT REPORTED 1 FS01291EH10974 S842 NR 1 STARTS HUNTING UP & DOWN AFTER 10-20 MIN. GOVERNOR BLEEDS OFF 200 RPM TOO EARLY. GOVERNOR LEVER, CAM LEVER AND FLY WEIGHT BEARINGS FOUND ROUGH AND DRY. PR DIAPHRAGM FOUND DEFORMED. 1G72 3U3 U H3EU E4CE 20020423000362002042300036GL 2002 4 23 ERAA078455 220020403G7320 BEARING ALLSN 250C 250C20B 03013GL ENG GOVERNOR ROUGH H ERAAO OTHER J WARNING INDICATION NRNOT REPORTED 1 FS01 11828 GOVERNOR HITS MAX STOP WITH COLLECTIVE UP. DROOPING AND OVERSPEEDING EARLY. FOUND CAN LEVER OVERSIZED, ECCENTRIC SHAFT UNDERSIZED, SIX INTERNAL BEARINGS FOUND ROUGH/ RATCHETY. 3 U E4CE 20020423000372002042300037EU 2002 4 23 ERAA078456 120020404G642010531714 HEAD BOLKMS105 BO105S 5626006EU TAIL ROTOR MALFUNCTIONED H ERAAO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 FS01 8715 EXCESSIVE RIGHT PEDAL REQUIRED IN A HOVER. FOUND NO DEFECTS ACTION TAKEN: REMOVED BLADES AND REPLACED WITH BLADES SN 211 & 218 FOR TROUBLESHOOTING PURPOSES. REMOVED STRAP PACK BOLTS FOR INSPECTION OF BUSHINGS. FOUND NO DEFCTS & REINSTALLED BOLTS. STATIC BALANCED. REPAIRED IAW BO105 REM 301, MM CH 33,34,102 & MARVEL MM. 1G72 3U H3EU 20020423000382002042300038EU 2002 4 23 ERAA078457 120020404G642010531714 HEAD BOLKMS105 BO105S 5626006EU TAIL ROTOR MALFUNCTIONED H ERAAO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 FS01298EH10028 S845 HEAVY LEFT PEDAL FORCES WITH MAX WEIGHT ADJUSTMENT. NO OBVIOUS DEFECTS. ACTION TAKEN: REMOVED BLADES AND MOUNTING FORKS. VISUALLY INSPECTED AND FOUND NO DEFECTS. RE-ASSEMBLED AND STATIC BALANCED., REPAIRED IAW BO-105 REM 301, MM CH 33, 34, 102 & 106. 1G72 3U H3EU 20020423000392002042300039SW 2002 4 23 ERAA078458 120020404G6210412015300109 BLADE BELL 412 412 1182202SW MAIN ROTOR DAMAGED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01419EH8855 INSPECTION DUE TOP SKIN 1/3 DOWN LENGTH OF BLADE FROM ROOT, VOIDED AREA AS MARKED, EDGES OF INBOARD TAB POPPED UP. ESTANE BOOT DAMAGED, LOWER SURFACE GRIP VOID, INBOARD TRIM TAB VOID WITH GLASS DAMAGE, INBOARD ABRASION STRIP TANG VOID UPPER AND LOWER SURFACE. WATER IN BLADES AT SKIN PATCH, FILLER CRACKING AT TABS. WATER IN BLADE 30 TO 40 CELLS. DETERMINED BY X-RAY INSPECTION OF SUSPECT AREA. ACTION TAKEN: REPAIRED AS PER 8130-3 BLK #13. 1G72 4U H4SW 20020423000402002042300040NE 2002 4 23 ERAA078459 120020404G62106117020201067 BLADE SKRSKYS61 S61N 8142104NE MAIN ROTOR DEBONDED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01563EH9656 61808 ABRASION STRIP DEBONDING ABOUT 2 FEET FROM END. LAST POCKET NR 25 CRACKED ON TOP AND BOTTOM, COMING SEPERATED FROM SPAR. CUFF LEAKING AT BOLTS, NR 25 POCKET CRACKED AND VOID, O/B ABRASION STRIP VOID, CTR ABRAISION STRIP VOID, NR`S 13, 15, 16 POCKETS VOID, NR 12 POCKET CRACKED, POLY SPLICE COVER ERRODED. ACTION TAKEN: REPAIRED AS PER 8130-3 BLOCK NR 13. 2G72 4U 1H15 20020423000412002042300041GL 2002 4 23 ERAA078460 220020404G7210 BEARING BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL GEARBOX WORN H ERAAK NONE O OTHER ININSP/MAINT 1 FS01130EH6891 558 ENGINE IS MAKING METAL. FOUND ROLLER ON 2 1/2 BEARING DAMAGED. GEARBOX PN 6894171 SN CAG-39145 INSTALLED. REPAIRED GEARBOX PN 6894171, SN CAG-23194. GEASHAFT DAMAGED, PN E23031922, SN CI-21-536, O/H OIL CHECK VALVE PN 23031856. ACTION TAKEN: INSTALLED REPAIRED GEARBOX PN 6894171, SN CAG-23194, INSTALLED NEW GEAR SHAFT, P/N E63031922, SN DG14-147, INSTALLED NEW CHECK VALVE PN 23069740. 1G72 3U3 U H3EU E4CE 20020423000422002042300042GL 2002 4 23 ERAA078461 220020404G72506898735 TURBINE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE FAILED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01127EH8895 571 TOT INDICATING AMBIENT TEMPERATURE. ACTION TAKEN: SENT HARNESS OUT FOR REPAIR. BURNED VANES ON NR 1 NOZZLE. INSTALLED NEW TAT HARNESS AND NR 1 NOZZLE. 1G72 3U3 U H3EU E4CE 20020423000432002042300043SW 2002 4 23 ERAA078462 120020404G6220 BUSHING BELL 412 412 1182202SW M/R HEAD MISSING H ERAAK NONE O OTHER ININSP/MAINT 1 FS01168EH13544 33067 BUSHINGS 412-010-121-101 MISSING FROM YOKE RED BLADE, COMPLY WITH 2500 HR INSPECTION. BUSHINGS MISSING, VISUAL INSPECTION APPEARS NORMAL ON YOKE & FITTING. ACTION TAKEN: DISASSEMBLED, CLEANED, INSPECTED, COMPLIED WITH 2500 HR INSPECTION IAW 412 CR&O & 412 M/M, INSTALLED YOKE BUSHINGS, SERVICEABLE LOWER CONE SEAT, SPLINE PLATE, LOWER CONE, NEW DAMPER SETS, ASSEMBLED IAW 412 CR&O. 1G72 4U H4SW 20020423000442002042300044SW 2002 4 23 ERAA078463 120020404G7921209062502101 BLOWER BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE OIL COOLER WORN H ERAAK NONE O OTHER ININSP/MAINT 1 FS01 11234 OIL COOLER BLOWER DUE 1500 HR OVERHAUL. WORN INBOARD BUSHING IN CASING ASSY. CRACKED IMPELLER. ACTION TAKEN: C/W PRELIMINARY INSPECTION. NO DEFECTS NOTED. DISASSEMBLED OIL COOLER, CLEANED, STRIPPED PAINT & PRIMER & VISUALLY INSPECT ALL PARTS. FOUND MECHANICAL DAMAGE ON BEARING BUSHING OF CASING ASSY AND SENT TO H&S TOOL FOR REPAIR. CLEANED UP LIGHT CORROSION ON REMAINING PARTS. C/W NDT INSP & FOUND CRACK ON IMPELLAR, PARTS FOUND TO BE IN SERVICEABLE CONDITION. INSTALLED 1EACH NEW BRG IN CASING ASS6Y, 1 EACH NEW BEARING ON SHAFT. PRIMED PARTS & REASSEMBLED OIL COOLER WITH ALL NEW HARDWARE, NEW DECAL & NEW SHAFT O RING. O/H OIL COOLER IAW BHT 412 CR&O9CHAP 79 & BHT-ALL-SPM CHAP 2 . 1G72 4U4 U H4SW E22EA 20020423000452002042300045EU 2002 4 23 ERAA078464 120020404G6321AHA1121MOD1234 BRAKE BOLKMS105 BO105S 5626006EU MAIN ROTOR DAMAGED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01 10777 INNER PISTON FROZEN. NEEDED ON ADDITIONAL SHIM INSTALLED UNDER THE DISC SPRINGS ON THE PIN RETRACTION. PADS MISSING. EXCLUDER DUST BOTH TORN. ACTION TAKEN: REPAIRED AND TESTED. 1G72 3U H3EU 20020423000462002042300046SW 2002 4 23 ERAA078465 120020404G6320412040002103 TRANSMISSION BELL 412 412 1182202SW TAIL ROTOR MAKING METAL H ERAAK NONE O OTHER ININSP/MAINT 1 FS01418EH8093 TRANSMISSION IS MAKING METAL. ACCESSORY T/R INPUT QUILL BEARING SET, ROLLERS & RACES MAKING METAL. ACTION TAKEN: CHANGED SUMP CASE, ASSY/ INPUT DRIVE QUILL. C/W 3100 HOUR INSPECTION. REPLACED MAIN INPUT PINION AND ALL BRGS. CLEANED AND FLUSHED ALL OIL PASSAGES.TESTED AND TOUCHED UP PAINT. 1G72 4U H4SW 20020625000132002062500013 2002 6 25 ERAA079864 420020430G344240008330208 INDICATOR SKRSKYS61 S61N 8142104NE RADAR SYSTEM CONTAMINATED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01563EH1102 61808 WILL NOT POWER UP ; NO INDICATION. UNIT HAS MAJOR WATER DAMAGE. REPAIRED BURNED TRACE, REMOVED CORROSION AND TESTED. 2G72 4U 1H15 20020719000432002071900043NE 2002 7 19 ERAA080332 120020610G62107615009043050 TIP CAP SKRSKYS76 S76A 8143006NE M/R BLADE CRACKED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01578EH1610 760099 TIP CAP IS CRACKED. FORWARD INTERNAL DOUBLERS VOID. ACTION TAKEN: REPLACED INTERNAL FWD DOUBLERS AND REBONDED C-CHANNEL, REFINISHED PAINT AND STATIC BALANCED. 1G72 3U H1NE 20020719000482002071900048NE 2002 7 19 ERAA080333 120020610G6210 BLADE SKRSKYS61 S61N 8142104NE MAIN ROTOR CRACKED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01 7686 MAIN ROTOR BLADE HAS CRACK IN POCKET NR 9 FROM ROOT END ON BOTTOM. ACTION TAKEN: REPLACED POCKET NR 17, NR 20 REPLACED O/B ABRAISION STRIP, REPLACED RUBBER CAP, TOUCHED UP, AND BALANCED, CHANGED SPAR, REPLACED NUT PLATE. 2G72 4U 1H15 20020719000542002071900054NE 2002 7 19 ERAA080334 120020610G62106117020201067 BLADE SKRSKYS61 S61N 8142104NE MAIN ROTOR DAMAGED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01 8724 SPAR PRESSURE BELOW MINIMUM CHECK PRESSURE. ACTION TAKEN: REPAIRED AS PER BLOCK NR 13 OF 8130-3. 2G72 4U 1H15 20020813001432002081300143 2002 8 13 ERAA080469 420020715G344240008330207 INDICATOR BELL 412 412 1182202SW WX RADAR CONTAMINATED H ERAAK NONE O OTHER ININSP/MAINT 1 FS01418EH INOPERABLE; UNIT WOULD NOT POWER UP. FOUND MAJOR WATER DAMAGE. ACTION TAKEN: REPLACED ALL BAD PARTS, REM'D CORROSION, REPAIRED BROKEN WIRES, RE-SOLDERED COLD SOLDER JOINTS, ALIGNED AND TESTED. NS 1G72 4U H4SW 20021015000392002101500039CE 2002 10 15 FAI001 120021011G3230100951X063XE WASHER BEECH 200 200BEECH 1152920CE MLG MISSING B A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 GL13432FA1700 1700 BB592 FOLLOWING TAKEOFF, GEAR RETRACTION FAILED, WITH GEAR STUCK IN-TRANSIT. A NOISE WAS HEARD FROM THE LEFT SIDE OF THE AIRCRAFT AT THE TIME OF FAILURE. EMERGENCY EXTENSION EFFORTS PRODUCED NO RESULTS, AND THE EMERGENCY EXTENSION HANDLE BECAME SEIZED. CONTACT WITH MAINTENANCE PERSONNEL CAUSED THE COPILOT TO OPEN THE CABIN FLOOR OVER THE GEAR DRIVE MECHANISM, AND REVEALED THAT THE LANDING GEAR MOTOR CONTROLLER CIRCUIT BREAKER WAS OPEN. BREAKER WAS RESET, AND THE LANDING GEAR EXTENDED NORMALLY. PRIOR TO LANDING, A FLYOVER OF THE MAINTENANCE PERSONNEL REVEALED THE LEFT MAIN GEAR WHEELS TO BE TURNED APPROXIMATELY 20 DEGREES RIGHT. LANDING WAS COMPLETED WITH NO INCIDENT. INVESTIGATION REVEALED THAT THE LEFT MAIN GEAR TOR1L72 4T A24CE 20021015000132002101500013NE 2002 10 15 FF6R112443 220020816G7210350A32314306 GEAR TMECA ARRIELARRIEL1D NE RGB DENTED B FF6RK NONE O OTHER ININSP/MAINT 1 NM11 PINION HAS DENT ON END OF SHAFT. BEVEL RING GEAR HAS CHATTER MARKS IN 7 HOLES. 3 U E19EU 20020419000262002041900026EU 2002 4 19 GSG 120020417G4960211746066 ECU AMD FALC50FALCON50MYST2730106EU APU DEFECTIVE C K NONE O OTHER ININSP/MAINT 1 GL05744X 185 58 APU WILL NOT START (NO START SEQUENCE AT ALL). AFTER PRESSING THE APU MASTER, THE APU START BUTTON NEVER ILLUMINATED. THE RPM GAUGE INDICATES 120 PERCENT AT ALL TIMES. THE APU FAULT PANEL INDICATES LOW OIL PRESSURE, OVERSPEED. DETERMINED THAT THE APU ECU WAS DEFECTIVE. WITH THE APU SHUT DOWN, THE ECU INDICATED THAT THE APU WAS RUNNING. THE APU WOULD NOT START BECAUSE THE LOW OIL PRESSURE LOGIC PREVENTED IT FROM STARTING. REPLACED THE ECU. APU STARTS AND RUNS NORMAL. 2L73 4F A46EU 20020122000372002012200037NE 2002 1 22 HEEA077553 220020104G73210292928540 METERING VALVE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE FUEL CONTROL LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW03973AE 3229 FUEL CONTROL METERING VALVE HAS INTERNAL FUEL LEAK. 1G71 3U3 U H9EU E19EU 20020122000382002012200038GL 2002 1 22 HEEA077554 220020104G7250230583299 TURBINE WHEEL BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE FAILED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW0330KH 358 51527 CAE895129 ENGINE WAS REMOVED DUE TO WHISTLING SOUND AT HOVER AND GRINDING ROAR ON COOL DOWN. UPON INSPECTION OF TURBINE PARTS NOTED NR 1 WHEEL BLADE FAILURE WITH 1/8 INCH OF BLADE REMAINING FROM BLADE ROOT LEADING EDGE. BLADE TIPS EXHIBIT TIP DRAG AND FOD DAMAGE. NR 2 NOZZLE 1ST STAGE TIP PATH RUNOUT AT DISASSEMBLY WAS .002 INCHES AND 1ST STAGE WHEEL TIP CLEARANCE IS .014 INCHES ASSEMBLY TIP CLEARANCE WAS .0135 INCHES. PART WILL BE RETURNED TO ROLLS ROYCE FOR FAILURE INVESTIGATION. 1G71 3U3 U H2SW E1GL 20020122000392002012200039GL 2002 1 22 HEEA077555 220020111G72506870832 COUPLING BELL 206 TH57A 1180821SW ALLSN 250C 250C18A 03011GL ENGINE MISMARKED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03128 162814 NEW PART RECEIVED WITH IMPROPER PART NUMBER 6850832 ENGRAVED ON PART. 1G71 3U3 U EXPA1G71E4CE 20020122000402002012200040GL 2002 1 22 HEEA077556 220020116G72306890550 COMPRESSOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL NR 1 ENGINE FAILED E HEEAEA ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW037136H3876 S833 ON SECOND FLIGHT OF THE DAY, IN CRUISE, THE AIRCRAFT YAWED FOLLOWING WITH GENERATOR LIGHT ON, AUDIO ON, DECLINE OF N2, N1 AND OIL PRESSURE ON NR 1 ENGINE. SECURED NR 1 ENGINE. MAINTENANCE FOUND NR 1 COMPRESSOR FAILURE. 1G72 3U3 U H3EU E4CE 20020122000412002012200041GL 2002 1 22 HEEA077558 220020116G7230 COMPRESSOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE FAILED E HEEAA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 SW037136H382 S833 CAE835247 ENGINE REMOVED DUE TO IN FLIGHT COMPRESSOR DAMAGE. UPON INSPECTION OF COMPRESSOR PARTS NOTED WIPE OUT OF 2ND THRU 5TH STAGE COMPRESSOR WHEEL BLADES, EXCESSIVE FOD TO CASE HALF ASSY, 1ST THRU 6TH STAGE WHEELS, IMPELLER AND TURBINE. SUSPECTED CAUSE IS 2ND STAGE COMPRESSOR BLADE FAILURE. 1G72 3U3 U H3EU E4CE 20020123001102002012300110SW 2002 1 23 HEEA077658 120020102G6300407340339101 BEARING BELL 407 407 1182206SW MAIN ROTOR FAILED E HEEAA UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 SW033193E140 53276 IN CRUISE, PILOT DETECTED VIBRATION / LOW RUMBLING NOISE FROM AFT AREA OF AIRCRAFT. NOISE/VIBRATION INCREASED WITH INCREASE IN POWER. MAINTENANCE INSPECTED AND FOUND NR 2 SHAFT / OIL COOLER ASSY AFT BEARING FAILURE. 1G71 3U O H2SW 20020123001112002012300111SW 2002 1 23 HEEA077659 120020104G5302 STRUCTURE BELL 214 214ST 1182106SW TAIL BOOM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033897N9962 28106 DURING POST FLIGHT INSPECTION, MAINTENANCE DISCOVERED CRACK IN TAIL BOOM VERTICAL PYLON STRUCTURE. 2G72 4U H10SW 20020123001122002012300112SW 2002 1 23 HEEA077660 120020104G2820222366621101 FUEL FILTER BELL 222 222 1182122SW FUEL SYSTEM MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 FUEL FILTER LIGHT WILL NOT COME ON WHEN BUTTON IS PUSHED. 1G72 3U H9SW 20020123001132002012300113SW 2002 1 23 HEEA077662 120020108G5302 STRUCTURE BELL 407 407 1182206SW TAIL BOOM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH2217 53399 TAIL BOOM STRUCTURE IS CRACKED. 1G71 3U O H2SW 20020123001142002012300114SW 2002 1 23 HEEA077663 120020108G6420407012101111 HUB BELL 407 407 1182206SW TAIL ROTOR G/B STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH2217 53399 TAIL ROTOR HUB IS STUCK ON GEARBOX. 1G71 3U O H2SW 20020123001152002012300115SW 2002 1 23 HEEA077664 120020108G6420 HUB BELL 407 407 1182206SW T/R GEARBOX STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH2217 53399 T/R HUB ASSY STUCK ON GEARBOX. 1G71 3U O H2SW 20020123001162002012300116SW 2002 1 23 HEEA077665 120020108G6420407012110101 STOP BELL 407 407 1182206SW T/R GEARBOX STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH2217 53399 STUCK ON GEARBOX. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PARTS PURCHASED. PHI HAS NOT YET RECEIVED REPLACEMENTS. REFERENCE: DMR#744646. 1G71 3U O H2SW 20020123001172002012300117SW 2002 1 23 HEEA077666 120020109G8011 PIN BELL 214 214ST 1182106SW CLUTCH SHAFT SHEARED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 95H1357 250 HOUR INSPECTION, PIN SHEARED IN CLUTCH SHAFT. 2G72 4U H10SW 20020123001182002012300118SW 2002 1 23 HEEA077670 120020111G2140205072277009 VALVE BELL 412 412 1182202SW HEATER MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 HEATER WILL NOT PUT OUT SUFFICIENT HEAT. 1G72 4U H4SW 20020123001192002012300119 2002 1 23 HEEA077671 420020111G2330222899604101 CONTROL PANEL BELL 222 222 1182122SW PA SYSTEM INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 PA INOPERATIVE. 1G72 3U H9SW 20020123001202002012300120SW 2002 1 23 HEEA077675 120020116G2497214175171103 RELAY BELL 214 214ST 1182106SW ELECTRICAL BURNED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 BURNT CONTACTS. VOLTAGE ON STARTS WON'T GO ABOVE 32 VDC. 2G72 4U H10SW 20020123001212002012300121SW 2002 1 23 HEEA077676 120020116G2497214175131103 RELAY BELL 214 214ST 1182106SW ELECTRICAL BURNED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 BURNT CONTACTS. VOLTAGE ON STARTS WON'T GO ABOVE 32 VDC. 2G72 4U H10SW 20020123001222002012300122SW 2002 1 23 HEEA077677 120020116G2560222320823119 SEAT BELT BELL 222 222 1182122SW COCKPIT MISINSTALLED E HEEAO OTHER W INADEQUATE Q C NRNOT REPORTED 1 SW03 RESTRAINT INSTALLED ON SPOOL BACKWARDS. 1G72 3U H9SW 20020123001232002012300123 2002 1 23 HEEA077678 420020116G2200214074303115 AMPLIFIER BELL 214 214ST 1182106SW AUTO FLIGHT WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 WON'T MONITOR TEST. STICK WANDERS. DIFFICULT TO ADJUST R91 ON BOARD 11 & 9. 2G72 4U H10SW 20020123001242002012300124 2002 1 23 HEEA077679 420020116G2200214074305105 AMPLIFIER BELL 214 214ST 1182106SW AUTO FLIGHT MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 CAUSES ELEVATOR LIGHT TO STAY ON. 2G72 4U H10SW 20020123001252002012300125 2002 1 23 HEEA077680 420020116G2200214074303115 AMPLIFIER BELL 214 214ST 1182106SW AUTO FLIGHT MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 AMPLIFIER CAUSING PITCH AXIS TO KICK. 2G72 4U H10SW 20020123001262002012300126EU 2002 1 23 HEEA077682 120020111G6400355A09103601 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR SEPARATED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03973AE224 3229 TAIL ROTOR BEARING SEPARATION. 1G71 3U H9EU 20020123001272002012300127EU 2002 1 23 HEEA077683 120020111G6410355A12004008 BLADE SNIAS 350 AS350B2 8680813EU TAIL ROTOR DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404665465 3004 TGT BLADE LOWER FACE POLY TAPE SEPARATED AND MISSING. 1G71 3U H9EU 20020123001282002012300128EU 2002 1 23 HEEA077684 120020111G7930648183031 INDICATOR SNIAS 350 AS350B 8680801EU COCKPIT CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03975AE 2777 NEEDLE STICKS ON LOW SIDE AND REAR RING CRACKED. 1G71 3U H9EU 20020123001292002012300129EU 2002 1 23 HEEA077685 120020111G6730SC5084 SERVO SNIAS 350 AS350B2 8680813EU CYCLIC STICK LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW0340466 3004 SERVO LEAKING. 1G71 3U H9EU 20020123001322002012300132EU 2002 1 23 HEEA077686 120020111G6410355A09103601 BEARING SNIAS 350 AS350B 8680801EU T/R BLADE DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03974AE384 2653 BEARING HAS RUBBER SEPARATION. 1G71 3U H9EU 20020301000172002030100017EU 2002 3 1 HEEA077699 120020123G6320 SEAL SNIAS 350 AS350B2 8680813EU M/R GEARBOX LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW034036H3473 2919 GEARBOX LEAKING OIL AT AIR / OIL SEPARATOR SEAL AT APPROXIMATELY 2 LITERS PER HOUR. 1G71 3U H9EU 20020301000442002030100044NE 2002 3 1 HEEA077705 220020219G73200292958050 VALVE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE ENGINE FAILED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03971AE1104 3230 22072 ENGINE WOULD START INTERMITTENTLY. 1G71 3U3 U H9EU E19EU 20020301000452002030100045SW 2002 3 1 HEEA077708 120020118G6320407340339101 BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 MAIN ROTOR BEARING FAILURE. 1G71 3U O H2SW 20020301000462002030100046SW 2002 3 1 HEEA077709 120020118G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X3156 53267 STARTER GEN HAS WORN BRUSHES. 1G71 3U O H2SW 20020301000532002030100053SW 2002 3 1 HEEA077714 120020121G6330406040056101 CASE 206040004107BELL 206 206L3 1182108SW TRANSMISSION CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038587X B51719 51464 CRACK INDICATIONS ON WEBS OF TRANSMISSION. 1G71 3U H2SW 20020301000552002030100055SW 2002 3 1 HEEA077721 120020122G7120206064105101 MOUNT BELL 206 206L3 1182108SW ENGINE MISMARKED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 ENGINE MOUNT LEG IS MISIDENTIFIED BY PART NUMBER. 1G71 3U H2SW 20020301000572002030100057 2002 3 1 HEEA077725 420020122G3417214175421101 ADC BELL 214 214ST 1182106SW COCKPIT WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 NR 1 POWER ASSURANCE WILL NOT TEST. 2G72 4U H10SW 20020301000582002030100058SW 2002 3 1 HEEA077726 120020122G8011214060056103 STARTER BELL 214 214ST 1182106SW ENGINE MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 SLOW STARTS. HAVING STARTER PROBLEMS. 2G72 4U H10SW 20020301000632002030100063SW 2002 3 1 HEEA077732 120020125G6310406040500113FM FREEWHEEL UNIT BELL 206 206L4 1182110SW MAIN ROTOR LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW037077B361 52037 FREEWHEEL UNIT IS LEAKING. 1G71 3U NCH2SW 20020301000642002030100064SW 2002 3 1 HEEA077733 120020125G3212407350300101 FLOAT BELL 407 407 1182206SW MLG LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03141MA 53016 EMERGENCY FLOAT BAG IS LEAKING. 1G71 3U O H2SW 20020301000652002030100065SW 2002 3 1 HEEA077734 120020125G7712407375003107 INDICATOR BELL 407 407 1182206SW TORQUE MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 TORQUE INDICATOR SPIKED TO 134.1 PERCENT FOR 1. 1G71 3U O H2SW 20020301000662002030100066SW 2002 3 1 HEEA077735 120020125G3110407375002103 INDICATOR BELL 407 407 1182206SW COCKPIT DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03406PH 53198 INTERNAL LIGHTING TOO DIM. DIFFICULT TO READ IN DAYLIGHT. 1G71 3U O H2SW 20020301000692002030100069SW 2002 3 1 HEEA077739 120020128G6700206076062107 CYCLIC STICK BELL 407 407 1182206SW COCKPIT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH2078 53398 CYCLIC STICK HAS FORWARD BEARING WEAR. 1G71 3U O H2SW 20020304000082002030400008SW 2002 3 4 HEEA077753 120020128G2922206076030111 PUMP BELL 407 407 1182206SW FUEL BOOST LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03719PH 53266 FUEL BOOST PUMP LEAKING OUT OF SEAL DRAIN. 1G71 3U O H2SW 20020304000132002030400013SW 2002 3 4 HEEA077760 120020128G6300400040055109 HOUSING BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH 53266 MAIN ROTOR HOUSING REMOVED FOR AN EVALUATION DUE TO EXCESSIVE CORROSION UNDER PAINT. 1G71 3U O H2SW 20020304000162002030400016SW 2002 3 4 HEEA077763 120020128G7712222375077119 TRANSMITTER BELL 407 407 1182206SW TORQUE INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03510PH 53209 TORQUE TRANSMITTER INOPERATIVE. 1G71 3U O H2SW 20020304000292002030400029SW 2002 3 4 HEEA077779 120020128G6300407340339101 BEARING PHIPBH40701 BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03740PH PHI0020 53435 MAIN ROTOR OIL COOLER BLOWER BEARING IS ROUGH. 1G71 3U O H2SW 20020304000302002030400030SW 2002 3 4 HEEA077780 120020128G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL SYSTEM MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03493PH 53393 LOW FUEL LIGHT STAYS ON. 1G71 3U O H2SW 20020304000332002030400033SW 2002 3 4 HEEA077788 120020130G28221C2710 CARTRIDGE BELL 407 407 1182206SW FUEL BOOST FAULTY E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03724PH 53327 FAULTY CARTRIGE CAUSING FUEL BOOST PUMP TO NOT RUN. 1G71 3U O H2SW 20020304000352002030400035 2002 3 4 HEEA077790 420020130G3197 CONNECTOR BELL 407 407 1182206SW INSTRUMENT PANELDAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 PINS BENT IN THE CONNECTOR THAT ATTACHES TO AIRFRAME. 1G71 3U O H2SW 20020304000532002030400053SW 2002 3 4 HEEA077808 120020130G6710 BEARING BELL 407 407 1182206SW T/R UNIVERSAL UNSTAKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH1018 RXFS5791 53400 TAIL ROTOR UNIVERSAL BEARING UNSTAKED. 1G71 3U O H2SW 20020311000722002031100072SW 2002 3 11 HEEA077871 120020219G6220407310101010 BEARING BELL 407 407 1182206SW M/R HEAD CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 MAIN ROTOR HEAD BEARINGS CORRODED. 1G71 3U O H2SW 20020311000962002031100096 2002 3 11 HEEA077882 420020219G2210214074305105 AMPLIFIER BELL 214 214ST 1182106SW AUTO FLIGHT FAILED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 AMPLIFIER KICKS ELEVATORS OFF LINE WHEN ENGAGED. 2G72 4U H10SW 20020311001022002031100102EU 2002 3 11 HEEA077888 120020208G2400410CC01Y140 CONTACTOR SNIAS 350 AS350B 8680801EU ELECTRICAL DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03855PH 3351 CONTACTOR HAS HIGH RESISTANCE. 1G71 3U H9EU 20020318001342002031800134NE 2002 3 18 HEEA078002 220020226G72000292005220 ENGINE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03855PH4813 3351 NO N1 INDICATION NOISE WHEN TURNING ENGINE. 1G71 3U3 U H9EU E19EU 20020318001352002031800135EU 2002 3 18 HEEA078003 120020301G2611 FIRE LOOP SNIAS 350 AS350B 8680801EU ENGINE LOOSE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03975AE 2777 PROBE BECAME UNSOLDERED AT PROBE ATTACH NUT AND CAME OUT OF ENGINE. 1G71 3U H9EU 20020319000632002031900063GL 2002 3 19 HEEA078019 220020311G723023056634 SPUR ADAPTER 23051643 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL COMPRESSOR FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033122G704 CAC90474 760232 CAE890279S COMPRESSOR WAS REMOVED WITH ENGINE DUE TO TURBINE NR 1 & 2 WHEEL CYCLES. DECISION MADE TO COMPLY WITH COMPRESSOR 2000 HOUR INSPECTION AND OVERHAUL FOR IHTI REQUIREMENTS. SPUR GEAR FAILED NO-GO GAUGE CHECK. SUBMITTAL FOR CREDIT ACCOMPLISHED ON AFA 63885A. 1G72 3U3 U H1NE E1GL 20020319000642002031900064SW 2002 3 19 HEEA078021 120020222G2730214001970111 ACTUATOR BELL 214 214ST 1182106SW ELEVATORS FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ELEVATORS WILL NOT TEST. 2G72 4U H10SW 20020319000672002031900067 2002 3 19 HEEA078022 420020222G2210214074305105 AMPLIFIER BELL 214 214ST 1182106SW AUTO FLIGHT FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ELEVATORS WILL NOT TEST. 2G72 4U H10SW 20020319000702002031900070 2002 3 19 HEEA078023 420020222G2210412074030101 ISOLATION AMP BELL 214 214ST 1182106SW AUTOFLIGHT FAILED E HEEAO OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW035748M 28102 IN FLIGHT THE CREW DETECTED A SMOKE ODOR. THE AARS AND NR 2 ELEVATOR SYSTEM WENT OFF LINE. THE CIRCUIT BREAKER FOR THE COPILOT ADI TRIPPED. MAINTENANCE REPLACED THE ISOLATION AMPLIFIER. 2G72 4U H10SW 20020319000722002031900072 2002 3 19 HEEA078024 420020222G2210222331617103 ISOLATION MOUNT BELL 230 230 1182149SW AUTOFLIGHT FAILED E HEEAO OTHER E VIBRATION/BUFFET CRCRUISE 1 SW0314UH 23028 IN CRUISE FLIGHT, AN AIRFRAME VIBRATION DEVELOPED. MAINTENANCE FOUND THE LATERAL ISOLATION MOUNT FAILED. MAINTENANCE REPLACED THE ISOLATION AMPLIFIER. 1G72 3U NCH9SW 20020319000732002031900073SW 2002 3 19 HEEA078025 120020222G8011214060056103 STARTER BELL 214 214ST 1182106SW ENGINE DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 STARTER HAS A DEAD SPOT. 2G72 4U H10SW 20020319000752002031900075SW 2002 3 19 HEEA078026 120020225G3246206053184122 SKID BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 UPON INSPECTION FOUND PRIMER COULD BE SEEN THROUGH WHITE PAINT ON THE MAJORITY OF TUBE. 1G71 3U O H2SW 20020319000772002031900077SW 2002 3 19 HEEA078027 120020225G2841407375006101 INDICATOR BELL 407 407 1182206SW FUEL QTY MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03402PH 53159 FUEL QUANTITY INDICATOR LEDS DO NOT LIGHT UP. 1G71 3U O H2SW 20020319000792002031900079SW 2002 3 19 HEEA078029 120020225G6300406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH2771 53393 MAIN ROTOR LEVER ASSY IS WORN. 1G71 3U O H2SW 20020319000802002031900080SW 2002 3 19 HEEA078030 120020225G7714407375008101 INDICATOR BELL 407 407 1182206SW DUAL TACH INTERMITTENT E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03494PH 53396 N2 DUAL TACH WORKING INTERMITTENTLY. 1G71 3U O H2SW 20020319000812002031900081SW 2002 3 19 HEEA078031 120020225G7714 NEEDLE BELL 407 407 1182206SW DUAL TACH STUCK E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03510PH 0062 53209 "T" NEEDLE STICKS AT APPROX. 35 PERCENT. 1G71 3U O H2SW 20020319000822002031900082SW 2002 3 19 HEEA078032 120020225G6220 SPRING BELL 407 407 1182206SW FRAHM ASSY BROKEN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03742PH LK75 53461 FRAHM ASSY HAS A BROKEN SPRING. 1G71 3U O H2SW 20020319000832002031900083SW 2002 3 19 HEEA078033 120020225G6230406010401117 SUPPORT BELL 407 407 1182206SW SWASHPLATE LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH316 53393 UPPER GREASE SEAL LEAKING GREASE ONTO UNIBALL. 1G71 3U O H2SW 20020319000842002031900084SW 2002 3 19 HEEA078034 120020225G6340407375001105 INDICATOR BELL 407 407 1182206SW MGB TACH INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 MAIN ROTOR GEARBOX TACH IS INOPERATIVE. 1G71 3U O H2SW 20020319000852002031900085SW 2002 3 19 HEEA078035 120020225G7714407375002103 INDICATOR BELL 407 407 1182206SW ENG NG MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 ENGINE NG TACH INTERNAL LIGHTING EXTREMELY DIM. DIFFICULT TO READ. 1G71 3U O H2SW 20020319000862002031900086SW 2002 3 19 HEEA078036 120020225G6320407375005101 INDICATOR BELL 407 407 1182206SW G/B OIL TEMP MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 INTERNAL LIGHT IS TOO WEAK. 1G71 3U O H2SW 20020319000872002031900087SW 2002 3 19 HEEA078037 120020225G6230407040011101 MAST BELL 407 407 1182206SW MAIN ROTOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03491PH1831 53386 MAIN ROTOR MAST IS LEAKING. 1G71 3U O H2SW 20020319000882002031900088SW 2002 3 19 HEEA078038 120020225G6230406010401117 SWASHPLATE BELL 407 407 1182206SW MAIN ROTOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03491PH1829 53386 SWASHPLATE GREASE LEAKING FROM UPPER SEAL. 1G71 3U O H2SW 20020319000892002031900089SW 2002 3 19 HEEA078039 120020225G6320407040006107 TRANSMISSION BELL 407 407 1182206SW M/R GEARBOX CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03721PH2677 53278 MAIN ROTOR GEARBOX TRANSMISSION HAS CORROSION ON SPLIT LINE. 1G71 3U O H2SW 20020319000902002031900090SW 2002 3 19 HEEA078040 120020225G6230406010428109 BUSHING BELL 407 407 1182206SW MAIN ROTOR HUB WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH2646 53159 MAIN ROTOR HUB BUSHINGS WORN. 1G71 3U O H2SW 20020319000922002031900092SW 2002 3 19 HEEA078042 120020225G6230406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH1046 53159 MAIN ROTOR LEVER ASSY IS WORN. 1G71 3U O H2SW 20020319000932002031900093SW 2002 3 19 HEEA078043 120020225G6230406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH1046 53159 MAIN ROTOR LEVER WORN. 1G71 3U O H2SW 20020319000942002031900094SW 2002 3 19 HEEA078045 120020226G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH2036 53396 MAIN ROTOR ROD END IS WORN. 1G71 3U O H2SW 20020319000962002031900096SW 2002 3 19 HEEA078046 120020226G2497407375012101 CONNECTOR BELL 407 407 1182206SW ECU DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 FACE ON THE CONNECTOR THAT ATTACHES TO THE ECU IS SCARRED NEAR PINS. 1G71 3U O H2SW 20020319000982002031900098SW 2002 3 19 HEEA078047 120020226G6300407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 MAIN ROTOR OIL COOLER BLOWER BEARING GREASE TURNED BLACK. 1G71 3U O H2SW 20020319000992002031900099SW 2002 3 19 HEEA078048 120020226G6720406012129101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 TAIL ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020319001122002031900112SW 2002 3 19 HEEA078049 120020226G6710PM212302 SWITCH BELL 407 407 1182206SW CYCLIC SWITCH BROKEN E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03493PH 53393 CYCLIC STICK SWITCH IS BROKEN. 1G71 3U O H2SW 20020319001152002031900115SW 2002 3 19 HEEA078050 120020226G3340MS2774318 RELAY BELL 407 407 1182206SW EXTERNAL LIGHTS STUCK E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03495PH 53397 RELAY INTERNAL CONTACTS STUCK SHUT. 1G71 3U O H2SW 20020319001232002031900123SW 2002 3 19 HEEA078051 120020226G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020319001242002031900124SW 2002 3 19 HEEA078052 120020226G3340MS2774318 RELAY BELL 407 407 1182206SW LANDING LIGHT FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 UPPER LANDING LIGHT WOULD NOT SHUT OFF. RELAY FAILED. 1G71 3U O H2SW 20020319001252002031900125SW 2002 3 19 HEEA078055 120020226G2510407370720101 SEAT BELT BELL 407 407 1182206SW COCKPIT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 SEAT BELT WORN. PART NUMBER TAG MISSING. HARDWARE RUSTING. 1G71 3U O H2SW 20020319001272002031900127SW 2002 3 19 HEEA078056 120020226G2840407362005103 SWITCH BELL 407 407 1182206SW COCKPIT FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 LOW LEVEL CAUTION LIGHT WOULD NOT EXTINGUISH. 1G71 3U O H2SW 20020319001292002031900129SW 2002 3 19 HEEA078057 120020226G7921407062021101 DUCT BELL 407 407 1182206SW OIL COOLER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 ENGINE OIL COOLER DUCT CRACKED. 1G71 3U O H2SW 20020319001312002031900131SW 2002 3 19 HEEA078058 120020226G6300407340339103 BEARING BELL 407 407 1182206SW MAIN ROTOR DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 BEARING HAS DETERIORATED RUBBER. 1G71 3U O H2SW 20020319001332002031900133SW 2002 3 19 HEEA078059 120020226G3212206050247132 COVER BELL 407 407 1182206SW EMERGENCY FLOAT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 VELCRO UNSEWN FROM COVER. 1G71 3U O H2SW 20020319001362002031900136SW 2002 3 19 HEEA078061 120020226G6710 BEARING BELL 407 407 1182206SW IDLER GEAR FROZEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 IDLER GEAR BEARING FROZEN. 1G71 3U O H2SW 20020319001402002031900140SW 2002 3 19 HEEA078062 120020226G6220 BEARING BELL 407 407 1182206SW BELLCRANK DEBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH2074 TE219 53003 BELLCRANK BUFFER UNBONDED. 1G71 3U O H2SW 20020319001452002031900145SW 2002 3 19 HEEA078063 120020226G6730206001556001 LINK BELL 407 407 1182206SW ROTOR SERVO ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 LINK BEARING RATCHETY. 1G71 3U O H2SW 20020319001462002031900146SW 2002 3 19 HEEA078064 120020226G3212206050247135 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 EMERGENCY FLOAT COVER IS TORN. 1G71 3U O H2SW 20020319001472002031900147SW 2002 3 19 HEEA078066 120020226G6510206061432121 HOUSING BELL 407 407 1182206SW COOLER BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 COOLER BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020319001482002031900148SW 2002 3 19 HEEA078067 120020226G6720406012129101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 WORN BEARINGS. 1G71 3U O H2SW 20020319001502002031900150SW 2002 3 19 HEEA078069 120020226G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT PRESSURE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 PRESSURE GAUGE FACE IS LOOSE. 1G71 3U O H2SW 20020320000012002032000001GL 2002 3 20 HEEA078070 220020226G7320412074101101 TRANSDUCER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 TRANSDUCER CAUSES ENGINE DECELERATION ON TAKE OFF. 1G71 3U3 UO H2SW E1GL 20020320000022002032000002SW 2002 3 20 HEEA078071 120020226G2822407362013101 PRESSURE SWITCH BELL 407 407 1182206SW FUEL SYSTEM INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 FUEL SYSTEM PRESSURE SWITCH IS INOPERATIVE. 1G71 3U O H2SW 20020320000032002032000003SW 2002 3 20 HEEA078072 120020226G3212206050247135 COVER BELL 407 407 1182206SW EMERGENCY FLOAT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 VELCRO COMING UNSEWN FROM END FLAPS OF EMERGENCY FLOAT COVER. 1G71 3U O H2SW 20020320000042002032000004SW 2002 3 20 HEEA078073 120020226G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL INDICATOR FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 SWITCH STICKING. 1G71 3U O H2SW 20020320000052002032000005SW 2002 3 20 HEEA078074 120020226G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH4159 53198 ROD END ON MAIN ROTOR IS WORN. 1G71 3U O H2SW 20020320000062002032000006SW 2002 3 20 HEEA078075 120020226G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 ROD END ON MAIN ROTOR IS WORN. 1G71 3U O H2SW 20020320000072002032000007SW 2002 3 20 HEEA078076 120020226G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH4159 53198 ROD END ON MAIN ROTOR IS WORN. 1G71 3U O H2SW 20020320000082002032000008SW 2002 3 20 HEEA078077 120020226G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH1269 53198 ROD END ON MAIN ROTOR IS WORN. 1G71 3U O H2SW 20020320000092002032000009SW 2002 3 20 HEEA078078 120020226G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL SYSTEM STUCK E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW03498PH 53399 STICKING LIGHT STAYS ON WITH FULLTAN. 1G71 3U O H2SW 20020320000102002032000010SW 2002 3 20 HEEA078079 120020226G6710 SPRING BELL 407 407 1182206SW SWITCH BROKEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03742PH 53461 WILL NOT KEY RADIUS. BROKEN SPRING. 1G71 3U O H2SW 20020320000112002032000011SW 2002 3 20 HEEA078080 120020226G7810407063001101 EXHAUST STACK BELL 407 407 1182206SW ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 ENGINE EXHAUST STACK IS CRACKED. 1G71 3U O H2SW 20020320000132002032000013SW 2002 3 20 HEEA078081 120020226G6320407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 COOLER BLOWER BEARING FEELS ROUGH. 1G71 3U O H2SW 20020320000142002032000014SW 2002 3 20 HEEA078082 120020226G28221C2710 CARTRIDGE BELL 407 407 1182206SW FUEL PUMP INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 FUEL PUMP CARTRIDGE IS INOPERATIVE. 1G71 3U O H2SW 20020320000152002032000015SW 2002 3 20 HEEA078083 120020226G32128226003 FUSEABLE PLUG BELL 407 407 1182206SW FLOAT LEAKING E K NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 EMERGENCY FLOAT FUSEABLE PLUG IS LEAKING. 1G71 3U O H2SW 20020320000172002032000017SW 2002 3 20 HEEA078087 120020226G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL SYSTEM MALFUNCTIONED E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW03741PH 53457 SWITCH FOR LOW LEVEL LIGHT STAYS ON. 1G71 3U O H2SW 20020320000192002032000019SW 2002 3 20 HEEA078088 120020226G6300406010417101 BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MAIN ROTOR BEARING IS WORN. 1G71 3U O H2SW 20020320000222002032000022SW 2002 3 20 HEEA078089 120020226G2510222320823130 SEAT BELT BELL 407 407 1182206SW COCKPIT FRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 COCKPIT SEAT BELT IS FRAYED. 1G71 3U O H2SW 20020320000232002032000023SW 2002 3 20 HEEA078090 120020226G6320206040156001 SEAL BELL 407 407 1182206SW M/R GEARBOX LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03720PH 53277 MAIN ROTOR GEARBOX SEAL IS LEAKING. 1G71 3U O H2SW 20020320000242002032000024SW 2002 3 20 HEEA078092 120020226G2820465C63TW VALVE BELL 407 407 1182206SW FUEL SYSTEM LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03406PH 53198 FUEL SYSTEM IS SEEPING FROM VALVE ASSY. 1G71 3U O H2SW 20020320000252002032000025SW 2002 3 20 HEEA078097 120020226G6310204040760109 FILTER ELEMENT BELL 407 407 1182206SW M/R GEARBOX CONTAMINATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03742PH 53461 MAIN ROTOR GEARBOX FILTER CAUSING CHIP LIGHT TO ILLUMINATE. 1G71 3U O H2SW 20020320000262002032000026SW 2002 3 20 HEEA078099 120020226G6520406040072105 SPLINE ADAPTER BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 TAIL ROTOR SPLINE ADAPTER SHAFT ASSY WORN. SCRAPPED IN HOUSE. 1G71 3U O H2SW 20020320000282002032000028SW 2002 3 20 HEEA078101 120020227G2435206062200123 STARTER GEN BELL 407 407 1182206SW ENGINE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03402PH 53159 STARTER GEN FAILED 300 HOUR INSPECTION. 1G71 3U O H2SW 20020320000312002032000031SW 2002 3 20 HEEA078103 120020227G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH1834 99333 53327 STARTER GEN HAS WORN BRUSHES. 1G71 3U O H2SW 20020320000322002032000032SW 2002 3 20 HEEA078104 120020227G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03490PH2927 95175 53378 STARTER GEN HAS WORN BRUSHES. 1G71 3U O H2SW 20020320000342002032000034SW 2002 3 20 HEEA078106 120020301G3212407350300101 FLOAT BELL 407 407 1182206SW MLG LEAKING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03721PH3067 53278 EMERGENCY FLOAT IS LEAKING. 1G71 3U O H2SW 20020320000362002032000036SW 2002 3 20 HEEA078107 120020301G6510407040325101 SHAFT BELL 407 407 1182206SW TAIL ROTOR PEELING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 PAINT PEELING OFF TAIL ROTOR DRIVE SHAFT. 1G71 3U O H2SW 20020320000392002032000039SW 2002 3 20 HEEA078108 120020301G6510406360500101 COOLER BELL 407 407 1182206SW TAIL ROTOR LEAKING E K NONE K FLUID LOSS ININSP/MAINT 1 SW03490PH 53378 TAIL ROTOR DRIVE SHAFT COOLER HAS A SLOW LEAK ON ENGINE COOLER SIDE. 1G71 3U O H2SW 20020320000442002032000044SW 2002 3 20 HEEA078109 120020301G28221C2710 CARTRIDGE BELL 407 407 1182206SW FUEL BOOST INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 BOOST PUMP CARTRIDGE IS INOPERATIVE. 1G71 3U O H2SW 20020320000462002032000046SW 2002 3 20 HEEA078110 120020301G6520406040400119 GEARBOX BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03740PH1000 53435 TAIL ROTOR GEARBOX HAS WORN SPLINES. 1G71 3U O H2SW 20020320000512002032000051SW 2002 3 20 HEEA078116 120020301G6220407010150103 FRAHM BELL 407 407 1182206SW M/R HEAD VIBRATION E HEEAO OTHER E VIBRATION/BUFFET NRNOT REPORTED 1 SW03404PH 53188 FRAHM ASSY CAUSING HIGH 4 REV. 1G71 3U O H2SW 20020320000532002032000053SW 2002 3 20 HEEA078118 120020301G6710206062721105 ACTUATOR BELL 206 206L3 1182108SW MAIN ROTOR INOPERATIVE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 MAIN ROTOR ACTUATOR WILL NOT MOVE WITH POWER APPLIED. 1G71 3U H2SW 20020320000552002032000055 2002 3 20 HEEA078119 420020301G2210574074264001 CONTROLLER BELL 214 214ST 1182106SW ALTITUDE MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 AIRCRAFT WILL NOT HOLD ALTITUDE. ALTITUDE CONTROLLER MALFUNCTIONED. 2G72 4U H10SW 20020320000592002032000059SW 2002 3 20 HEEA078120 120020301G6510206040339103 BEARING BELL 206 206L3 1182108SW COOLER HANGER FAILED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03 TAIL ROTOR DRIVE SHAFT COOLER HANGER BEARING FAILED. 1G71 3U H2SW 20020320000612002032000061SW 2002 3 20 HEEA078121 120020301G6510407040316101 FLYWHEEL BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03402PH 53159 TAIL ROTOR FLYWHEEL HAS WORN SPLINES. 1G71 3U O H2SW 20020320000622002032000062SW 2002 3 20 HEEA078122 120020301G6710407001523101 IDLER ASSY BELL 407 407 1182206SW M/R CONTROL WORN E O OTHER O OTHER NRNOT REPORTED 1 SW03723PH 53283 MAIN ROTOR IDLER ASSY HAS A WORN BEARING. 1G71 3U O H2SW 20020320000632002032000063SW 2002 3 20 HEEA078123 120020301G6720406012129101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03498PH 53399 MAIN ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020320000652002032000065SW 2002 3 20 HEEA078125 120020301G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03724PH 53327 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020320000662002032000066SW 2002 3 20 HEEA078126 120020301G3242D01631 PAD BELL 407 407 1182206SW BRAKE FLAKING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03719PH 53266 BRAKE PAD IS FLAKING, CAUSED BY VIBRATION. 1G71 3U O H2SW 20020320000682002032000068SW 2002 3 20 HEEA078127 120020301G6330406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03493PH 53393 LEVER HAS WEAR. 1G71 3U O H2SW 20020320000702002032000070SW 2002 3 20 HEEA078128 120020301G3212206050247135 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03493PH 53393 EMERGENCY FLOAT COVER HAS TORN STITCHING. 1G71 3U O H2SW 20020320000722002032000072SW 2002 3 20 HEEA078129 120020301G6220 BEARING BELL 407 407 1182206SW BELLCRANK WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH2074 TI473 53003 PIVOT BEARING IS WORN BEYOND LIMITS. 1G71 3U O H2SW 20020320000752002032000075SW 2002 3 20 HEEA078132 120020301G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT PRESSURE CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 CORROSION INSIDE OF FLOAT PRESSURE GAUGE. 1G71 3U O H2SW 20020320000772002032000077SW 2002 3 20 HEEA078133 120020301G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL SYSTEM MALFUNCTIONED E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03510PH 53209 MALFUNCTIONING SWITCH IS CAUSING LIGHT NOT TO GO OUT. 1G71 3U O H2SW 20020320000792002032000079SW 2002 3 20 HEEA078134 120020301G6420 BEARING BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 WORN TAIL ROTOR BEARING. 1G71 3U O H2SW 20020320000802002032000080SW 2002 3 20 HEEA078135 120020301G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 TAIL ROTOR DRIVE DISC PACK IS CRACKED. 1G71 3U O H2SW 20020320000822002032000082SW 2002 3 20 HEEA078136 120020301G6310406040548101 CONE SET BELL 407 407 1182206SW FREEWHEEL UNIT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 FREEWHEEL UNIT CONE SET IS WORN. 1G71 3U O H2SW 20020320000852002032000085SW 2002 3 20 HEEA078137 120020301G6710206001396001 SHAFT BELL 407 407 1182206SW CYCLIC STICK DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 UNABLE TO ADJUST FRICTION ROD ON CYCLIC STICK SHAFT. 1G71 3U O H2SW 20020320000862002032000086SW 2002 3 20 HEEA078138 120020301G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 TAIL ROTOR DISC PACK IS CORRODED. 1G71 3U O H2SW 20020320000892002032000089SW 2002 3 20 HEEA078139 120020301G6300406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03722PH1766 53288 MAIN ROTOR UNIVERSAL IS WORN. 1G71 3U O H2SW 20020320000932002032000093SW 2002 3 20 HEEA078140 120020301G6220407310203101 MOUNT BELL 407 407 1182206SW MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 MAIN ROTOR MOUNT HAS RUBBER SEPARATION. 1G71 3U O H2SW 20020320000952002032000095SW 2002 3 20 HEEA078141 120020301G7931222375077113 TRANSMITTER BELL 407 407 1182206SW OIL PRESSURE FLUCTUATES E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03501PH 53401 OIL PRESSURE TRANSMITTER FLUCTUATING. 1G71 3U O H2SW 20020320001092002032000109SW 2002 3 20 HEEA078142 120020301G321270079H100F210 HOSE BELL 407 407 1182206SW EMERGENCY FLOAT CHAFED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03742PH 53461 EMERGENCY FLOAT HOSE CHAFED. 1G71 3U O H2SW 20020320001102002032000110SW 2002 3 20 HEEA078143 120020301G6720 BEARING BELL 407 407 1182206SW LINK WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03402PH 53159 LINK BEARING HAS WEAR AND CORROSION. 1G71 3U O H2SW 20020320001112002032000111SW 2002 3 20 HEEA078144 120020301G2420SM20ACD300A21 RELAY BELL 407 407 1182206SW COCKPIT FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 INTERMITTENT FADEC FAULTS ON START. 1G71 3U O H2SW 20020320001232002032000123SW 2002 3 20 HEEA078147 120020301G7120407064105102 TUBE BELL 407 407 1182206SW ENGINE MOUNT DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 ENGINE MOUNT TUBE DAMAGED BEYOND LIMITS. TUBE WAS FULL OF WATER UPON REMOVAL FROM AIRCRAFT. 1G71 3U O H2SW 20020320001242002032000124SW 2002 3 20 HEEA078148 120020301G52103161201 HANDLE BELL 407 407 1182206SW CREW DOOR BENT E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 HANDLE ARM IS BENT. 1G71 3U O H2SW 20020320001252002032000125SW 2002 3 20 HEEA078149 120020301G5210407030601103 DOOR BELL 407 407 1182206SW CREW DOOR LOOSE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 DOOR WAS LOOSE ON IT'S HINGES. 1G71 3U O H2SW 20020320001262002032000126SW 2002 3 20 HEEA078150 120020301G5210407030601105 DOOR BELL 407 407 1182206SW CREW LOOSE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 DOOR WAS LOOSE ON IT'S HINGES. 1G71 3U O H2SW 20020320001272002032000127SW 2002 3 20 HEEA078153 120020301G3200400052007109 BEAM BELL 407 407 1182206SW MLG CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 MOUNT HARDWARE FROZEN IN BEAM ASSY. FOUND INNER BUSHING FACE CORRODED BEYOND LIMITS. SENDING FOR AN EVALUATION DUE TO NO PREVENTIVE MAINT ON MFG PART. 1G71 3U O H2SW 20020320001282002032000128SW 2002 3 20 HEEA078154 120020301G6710406310404101 ROD END BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X3464 53267 ROD END WORN BEYOND LIMITS. 1G71 3U O H2SW 20020320001292002032000129SW 2002 3 20 HEEA078157 120020301G3212206050247137 COVER BELL 407 407 1182206SW EMERGENCY FLOAT WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03612PH 53199 EMERGENCY FLOAT COVER HAS WORN STITCHING ON END CAPS. 1G71 3U O H2SW 20020320001312002032000131SW 2002 3 20 HEEA078158 120020301G3212206050247138 COVER BELL 407 407 1182206SW EMERGENCY FLOAT WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03612PH 53199 EMERGENCY FLOAT COVER HAS WORN STITCHING ON END CAPS. 1G71 3U O H2SW 20020320001332002032000133SW 2002 3 20 HEEA078159 120020301G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03742PH 53461 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020320001362002032000136SW 2002 3 20 HEEA078160 120020301G5321407030713103 FLOOR PANEL BELL 407 407 1182206SW CARGO BAY SEPARATED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 FLOOR PANEL SEPARATED BEYOND LIMITS. 1G71 3U O H2SW 20020320001412002032000141SW 2002 3 20 HEEA078161 120020301G6230406010427109 GIMBAL RING BELL 407 407 1182206SW SWASHPLATE CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH2791 53147 SWASHPLATE GIMBAL RING CORRODED AROUND BUSHINGS. 1G71 3U O H2SW 20020320001432002032000143SW 2002 3 20 HEEA078162 120020301G6310406040550101 ADAPTER BELL 407 407 1182206SW TRANSMISSION WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03742PH 53461 TRANSMISSION ADAPTER HAS A WORN WEAR SLEEVE. OUT OF LIMITS. 1G71 3U O H2SW 20020320001442002032000144SW 2002 3 20 HEEA078163 120020301G6310406040500119 SEAL BELL 407 407 1182206SW SUPPORT LEAKING E O OTHER O OTHER NRNOT REPORTED 1 SW03742PH 53461 SUPPORT SEAL IS LEAKING. 1G71 3U O H2SW 20020320001482002032000148SW 2002 3 20 HEEA078164 120020301G6300407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03495PH 53397 COOLER BLOWER BEARING ROUGH. 1G71 3U O H2SW 20020320001502002032000150SW 2002 3 20 HEEA078165 120020301G6310407060111101 BEARING BELL 407 407 1182206SW MOUNT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 MAIN ROTOR MOUNT HAS A WORN BEARING. 1G71 3U O H2SW 20020320001512002032000151SW 2002 3 20 HEEA078166 120020301G6310406040516101 SHAFT BELL 407 407 1182206SW FREEWHEEL UNIT WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03491PH A4845 53386 MAIN ROTOR FREEWHEEL UNIT SHAFT HAS WORN SPLINES. 1G71 3U O H2SW 20020321000012002032100001 2002 3 21 HEEA078171 420020307G2210214001970111 ACTUATOR BELL 214 214ST 1182106SW ELEVATOR MALFUNCTIONED E O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 SW03 ELEVATOR ACTUATOR OCCASSIONALLY KICKS OFF LINE ON TAKE OFF AND LANDING. 2G72 4U H10SW 20020321000022002032100002 2002 3 21 HEEA078172 420020307G2210214001970111 ACTUATOR BELL 214 214ST 1182106SW ELEVATOR WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 OPPOSITE ELEVATOR SYSTEM WOULD NOT MONITOR TEST. 2G72 4U H10SW 20020321000032002032100003SW 2002 3 21 HEEA078173 120020307G6320407375001105 INDICATOR BELL 407 407 1182206SW MGT READS LOW E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03742PH 53461 MGT INDICATOR INDICATES 10 DEGREES LOW. 1G71 3U O H2SW 20020321000042002032100004SW 2002 3 21 HEEA078174 120020307G6320406340100101 PUMP BELL 407 407 1182206SW TRANSMISSION LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW038595X 53267 EXCESSIVE LEAKAGE ON TRANSMISSION DECK. 1G71 3U O H2SW 20020321000052002032100005SW 2002 3 21 HEEA078175 120020307G7712407375003107 INDICATOR BELL 407 407 1182206SW ENG TORQUE INTERMITTENT E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03719PH 53266 TORQUE INDICATOR WORKS INTERMITTENTLY. 1G71 3U O H2SW 20020321000062002032100006SW 2002 3 21 HEEA078176 120020307G6510206340300105 DRIVE SHAFT BELL 407 407 1182206SW TAIL ROTOR SCRATCHED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03499PH842 53400 TAIL ROTOR DRIVE SHAFT SCRATCHED. 1G71 3U O H2SW 20020321000072002032100007SW 2002 3 21 HEEA078177 120020307G6321206340301103 BRAKE BELL 407 407 1182206SW ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03723PH2821 53283 ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR. 1G71 3U O H2SW 20020321000082002032100008SW 2002 3 21 HEEA078178 120020307G6321206340301103 BRAKE BELL 407 407 1182206SW ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03447PH4941 53114 MAIN ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR. 1G71 3U O H2SW 20020321000092002032100009SW 2002 3 21 HEEA078179 120020311G6710406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03740PH977 53435 MAIN ROTOR UNIVERSAL IS WORN. 1G71 3U O H2SW 20020321000102002032100010SW 2002 3 21 HEEA078180 120020311G6710406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03492PH1818 53390 MAIN ROTOR UNIVERSAL IS WORN. 1G71 3U O H2SW 20020321000112002032100011SW 2002 3 21 HEEA078181 120020311G6710406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404PH1267 53188 MAIN ROTOR UNIVERSAL IS WORN. 1G71 3U O H2SW 20020321000122002032100012SW 2002 3 21 HEEA078182 120020311G6710406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X1796 53267 MAIN ROTOR UNIVERAL IS WORN AND HAS A DEAD SPOT IN THE BEARING. 1G71 3U O H2SW 20020321000142002032100014SW 2002 3 21 HEEA078183 120020311G2820206064520103 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03407PH 53003 FUEL SYSTEM LINE HAS CORROSION. 1G71 3U O H2SW 20020321000152002032100015SW 2002 3 21 HEEA078184 120020311G6230406010427109 GIMBAL RING BELL 407 407 1182206SW SWASHPLATE WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03510PH1718 53209 SWASHPLATE GIMBLE RING IS WORN. 1G71 3U O H2SW 20020321000162002032100016SW 2002 3 21 HEEA078185 120020311G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW034999 53323 TAIL ROTOR DISC PACK IS CRACKED. 1G71 3U O H2SW 20020321000172002032100017SW 2002 3 21 HEEA078186 120020311G6220406310203101 MOUNT BELL 407 407 1182206SW MAIN ROTOR SEPARATED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03499PH 53400 MAIN ROTOR HEAD MOUNT HAS SEPARATION. 1G71 3U O H2SW 20020321000182002032100018SW 2002 3 21 HEEA078187 120020311G6220406012129101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03495PH 53397 MAIN ROTOR HEAD LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020321000192002032100019SW 2002 3 21 HEEA078188 120020311G6220407310203101 MOUNT BELL 407 407 1182206SW MAIN ROTOR DEBONDED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03612PH 53199 MAIN ROTOR HEAD MOUNT RUBBER IS DEBONDING. 1G71 3U O H2SW 20020321000202002032100020SW 2002 3 21 HEEA078189 120020311G6220407310203101 MOUNT BELL 407 407 1182206SW MAIN ROTOR DEBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MAIN ROTOR HEAD MOUNT RUBBER IS DEBONDING. 1G71 3U O H2SW 20020321000272002032100027SW 2002 3 21 HEEA078196 120020311G7714407375002103 INDICATOR BELL 407 407 1182206SW NG FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 INDICATOR BLINKS OFF. 1G71 3U O H2SW 20020321000282002032100028SW 2002 3 21 HEEA078197 120020311G7712407375003107 INDICATOR BELL 407 407 1182206SW TORQUE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW038595X 53267 TORQUE INDICATOR LIGHTING IS DIM. 1G71 3U O H2SW 20020321000292002032100029SW 2002 3 21 HEEA078198 120020311G3212407350301101 FLOAT BELL 407 407 1182206SW MLG LEAKING E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03612PH 53199 EMERGENCY FLOAT BAG LEAKING ON SIX MONTH INSPECTION. 1G71 3U O H2SW 20020321000302002032100030SW 2002 3 21 HEEA078199 120020311G6310406040500127FM FREEWHEEL UNIT BELL 407 407 1182206SW MAIN ROTOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW038595X4599 53267 MAIN ROTOR FREEWHEEL UNIT LEAKING AT FORWARD AND AFT SEALS. 1G71 3U O H2SW 20020321000312002032100031SW 2002 3 21 HEEA078200 120020311G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT PRESSURE STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 EMERGENCY FLOAT PRESSURE GAUGE STICKING. 1G71 3U O H2SW 20020321000322002032100032SW 2002 3 21 HEEA078201 120020311G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 TAIL ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020321000332002032100033SW 2002 3 21 HEEA078202 120020311G6321206340301103 BRAKE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH2426 53199 MAIN ROTOR BRAKE HAS EXCESSIVE HOUSING WEAR. 1G71 3U O H2SW 20020321000342002032100034SW 2002 3 21 HEEA078203 120020311G6321206340301103 BRAKE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH1603 53003 MAIN ROTOR BRAKE HAS EXCESSIVE PISTON WEAR IN HOUSING. 1G71 3U O H2SW 20020321000352002032100035SW 2002 3 21 HEEA078204 120020311G6321206340301103 BRAKE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03722PH1962 53288 MAIN ROTOR BRAKE HAS EXCESSIVE PISTON WEAR IN HOUSING. 1G71 3U O H2SW 20020321000362002032100036SW 2002 3 21 HEEA078205 120020311G6710406010417101 BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MAIN ROTOR BEARING IS WORN. 1G71 3U O H2SW 20020321000372002032100037SW 2002 3 21 HEEA078206 120020311G6520406040453101 SEAL BELL 407 407 1182206SW T/R GEARBOX LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03407PH 53003 TAIL ROTOR GEARBOX IS LEAKING. 1G71 3U O H2SW 20020321000382002032100038SW 2002 3 21 HEEA078207 120020311G7931222375077113 TRANSMITTER BELL 407 407 1182206SW ENGINE OIL FLUCTUATES E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW03496PH 53398 ENGINE OIL PRESSURE TRANSMITTER IS FLUCTUATING. 1G71 3U O H2SW 20020321000392002032100039SW 2002 3 21 HEEA078208 120020311G6321206340301103 BRAKE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH2740 53277 MAIN ROTOR BRAKE HAS EXCESSIVE PISTON WEAR IN HOUSING. 1G71 3U O H2SW 20020321000402002032100040SW 2002 3 21 HEEA078209 120020311G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 TAIL ROTOR LINK HAS WORN BEARINGS. 1G71 3U O H2SW 20020321000412002032100041SW 2002 3 21 HEEA078210 120020311G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 ENGINE MOUNT HAS MECHANICAL DAMAGE ON ONE LEG BEYOND MAINTENANCE MANUAL LIMITS. 1G71 3U O H2SW 20020321000422002032100042SW 2002 3 21 HEEA078211 120020311G6210406010120101 BOLT BELL 407 407 1182206SW M/R BLADE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 MAIN ROTOR BLADE BOLTS HAS PLATING MISSING AT LOWER END OF BOLT SHANK. 1G71 3U O H2SW 20020321000432002032100043SW 2002 3 21 HEEA078212 120020311G7712222375077119 TRANSMITTER BELL 407 407 1182206SW TORQUE INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03719PH 53266 TORQUE INDICATION INTERMITTENT. 1G71 3U O H2SW 20020321000442002032100044SW 2002 3 21 HEEA078213 120020311G7810407062021101 DUCT BELL 407 407 1182206SW EXHAUST CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 EXHAUST DUCT IS CRACKED. 1G71 3U O H2SW 20020321000452002032100045SW 2002 3 21 HEEA078214 120020311G6510206061432121 HOUSING BELL 407 407 1182206SW COOLER BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020321000462002032100046SW 2002 3 21 HEEA078215 120020311G3212206050247131 COVER BELL 407 407 1182206SW EMERGENCY FLOAT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 EMERGENCY FLOAT COVER HAS FORWARD END FLAP WORN. 1G71 3U O H2SW 20020321000472002032100047SW 2002 3 21 HEEA078216 120020311G6310407340102101 SEAL BELL 407 407 1182206SW TRANSMISSION LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03491PH 53386 TRANSMISSION SEAL IS LEAKING. 1G71 3U O H2SW 20020321000482002032100048SW 2002 3 21 HEEA078217 120020311G6320214040806003 PRESSURE SWITCH BELL 407 407 1182206SW M/R GEARBOX MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 MAIN ROTOR GEARBOX PRESSURE SWITCH HAS NO LIGHT INDICATION ON RUN UP. 1G71 3U O H2SW 20020321000492002032100049 2002 3 21 HEEA078222 420020228G3120B1894522282A CLOCK SNIAS 350 AS350B 8680801EU COCKPIT INACCURATE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03856PH 3352 CLOCK GAINS 5 TO 10 MINUTES AN HOUR. 1G71 3U H9EU 20020321000502002032100050EU 2002 3 21 HEEA078223 120020228G6420350A33214501 PITCH CONTROL SNIAS 350 AS350B2 8680813EU TAIL ROTOR CRACKED E O OTHER O OTHER NRNOT REPORTED 1 SW034031L 2907 CRACKED BUSHINGS AT ELASTOMERIC END. 1G71 3U H9EU 20020321000512002032100051EU 2002 3 21 HEEA078224 120020228G6420350A33214501 PITCH CONTROL SNIAS 350 AS350B 8680801EU TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03856PH 3352 TAIL ROTOR PITCH CONTROL ROD HAS BEARING WEAR. 1G71 3U H9EU 20020321000522002032100052EU 2002 3 21 HEEA078225 120020228G63229696 MOTOR SNIAS 350 AS350B 8680801EU COOLER BLOWER SEIZED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03855PH 3351 COOLER BLOWER MOTOR HAS IT`S BEARINGS FROZEN. 1G71 3U H9EU 20020321000532002032100053 2002 3 21 HEEA078226 420020228G3120B1894522282A CLOCK SNIAS 350 AS350B 8680801EU COCKPIT INACCURATE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03856PH 3352 CLOCK DOES NOT KEEP PROPER TIME. 1G71 3U H9EU 20020321000542002032100054EU 2002 3 21 HEEA078227 120020228G7931642790041 TRANSMITTER SNIAS 350 AS350B 8680801EU OIL PRESSURE MALFUNCTIONED E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03975AE 2777 OIL PRESSURE INDICATOR SHOWS NO PRESSURE ON ENGINE START. REPLACED THE OIL PRESSURE TRANSMITTER. 1G71 3U H9EU 20020321000562002032100056EU 2002 3 21 HEEA078229 120020307G6220350A31191600 STARFLEX SNIAS 350 AS350B 8680801EU MAIN ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03970AE226 3235 CRACK IN THICK PART OF STARFLEX WHERE ARMS MEET. 1G71 3U H9EU 20020321000572002032100057EU 2002 3 21 HEEA078230 120020307G6220350A33215001 BEARING SNIAS 350 AS350B 8680801EU MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03856PH 3352 MAIN ROTOR HAS WORN BEARINGS. 1G71 3U H9EU 20020321000582002032100058EU 2002 3 21 HEEA078231 120020307G7714614764021 INDICATOR SNIAS 350 AS350B 8680801EU TACHOMETER MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03975AE 2777 PILOT REPORTED NR SPLITTING 8-10 RPM HIGH. 1G71 3U H9EU 20020321000592002032100059EU 2002 3 21 HEEA078232 120020311G524310562582 DOOR BOLKMS105 BO105S 5626006EU HYD PACK DEPARTED E HEEAO OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 SW038199J S826 WHILE IN FLIGHT, THE HYDRAULIC PACK INSPECTION DOOR ON THE LT SIDE OF TRANSMISSION COWL DEPARTED AIRCRAFT. NO ADDITIONAL DAMAGE TO AIRCRAFT. REPLACED COVER. 1G72 3U H3EU 20020325001012002032500101NE 2002 3 25 HEEA078251 120020319G3110RCR32G100JM RESISTOR SKRSKYS76 S76A 8143006NE INSTRUMENT PANELFAILED E HEEAC ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TOTAKEOFF 1 SW0322342 760096 AFTER TAKEOFF, SMELLED ELECTRICAL BURNING THEN OBSERVED SMOKE COMING FROM THE INSTRUMENT PANEL. 1G72 3U H1NE 20020325001032002032500103GL 2002 3 25 HEEA078252 220020322G720023063392 ENGINE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE BAY FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 1969 53323 FADEC FAILURE ON ENG START. TOT MAXED AT 1063 DEGREES. RETURNED ENGINE TO ROLLS ROYCE FOR REPAIR 1G71 3U3 UO H2SW E1GL 20020325001052002032500105GL 2002 3 25 HEEA078253 220020322G725023007189 NOZZLE BELL 206 TH57A 1180821SW ALLSN 250C 250C18A 03011GL TURBINE SECTION FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03116 162678 TURBINE REMOVED FOR OVERHAUL. LOW AREA FLOW 10.17 CAUSE LOW POWER ON TEST CELL. POWER WENT FROM -5.3 TO -7.0. OVERHAULED NOZZLE, INSTALLED AND POWER WENT TO -3. 1G71 3U3 U EXPA1G71E4CE 20020325001062002032500106GL 2002 3 25 HEEA078254 220020322G720023071644 ECU BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 2548 53323 FADEC FAILURE ON ENG. START. T.O.T. MAXED AT 1063 DEGREES. RETURNED TO ROLLS ROYCE 1G71 3U3 UO H2SW E1GL 20020325001072002032500107NE 2002 3 25 HEEA078255 120020322G3220 PROXIMITY SWITCH SKRSKYS76 S76A 8143006NE MLG DOWNLOCK OUT OF ADJUST E HEEAO OTHER O OTHER LDLANDING 1 SW0322342 760096 WHEN PREPARING TO LAND, GOT A NOSE GEAR UNSAFE LIGHT. MAINTENANCE ADJUSTED THE DOWN LOCK PROXIMITY SWITCH. 1G72 3U H1NE 20020325001132002032500113 2002 3 25 HEEA078256 420020313G2210214074301105 AMPLIFIER BELL 214 214ST 1182106SW SCAS WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 WILL NOT MONITOR TEST AND YAW DISENGAGE LIGHT TOO DIM. 2G72 4U H10SW 20020325001162002032500116SW 2002 3 25 HEEA078257 120020313G7800212061117001 TUBE BELL 412 412 1182202SW EXHAUST WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 EXHAUST TUBE BEARINGS WORN. 1G72 4U H4SW 20020325001182002032500118SW 2002 3 25 HEEA078258 120020313G7800212061117001 TUBE BELL 412 412 1182202SW EXHAUST WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 EXHAUST TUBE BEARINGS WORN. 1G72 4U H4SW 20020325001202002032500120SW 2002 3 25 HEEA078259 120020314G3211412050045107 CROSSTUBE BELL 412 412 1182202SW AFT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 AFT CROSSTUBE HAS CORROSION BEYOND BHT LIMITS. 1G72 4U H4SW 20020325001212002032500121SW 2002 3 25 HEEA078260 120020315G7120206064107103 LEG ASSY BELL 206 206L3 1182108SW ENG MOUNT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 LOWER BEARING WORN. TUBE OPENING IS TOO LARGE FOR BEARING DIAMETER. FASTENER HOLES ARE ELONGATED. PART SCRAPPED IN HOUSE. 1G71 3U H2SW 20020325001252002032500125SW 2002 3 25 HEEA078261 120020319G6710214001970111 ACTUATOR BELL 214 214ST 1182106SW M/R CONTROL MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ELEVATOR TRIPS OFF LINE. 2G72 4U H10SW 20020325001322002032500132SW 2002 3 25 HEEA078265 120020320G8011214060056103 STARTER BELL 214 214ST 1182106SW ENGINE MALFUNCTIONED E HEEAO OTHER O OTHER TXTAXI/GRND HDL 1 SW03 STARTER WILL NOT DISENGAGE. 2G72 4U H10SW 20020326000012002032600001SW 2002 3 26 HEEA078266 120020321G3212206373901103 SOLENOID VALVE BELL 206 206L3 1182108SW MLG LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 MLG SOLENOID VALVE LEAKING. 1G71 3U H2SW 20020326000022002032600002SW 2002 3 26 HEEA078267 120020321G32121100891S TEE FITTING BELL 407 407 1182206SW MLG CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 PART IS CORRODED. 1G71 3U O H2SW 20020326000142002032600014SW 2002 3 26 HEEA078272 120020321G5311206032308121S FRAME BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 FRAME CRACK AT RT UPPER CORNER, BOLT HOLE. 1G71 3U O H2SW 20020326000152002032600015SW 2002 3 26 HEEA078273 120020321G3212206050247132 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 EMERGENCY FLOAT COVER IS TORN AND DETERIORATED. 1G71 3U O H2SW 20020326000162002032600016SW 2002 3 26 HEEA078274 120020321G3212206050247137 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 EMERGENCY FLOAT COVER IS TORN AND DETERIORATED. 1G71 3U O H2SW 20020326000172002032600017SW 2002 3 26 HEEA078275 120020321G3212206050247138 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 EMERGENCY FLOAT COVER IS TORN AND DETERIORATED. 1G71 3U O H2SW 20020326000182002032600018SW 2002 3 26 HEEA078276 120020321G6510206061432118 INLET BELL 407 407 1182206SW COOLER HOUSING CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404PH 53188 OIL COOLER BLOWER HOUSING INLET CRACKED. 1G71 3U O H2SW 20020326000192002032600019SW 2002 3 26 HEEA078277 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03721PH649 Y0292 53278 FOUND WORN BRUSHES ON 300 HOUR INSPECTION. 1G71 3U O H2SW 20020326000202002032600020SW 2002 3 26 HEEA078279 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03742PH2755 98008 53461 FAILED 300 HOUR INSPECTION (BRUSHES WORN). 1G71 3U O H2SW 20020326000212002032600021SW 2002 3 26 HEEA078280 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X2597 98084 53267 FAILED 300 HOUR INSPECTION (BRUSHES WORN). 1G71 3U O H2SW 20020326000222002032600022SW 2002 3 26 HEEA078281 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 98209 53398 STARTER GEN HAS IT`S BRUSHES WORN. 1G71 3U O H2SW 20020326000242002032600024SW 2002 3 26 HEEA078282 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404PH709 99262 53188 STARTER GEN HAS WORN BRUSHES. 1G71 3U O H2SW 20020326000252002032600025SW 2002 3 26 HEEA078283 120020321G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH1289 99318 53393 BRUSHES WORN ON STARTER GEN. 1G71 3U O H2SW 20020326000262002032600026SW 2002 3 26 HEEA078286 120020321G2820206064263101 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 FUEL LINE CORRODED. 1G71 3U O H2SW 20020326000272002032600027SW 2002 3 26 HEEA078287 120020321G2820206064263101 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 FUEL LINE CORRODED. 1G71 3U O H2SW 20020326000282002032600028SW 2002 3 26 HEEA078288 120020321G2820206064520103 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 FUEL LINE CORRODED. 1G71 3U O H2SW 20020326000292002032600029SW 2002 3 26 HEEA078289 120020321G7110206064804113 COWLING BELL 407 407 1182206SW ENG NACELLE CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 ENGINE COWL CORRODED. 1G71 3U O H2SW 20020326000302002032600030SW 2002 3 26 HEEA078290 120020321G7110206064804113 COWLING BELL 407 407 1182206SW ENG BAY CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 ENGINE COWLING CORRODED. 1G71 3U O H2SW 20020326000312002032600031SW 2002 3 26 HEEA078291 120020321G5210206064819005S SKIN BELL 407 407 1182206SW CREW DOOR CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X3264 53267 CREW DOOR SKIN IS CORRODED. 1G71 3U O H2SW 20020326000322002032600032SW 2002 3 26 HEEA078292 120020321G7110206064819006 COWLING BELL 407 407 1182206SW ENGINE BAY CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X3261 53267 COWLING CORRODED. 1G71 3U O H2SW 20020326000332002032600033SW 2002 3 26 HEEA078301 120020321G6321206340301103 BRAKE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03447PH3318 53114 COMPLY WITH 407-11-30. FOUND EXCESSIVE WEAR ON HOUSING OR MAIN ROTOR BRAKE. 1G71 3U O H2SW 20020326000502002032600050SW 2002 3 26 HEEA078302 120020321G2840206362002103 CAP BELL 407 407 1182206SW FUEL CELL CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 FUEL CAP EARS CORRODED AND BROKEN OFF ALSO STICKING. 1G71 3U O H2SW 20020326000522002032600052SW 2002 3 26 HEEA078303 120020321G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT PRESSURE DAMAGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW034999 53323 EMERGENCY FLOAT PRESSURE GAUGE FACEPLATE SPINS INSIDE GAUGE. 1G71 3U O H2SW 20020326000572002032600057SW 2002 3 26 HEEA078304 120020321G3201400052007109 BEAM BELL 407 407 1182206SW MLG CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH2791 53147 DISSIMILAR METAL, PITTING AROUND FAYING EDGE OF BUSHING AND BEAM ASSY. 1G71 3U O H2SW 20020326000582002032600058SW 2002 3 26 HEEA078305 120020321G6230406010401117 SWASHPLATE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03495PH 53397 SWASHPLATE HAS WORN COLLECTIVE LEVER BUSHINGS AND PINS. 1G71 3U O H2SW 20020326000612002032600061SW 2002 3 26 HEEA078306 120020321G6710406010417101 BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 53398 MAIN ROTOR BEARING UNSTAKED. 1G71 3U O H2SW 20020326000622002032600062SW 2002 3 26 HEEA078307 120020321G6710406010421103 SPACER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 53398 MAIN ROTOR SPACER DRIVE LINKS HAVE PLAY. 1G71 3U O H2SW 20020326001002002032600100SW 2002 3 26 HEEA078308 120020321G6710 BUSHING BELL 407 407 1182206SW LEVER WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH A2614A2627 53398 MAIN ROTOR LEVER HAS WORN BUSHINGS. 1G71 3U O H2SW 20020326001012002032600101SW 2002 3 26 HEEA078309 120020321G6710406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 53398 MAIN ROTOR LINK WORN. 1G71 3U O H2SW 20020326001022002032600102SW 2002 3 26 HEEA078310 120020321G6230406010428109 BUSHING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 53398 MAIN ROTOR BUSHING WORN. 1G71 3U O H2SW 20020326001032002032600103SW 2002 3 26 HEEA078311 120020321G6321406010429101 PIN BELL 407 407 1182206SW DRIVE LINK LOOSE E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03496PH 53398 DRIVE LINK PIN HAS PLAY. 1G71 3U O H2SW 20020326001042002032600104SW 2002 3 26 HEEA078312 120020321G6230406010432101 LINK BELL 407 407 1182206SW SWASHPLATE WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03495PH 53397 SWASHPLATE INNER RING ANTI-DRIVE LINK DUE TO BEARING WEAR. 1G71 3U O H2SW 20020326001052002032600105SW 2002 3 26 HEEA078313 120020321G6520406040400115 GEARBOX BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 TAIL ROTOR GEARBOX OUTPUT SHAFT SPLINES CORRODED. 1G71 3U O H2SW 20020326001062002032600106SW 2002 3 26 HEEA078314 120020321G6520406040400117FM GEARBOX BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH1701 53147 TAIL ROTOR GEARBOX SPLINES PITTED ON OUTPUT SHAFT. 1G71 3U O H2SW 20020326001072002032600107SW 2002 3 26 HEEA078315 120020321G6510406040453101 SEAL BELL 407 407 1182206SW TAIL ROTOR LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW03402PH 53159 TAIL ROTOR SEAL LEAKING. 1G71 3U O H2SW 20020326001082002032600108SW 2002 3 26 HEEA078316 120020321G6510406040453101 SEAL BELL 407 407 1182206SW TAIL ROTOR LEAKING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03723PH 53283 TAIL ROTOR SEAL LEAKING. 1G71 3U O H2SW 20020326001092002032600109SW 2002 3 26 HEEA078317 120020321G6310406040500119 SUPPORT 406040500123BELL 407 407 1182206SW FREEWHEEL UNIT LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW03417PH A3344 53038 MAIN ROTOR FREEWHEEL UNIT SUPPORT LEAKING. 1G71 3U O H2SW 20020326001102002032600110SW 2002 3 26 HEEA078318 120020321G6310406040500119 SUPPORT BELL 407 407 1182206SW MAIN ROTOR LEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW03493PH 53393 MAIN ROTOR SUPPORT IS LEAKING. 1G71 3U O H2SW 20020326001112002032600111SW 2002 3 26 HEEA078319 120020321G6310406040532103 BEARING 406040500119BELL 407 407 1182206SW M/R SUPPORT WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03491PH A1667 53386 MAIN ROTOR SUPPORT BEARING WORN. 1G71 3U O H2SW 20020326001122002032600112SW 2002 3 26 HEEA078320 120020321G6710406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR RATCHETING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 MAIN ROTOR UNIVERSAL IS RATCHETY. 1G71 3U O H2SW 20020326001132002032600113SW 2002 3 26 HEEA078321 120020321G6710406310411101 BOOT BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03612PH 53199 MAIN ROTOR BOOT IS CRACKED. 1G71 3U O H2SW 20020326001142002032600114SW 2002 3 26 HEEA078322 120020321G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404PH 53188 TAIL ROTOR LINK HAS WORN BEARINGS. 1G71 3U O H2SW 20020326001152002032600115SW 2002 3 26 HEEA078323 120020321G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 TAIL ROTOR LINK HAS WORN BEARINGS. 1G71 3U O H2SW 20020326001162002032600116SW 2002 3 26 HEEA078324 120020321G6220407010100115FM HUB BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH3747 53199 MAIN ROTOR HUB HAS SURFACE CORROSION. 1G71 3U O H2SW 20020326001172002032600117SW 2002 3 26 HEEA078325 120020321G6220407010100115 HUB BELL 407 407 1182206SW MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH3756 53400 MAIN ROTOR HUB HAS DAMAGE ON LOWER CONE SEAT SPLINE. 1G71 3U O H2SW 20020326001182002032600118SW 2002 3 26 HEEA078326 120020321G6220 BEARING 407010100115BELL 407 407 1182206SW M/R HEAD SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH A262 53147 MAIN ROTOR HEAD HAS SHEAR BEARING SEPARATION. REPLACED SHEAR BEARING 2 EACH. 1G71 3U O H2SW 20020326001192002032600119SW 2002 3 26 HEEA078327 120020321G6220 BEARING 407010100115BELL 407 407 1182206SW LAG DAMPER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH A348 53114 LEAD LAG DAMPER BEARINGS WORN. 1G71 3U O H2SW 20020326001202002032600120SW 2002 3 26 HEEA078328 120020321G6420 BEARING 407012101111BELL 407 407 1182206SW T/R HUB DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53198 53038 TAIL ROTOR HEAD HAS A FLAPPING BEARING,. 1G71 3U O H2SW 20020326001212002032600121SW 2002 3 26 HEEA078329 120020321G6420407312100101 BEARING 407012101111BELL 407 407 1182206SW T/R HUB DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53277 53400 TAIL ROTOR HUB HAS A FLAPPING BEARING OUTER RACE UNBONDED FROM HUB/YOKE. CLICKING WHEN FLAPPED. 1G71 3U O H2SW 20020326001322002032600132SW 2002 3 26 HEEA078330 120020321G6420407012101111 HUB BELL 407 407 1182206SW TAIL ROTOR HEAD NOISY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH2833 53209 CLICKING. 1G71 3U O H2SW 20020326001352002032600135SW 2002 3 26 HEEA078331 120020321G6420 BEARING 407012101111BELL 407 407 1182206SW TAIL ROTOR HEAD DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53393 53267 TAIL ROTOR HEAD HAS A FLAPPING BEARING 1G71 3U O H2SW 20020326001362002032600136SW 2002 3 26 HEEA078332 120020321G6410 BLADE BELL 407 407 1182206SW T/R BLADE PEELING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH443 53199 PAINT PEELING OFF BLADES. 1G71 3U O H2SW 20020326001402002032600140SW 2002 3 26 HEEA078333 120020321G6420407312100101 BEARING 407012101111BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407XM 53464 53464 TAIL ROTOR HEAD BEARING RUBBER IS WORN. 1G71 3U O H2SW 20020326001422002032600142SW 2002 3 26 HEEA078334 120020321G6210407015001117 BLADE BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53038 MAIN ROTOR BLADE IS CRACKED. 1G71 3U O H2SW 20020326001432002032600143SW 2002 3 26 HEEA078335 120020321G6210407015001117 BLADE BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 MAIN ROTOR BLADE IS CRACKED. 1G71 3U O H2SW 20020326001442002032600144SW 2002 3 26 HEEA078336 120020321G6210407015001117 BLADE BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 MAIN ROTOR BLADE LEADING EDGE EROSION STRIP AT INBOARD END OF TOP WEIGHT POCKET CRACKED. 1G71 3U O H2SW 20020326001462002032600146SW 2002 3 26 HEEA078337 120020321G5310 BRACKET BELL 407 407 1182206SW SLAT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 SLAT BRACKET CRACKED. 1G71 3U O H2SW 20020326001522002032600152SW 2002 3 26 HEEA078338 120020321G6300407040628101 TUBE BELL 407 407 1182206SW MAIN ROTOR DENTED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 TUBE DENTED. 1G71 3U O H2SW 20020326001562002032600156SW 2002 3 26 HEEA078339 120020321G3213407050201103 CROSSTUBE BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 MLG CROSSTUBE SPREAD BEYOND LIMITS. 1G71 3U O H2SW 20020326001582002032600158SW 2002 3 26 HEEA078340 120020321G3213407050202101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 CROSSTUBE HAS CORROSION BEYOND LIMITS. 1G71 3U O H2SW 20020326001592002032600159SW 2002 3 26 HEEA078341 120020321G3213407050202103 CROSSTUBE BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 CROSSTUBE SPREAD BEYOND LIMITS. 1G71 3U O H2SW 20020326001612002032600161SW 2002 3 26 HEEA078342 120020321G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 ENGINE MOUNT LOWER BEARING ON RT SIDE IS WORN. 1G71 3U O H2SW 20020326001632002032600163SW 2002 3 26 HEEA078343 120020321G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020326001652002032600165SW 2002 3 26 HEEA078344 120020321G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020326001672002032600167SW 2002 3 26 HEEA078345 120020321G7810407062021101 DUCT BELL 407 407 1182206SW EXHAUST CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 EXHAUST DUCT CRACKED. 1G71 3U O H2SW 20020326001682002032600168SW 2002 3 26 HEEA078346 120020321G2820407062532101 TUBE BELL 407 407 1182206SW FUEL SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 FUEL TUBE KINKED. 1G71 3U O H2SW 20020326001702002032600170SW 2002 3 26 HEEA078347 120020321G2820407062532101 TUBE BELL 407 407 1182206SW FUEL SYSTEM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 FUEL TUBE SLEEVE CRACKED. 1G71 3U O H2SW 20020326001722002032600172SW 2002 3 26 HEEA078348 120020321G5310407064807119 SUPPORT BELL 407 407 1182206SW FUSELAGE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 HOLES FOR BUSHING AND PIN WORN. 1G71 3U O H2SW 20020326001742002032600174SW 2002 3 26 HEEA078349 120020321G5320407070731101 SUPPORT BELL 407 407 1182206SW COCKPIT BROKEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 ADJUSTMENT DETENT SPRINGS BROKEN ON HEADSET SUPPORT BRACKET. 1G71 3U O H2SW 20020326001762002032600176SW 2002 3 26 HEEA078350 120020321G5320407070731103 SUPPORT BELL 407 407 1182206SW HEADREST BROKEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 ADJUSTMENT DETENT SPRINGS BROKEN ON HEADREST SUPPORT BRACKET 1G71 3U O H2SW 20020326001782002032600178SW 2002 3 26 HEEA078351 120020321G3213407073854101 TUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 CORROSION UNDER SLEEVE. 1G71 3U O H2SW 20020326001802002032600180SW 2002 3 26 HEEA078353 120020321G6300407310203101 MOUNT BELL 407 407 1182206SW MAIN ROTOR DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53038 ELASTOMERIC MATERIAL ON CORNER MOUNT IS DETERIORATED. 1G71 3U O H2SW 20020326001822002032600182SW 2002 3 26 HEEA078354 120020321G6510407340340101 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH 53283 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020326001832002032600183SW 2002 3 26 HEEA078355 120020321G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 TAIL ROTOR DISC PACK PITTED. 1G71 3U O H2SW 20020326001842002032600184SW 2002 3 26 HEEA078356 120020322G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW038595X 53267 ENGINE MOUNT IS WORN EXCESSIVELY. 1G71 3U O H2SW 20020326001862002032600186SW 2002 3 26 HEEA078357 120020322G3212407350300101 FLOAT BELL 407 407 1182206SW MLG LEAKING E HEEAO OOTHER OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 EMERGENCY FLOAT BAG LEAKING. 1G71 3U O H2SW 20020326001882002032600188SW 2002 3 26 HEEA078358 120020322G291070061F000X176A HOSE BELL 407 407 1182206SW T/R SERVO CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 TAIL ROTOR SERVO PRESSURE HOSE IS CORRODED AT SLEEVE DUE TO DISSMILAR METAL. 1G71 3U O H2SW 20020326001902002032600190SW 2002 3 26 HEEA078359 120020322G282070061J000V204A HOSE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH 53038 FUEL HOSE END FITTING ON HOSE CORRODED. 1G71 3U O H2SW 20020326001922002032600192SW 2002 3 26 HEEA078360 120020322G630070061J180W164A HOSE BELL 407 407 1182206SW MAIN ROTOR FRAYED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 EXCESSIVE AMOUNT OF RUBBER PROTRUDING FROM BRAIDS. 1G71 3U O H2SW 20020326001942002032600194SW 2002 3 26 HEEA078361 120020322G282070061J000V204A FITTING BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03457PH 53147 HOSE IS CORRODED AT FITTING. 1G71 3U O H2SW 20020326001952002032600195SW 2002 3 26 HEEA078362 120020322G282070079H000Y150 HOSE BELL 407 407 1182206SW FUEL SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53038 FUEL HOSE KINKED. 1G71 3U O H2SW 20020326001962002032600196SW 2002 3 26 HEEA078363 120020322G282070079H100F210 HOSE BELL 407 407 1182206SW FUEL SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 FUEL HOSE KINKED. 1G71 3U O H2SW 20020326001982002032600198SW 2002 3 26 HEEA078364 120020322G282070079K000Z232 HOSE BELL 407 407 1182206SW FUEL SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 FUEL HOSE KINKED. 1G71 3U O H2SW 20020326001992002032600199SW 2002 3 26 HEEA078365 120020322G2822407362013101 PRESSURE SWITCH BELL 407 407 1182206SW BOOST PUMP FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 BOOST PUMP CAUTION LIGHT WILL NOT COME ON. 1G71 3U O H2SW 20020327000022002032700002SW 2002 3 27 HEEA078366 120020322G2910B923X0147C HOSE BELL 407 407 1182206SW HYD SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 HYDRAULIC HOSE KINKED. 1G71 3U O H2SW 20020327000032002032700003SW 2002 3 27 HEEA078367 120020322G6400J123131 MOUNT BELL 407 407 1182206SW TAIL ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 RUBBED IS UNBONDED FROM SHOCK MOUNT. 1G71 3U O H2SW 20020327000042002032700004SW 2002 3 27 HEEA078368 120020322G6300407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 OIL COOLER BLOWER AFT BEARING ROUGH. 1G71 3U O H2SW 20020326002542002032600254SW 2002 3 26 HEEA078372 120020322G6510407040320101 SHAFT PHIPBH40701 BELL 407 407 1182206SW COOLER BLOWER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH PHI0019 53147 COOLER BLOWER SHAFT HAS SPLINE WEAR. 1G71 3U O H2SW 20020327000052002032700005SW 2002 3 27 HEEA078374 120020322G6510407340339101 BEARING PHIPBH40701FBELL 407 407 1182206SW COOLER BLOWER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH PHI0033 53398 OIL COOLER BLOWER BEARING HAS EXCESSIVE PLAY. 1G71 3U O H2SW 20020327000062002032700006SW 2002 3 27 HEEA078375 120020322G6510400040055109 HOUSING BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 TAIL ROTOR HOUSING HAS CORROSION. 1G71 3U O H2SW 20020327000072002032700007SW 2002 3 27 HEEA078376 120020322G6300S924EC2 SHROUD BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 SHROUD COVER ALL CRACKED OUT. LEXAN COVER CRACKED AND PARTS MISSING. 1G71 3U O H2SW 20020327000082002032700008SW 2002 3 27 HEEA078377 120020322G6220 PIN BELL 407 407 1182206SW M/R HUB MISINSTALLED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH109 LK21 53114 BLADE GRIP PINS INSTALLED UPSIDE DOWN. 1G71 3U O H2SW 20020327000092002032700009 2002 3 27 HEEA078380 420020322G2312064105430 TRANSCEIVER BELL 407 407 1182206SW COCKPIT MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 CANNOT CHANGE CHANNELS. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE PROBLEM. FOUND CORRODED FOILS ON DISPLAY BOARD BENEATH HEADER. REPLACED DISPLAY BOARD. REPAIRED. ADJUSTED C/N SQUELCH, FREQUENCY AND SIDETONE. BENCH CHECK GOOD. 1G71 3U O H2SW 20020327000102002032700010SW 2002 3 27 HEEA078381 120020322G5302206020113255 STRUCTURE BELL 407 407 1182206SW TAIL BOOM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 TAIL BOOM FIN IS SEPARATED AND CORRODED BEYOND LIMITS. 1G71 3U O H2SW 20020327000112002032700011GL 2002 3 27 HEEA078383 220020322G753223005366 BLEED VALVE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH9089 53283 HIGH TOT. REPLACED WITH SERVICEABLE BLEED VALVE. 1G71 3U3 UO H2SW E1GL 20020327000122002032700012GL 2002 3 27 HEEA078384 220020322G753223005366 BLEED VALVE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH2995 53283 FAILED POWER ASSURANCE CHECK. REPLACED WITH SERVICEABLE BLEED VALVE. 1G71 3U3 UO H2SW E1GL 20020327000132002032700013GL 2002 3 27 HEEA078385 220020322G724023030911 COMBUSTION LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 COMBUSTION LINER CRACKED AT FUEL NOZZLE MOUNT BOSS. 1G71 3U3 UO H2SW E1GL 20020327000162002032700016GL 2002 3 27 HEEA078386 220020322G732123054164 SENSOR BELL 407 407 1182206SW ALLSN 250C 250C47B GL FADEC MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 CAE847060 CAUSING NP1, NP1 RATE, OS, NPOS AND NPD FAULTS TO FADEC SYSTEM. REPLACED WITH SERVICEABLE PICKUP ASSY. 1G71 3U3 UO H2SW E1GL 20020327000172002032700017GL 2002 3 27 HEEA078388 220020322G742123064130 IGNITER BOX BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE INTERMITTENT E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 IGNITER WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000182002032700018GL 2002 3 27 HEEA078389 220020322G723023064570 LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL COMPRESSOR CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 CHAFING ON FUEL NOZZLE. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000192002032700019SW 2002 3 27 HEEA078390 120020322G7120 BEARING BELL 407 407 1182206SW ENG MOUNT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 10190 53147 ENGINE MOUNT BEARING WORN. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000202002032700020GL 2002 3 27 HEEA078391 220020322G732023072725 HMU BELL 407 407 1182206SW ALLSN 250C 250C47B GL FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03496PH 53398 ELONGATED DRIVE PIN HOLE, FAILED 300 HOUR BACKLASH INSPECTION. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000212002032700021GL 2002 3 27 HEEA078392 220020322G732023072725 HMU BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH2526 53398 WHEN SWITCH TO MANUAL MODE, ENGINE HAS HIGH ACCELERATION. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000222002032700022SW 2002 3 27 HEEA078393 120020322G243231908001 BATTERY BELL 407 407 1182206SW MAIN WEAK E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03723PH 53283 WEAK. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000232002032700023SW 2002 3 27 HEEA078394 120020322G243231908001 BATTERY BELL 407 407 1182206SW MAIN MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 FAILED DURING START CAUSING FADEC HORN AND RAPID RISE IN TOT. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000242002032700024SW 2002 3 27 HEEA078395 120020322G243232007001 BATTERY BELL 407 407 1182206SW MAIN DISCHARGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03436PH 51436 BATTERY WEAK. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000252002032700025SW 2002 3 27 HEEA078396 120020322G6220407010100115 HUB BELL 407 407 1182206SW MAIN ROTOR MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03417PH3756 53038 HUB WILL NOT FIT ON MAST. REPLACED WITH SERVICEABLE ASSY. 1G71 3U O H2SW 20020327000262002032700026SW 2002 3 27 HEEA078397 120020322G3213407050201101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MLG CROSSTUBE HAS CORROSION PITS. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1G71 3U O H2SW 20020327000272002032700027SW 2002 3 27 HEEA078398 120020322G5230407070620143 PANEL BELL 407 407 1182206SW CARGO DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH 53399 SIDE CARGO (LITTER) DOOR TRIM PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL. 1G71 3U O H2SW 20020327000282002032700028SW 2002 3 27 HEEA078399 120020322G5230407070620155 PANEL BELL 407 407 1182206SW CARGO DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 CARGO DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL. 1G71 3U O H2SW 20020327000292002032700029SW 2002 3 27 HEEA078400 120020322G5200407070620155 PANEL BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 GREENHOUSE WINDOW TRIM PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL. 1G71 3U O H2SW 20020327000312002032700031SW 2002 3 27 HEEA078401 120020322G5210407070620157 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 LT UPPER DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL. 1G71 3U O H2SW 20020327000402002032700040SW 2002 3 27 HEEA078402 120020322G5210407070620180 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 DOOR PANEL CRACKED. REPLACED WITH SERVICEABLE PANEL. 1G71 3U O H2SW 20020327000412002032700041SW 2002 3 27 HEEA078403 120020322G2510407070700103 FRAME BELL 407 407 1182206SW SEAT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 LOWER SEAT FRAME SUPPORT AROUND INSERTS HEAVILY CORRODED. REPLACED WITH SERVICEABLE FRAME. 1G71 3U O H2SW 20020327000422002032700042SW 2002 3 27 HEEA078404 120020322G3212407073848101 BOTTLE BELL 407 407 1182206SW EMERGENCY FLOAT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53038 RELEASE VALVE TO RESERVOIR ADAPTER CORRODED. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000432002032700043SW 2002 3 27 HEEA078405 120020322G3212407073848101 BOTTLE BELL 407 407 1182206SW EMERGENCY FLOAT LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 EMERGENCY FLOAT BOTTLE LEAKING. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000442002032700044SW 2002 3 27 HEEA078406 120020322G3212407301110 STEP BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 CORRODED AT BRACKET MOUNT BOLT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000462002032700046SW 2002 3 27 HEEA078407 120020322G3212407303003 STEP BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 CORRODED AND ELONGATED HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000472002032700047SW 2002 3 27 HEEA078408 120020322G3212407303003 STEP BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 CORRODED AROUND BOLT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000482002032700048SW 2002 3 27 HEEA078409 120020322G5210407314102 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 PILOT DOOR TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000512002032700051SW 2002 3 27 HEEA078410 120020322G2500407570001117 PANEL BELL 407 407 1182206SW CABIN CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000522002032700052SW 2002 3 27 HEEA078411 120020322G5620407706301106 WINDOW BELL 407 407 1182206SW PAX CABIN CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH 53266 RT PASSENGER WINDOW IS CRACKED NEAR UPPER MOUNTING SCREW HOLE. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020327000532002032700053 2002 3 27 HEEA078412 420020322G2562453015001 TRANSMITTER BELL 407 407 1182206SW ELT INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 SWITCH INOPERATIVE. SENT TO ARTEX AIRCRAFT SUPPLIES FOR WARRANTY REPAIR. 1G71 3U O H2SW 20020430000032002043000003NE 2002 4 30 HEEA078471 220020326G74209550168600 LEAD SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE IGNITER CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 IGNITER LEAD CHAFED. 1G71 3U3 U H9EU E19EU 20020430000042002043000004NE 2002 4 30 HEEA078472 220020326G74219550168760 IGNITER SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D1 NE ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 IGNITER HAS EXCESSIVE WEAR. 1G71 3U3 U H9EU E19EU 20020430000052002043000005NE 2002 4 30 HEEA078473 220020326G74219550175400 IGNITER SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D1 NE ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 IGNITER HAS EXCESSIVE WEAR. 1G71 3U3 U H9EU E19EU 20020430000062002043000006GL 2002 4 30 HEEA078474 220020326G73210164348810 FUEL CONTROL SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL ENGINE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034253S 760035 FUEL CONTROL ANTICIPATOR SHAFT RATCHETY. 1G72 3U3 U H1NE E1GL 20020430000072002043000007GL 2002 4 30 HEEA078481 220020329G725023071309 BEARING RACE BELL 206 TH57A 1180821SW ALLSN 250C 250C18 03011GL TURBINE SECTION SPALLED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03131 727 162817 TURBINE WAS REMOVED DUE TO METAL IN OIL. INSPECTION REVEALED SPALLING ON INNER RACE COUPLING BEARING RACE. INSTALLED NEW INNER RACE COUPLING. 1G71 3U3 U EXPA1G71E4CE 20020430000082002043000008NE 2002 4 30 HEEA078482 120020408G79209560115450 MAGNETIC SEAL SKRSKYS76 S76A 8143006NE AIR/OIL SEP FAILED E HEEAO OTHER J WARNING INDICATION CRCRUISE 1 SW0322342107 760096 DURING CRUISE FLIGHT NR 2 ENGINE LOST OIL PRESSURE. MAINTENANCE FOUND THE MAGNETIC SEAL ON THE AIR / OIL SEPARATOR GEAR HAD FAILED RESULTING IN THE LOSS OF ALL ENGINE OIL. 1G72 3U H1NE 20020430000092002043000009SW 2002 4 30 HEEA078485 120020426G63103024780 GEARBOX BELL 212 212 1181420SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03278054217 31106 GEARBOX HAS CORROSION ON CASE. 1G71 4U H4SW 20020430000102002043000010SW 2002 4 30 HEEA078486 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW03330082536 36004 MAIN ROTOR COMBINING GEARBOX MAKING METAL. 1G72 4U H4SW 20020430000112002043000011SW 2002 4 30 HEEA078487 120020426G63103024780 GEARBOX BELL 212 212 1181420SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW035736D11885 31135 MAIN ROTOR COMBINING GEARBOX MAKING METAL. 1G71 4U H4SW 20020430000122002043000012SW 2002 4 30 HEEA078488 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03223472408 36005 MAIN ROTOR COMBINING GEARBOX HAS LOW OIL PRESSURE. 1G72 4U H4SW 20020430000132002043000013SW 2002 4 30 HEEA078489 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW03108X 7162 33115 MAIN ROTOR COMBINING GEARBOX IS MAKING METAL. 1G72 4U H4SW 20020430000142002043000014SW 2002 4 30 HEEA078490 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW032258F13260 33073 MAIN ROTOR COMBINING GEARBOX IS MAKING METAL. 1G72 4U H4SW 20020430000152002043000015SW 2002 4 30 HEEA078491 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW03800Y 2914 33134 MAIN ROTOR COMBINING GEARBOX IS MAKING METAL. 1G72 4U H4SW 20020430000162002043000016SW 2002 4 30 HEEA078492 120020426G63103024780 GEARBOX BELL 412 412 1182202SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW03142PH3389 33150 MAIN ROTOR GEARBOX IS MAKING METAL. 1G72 4U H4SW 20020430000172002043000017SW 2002 4 30 HEEA078493 120020426G63103024780 GEARBOX BELL 212 212 1181420SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW035736D15707 31135 NR 1 MAIN ROTOR COMBINING GEARBOX IS MAKING METAL. 1G71 4U H4SW 20020430000182002043000018GL 2002 4 30 HEEA078505 220020426G7250 SEAL BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL TURBINE WHEEL FAILED E HEEAO OTHER KJ FLUID LOSS WARNING INDICATION NRNOT REPORTED 1 SW033107N1135 51512 CAE890024 ENGINE REMOVED DUE TO EXCESSIVE OIL CONSUMPTION. TURBINE WAS REPAIRED DUE TO EXCESSIVE OIL CONSUMPTION AND OIL QUENCHED 1ST STAGE WHEEL. GEARBOX SCAVENGE CHECKED OK. REPLACED 35-37 SEAL P/N 23031494. PART SCRAPPED. 1G71 3U3 U H2SW E1GL 20020430000192002043000019GL 2002 4 30 HEEA078506 220020426G723023004513 CARBON SEAL 23051643 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL COMPRESSOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW031545K925 CAC90511 760047 CAE890522S COMPRESSOR CARBON SEAL HAS WORN TANGS AND SLOTS. 1G72 3U3 U H1NE E1GL 20020430000202002043000020GL 2002 4 30 HEEA078507 220020426G723023004513 CARBON SEAL 23051643 BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL COMPRESSOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0331073746 CAC91631 51519 CAE895535 COMPRESSOR CARBON SEAL HAS WORN TANGS AND SLOTS. 1G71 3U3 U H2SW E1GL 20020501000012002050100001 2002 5 1 HEEA078508 420020325G345713824120234 RECEIVER BELL 407 407 1182206SW GPS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03724PH 53327 SENSITIVE TO TOUCH / VIBRATION. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000022002050100002 2002 5 1 HEEA078510 420020325G345713824120234 RECEIVER BELL 407 407 1182206SW GPS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03406PH 53198 SAFEGUARD ENABLED AND NOT DATA BASE INDICATED. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000032002050100003SW 2002 5 1 HEEA078511 120020325G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH1529 53199 STARTER GEN HAS WORN BRUSHES, FOUND ON 300 HOUR INSPECTION. 1G71 3U O H2SW 20020501000042002050100004GL 2002 5 1 HEEA078512 220020325G729723065805 HARNESS BELL 407 407 1182206SW ALLSN 250C 250C47B GL FADEC FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 FADEC FAILURE DUE TO SHORT BETWEEN PINS U & V OF HMU CONNECTOR. REPLACED WITH SERVICEABLE HARNESS. 1G71 3U3 UO H2SW E1GL 20020501000052002050100005GL 2002 5 1 HEEA078513 220020325G729723065805 HARNESS BELL 407 407 1182206SW ALLSN 250C 250C47B GL FADEC FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 FADEC FAIL AND FADEC FAULT LIGHTS KEEP COMING ON. REPLACED WITH SERVICEABLE HARNESS. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 1G71 3U3 UO H2SW E1GL 20020501000062002050100006SW 2002 5 1 HEEA078514 120020325G33404596 BULB BELL 407 407 1182206SW EXTERIOR BURNED OUT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03490PH 53378 LIGHT BURNED OUT. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE LIGHT. 1G71 3U O H2SW 20020501000072002050100007 2002 5 1 HEEA078515 420020325G34215040017901 INDICATOR BELL 407 407 1182206SW ATTITUDE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03724PH 53327 READS TWO DEGREES RIGHT WING DOWN. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000082002050100008 2002 5 1 HEEA078516 420020325G342150400179015 INDICATOR BELL 407 407 1182206SW COCKPIT PRECESSES E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03490PH 53378 PRECESSES AND TURNS COMPLETELY UPSIDE DOWN AFTER WARMED UP. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000092002050100009 2002 5 1 HEEA078517 420020325G34225050031904 INDICATOR BELL 407 407 1182206SW GYRO MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03447PH 53114 FLAG WILL NOT STAY PULLED. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000102002050100010 2002 5 1 HEEA078518 420020325G34225050031904 GYRO BELL 407 407 1182206SW COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03724PH 53327 DG SPINS AFTER AIRCRAFT STRAIGHTENS OUT. 1G71 3U O H2SW 20020501000112002050100011 2002 5 1 HEEA078519 420020325G34225050031904 GYRO BELL 407 407 1182206SW COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03406PH 53198 COMPASS CARD ON DIRECTIONAL GYRO SPINS OCCASSIONALLY WITHOUT STOPPING. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000122002050100012 2002 5 1 HEEA078520 420020325G34225050031904 GYRO BELL 407 407 1182206SW COCKPIT FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03501PH 53401 TEMPORARILY FAIL. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000132002050100013 2002 5 1 HEEA078521 420020325G34225050010902 GYRO BELL 407 407 1182206SW COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03406PH 53198 PRECESSES 50 DEGREES IN 6 MINUTES. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000142002050100014SW 2002 5 1 HEEA078522 120020325G33406839 BULB BELL 407 407 1182206SW EXTERNAL BURNED OUT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03719PH 53266 LIGHT BURNED OUT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000152002050100015SW 2002 5 1 HEEA078523 120020325G291070030X000D494 HOSE BELL 407 407 1182206SW HYD SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 HOSE KINKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000162002050100016 2002 5 1 HEEA078525 420020325G34578143902240B GPS BELL 407 407 1182206SW COCKPIT FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03740PH 53435 WILL NOT HOLD SIGNAL. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. TIGHTENED ON/OFF SWITCH. BENCH CHECK GOOD. 1G71 3U O H2SW 20020501000172002050100017SW 2002 5 1 HEEA078526 120020325G521090015102156 LATCH BELL 407 407 1182206SW PAX DOOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 LATCHES WORN AT HINGE PIN MOUNT HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020501000182002050100018SW 2002 5 1 HEEA078528 120020325G2432BD131 CONTACTOR BELL 407 407 1182206SW GENERATOR BURNED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03447PH 53114 DC GENERATOR CONTACTOR BURNED. SCRAPPED AND REPLACED PART. 1G71 3U O H2SW 20020501000192002050100019GL 2002 5 1 HEEA078529 220020325G7421CH34187A IGNITER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW038595X 53267 DELAYED STARTING. SCRAPPED LOCALLY DUE TO WORN BEYOND LIMITS. 1G71 3U3 UO H2SW E1GL 20020501000202002050100020SW 2002 5 1 HEEA078530 120020325G6510 BEARING BELL 407 407 1182206SW T/R DRIVE ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03436PH 51436 ROUGH FWD BEARING. REPLACED BEARING. 1G71 3U O H2SW 20020501000662002050100066 2002 5 1 HEEA078532 420020326G2330002000002 AMPLIFIER PA SYSTEM MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 BLOWS FUSE WHEN POWER IS APPLIED. VERIFY COMPLAINT. FOUND FUSE F1 BAD AND INTERMITTENT SHORT WHEN TAP ON TRANSFORMER T2. REPLACED FUSE F1 AND RESOLDERED CONNECTIONS ON TRANSFORMER T2. REPAIRED. 20020501000692002050100069NE 2002 5 1 HEEA078533 220020326G7314 DRIVE GEAR BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE FUEL PUMP WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03102PH PE4172 30899 WORN DRIVE SPLINES. REPLACED WITH SERVICEABLE FUEL PUMP. 1G71 4U4 U H4SW E22EA 20020501000712002050100071GL 2002 5 1 HEEA078535 220020326G726103808808 ELEMENT BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL ENGINE OIL BYPASSING E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0331821124 51076 FACET FILTER IN BYPASS CONDITION. REPLACED FILTER. 1G71 3U3 U H2SW E1GL 20020501000722002050100072GL 2002 5 1 HEEA078536 220020326G726103808808 ELEMENT BELL 206 206L1 1182107SW ALLSN 250C 250C30 03013GL ENGINE OIL BYPASSING E HEEAK NONE L NO TEST ININSP/MAINT 1 SW033905B128 45598 FACET FILTER IN BYPASS CONDITION. SCRAPPED AND REPLACED FILTER. 1G71 3U3 U H2SW E1GL 20020501000732002050100073 2002 5 1 HEEA078537 420020326G3422060002600 GYRO BELL 230 230 1182149SW COCKPIT FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03911RC 23037 INOPERATIVE WITH ATTITUDE FAIL DISPLAYED ON EADI. SENT TO GREATLAKES AVIONICS FOR INSPECTION AND REPAIR. 1G72 3U NCH9SW 20020501000742002050100074 2002 5 1 HEEA078538 420020326G2312063100700 TRANSCEIVER BELL 212 212 1181420SW COCKPIT FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW033208H 31304 TRANSCEIVER FAILED 2 YEAR INSPECTION. 1G71 4U H4SW 20020501000752002050100075SW 2002 5 1 HEEA078542 120020401G3213AB205050400063 CROSSTUBE BELL 212 212 1181420SW MLG FAILED E HEEAO OTHER O OTHER TXTAXI/GRND HDL 1 SW035736J2096 31140 DURING PASSENGER LOADING (ENGINES SECURED) AFT CROSSTUBE FAILED ONE INCH OUTBOARD OF RIGHT HAND ATTACHMENT POINT (STRESS MARKS ON TUBE INDICATES FAILURE STARTED AT THE 12 O`CLOCK POSITION). AIRCRAFT SETTLED TO THE RIGHT RESULTING IN DAMAGE TO RIGHT HAND AFT FLOAT BOARD ASSEMBLY AND TO THE RIGHT HAND SKID TUBE IN THE AREA OF THE FWD SADDLE. REPLACED AFT CROSSTUBE AND RT SKID TUBE. 1G71 4U H4SW 20020501000762002050100076SW 2002 5 1 HEEA078546 120020404G6210407015001107 BLADE BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03417PH4194 53038 CRACKED AT TRIM TAB AREA. CORROSION AROUND UPPER SCREWS FOR LOWER WEIGHT POCKETS BUILDING. 1G71 3U O H2SW 20020501000772002050100077SW 2002 5 1 HEEA078547 120020404G6320407040006107 GEARBOX BELL 407 407 1182206SW MAIN ROTOR MAKING METAL E HEEAO OTHER J WARNING INDICATION NRNOT REPORTED 1 SW03721PH998 53278 CHIP LIGHT. 3 FLAKES IN LOWER PLUG. CHIP LIGHT DURING PENALTY RUN. FLAKES AND BRASS IN FILTER. 1G71 3U O H2SW 20020501000782002050100078SW 2002 5 1 HEEA078549 120020404G6230407040011101 MAST BELL 407 407 1182206SW MAIN ROTOR CRACKED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03612PH2496 53199 MAST 2ND STAGE FORWARD COOLING PLATE CRACKED. 1G71 3U O H2SW 20020501000792002050100079SW 2002 5 1 HEEA078554 120020405G2822407362005105 SWITCH BELL 407 407 1182206SW FUEL BOOST CORRODED E HEEAO OTHER L NO TEST NRNOT REPORTED 1 SW03447PH 53114 CORROSION ON EXTERIOR OF BOOST PUMP SWITCH. 1G71 3U O H2SW 20020501000802002050100080SW 2002 5 1 HEEA078555 120020405G6710406310404101 ROD END BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 WORN ROD END BEARING. 1G71 3U O H2SW 20020501000922002050100092SW 2002 5 1 HEEA078556 120020405G6510206061432117 IMPELLER BELL 407 407 1182206SW T/R BLOWER BENT E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03510PH 53209 TAIL ROTOR BLOWER IMPELLER IS BENT. 1G71 3U O H2SW 20020501000932002050100093SW 2002 5 1 HEEA078558 120020405G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03404PH 53188 TAIL ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020501000942002050100094SW 2002 5 1 HEEA078559 120020405G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03491PH 53386 TAIL ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020501000952002050100095SW 2002 5 1 HEEA078560 120020405G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03491PH 53386 WORN BEARING. 1G71 3U O H2SW 20020501000962002050100096SW 2002 5 1 HEEA078561 120020405G3212206050247138 COVER BELL 407 407 1182206SW MLG FLOAT WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03402PH 53159 MLG EMERGENCY FLOAT COVER IS WORN AND TORN. 1G71 3U O H2SW 20020501000982002050100098SW 2002 5 1 HEEA078562 120020405G6300407040628101 TUBE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03721PH 53278 MAIN ROTOR TUBE HAS WORN SPOTS. 1G71 3U O H2SW 20020501000992002050100099SW 2002 5 1 HEEA078563 120020405G6300407040627101 TUBE BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03721PH 53278 MAIN ROTOR TUBE HAS WORN SPOTS. 1G71 3U O H2SW 20020501001002002050100100SW 2002 5 1 HEEA078573 120020405G7921406360500101 OIL COOLER BELL 407 407 1182206SW ENGINE OIL CLOGGED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03447PH 53114 ENGINE OIL COOLER IS CLOGGED WITH GREASE. 1G71 3U O H2SW 20020501001172002050100117SW 2002 5 1 HEEA078574 120020405G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH 53399 TAIL ROTOR DISC PACK IS SEPARATED. 1G71 3U O H2SW 20020502000052002050200005SW 2002 5 2 HEEA078575 120020405G2821 WARNING LIGHT BELL 407 407 1182206SW COCKPIT ILLUMINATED E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03612PH 53199 FUEL FILTER LIGHT ILLUMINATED, CHANGED FILTER AND LIGHT STILL ILLUMINATED. 1G71 3U O H2SW 20020502000062002050200006SW 2002 5 2 HEEA078576 120020405G291070079H100F210 HOSE BELL 407 407 1182206SW HYD SYSTEM CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 HYDRAULIC HOSE CHAFING ON THE FIRE SLEEVE FROM THE MLG DOOR SUPPORT. 1G71 3U O H2SW 20020502000072002050200007SW 2002 5 2 HEEA078577 120020405G6220407001526105 BELLCRANK BELL 407 407 1182206SW MAIN ROTOR HEAD UNBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03742PH1006 53461 BELLCRANK WASHERS UNBONDED. 1G71 3U O H2SW 20020502000082002050200008SW 2002 5 2 HEEA078578 120020405G6220407001524105 BELLCRANK BELL 407 407 1182206SW MAIN ROTOR HEAD UNBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03742PH1006 53461 WASHERS UNBONDED. 1G71 3U O H2SW 20020502000092002050200009SW 2002 5 2 HEEA078579 120020405G3212206050247138 COVER BELL 407 407 1182206SW EMERGENCY FLOAT DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 DETERIORATED. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#72948902. 1G71 3U O H2SW 20020502000102002050200010SW 2002 5 2 HEEA078580 120020405G3212206050247137 COVER BELL 407 407 1182206SW EMERGENCY FLOAT DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 DETERIORATED, END CAP TORN. 1G71 3U O H2SW 20020502000112002050200011SW 2002 5 2 HEEA078581 120020405G6230406010126107 DRIVE RING BELL 407 407 1182206SW MAIN ROTOR FLAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH1262 53038 DRIVE RING SET BLUE EPOXY FLAKING. 1G71 3U O H2SW 20020502000122002050200012SW 2002 5 2 HEEA078582 120020405G7714407375008101 INDICATOR BELL 407 407 1182206SW DUAL TACH INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03407PH 53003 DUAL TACHOMETER IS INOPERATIVE. 1G71 3U O H2SW 20020502000132002050200013SW 2002 5 2 HEEA078583 120020405G6710406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH3292 53198 LINK ASSY HAS WORN BUSHINGS. 1G71 3U O H2SW 20020502000142002050200014SW 2002 5 2 HEEA078584 120020405G6230406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH1961 53198 MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS. 1G71 3U O H2SW 20020502000152002050200015SW 2002 5 2 HEEA078585 120020405G6230406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH4335 53198 MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS. 1G71 3U O H2SW 20020502000162002050200016SW 2002 5 2 HEEA078586 120020405G6230406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH1706 53198 LINK ASSY HAS WORN BUSHINGS. 1G71 3U O H2SW 20020502000172002050200017SW 2002 5 2 HEEA078588 120020405G6321 PAD BELL 407 407 1182206SW ROTOR BRAKE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 PAD AND BOLTS WORN. 1G71 3U O H2SW 20020502000182002050200018 2002 5 2 HEEA078592 420020408G2210214074305105 AMPLIFIER BELL 214 214ST 1182106SW AUTOFLIGHT INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 NR 1 ELEVATOR SYSTEM WILL ONLY STAY ON LINE FROM 15 MINUTES TO ONE HOUR 30 MINUTES. CAN RE-ENGAGE SYSTEM AND WILL WORK FOR ABOUT ANOTHER HOUR BEFORE KICKING OFF LINE. 2G72 4U H10SW 20020502000192002050200019SW 2002 5 2 HEEA078593 120020408G2497 CONNECTOR BELL 407 407 1182206SW BUSS BAR LOOSE E HEEAO OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SW03436PH 51436 IN CRUISE FLIGHT PILOT SMELLED SOMETHING BURNING. SMELL FROM BAGGAGE COMPARTMENT. MAINTENANCE FOUND LOOSE CONNECTIONS AT STARTER RELAY TO LINE CONTROL RELAY. ARCING OCCURRED AT STARTER RELAY TERMINAL A2 AND AT LINE CONTROL RELAY TERMINAL A2 ALSO FOUND BURNED AND MELTED HEAT SHRINK. 1G71 3U O H2SW 20020502000202002050200020SW 2002 5 2 HEEA078594 120020412G6300412040385101 CASE BELL 412 412 1182202SW MAIN ROTOR CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 RE-INFORCEMENT RIB NEXT TO OIL JET BOSS WAS IMPROPERLY MACHINED AND OIL COLLECTOR PAN P/N 212-040-146-001 RUBS ON RIB. 1G72 4U H4SW 20020502000212002050200021SW 2002 5 2 HEEA078599 120020418G8011214060056103 STARTER BELL 214 214ST 1182106SW ENGINE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 STARTER SPINS BUT DOES NOT ENGAGE. 2G72 4U H10SW 20020502000222002050200022SW 2002 5 2 HEEA078600 120020418G5311205032810115S FRAME BELL 412 412 1182202SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 AIRCRAFT RECEIVED WITH CRACK IN LOWER FORWARD RADIUS ON FLANGE. 1G72 4U H4SW 20020502000232002050200023SW 2002 5 2 HEEA078601 120020418G6710214001347005 ACTUATOR BELL 214 214ST 1182106SW AUTOFLIGHT SYS FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ROTARY ACTUATOR IS STICKING. WILL NOT RELEASE. 2G72 4U H10SW 20020502000242002050200024SW 2002 5 2 HEEA078604 120020422G5620206031501133 WINDOW BELL 206 206L3 1182108SW FUSELAGE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 NO RAILS FOR SLIDING WINDOW. NO PLASTIC BORDER FOR RIVETING TO DOOR. 1G71 3U H2SW 20020502000252002050200025SW 2002 5 2 HEEA078605 120020422G3212214031792101 COVER BELL 214 214ST 1182106SW EMERGENCY FLOAT LOOSE E HEEAK NONE O OTHER ININSP/MAINT 1 SW035748M 28102 FOUND LT FLOAT FAIRING LOOSE. FOUND TOP EDGE HAD COME LOOSE FROM SCREWS AND WIND HAD PULLED COVER OPEN. 2G72 4U H10SW 20020502000262002050200026SW 2002 5 2 HEEA078608 120020423G8011214060056103 STARTER BELL 214 214ST 1182106SW ENGINE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 WILL NOT MOTOR ENGINE. SOUNDS LIKE STARTER PAWL NOT ENGAGING. 2G72 4U H10SW 20020502000272002050200027SW 2002 5 2 HEEA078611 120020426G2435 DAMPENER BELL 407 407 1182206SW STARTER GEN CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH1761 99261 53399 STARTER GEN HAS A PITTED DAMPNER PLATE. 1G71 3U O H2SW 20020502000282002050200028EU 2002 5 2 HEEA078621 120020326G6321350A32050002 BRAKE SNIAS 350 AS350B 8680801EU MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH1137 3352 ROTOR BRAKE WORN. REPLACED WITH SERVICEABLE PART. 1G71 3U H9EU 20020502000292002050200029EU 2002 5 2 HEEA078622 120020326G6321350A32501000 BRAKE SNIAS 350 AS350B 8680801EU MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03974AE 2653 ROTOR BRAKE LINING WORN. SCRAPPED PER AEC. 1G71 3U H9EU 20020502000302002050200030EU 2002 5 2 HEEA078623 120020326G6220350A32308801 FLANGE SNIAS 350 AS350B 8680801EU MAIN ROTOR GOUGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03974AE 2653 FACE OF FLANGE ON MAIN ROTOR, HAS DEEP GOUGE. 1G71 3U H9EU 20020502000312002050200031EU 2002 5 2 HEEA078624 120020326G6420704A33651190 BEARING 350A33200406SNIAS 350 AS350B 8680801EU T/R SPIDER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03854PH1958 MA0542 3248 T/R SPIDER SLIDER BEARINGS WORN. 1G71 3U H9EU 20020502000322002050200032EU 2002 5 2 HEEA078625 120020326G6420 BEARING SNIAS 350 AS350B2 8680813EU TAIL ROTOR HEAD WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 TAIL ROTOR HUB HAS WORN BEARINGS. 1G71 3U H9EU 20020502000332002050200033EU 2002 5 2 HEEA078626 120020326G6420 BEARING SNIAS 350 AS350B 8680801EU T/R HEAD WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 BEARINGS DELAMINATED. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1G71 3U H9EU 20020502000342002050200034EU 2002 5 2 HEEA078627 120020326G6420 BEARING SNIAS 350 AS350B 8680801EU T/R HEAD WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03855PH 3351 WORN BEARINGS. REPLACED WITH SERVICEABLE ASSY. 1G71 3U H9EU 20020502000352002050200035EU 2002 5 2 HEEA078628 120020326G6720 BEARING SNIAS 350 AS350B 8680801EU T/R PITCH CTRL WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 T/R PITCH CONTROL BEARING WORN. 1G71 3U H9EU 20020502000362002050200036EU 2002 5 2 HEEA078629 120020326G6720 BUSHING SNIAS 350 AS350B 8680801EU T/R PITCH CNTL CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 BUSHINGS CRACKED AND CORRODED. SCRAPPED PER AEC. 1G71 3U H9EU 20020502000372002050200037EU 2002 5 2 HEEA078630 120020326G6520350A33215300 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03971AE1120 3230 TAIL ROTOR BEARING HAS RUBBER CRACKED AND DETERIORATED ON BEARING. SCRAPPED PER AEC. 1G71 3U H9EU 20020502000382002050200038EU 2002 5 2 HEEA078631 120020326G6230 TUBE SNIAS 350 AS350B2 8680813EU SWASHPLATE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 SWASHPLATE GUIDE HAS A WORN TUBE. 1G71 3U H9EU 20020502000392002050200039EU 2002 5 2 HEEA078632 120020326G6220350A37124420 BOLT SNIAS 350 AS350B2 8680813EU MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 M/R ATTACHMENT BOLT WORN THREADS ON SMALL STUD. SCRAPPED. 1G71 3U H9EU 20020502000402002050200040EU 2002 5 2 HEEA078633 120020326G6410355A09103601 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03856PH 3352 TAIL ROTOR HAS A WORN BEARING. 1G71 3U H9EU 20020502000412002050200041EU 2002 5 2 HEEA078634 120020326G6410355A09103601 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03971AE238 3230 TAIL ROTOR LAMINANT SEPARATION AT THE END OF THE BEARINGS. (SCRAPPED) 1G71 3U H9EU 20020502000422002050200042EU 2002 5 2 HEEA078635 120020326G6410355A09103601 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03974AE 2653 TAIL ROTOR BEARING WEAR AND DETERIORATION AND DELAMINATION. (SCRAPPED) 1G71 3U H9EU 20020502000432002050200043 2002 5 2 HEEA078636 420020326G3421504001790116 GYRO SNIAS 350 AS350B 8680801EU COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03856PH 3352 INDICATOR UNRELIABLE. REPLACED WITH SERVICEABLE PART. 1G71 3U H9EU 20020502000442002050200044 2002 5 2 HEEA078637 420020326G34225050010902 GYRO SNIAS 350 AS350B2 8680813EU COCKPIT INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0340466 3004 DG TOTALLY INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1G71 3U H9EU 20020502000452002050200045EU 2002 5 2 HEEA078638 120020326G6220704A33633211 STOP SNIAS 350 AS350B 8680801EU STARFLEX SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03971AE1120 3230 SEPARATION AT STARFLEX ATTACH POINT. 1G71 3U H9EU 20020502000462002050200046EU 2002 5 2 HEEA078639 120020326G8000845UN01Q1AA5F SWITCH SNIAS 350 AS350B 8680801EU STARTER FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03971AE309 3230 INTERMITTENT STARTING PROBLEM. 1G71 3U H9EU 20020502000472002050200047EU 2002 5 2 HEEA078640 120020326G2140857A1641 VALVE SNIAS 350 AS350B 8680801EU HEATER STIFF E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03856PH 3352 HEATER VALVE HARD TO TURN, WILL NOT TURN OFF. 1G71 3U H9EU 20020502000482002050200048EU 2002 5 2 HEEA078641 120020326G79209560158180 FILTER SNIAS 350 AS350B 8680801EU OIL SYSTEM DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03854PH 3248 OIL FILTER MESH DAMAGE. 1G71 3U H9EU 20020502000492002050200049 2002 5 2 HEEA078642 420020326G23129710831 RADIO SNIAS 350 AS350B 8680801EU COCKPIT MALADJUSTMENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03970AE 3235 VHF WILL NOT TRANSMIT. 1G71 3U H9EU 20020502000502002050200050 2002 5 2 HEEA078643 420020326G23129710831 RADIO SNIAS 350 AS350B 8680801EU COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03970AE 3235 RECEPTION ON VHF BAND BREAKS UP GD-1, GD-2 ON VHF BAND. 1G71 3U H9EU 20020502000512002050200051 2002 5 2 HEEA078644 420020326G3416D120P2T ANEROID SNIAS 350 AS350B 8680801EU COCKPIT READS LOW E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03971AE982 3230 READS 100 FEET LOW AND SOMETIMES 300 FEET LOW. 1G71 3U H9EU 20020502000522002050200052EU 2002 5 2 HEEA078645 120020326G2550S12 GAUGE SNIAS 350 AS350B 8680801EU CARGO LIFT INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03856PH 3352 SHACKLE GAUGE WOULD NOT INDICATE LOAD WEIGHT. 1G71 3U H9EU 20020502000532002050200053 2002 5 2 HEEA078646 420020326G34570110005400 GPS BOLKMS105 BO105S 5626006EU COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03135AE S838 PILOT REPORTS THAT GPS TAKES 5-10 MINUTES TO CHANGE FUNCTIONS. PERFORMED PRELIMINARY INSPECTION. VERIFIED UNIT TAKES TOO LONG TO LOCK ON AND CRSR AND ENT BUTTONS INTERMITTENT AND NAV LED NOT WORKING. SENT TO GARMIN INTERNATIONAL FOR INSPECTION AND REPAIR. 1G72 3U H3EU 20020502000542002050200054EU 2002 5 2 HEEA078647 120020412G2510350A77125807 SEAT SNIAS 350 AS350B 8680801EU COCKPIT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03973AE 3229 COCKPIT SEAT IS CRACKED. 1G71 3U H9EU 20020502000552002050200055EU 2002 5 2 HEEA078648 120020426G6420 BEARING SNIAS 350 AS350B2 8680813EU TAIL ROTOR HUB WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 TAIL ROTOR HUB HAS A WORN BEARING. 1G71 3U H9EU 20020502000562002050200056EU 2002 5 2 HEEA078649 120020426G6420 BEARING SNIAS 350 AS350B 8680801EU TAIL ROTOR HUB DELAMINATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03855PH 3351 TAIL ROTOR HUB HAS BEARINGS DELAMINATED. 1G71 3U H9EU 20020529000012002052900001NE 2002 5 29 HEEA078701 120020506G760070BMA01040 ECU SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S1 60030NE NR 2 ENGINE FAILED E HEEAO OTHER J WARNING INDICATION NRNOT REPORTED 1 SW03505PH 760505 RECEIVED MAJOR FAULT ON NR 2 ENGINE. FOUND NR 2 ENGINE ECU FAILED. 1G72 3U3 UNCH1NE E19EU 20020529000102002052900010GL 2002 5 29 HEEA078702 220020514G726023031219 BEARING 23008586 BELL 206 206L 1181522SW ALLSN 250C 250C30 03013GL ENGINE FAILED E HEEAO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 SW03530JC CAG97610 CAE900110 REMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE. NR 3 AND 4 BEARING FAILURE. 1G71 3U3 U H2SW E1GL 20020529000132002052900013GL 2002 5 29 HEEA078703 220020514G7260230312681 BEARING 23008586 BELL 206 206L 1181522SW ALLSN 250C 250C30 03013GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03530JC CAG97610 CAE900110 REMOVED DUE TO ENGINE RAN WITH LOW OIL PRESSURE. NR 3 AND 4 BEARING FAILURE. 1G71 3U3 U H2SW E1GL 20020529000202002052900020GL 2002 5 29 HEEA078704 220020515G725023053299 TURBINE WHEEL BELL 230 230 1182149SW ALLSN 250C 250C30 03013GL ENGINE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0314UH 1697 23028 CAE898258 TURBINE REMOVED FOR OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED LIGHT SULFIDATION ON BACK SIDE OF 1ST STAGE WHEEL LEADING EDGE BLADES. SCRAPPED. 1G72 3U3 UNCH9SW E1GL 20020529000212002052900021GL 2002 5 29 HEEA078705 220020515G724023064570 LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 WORN NOZZLE FERRULE AND CRACKS IN VARIOUS WELDMENTS. 1G71 3U3 UO H2SW E1GL 20020529000222002052900022SW 2002 5 29 HEEA078706 120020515G760023071644 ECU BELL 407 407 1182206SW ENGINE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 ECU HAS TWO PINS BENT OVER IN FORWARD CONNECTOR PLUG. 1G71 3U O H2SW 20020529000242002052900024NE 2002 5 29 HEEA078707 220020516G7200 ENGINE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D1 NE NACELLE MALFUNCTIONED E HEEAK NONE O OTHER NRNOT REPORTED 1 SW03971AE1558 3230 22072 ENGINE TAKES SEVERAL ATTEMPTS TO START AFTER THE ENGINE IS RUN AND GETS WARMED UP. STARTS OK WHEN COLD. 1G71 3U3 U H9EU E19EU 20020529000272002052900027EU 2002 5 29 HEEA078708 120020516G75009550166140 TRANSDUCER SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D1 NE P3 PRESSURE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03972AE 3234 22087 INTERMITTENT P3 FAILURES WITH AMBER GOVERNOR CAUTION LIGHT COMING ON. 1G71 3U3 U H9EU E19EU 20020529000282002052900028NE 2002 5 29 HEEA078709 220020516G74219550175400 IGNITER SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D1 NE ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03854PH 3248 ENGINE IGNITER WORN. 1G71 3U3 U H9EU E19EU 20020529000312002052900031NE 2002 5 29 HEEA078710 120020520G78100401287410 EXHAUST STACK SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03505PH 760505 LT ENGINE EXHAUST STACK IS CRACKED. 1G72 3U3 UNCH1NE E19EU 20020529000332002052900033 2002 5 29 HEEA078711 420020520G2312064100900 TRANSCEIVER SKRSKYS76 S76A 8143006NE COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW034253S 760035 TRANSCEIVER RECEIVES GARBLED. PERFORMED PRELIMINARY INSPECTION. FOUND RECEIVER VERY WEAK. REALIGNED RECEIVER. NO HELP. FOUND SEVERAL INCORRECT VOLTAGES IN IF AND DETECTOR CIRCUITS. SWAPPED CR309 AND CR310 DIODES AND C323 AND C324 CAPACITORS. REALIGNED PRESELECTOR AND I F, NO HELP. SWAPPED C376 CAPACITOR. ALIGNED I F, NO HELP. REALIGNED PRESELECTOR AND I F AND ADJUSTED R333 IF AGC. RECEIVER SENSITIVITY GOOD, BUT COULD NOT ADJUST SQUELCH TO SPECS. REPLACED I303 IC AND RECEIVER NOW RECEIVING STRONG. REPLACED Q304 RESISTOR. REPLACED I304 IC CHIP AND REALIGNED RECEIVER. REPAIRED. BENCH CHECK GOOD. 1G72 3U H1NE 20020529000362002052900036NE 2002 5 29 HEEA078712 120020520G25101S20B25A4X27 INERTIA REEL SKRSKYS76 S76A 8143006NE COCKPIT DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03792CH 760193 PILOT AND COPILOT INERTIA REEL WEBBING DETERIORATED. REPLACED WITH SERVICEABLE ASSEMBLIES. 1G72 3U H1NE 20020529000372002052900037GL 2002 5 29 HEEA078713 220020520G732023007827 VALVE SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30 03013GL ENGINE STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW035435V 760158 SOLENOID VALVE STUCK OPEN. REPLACED WITH SERVICEABLE VALVE. 1G72 3U3 U H1NE E1GL 20020529000382002052900038GL 2002 5 29 HEEA078714 220020520G732025490925 FUEL CONTROL SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL NR 2 ENGINE SURGES E HEEAK NONE O OTHER ININSP/MAINT 1 SW035435V1689 760158 CAE890432S NR 2 ENGINE SURGES. TESTED UNIT AS RECEIVED AND COULD NOT DUPLICATE PROBLEM. UNIT TESTED SATISFACTORY. 1G72 3U3 U H1NE E1GL 20020529000412002052900041NE 2002 5 29 HEEA078715 220020520G720070BMA01080 ECU SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S1 60030NE ENGINE FAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03505PH 760505 ECU FAULT. TO BE SENT TO VENDOR FOR REPAIR. 1G72 3U3 UNCH1NE E19EU 20020529000452002052900045NE 2002 5 29 HEEA078716 120020520G6230SB5200103 BEARING SKRSKYS76 S76A 8143006NE SWASHPLATE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03913UK 760276 SWASHPLATE BEARING HAS WORN TEFLON. REPLACED WITH SERVICEABLE BEARINGS. 1G72 3U H1NE 20020529000462002052900046NE 2002 5 29 HEEA078717 120020520G6230SB5200102 BEARING SKRSKYS76 S76A 8143006NE SWASHPLATE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW031545K 760047 SWASHPLATE BUSHING WORN. REPLACED WITH SERVICEABLE BEARINGS. 1G72 3U H1NE 20020529000482002052900048NE 2002 5 29 HEEA078718 120020520G6230SB5200103 BEARING SKRSKYS76 S76A 8143006NE SWASHPLATE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03761PH 760224 SWASHPLATE BEARING HAS WORN TEFLON. REPLACED WITH SERVICEABLE BEARINGS. 1G72 3U H1NE 20020529000492002052900049NE 2002 5 29 HEEA078719 120020520G62107615009100051A BLADE SKRSKYS76 S76A 8143006NE MAIN ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911MJ14894 760231 BLADE SKIN CRACKED ON LOWER SURFACE NEAR THE TIP OF TIP RIB. 1G72 3U H1NE 20020529000522002052900052NE 2002 5 29 HEEA078720 120020520G62107615009100051A BLADE SKRSKYS76 S76A 8143006NE MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034253S13778 760035 NICKEL LEADING EDGE STRIP IS COMING OFF AFTER BEING REPAIRED ONLY 378:25 HOURS. 1G72 3U H1NE 20020529000532002052900053NE 2002 5 29 HEEA078721 120020520G62107615009100053 BLADE SKRSKYS76 S76A 8143006NE MAIN ROTOR MISMANUFACTURED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 5266 MAIN ROTOR BLADE MISMANUFACTURED, UNABLE TO BALANCE. TOO HEAVY. 1G72 3U H1NE 20020529000552002052900055NE 2002 5 29 HEEA078722 120020520G3020 ANTI-ICE SYSTEM SKRSKYS76 S76A 8143006NE BELLMOUTH INTAKEMALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03792CH 760193 BELLMOUTH HEATS UP BUT WILL NOT EXTINGUISH ANTI ICE CAUTION LIGHT. SENT TO VENDOR FOR REPAIR. 1G72 3U H1NE 20020529000562002052900056NE 2002 5 29 HEEA078723 120020520G6420 BUSHING SKRSKYS76 S76A 8143006NE FRICTION LEVER LOOSE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911MJ 760231 ROLL FRICTION ASSEMBLY LEVERS WORN AND BUSHINGS LOOSE. SCRAPPED AND REPLACED WITH SERVICEABLE LEVER. 1G72 3U H1NE 20020529000572002052900057NE 2002 5 29 HEEA078724 120020520G67207640003210043 BELLCRANK SKRSKYS76 S76A 8143006NE TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW035426U 760167 TAIL ROTOR BELLCRANK HAS WORN BEARINGS. REPLACED WITH SERVICEABLE BELLCRANK. 1G72 3U H1NE 20020529000582002052900058NE 2002 5 29 HEEA078725 120020520G3110 LIGHT SKRSKYS76 S76A 8143006NE TRIPLE TACH INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03911MJ 760231 PILOT TRIPLE TACH INSTRUMENT LIGHT INTERMITTENT. REPLACED WITH SERVICEABLE PART. 1G72 3U H1NE 20020529000592002052900059NE 2002 5 29 HEEA078726 120020520G77227645001076107 INDICATOR SKRSKYS76 S76A 8143006NE COCKPIT READS HIGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911MJ 760231 INDICATOR READS 100 - 150 DEGREES HIGH THROUGHOUT ITS OPERATIONAL RANGE. 1G72 3U H1NE 20020529000602002052900060NE 2002 5 29 HEEA078727 120020520G77147645001076110 INDICATOR SKRSKYS76 S76A 8143006NE ENGINE N1 INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03792CH 760193 AFTER START, PILOT N1 INDICATOR DROPPED TO ZERO AND STAYED THERE. 1G72 3U H1NE 20020529000612002052900061NE 2002 5 29 HEEA078728 120020520G28417645001078103 INDICATOR SKRSKYS76 S76A 8143006NE FUEL QTY INOPERATIVE E HEEAK NONE LW NO TEST INADEQUATE Q C ININSP/MAINT 1 SW035435V 760158 INDICATOR BAD FROM STOCK. NO INDICATION OR NEEDLE MOVEMENT. 1G72 3U H1NE 20020529000622002052900062NE 2002 5 29 HEEA078729 120020520G21217650007901103 BLOWER SKRSKYS76 S76A 8143006NE CABIN AIR INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03199CH 760261 VENT BLOWER INOPERATIVE. 1G72 3U H1NE 20020529000632002052900063NE 2002 5 29 HEEA078730 120020520G21217650007901103 BLOWER SKRSKYS76 S76A 8143006NE CABIN AIR INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035435V 760158 VENT BLOWER INOPERATIVE. 1G72 3U H1NE 20020529000642002052900064NE 2002 5 29 HEEA078731 120020520G63217665009803103 POWERPACK SKRSKYS76 S76A 8143006NE ROTOR BRAKE MALFUNCTIONED E HEEAK NONE P NO WARNING INDICATION ININSP/MAINT 1 SW0315460 760223 ROTOR BRAKE CAUTION LIGHT DOES NOT ILLUMINATE WHEN ROTOR BRAKE IS SWITCHED ON. RETURNED TO VENDOR FOR REPAIR. 1G72 3U H1NE 20020529000662002052900066NE 2002 5 29 HEEA078732 120020520G67307665009807101 SERVO SKRSKYS76 S76C 8143008NE MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03505PH 760505 MAIN ROTOR SERVO HAS WORN UPPER BEARING. TO BE SENT TO VENDOR FOR REPAIR. 1G72 3U NCH1NE 20020529000672002052900067 2002 5 29 HEEA078733 420020520G344278806059008 DISPLAY SKRSKYS76 S76A 8143006NE WX RADAR MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031546G 760076 WEATHER RADAR DISPLAY PRODUCING DOUBLE IMAGING. 1G72 3U H1NE 20020529000692002052900069 2002 5 29 HEEA078734 420020520G3120811B CLOCK SKRSKYS76 S76A 8143006NE COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03792CH 760193 PILOT CLOCK WILL NOT KEEP TIME. REPLACED WITH SERVICEABLE CLOCK. 1G72 3U H1NE 20020529000702002052900070 2002 5 29 HEEA078735 420020520G3457 SCREW SKRSKYS76 S76A 8143006NE GPS ON/OFF KNOB STRIPPED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033122H 760233 INTERMITTENTLY LOSES RAIM. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE PROBLEM. FOUND SEVERAL BUTTONS UNREADABLE AND FOUND SET SCREW ON/OFF KNOB STRIPPED. REPAIRED. BENCH CHECK GOOD. 1G72 3U H1NE 20020529000712002052900071 2002 5 29 HEEA078736 420020520G34578143902240B GPS SKRSKYS76 S76A 8143006NE COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03911UK 760275 WILL NOT HOLD COORDINATES. PERFORMED PRELIMINARY INSPECTION. FOUND BATTERY DEAD AND CORROSION ON BOARD NEAR BATTERY. REMOVED CORROSION FROM BOARD. FOUND L212 COIL BROKEN. ALSO DISPLAY IS BLURRY AND MISSING ON/OFF KNOB. SENT TO ASM FREEFLIGHT FOR INSPECTION AND REPAIR. 1G72 3U H1NE 20020529000732002052900073 2002 5 29 HEEA078737 420020520G34578144002241D GPS SKRSKYS76 S76C 8143008NE COCKPIT INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03505PH 760505 GPS FALLS OFF LINE. 1G72 3U NCH1NE 20020529000742002052900074NE 2002 5 29 HEEA078738 120020520G2110JBS2014 COMPRESSOR SKRSKYS76 S76A 8143006NE AIR CONDITIONER DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03792CH 760193 INSUFFICIENT COOLING FROM AIR CONDITIONER SYSTEM. EQUAL PRESSURES READ ON HIGH AND LOW SIDES. REPAIRED. 1G72 3U H1NE 20020529000752002052900075 2002 5 29 HEEA078740 420020520G3442MI5852013 DISPLAY SKRSKYS76 S76A 8143006NE WX RADAR MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW034253S 760035 WEATHER RADAR SYSTEM HAS NO TEST PATTERN ON DISPLAY. REPLACED WITH SERVICEABLE PART. 1G72 3U H1NE 20020529000762002052900076 2002 5 29 HEEA078741 420020520G3442MI5852013 DISPLAY SKRSKYS76 S76A 8143006NE WX RADAR DISTORTED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0322342 760096 SCREEN DISTORTED AFTER 10 MINUTES OF OPERATION. COULD NOT DUPLICATE PROBLEM. BENCH CHECK GOOD. 1G72 3U H1NE 20020529000772002052900077 2002 5 29 HEEA078742 420020520G2340PHI20004 MIXER BOX SKRSKYS76 S76A 8143006NE CABIN MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031545X 760050 BLEED OVER TO OTHER CHANNELS OF MIXER BOX WITHOUT SWITCH SELECTED. PERFORMED PRELIMINARY INSPECTION. FOUND SWITCH S1 AND SELECTOR KNOB BAD. REPLACED AND REPAIRED. BENCH CHECK GOOD. 1G72 3U H1NE 20020529000782002052900078 2002 5 29 HEEA078743 420020524G34578143902240B GPS SKRSKYS76 S76A 8143006NE COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW034253S 760035 GPS DOES NOT DRIVE YELLOW NEEDLE ON HSI IN CAL MODE. UNABLE TO CHANGE FUEL FROM GALLONS TO POUNDS. TO BE SENT TO VENDOR FOR REPAIR. 1G72 3U H1NE 20020529000792002052900079 2002 5 29 HEEA078744 420020524G2350AA38300 AMPLIFIER SKRSKYS76 S76A 8143006NE ICS INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW034253S 760035 ICS AMPLIFIER INOPERATIVE. TO BE SENT TO VENDOR FOR REPAIR. 1G72 3U H1NE 20020529000802002052900080SW 2002 5 29 HEEA078747 120020501G6710214001970111 ACTUATOR BELL 214 214ST 1182106SW MAIN ROTOR WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 WOULD NOT COMPLETE MONITOR TEST AFTER INSTALLATION. WOULD MOVE SLOW OR VERY LITTLE. 2G72 4U H10SW 20020529000812002052900081SW 2002 5 29 HEEA078748 120020501G6710214001970111 ACTUATOR BELL 214 214ST 1182106SW MAIN ROTOR WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 MAIN ROTOR ACTUATOR WON'T COMPLETE TEST. 2G72 4U H10SW 20020529000822002052900082 2002 5 29 HEEA078749 420020501G2210214074303115 AMPLIFIER BELL 214 214ST 1182106SW COCKPIT FAILED E HEEAO OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 SW03 ACTUATOR ROLL DROPS OFF DURING FLIGHT. 2G72 4U H10SW 20020529000842002052900084SW 2002 5 29 HEEA078750 120020501G2932222375019105 TRANSMITTER BELL 222 222 1182122SW HYD INDICATOR READS LOW E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03 HYDRAULIC PRESSURE INDICATOR READS LOW PRESSURE. REPLACED HYD PRESSURE INDICATOR TRANSMITTER. 1G72 3U H9SW 20020529000852002052900085SW 2002 5 29 HEEA078751 120020501G5260 ARM BELL 412 412 1182202SW STEP ACTUATOR CORRODED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 RT34006 STEP ACTUATOR HAS A CORRODED ARM. 1G72 4U H4SW 20020529000862002052900086SW 2002 5 29 HEEA078752 120020501G7120206064107101 MOUNT BELL 206 206L3 1182108SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW038590X 51494 IN SERVICE FOR 11 1/2 MONTHS. REMOVED DUE TO WEAR OF THE BEARING. ALSO NOTED THE TUBE INSIDE DIAMETER IS MUCH LARGER THAT THE FITTING OUTSIDE DIAMETER CREATING A LOOSE FIT BETWEEN THE TWO. CAUSES THE HI LOC TO BECOME OVERSIZED AND BEYOND LIMITS. SCRAPPED ENGINE MOUNT. 1G71 3U H2SW 20020529000872002052900087SW 2002 5 29 HEEA078753 120020506G7120206064105101 MOUNT BELL 206 206L3 1182108SW ENGINE MISMARKED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 ENGINE MOUNT MIS-IDENTIFIED. P/N SHOULD BE -102. 1G71 3U H2SW 20020529000892002052900089 2002 5 29 HEEA078756 420020506G3422060001500 GYRO BELL 407 407 1182206SW COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03407PH 53003 DIRECTIONAL GYRO HEADING FLAP WILL NOT MOVE. 1G71 3U O H2SW 20020529000902002052900090 2002 5 29 HEEA078757 420020506G2312064105430 TRANSCEIVER BELL 407 407 1182206SW COCKPIT INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03402PH 53159 DOES NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION AND FOUND CHANNELING KNOBS BENT AND CHANNELING INTERMITTENT. REPLACED S101 SWITCH, MHZ AND KHZ KNOBS AND WAFER SWITCHES. CLEANED CHANNELING CONTACTS ON DISPLAY BOARD. REPAIRED CHANNELING PROBLEM BUT FOUND TRANSMITTER WORKING INTERMITTENTLY. 1G71 3U O H2SW 20020529000922002052900092 2002 5 29 HEEA078758 420020506G3452066106200 TRANSCEIVER BELL 407 407 1182206SW VOR SYSTEM INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03491PH 53386 WOULD NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION, FOUND V101 BAD, AND R477 BAD. REPLACED. REPAIRED. ADJUSTED TO SPECS. BENCH CHECK GOOD. 1G71 3U O H2SW 20020529000932002052900093SW 2002 5 29 HEEA078759 120020506G32121100891S TEE FITTING BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CORROSION BEYOND LIMITS. 1G71 3U O H2SW 20020529000942002052900094 2002 5 29 HEEA078760 420020506G345713824120234 GPS BELL 407 407 1182206SW COCKPIT INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03721PH 53278 GPS RECEIVER HAS NO DISPLAY. 1G71 3U O H2SW 20020529000952002052900095SW 2002 5 29 HEEA078765 120020506G3270206020110103 SKID BELL 407 407 1182206SW TAIL CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 TAIL SKID ASSY IS CRACKED. 1G71 3U O H2SW 20020529000962002052900096SW 2002 5 29 HEEA078766 120020506G5302 STRUCTURE BELL 407 407 1182206SW TAIL BOOM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03467PH 53142 TAIL BOOM HAS CORROSION AT TOP CAP AND LOWER STRINGER MOUNT AREAS. 1G71 3U O H2SW 20020529000972002052900097SW 2002 5 29 HEEA078767 120020506G3270206050129001 SHOE BELL 407 407 1182206SW TAIL SKID WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 TAIL SKID SHOE WELDED BEADS ARE WORN. 1G71 3U O H2SW 20020529000992002052900099SW 2002 5 29 HEEA078768 120020506G3212206050247101 COVER BELL 407 407 1182206SW MLG FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 EMERGENCY FLOAT COVER IS WORN, TORN AND DIRTY. 1G71 3U O H2SW 20020529001002002052900100SW 2002 5 29 HEEA078769 120020506G3212206050247132 COVER BELL 407 407 1182206SW MLG FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 EMERGENCY FLOAT COVER HAS A TORN END FLAP. 1G71 3U O H2SW 20020529001012002052900101SW 2002 5 29 HEEA078770 120020507G3212206050247135 COVER BELL 407 407 1182206SW MLG FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 EMERGENCY FLOAT COVER IS DETERIORATED. END CAPS TORN. 1G71 3U O H2SW 20020529001032002052900103SW 2002 5 29 HEEA078771 120020507G3212206050247137 COVER BELL 407 407 1182206SW MLG FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 EMERGENCY FLOAT COVER IS TORN. 1G71 3U O H2SW 20020529001052002052900105SW 2002 5 29 HEEA078772 120020507G3246206053184121 SKID BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 SKID TUBE HAS CORROSION OUT OF LIMITS. 1G71 3U O H2SW 20020529001062002052900106SW 2002 5 29 HEEA078774 120020507G3246206053184122 SKID BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 SKID TUBE HAS CORROSION OUT OF LIMITS. 1G71 3U O H2SW 20020529001072002052900107SW 2002 5 29 HEEA078775 120020507G3246206053184122 SKID BELL 407 407 1182206SW MLG WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 WORN ON AFT SECTION OF SKID TUBE. 1G71 3U O H2SW 20020529001082002052900108SW 2002 5 29 HEEA078776 120020507G6510206061432119 BLOWER BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 BLOWER HAS A CRACK NEAR TOP LEFT HAND SECTION. 1G71 3U O H2SW 20020529001092002052900109SW 2002 5 29 HEEA078777 120020507G6510206061432121 HOUSING BELL 407 407 1182206SW BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 TAIL ROTOR BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020529001102002052900110SW 2002 5 29 HEEA078778 120020507G6510206061432121 HOUSING BELL 407 407 1182206SW BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 TAIL ROTOR BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020529001112002052900111SW 2002 5 29 HEEA078780 120020507G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH3443 97332 53277 STARTER GEN HAS BRUSHES WORN, BRUSH PIGTAILS HAVE BROKEN STRANDS, ONE FAN COVER SCREW HEAD CORRODED OFF. 1G71 3U O H2SW 20020529001122002052900112SW 2002 5 29 HEEA078781 120020507G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03741PH2741 53457 STARTER GEN HAS BRUSHES WORN. 1G71 3U O H2SW 20020529001132002052900113SW 2002 5 29 HEEA078782 120020507G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH2493 98136 53159 STARTER GEN HAS BRUSHES WORN. 1G71 3U O H2SW 20020529001142002052900114SW 2002 5 29 HEEA078783 120020507G2435 BRUSHES BELL 407 407 1182206SW STARTER GEN WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH1529 98262 53199 STARTER GEN HAS BRUSHES WORN. 1G71 3U O H2SW 20020529001202002052900120SW 2002 5 29 HEEA078788 120020507G2820206064263101 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 FUEL LINE HAS CORROSION AROUND SLEEVES. 1G71 3U O H2SW 20020529001212002052900121SW 2002 5 29 HEEA078789 120020507G2820206064264101 LINE BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 FUEL LINE HAS CORROSION. 1G71 3U O H2SW 20020529001232002052900123SW 2002 5 29 HEEA078790 120020507G7921206064515001 SUPPORT BELL 407 407 1182206SW OIL COOLER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 OIL COOLER SUPPORT ASSY IS CRACKED IN TWO PLACES. 1G71 3U O H2SW 20020529001262002052900126SW 2002 5 29 HEEA078792 120020507G5210206064819005S SKIN BELL 407 407 1182206SW CREW DOOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03490PH 53378 SKIN ON CREW DOOR HAS CORROSION. 1G71 3U O H2SW 20020529001272002052900127SW 2002 5 29 HEEA078793 120020507G5210206064819005S SKIN BELL 407 407 1182206SW CREW DOOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03490PH 53378 SKIN ON CREW DOOR HAS CORROSION. 1G71 3U O H2SW 20020529001352002052900135SW 2002 5 29 HEEA078795 120020507G7160206064819159 COWLING BELL 407 407 1182206SW AIR INLET CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 COWLING HAS CORROSION AND CRACKED IN SEVERAL PLACES. 1G71 3U O H2SW 20020529001652002052900165SW 2002 5 29 HEEA078798 120020507G7160206064912103 SEAL BELL 407 407 1182206SW COWLING TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 COWLING SEAL TORN. SCRAPPED AND REPLACED WITH SERVICEABLE SEAL. 1G71 3U O H2SW 20020530000012002053000001SW 2002 5 30 HEEA078799 120020507G2120206070471010 NOZZLE BELL 407 407 1182206SW WINDSHIELD DEFOGCRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 WINDSHIELD DE-FOG NOZZLE IS CRACKED AT MOUNTING HOLE. 1G71 3U O H2SW 20020530000022002053000002SW 2002 5 30 HEEA078801 120020507G2810206362002103 CAP BELL 407 407 1182206SW FUEL STORAGE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 TABS AROUND OUTER EDGE OF FUEL CAP MISSING. 1G71 3U O H2SW 20020530000052002053000005SW 2002 5 30 HEEA078802 120020507G6320214040805001 THERMOSWITCH BELL 407 407 1182206SW M/R GEARBOX DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 MAIN ROTOR GEARBOX THERMOSWITCH DAMAGED, STUD TURNS FREELY IN HOUSING. 1G71 3U O H2SW 20020530000172002053000017SW 2002 5 30 HEEA078803 120020507G2560222320823129 SEAT BELT BELL 407 407 1182206SW COCKPIT FRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 CREW SEAT BELTS FRAYED AND CORRODED. 1G71 3U O H2SW 20020530000192002053000019SW 2002 5 30 HEEA078804 120020507G2560222320823130 SEAT BELT BELL 407 407 1182206SW COCKPIT FRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 CREW SEAT BELTS FRAYED AND CORRODED. 1G71 3U O H2SW 20020530000232002053000023GL 2002 5 30 HEEA078805 220020507G753223005366 BLEED VALVE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE MALFUNCTIONED E K NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 ENGINE POWER OSCILLATIONS AT HIGH POWER SETTINGS. REPLACED WITH SERVICEABLE BLEED VALVE. 1G71 3U3 UO H2SW E1GL 20020530000382002053000038GL 2002 5 30 HEEA078806 220020507G751023007827 VALVE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 VALVE INOPERATIVE. REPLACED WITH SERVICEABLE VALVE. 1G71 3U3 UO H2SW E1GL 20020530000402002053000040GL 2002 5 30 HEEA078807 220020507G751023007827 VALVE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 VALVE STUCK IN ON POSITION. REPLACED WITH SERVICEABLE VALVE. 1G71 3U3 UO H2SW E1GL 20020530000422002053000042GL 2002 5 30 HEEA078808 220020507G732123054164 SENSOR BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 SENSOR PICKUP CAUSING NP1, NP1 RATE, OS, NPOS AND NPD FAULTS TO FADED SYSTEM. REPLACED WITH SERVICEABLE SENSOR PICKUP ASSY. 1G71 3U3 UO H2SW E1GL 20020530000432002053000043GL 2002 5 30 HEEA078809 220020507G731023056649 HOSE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL FUEL SYSTEM KINKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 FIRE SHIELD TO FUEL NOZZLE HOSE KINKED. REPLACED WITH SERVICEABLE HOSE. 1G71 3U3 UO H2SW E1GL 20020530000452002053000045GL 2002 5 30 HEEA078810 220020507G731023060435 LINE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL FUEL SYSTEM LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 FUEL LINE LEAKING. REPLACED WITH SERVICEABLE LINE. 1G71 3U3 UO H2SW E1GL 20020530000472002053000047GL 2002 5 30 HEEA078811 220020507G741223064130 IGNITER BOX BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE WEAK E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03490PH 53378 IGNITOR BOX WEAK. 1G71 3U3 UO H2SW E1GL 20020530000482002053000048SW 2002 5 30 HEEA078812 120020507G282123066697 FILTER BELL 407 407 1182206SW FUEL SYSTEM CLOGGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 FILTER BYPASSED. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE FILTER. 1G71 3U O H2SW 20020530000512002053000051SW 2002 5 30 HEEA078813 120020507G772223071644 ECU BELL 407 407 1182206SW ENGINE MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 NP AND OVERSPEED SENSOR FAILURES (FADEC FAULT & DEGRADE LIGHTS) REPLACED WITH SERVICEABLE ECU. 1G71 3U O H2SW 20020530000522002053000052SW 2002 5 30 HEEA078814 120020507G772223071644 ECU BELL 407 407 1182206SW ENGINE MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 BOTTOM PLATE OPEN TO SEARCH FOR MOISTURE. 1G71 3U O H2SW 20020530000542002053000054GL 2002 5 30 HEEA078815 220020507G732023072725 HMU BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL FUEL CONTROL FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03493PH 53393 HMU HAS METERING VALVE CIRCUIT FAULT. REPLACED WITH SERVICEABLE HMU. 1G71 3U3 UO H2SW E1GL 20020530000552002053000055SW 2002 5 30 HEEA078816 120020507G772223072790 ECU BELL 407 407 1182206SW ENGINE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03719PH 53266 FADEC FAULT AND FADEC DEGRADE LIGHTS ILLUMINATED. CLEARED FAULT. REPLACED WITH SERVICEABLE ECU. 1G71 3U O H2SW 20020530000592002053000059SW 2002 5 30 HEEA078819 120020507G3201400052009101 BOLT BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MLG ROCKER BEAM BOLT PITTED. 1G71 3U O H2SW 20020530000602002053000060SW 2002 5 30 HEEA078820 120020507G6210406010120101 BOLT BELL 407 407 1182206SW M/R BLADES FRETTED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 BOLT HAS FRETTING ON SHANK. 1G71 3U O H2SW 20020530000622002053000062SW 2002 5 30 HEEA078821 120020507G6230406010413117 PITCH LINK BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 PITCH LINK HAS CORROSION ON TUBE NEAR COLLAR. 1G71 3U O H2SW 20020530000632002053000063SW 2002 5 30 HEEA078822 120020507G6710 PAD BELL 407 407 1182206SW LEVER ASSY WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 LEVER ASSY HAS PHENOLIC WEAR PAD MISSING TWO SIDES. 1G71 3U O H2SW 20020530000642002053000064SW 2002 5 30 HEEA078823 120020507G6230406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CORROSION AROUND BASE MOUNT AREA LIGHTLY PAINTED AREA. 1G71 3U O H2SW 20020530000652002053000065SW 2002 5 30 HEEA078825 120020507G6230 BUSHING BELL 407 407 1182206SW LINK ASSY WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH AFS2265 53198 LINK ASSY HAS WORN BUSHINGS. 1G71 3U O H2SW 20020530000662002053000066SW 2002 5 30 HEEA078826 120020507G6230406010427109 GIMBAL RING BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 GIMBAL RING HAS CORROSION AROUND MOUNT PINS. 1G71 3U O H2SW 20020530000682002053000068SW 2002 5 30 HEEA078827 120020507G6220406010428109 BUSHING BELL 407 407 1182206SW MAIN ROTOR HUB CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MAIN ROTOR HUB BUSHING HAS CORROSION AROUND SPLINE AREA. 1G71 3U O H2SW 20020530000702002053000070SW 2002 5 30 HEEA078828 120020507G6710 BUSHING BELL 407 407 1182206SW IDLER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH AFS1179 53386 WORN BUSHING. 1G71 3U O H2SW 20020530000712002053000071SW 2002 5 30 HEEA078829 120020507G6220406012129101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 LINK ASSY WORN. 1G71 3U O H2SW 20020530000722002053000072SW 2002 5 30 HEEA078832 120020507G6520406040406109 CASE BELL 407 407 1182206SW T/R GEARBOX CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 TAIL ROTOR GEARBOX HAS EXCESSIVE PITTING BETWEEN CHIP DETECTOR AND RIGHT FORWARD MOUNTING STUD. 1G71 3U O H2SW 20020530000762002053000076SW 2002 5 30 HEEA078833 120020507G6510406040450101 BREATHER TUBE BELL 407 407 1182206SW T/R DRIVESHAFT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 STEP WORN AROUND OUTSIDE OF FLARE. 1G71 3U O H2SW 20020530000772002053000077SW 2002 5 30 HEEA078836 120020507G6300 BEARING BELL 407 407 1182206SW UNIVERSAL WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH RXFS5555 53188 UNIVERSAL HAS WORN BEARING. 1G71 3U O H2SW 20020530000782002053000078SW 2002 5 30 HEEA078837 120020507G6300 BEARING BELL 407 407 1182206SW UNIVERSAL WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH RXFS5989 53398 UNIVERSAL HAS A WORN BEARING. 1G71 3U O H2SW 20020530000802002053000080SW 2002 5 30 HEEA078838 120020507G6720 BEARING BELL 407 407 1182206SW LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH NHFS5192 53327 LINK ASSY HAS A WORN BEARING. 1G71 3U O H2SW 20020530000832002053000083SW 2002 5 30 HEEA078839 120020507G6720 BEARING BELL 407 407 1182206SW LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH NHFS5246 53327 LINK ASSY HAS A WORN BEARING. 1G71 3U O H2SW 20020530000862002053000086SW 2002 5 30 HEEA078840 120020507G6720 BEARING RACE BELL 407 407 1182206SW LINK CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH NHFS5853 53199 CRACKED AT BEARING HOLE. CORROSION BLEEDING FROM BEARING RACE. 1G71 3U O H2SW 20020530000892002053000089SW 2002 5 30 HEEA078841 120020507G6720 BEARING RACE BELL 407 407 1182206SW LINK CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH NHFS5867 53199 CORROSION BLEEDING FROM BEARING RACE. 1G71 3U O H2SW 20020530000902002053000090SW 2002 5 30 HEEA078842 120020507G6320406340100101 PUMP BELL 407 407 1182206SW M/R XMSN OIL LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03742PH 53461 TRANSMISSION OIL PUMP LEAKING PAST INTERNAL SEAL. 1G71 3U O H2SW 20020530000912002053000091GL 2002 5 30 HEEA078843 220020507G7230 BEARING BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL TUBE ASSY. WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 BEARINGS WORN. 1G71 3U3 UO H2SW E1GL 20020530000922002053000092SW 2002 5 30 HEEA078845 120020507G6220 BEARING BELL 407 407 1182206SW IDLER ASSY WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH CT427 53199 IDLER ASSY HAS BEARINGS WORN. 1G71 3U O H2SW 20020530000932002053000093SW 2002 5 30 HEEA078846 120020507G6220 BEARING BELL 407 407 1182206SW IDLER ASSY WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 IDLER ASSY HAS BEARINGS WORN. 1G71 3U O H2SW 20020530000942002053000094SW 2002 5 30 HEEA078847 120020507G6220407001524105 BELLCRANK BELL 407 407 1182206SW MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MAIN ROTOR HEAD BELLCRANK HAS THE RUBBER BUMPER UNBONDED. 1G71 3U O H2SW 20020530000952002053000095SW 2002 5 30 HEEA078848 120020507G6220407001524105 BELLCRANK BELL 407 407 1182206SW MAIN ROTOR HEAD DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MAIN ROTOR HEAD BELLCRANK HAS THE RUBBER BUMPER UNBONDED. 1G71 3U O H2SW 20020530000962002053000096SW 2002 5 30 HEEA078849 120020507G6220407001528101 BELLCRANK BELL 407 407 1182206SW MAIN ROTOR HEAD DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MAIN ROTOR BELLCRANK HAS THE RUBBER BUMPER UNBONDED. 1G71 3U O H2SW 20020530000982002053000098SW 2002 5 30 HEEA078850 120020507G6720407001732101 BELLCRANK BELL 407 407 1182206SW T/R CONTROL WORN E K NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 TAIL ROTOR CONTROL BELLCRANK IS WORN. 1G71 3U O H2SW 20020530000992002053000099SW 2002 5 30 HEEA078851 120020507G6220407010100115FM HUB BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH3369 53038 MAIN ROTOR HUB IS CORROSION. 1G71 3U O H2SW 20020530001002002053000100SW 2002 5 30 HEEA078852 120020507G6220 BEARING BELL 407 407 1182206SW MAIN ROTOR BLADESEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH A289 53198 MAIN ROTOR HUB HAS A SHEAR BEARING ON ORANGE BLADE SEPARATED. 1G71 3U O H2SW 20020530001022002053000102SW 2002 5 30 HEEA078854 120020507G6220407010150103 FRAHM BELL 407 407 1182206SW MAIN ROTOR HUB CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 FRAHM ASSY HAS CORROSION AROUND SPRING ACCESS PLATES AND CAP NUTPLATES. 1G71 3U O H2SW 20020530001052002053000105SW 2002 5 30 HEEA078855 120020507G6300407010221101 STOP BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 MAIN ROTOR STOPS WORN, TORN, DELAMINATED. 1G71 3U O H2SW 20020530001092002053000109SW 2002 5 30 HEEA078856 120020507G6220407010221101 STOP BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 MAIN ROTOR STOP WORN. 1G71 3U O H2SW 20020530001262002053000126SW 2002 5 30 HEEA078860 120020507G6420407312100101 BEARING BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 BEARING HAS WORN ELASTOMER. 1G71 3U O H2SW 20020530001272002053000127SW 2002 5 30 HEEA078861 120020507G6420 BEARING BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 BEARING HAS WORN ELASTOMER. 1G71 3U O H2SW 20020530001282002053000128SW 2002 5 30 HEEA078862 120020507G6410 BLADE BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 BLADE HAS CRACK IN ROOT END, INTERIOR OF LEADING EDGE. 1G71 3U O H2SW 20020530001292002053000129SW 2002 5 30 HEEA078863 120020507G6420407312100101 BEARING BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03741PH 53457 BEARING BELOW NOMINAL LENGTH. 1G71 3U O H2SW 20020530001302002053000130SW 2002 5 30 HEEA078864 120020507G5610407030115123 WINDSHIELD BELL 407 407 1182206SW COCKPIT CRAZED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 WINDSHEILD CRAZED. 1G71 3U O H2SW 20020530001312002053000131SW 2002 5 30 HEEA078865 120020507G5610407030115125 WINDSHIELD BELL 407 407 1182206SW COCKPIT CRAZED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 WINDSHIELD CRAZED. 1G71 3U O H2SW 20020530001322002053000132SW 2002 5 30 HEEA078866 120020507G5610407030115125 WINDSHIELD BELL 407 407 1182206SW COCKPIT CRAZED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 WINDSHIELD CRAZED. 1G71 3U O H2SW 20020530001332002053000133SW 2002 5 30 HEEA078867 120020507G5610407030115125 WINDSHIELD BELL 407 407 1182206SW COCKPIT CRAZED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 WINDSHIELD CRAZED. 1G71 3U O H2SW 20020530001342002053000134SW 2002 5 30 HEEA078868 120020507G5610407030118103 CHIN BUBBLE BELL 407 407 1182206SW COCKPIT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 CHIN BUBBLE CRACKED. 1G71 3U O H2SW 20020530001352002053000135SW 2002 5 30 HEEA078869 120020507G5610407030118105 CHIN BUBBLE BELL 407 407 1182206SW COCKPIT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CHIN BUBBLE CRACKED AT OUTBOARD CORNER. 1G71 3U O H2SW 20020530001372002053000137SW 2002 5 30 HEEA078871 120020507G5610407030403116 WINDOW BELL 407 407 1182206SW COCKPIT CRAZED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 SKYLIGHT CRAZED. 1G71 3U O H2SW 20020531000012002053100001SW 2002 5 31 HEEA078872 120020507G5630407030607101 WINDOW BELL 407 407 1182206SW LITTER DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 LITTER DOOR WINDOW CRACKED. 1G71 3U O H2SW 20020531000022002053100002SW 2002 5 31 HEEA078873 120020507G5321407030713113 FLOOR PANEL BELL 407 407 1182206SW CARGO AREA CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CARGO FLOOR PANEL SEPARATED/CORRODED. 1G71 3U O H2SW 20020531000032002053100003SW 2002 5 31 HEEA078874 120020508G7714407375002103 INDICATOR BELL 407 407 1182206SW ENGINE NG FAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 FADEC NG2 FAULT AND NG2 CONTINUITY FAULT. 1G71 3U O H2SW 20020531000042002053100004GL 2002 5 31 HEEA078875 220020508G7297407375012101 WIRE HARNESS BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL FADEC BROKEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 BREAK IN CABLE CAUSING FADEC NG1 FAULT AND NG1 CONTINUITY FAULT. BREAK IS APPROXIMATELY 3 INCHES FROM ECU CONNECTOR PLUG. 1G71 3U3 UO H2SW E1GL 20020531000052002053100005SW 2002 5 31 HEEA078878 120020510G6230406010428109 BUSHING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03721PH3142 53278 MAIN ROTOR BUSHING SET WORN. 1G71 3U O H2SW 20020531000062002053100006SW 2002 5 31 HEEA078879 120020510G6720407001526101 BELLCRANK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH4209 53038 BELLCRANK ON TAIL ROTOR HAS RUBBER DETERIORATED. 1G71 3U O H2SW 20020531000072002053100007SW 2002 5 31 HEEA078880 120020510G6230406010425107 LEVER BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH1942 53386 WORN BUSHINGS. 1G71 3U O H2SW 20020531000082002053100008SW 2002 5 31 HEEA078881 120020510G6230406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH1942 53386 MAIN ROTOR LINK HAS WORN BUSHINGS. 1G71 3U O H2SW 20020531000092002053100009SW 2002 5 31 HEEA078882 120020510G6220407010100115 HUB BELL 407 407 1182206SW MAIN ROTOR VIBRATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH1778 53397 MAIN ROTOR HUB HAS VERTICAL VIBRATION. 1G71 3U O H2SW 20020531000102002053100010SW 2002 5 31 HEEA078883 120020510G6230406010428109 BUSHING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 MAIN ROTOR HUB HAS WORN BUSHINGS. 1G71 3U O H2SW 20020531000112002053100011SW 2002 5 31 HEEA078884 120020510G3213407050201101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 MLG CROSSTUBE HAS CORROSION. 1G71 3U O H2SW 20020531000122002053100012SW 2002 5 31 HEEA078885 120020510G7714407375012101 WIRE HARNESS BELL 407 407 1182206SW FADEC DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 FADEC WIRE HARNESS IS OIL SOAKED AND DETERIORATED. 1G71 3U O H2SW 20020531000132002053100013SW 2002 5 31 HEEA078886 120020510G5210407070620138 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 CREW DOOR PANEL IS CRACKED. 1G71 3U O H2SW 20020531000142002053100014SW 2002 5 31 HEEA078887 120020510G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03490PH 53378 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020531000152002053100015SW 2002 5 31 HEEA078890 120020510G6710406312103101 LINK BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 MAIN ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020531000162002053100016SW 2002 5 31 HEEA078891 120020510G6510206061432121 HOUSING BELL 407 407 1182206SW BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 TAIL ROTOR BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020531000172002053100017SW 2002 5 31 HEEA078892 120020513G6710406010429101 PIN BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 MAIN ROTOR PIN WORN. 1G71 3U O H2SW 20020531000182002053100018SW 2002 5 31 HEEA078893 120020513G6300406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH1968 53266 MAIN ROTOR UNIVERSAL WORN. 1G71 3U O H2SW 20020531000192002053100019SW 2002 5 31 HEEA078894 120020513G6310407340107101 SHAFT BELL 407 407 1182206SW XMSN COUPLING WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 WORN SPLINES. 1G71 3U O H2SW 20020531000202002053100020SW 2002 5 31 HEEA078895 120020513G6310407340108101 ADAPTER BELL 407 407 1182206SW XMSN COUPLING WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 TRANSMISSION/ENGINE COUPLING ADAPTER HAS WORN SPLINES. 1G71 3U O H2SW 20020531000212002053100021SW 2002 5 31 HEEA078896 120020513G6710206001396001 SHAFT BELL 407 407 1182206SW CYCLIC STICK STRIPPED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 STRIPPED BARREL NUT ON SHAFT. 1G71 3U O H2SW 20020531000222002053100022SW 2002 5 31 HEEA078897 120020513G6720406312103101 LINK BELL 407 407 1182206SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 TAIL ROTOR LINK HAS A WORN BEARING. 1G71 3U O H2SW 20020531000232002053100023SW 2002 5 31 HEEA078898 120020513G2822407362013101 PRESSURE SWITCH BELL 407 407 1182206SW BOOST PUMP FAILED E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW03724PH 53327 BOOST PUMP CAUTION LIGHT WILL NOT COME ON. REPLACED FAILED PRESSURE SWITCH. 1G71 3U O H2SW 20020531000242002053100024 2002 5 31 HEEA078899 420020513G3120M803B205VBATT CLOCK BELL 407 407 1182206SW COCKPIT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 COCKPIT CLOCK DAMAGED, BATTERY MOUNT CORRODED. 1G71 3U O H2SW 20020531000252002053100025SW 2002 5 31 HEEA078900 120020513G6520406040072105 SPLINE ADAPTER BELL 407 407 1182206SW T/R GEARBOX WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 SPLINE ADAPTER HAS WORN SPLINES. 1G71 3U O H2SW 20020531000262002053100026SW 2002 5 31 HEEA078901 120020513G7810407063001101 EXHAUST STACK BELL 407 407 1182206SW ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 EXHAUST STACK IS CRACKED. 1G71 3U O H2SW 20020531000282002053100028SW 2002 5 31 HEEA078902 120020513G6520407040330101 SHAFT BELL 407 407 1182206SW T/R GEARBOX PEELING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 PAINT PEELING FROM SHAFT. 1G71 3U O H2SW 20020531000392002053100039SW 2002 5 31 HEEA078903 120020513G3210407030112103 STRAP BELL 407 407 1182206SW MLG WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 MLG STRAP WORN AND CHAFED BEYOND LIMITS. 1G71 3U O H2SW 20020531000552002053100055GL 2002 5 31 HEEA078904 220020513G7230407070211102 PLENUM BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 PLENUM CRACKED. 1G71 3U3 UO H2SW E1GL 20020531000602002053100060GL 2002 5 31 HEEA078905 220020513G7230407070211101 PLENUM BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 PLENUM CRACKED. 1G71 3U3 UO H2SW E1GL 20020531000612002053100061SW 2002 5 31 HEEA078906 120020513G2420SM20ACD300A21 RELAY BELL 407 407 1182206SW COCKPIT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 RELAY CORRODED. 1G71 3U O H2SW 20020531000622002053100062SW 2002 5 31 HEEA078907 120020513G3212206050247135 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 EMERGENCY FLOAT COVER TORN. 1G71 3U O H2SW 20020531000642002053100064SW 2002 5 31 HEEA078908 120020513G282070079H000D142 HOSE BELL 407 407 1182206SW FUEL SYSTEM COLLAPSED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 FUEL HOSE COLLAPSED. 1G71 3U O H2SW 20020531000652002053100065SW 2002 5 31 HEEA078909 120020513G2810F507ST FUEL CAP BELL 407 407 1182206SW FUEL CELL MISSING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 FUEL CELL CAP MISSING. 1G71 3U O H2SW 20020531000662002053100066SW 2002 5 31 HEEA078910 120020513G243228SP100 CELL BELL 407 407 1182206SW BATTERY BURNED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03722PH 53288 BATTERY CELL BURNED. 1G71 3U O H2SW 20020531000682002053100068SW 2002 5 31 HEEA078911 120020513G7710407375021103 SENSOR BELL 407 407 1182206SW ENGINE MALFUNCTIONED E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW03457PH 53147 WARNING HORN ACTIVATED AT 100 PERCENT NR. 1G71 3U O H2SW 20020531000782002053100078SW 2002 5 31 HEEA078912 120020513G7100 BEARING BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH 53327 WORN BEARINGS. 1G71 3U O H2SW 20020531000822002053100082SW 2002 5 31 HEEA078914 120020513G5320407064807117 SUPPORT BELL 407 407 1182206SW FUSELAGE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 SUPPORT WORN. 1G71 3U O H2SW 20020531000832002053100083SW 2002 5 31 HEEA078915 120020513G5320407064807119 SUPPORT BELL 407 407 1182206SW FUSELAGE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 SUPPORT WORN. 1G71 3U O H2SW 20020531000862002053100086SW 2002 5 31 HEEA078916 120020513G3213407050202101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 CORROSION ON CROSSTUBE. 1G71 3U O H2SW 20020531000872002053100087SW 2002 5 31 HEEA078921 120020513G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 TAIL ROTOR DRIVE SHAFT DISC PACK CRACKED. 1G71 3U O H2SW 20020531000892002053100089SW 2002 5 31 HEEA078925 120020513G6710 BEARING BELL 407 407 1182206SW IDLER ASSY ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 IDLER ASSY BEARINGS ROUGH. 1G71 3U O H2SW 20020531000902002053100090SW 2002 5 31 HEEA078926 120020513G5210206064819005S DOOR BELL 407 407 1182206SW PAX/CREW CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 CORROSION ON DOOR ASSY. 1G71 3U O H2SW 20020531001022002053100102SW 2002 5 31 HEEA078927 120020513G3210400052009101 BOLT BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03722PH 53288 MLG BOLT HAS CORROSION. 1G71 3U O H2SW 20020531001032002053100103SW 2002 5 31 HEEA078928 120020513G5311206032308121S FRAME BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 FRAME CRACKED ABOVE RIGHT HAND UPPER BOLT HOLE. 1G71 3U O H2SW 20020531001042002053100104SW 2002 5 31 HEEA078931 120020514G3212407073848101 BOTTLE BELL 407 407 1182206SW EMERGENCY FLOAT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03417PH 53038 EMERGENCY FLOAT INFLATION BOTTLE HAS CORROSION ON FITTING BETWEEN BOTTLE AND VALVE. 1G71 3U O H2SW 20020531001062002053100106SW 2002 5 31 HEEA078932 120020514G6730214001970111 ACTUATOR BELL 214 214ST 1182106SW FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ELEVATOR WILL NOT STAY ON LINE. 2G72 4U H10SW 20020604000012002060400001 2002 6 4 HEEA078933 420020514G2214214074305105 AMPLIFIER BELL 214 214ST 1182106SW ELEVATOR WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ELEVATOR AMPLIFIER WILL NOT MONITOR TEST ON NR 1 SIDE. 2G72 4U H10SW 20020604000022002060400002 2002 6 4 HEEA078934 420020514G3460214074108101 TRANSDUCER BOLKMS105 BO105S 5626006EU FLT COMPUTER FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 YAW DROPS OFF LINE AND HAS NO RESISTANCE MOVEMENT. 1G72 3U H3EU 20020604000032002060400003SW 2002 6 4 HEEA078935 120020515G6300407010206103 BEARING BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03723PH 53283 BEARING WEAR AND MAIN ROTOR VIBRATION. 1G71 3U O H2SW 20020604000042002060400004SW 2002 6 4 HEEA078947 120020515G2520407030504103 PANEL BELL 407 407 1182206SW PAX SEAT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH2545 53199 PANEL ON PASSENGER SEAT IS CORROSION BEYOND LIMITS. 1G71 3U O H2SW 20020604000052002060400005SW 2002 6 4 HEEA078948 120020515G6510407340339101 BEARING 407040302101BELL 407 407 1182206SW T/R DRIVESHAFT FAILED E HEEAO OTHER M OVER TEMP NRNOT REPORTED 1 SW03407PH A926 53003 BEARING ON TAIL ROTOR DRIVESHAFT OVERHEATED AND FAILED. 1G71 3U O H2SW 20020604000062002060400006SW 2002 6 4 HEEA078949 120020515G6510 BEARING BELL 407 407 1182206SW T/R DRIVESHAFT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03722PH2056 53288 TAIL ROTOR DRIVESHAFT BEARING PRODUCING BLACK GREASE, AND FEELS ROUGH. 1G71 3U O H2SW 20020604000072002060400007SW 2002 6 4 HEEA078951 120020515G7920407040623101 LINE BELL 407 407 1182206SW OIL DISTRIBUTIONCORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 OIL LINE HAS CORROSION UNDER SLEEVE AT FITTING. 1G71 3U O H2SW 20020604000082002060400008SW 2002 6 4 HEEA078952 120020515G7920407040623101 LINE BELL 407 407 1182206SW OIL DISTRIBUTIONTWISTED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 TUBE IS TWISTED ON TOP WHERE IT CONNECTS TO OIL COOLER. 1G71 3U O H2SW 20020604000092002060400009SW 2002 6 4 HEEA078953 120020515G7920407040624101 LINE BELL 407 407 1182206SW OIL DISTRIBUTIONCORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 OIL LINE HAS CORROSION UNDER SLEEVE AT FITTING. 1G71 3U O H2SW 20020604000102002060400010SW 2002 6 4 HEEA078954 120020515G3212407050003105 RETAINER BELL 407 407 1182206SW EMERGENY FLOAT CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 MLG EMERGENCY FLOAT RETAINER IS CORRODED. SCRAPPED LOCALLY. 1G71 3U O H2SW 20020604000112002060400011SW 2002 6 4 HEEA078955 120020515G3213407050201101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 FWD CROSSTUBE CORRODED AT RT SADDLE ZONE A2 MAXIMUM ALLOWED .005 INCH MEASURED CORROSION .008 INCH. 1G71 3U O H2SW 20020604000122002060400012SW 2002 6 4 HEEA078956 120020515G3213407050201101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CROSSTUBE IS CORROSION OUT OF LIMITS. 1G71 3U O H2SW 20020604000132002060400013SW 2002 6 4 HEEA078957 120020515G3213407050201103 CROSSTUBE BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 CROSSTUBE IS SPREAD ON RT SIDE. 1G71 3U O H2SW 20020604000142002060400014SW 2002 6 4 HEEA078958 120020515G3213407050201103 CROSSTUBE BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 LANDING GEAR CROSSTUBE SPREAD OUT OF LIMITS. 1G71 3U O H2SW 20020604000152002060400015SW 2002 6 4 HEEA078959 120020515G3213407050202101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 FOUND PITS OF CORROSION UNDER "T" BOLT AT A DEPTH OF .032. SCRAPPED CROSSTUBE. 1G71 3U O H2SW 20020604000162002060400016SW 2002 6 4 HEEA078967 120020515G3213407050202103 CROSSTUBE BELL 407 407 1182206SW MLG DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 LANDING GEAR CROSSTUBE SPREAD OUT OF LIMITS. 1G71 3U O H2SW 20020604000172002060400017SW 2002 6 4 HEEA078968 120020515G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020604000182002060400018SW 2002 6 4 HEEA078969 120020515G7120407060111101 MOUNT BELL 407 407 1182206SW ENGINE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH 53266 ENGINE MOUNT BEARING WORN. 1G71 3U O H2SW 20020604000192002060400019SW 2002 6 4 HEEA078970 120020515G7920407062532101 TUBE BELL 407 407 1182206SW OIL DISTRIBUTIONDENTED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 OIL TUBE DENTED. 1G71 3U O H2SW 20020604000202002060400020SW 2002 6 4 HEEA078971 120020515G7810407063001101 EXHAUST STACK BELL 407 407 1182206SW ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 EXHAUST STACK CRACKED. 1G71 3U O H2SW 20020604000212002060400021SW 2002 6 4 HEEA078972 120020515G7810407063001101 EXHAUST STACK BELL 407 407 1182206SW ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 EXHAUST STACK CRACKED. 1G71 3U O H2SW 20020604000222002060400022GL 2002 6 4 HEEA078973 220020515G7230407070211102 PLENUM BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CRACKED AT BOTTOM AND NUTPLATE BROKE LOOSE FROM PLENUM. 1G71 3U3 UO H2SW E1GL 20020604000232002060400023SW 2002 6 4 HEEA078974 120020515G5320407070620112 PANEL BELL 407 407 1182206SW FUSELAGE TRIM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 TRIM PANEL CRACKED IN SEVERAL PLACES. 1G71 3U O H2SW 20020604000242002060400024SW 2002 6 4 HEEA078975 120020515G5320407070620113 PANEL BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 FUSELAGE PANEL CRACKED IN SEVERAL PLACES. 1G71 3U O H2SW 20020604000252002060400025SW 2002 6 4 HEEA078976 120020515G5320407070620155 PANEL BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 FUSELAGE PANEL CRACKED IN SEVERAL PLACES. SCRAPPED. 1G71 3U O H2SW 20020604000262002060400026SW 2002 6 4 HEEA078977 120020515G5320407070620156 PANEL BELL 407 407 1182206SW HEADLINER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 HEADLINER CRACKED IN SEVERAL PLACES. SCRAPPED. 1G71 3U O H2SW 20020604000272002060400027SW 2002 6 4 HEEA078978 120020515G2510407070620152 PANEL BELL 407 407 1182206SW CREW SEAT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 SEAT PANEL CRACKED. SCRAPPED. 1G71 3U O H2SW 20020604000282002060400028SW 2002 6 4 HEEA078979 120020515G5210407070620151 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 CREW DOOR PANEL CRACKED. SCRAPPED. 1G71 3U O H2SW 20020604000292002060400029SW 2002 6 4 HEEA078980 120020515G5320407070620150 PANEL BELL 407 407 1182206SW INTERIOR TRIM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 INTERIOR TRIM PANEL CRACKED. SCRAPPED. 1G71 3U O H2SW 20020604000302002060400030SW 2002 6 4 HEEA078981 120020515G2510407070620149 PANEL BELL 407 407 1182206SW CREW SEAT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 CREW SEAT PANEL CRACKED. SCRAPPED. 1G71 3U O H2SW 20020604000312002060400031SW 2002 6 4 HEEA078982 120020515G5320407070620113 PANEL BELL 407 407 1182206SW INTERIOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 INTERIOR PANEL CRACKED. 1G71 3U O H2SW 20020604000322002060400032SW 2002 6 4 HEEA078983 120020515G5210407070620137 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 CREW DOOR PANEL CRACKED. 1G71 3U O H2SW 20020604000332002060400033SW 2002 6 4 HEEA078984 120020515G5210407070620205 COVER BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 STRIKER COVER CRACKED. 1G71 3U O H2SW 20020604000342002060400034SW 2002 6 4 HEEA078985 120020515G5320407070620207 STRUCTURE BELL 407 407 1182206SW HAT BIN CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 HAT BIN STRUCTURE CRACKED. 1G71 3U O H2SW 20020604000352002060400035SW 2002 6 4 HEEA078986 120020515G5210407070620217 PANEL BELL 407 407 1182206SW PAX DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 PAX / CREW DOOR CRACKED. 1G71 3U O H2SW 20020604000362002060400036SW 2002 6 4 HEEA078987 120020515G2510407070731103 BRACKET BELL 407 407 1182206SW SEAT HEADREST CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 DETENT PINS FOR HEADREST BRACKET NOT WORKING AND STICKING. 1G71 3U O H2SW 20020604000402002060400040SW 2002 6 4 HEEA078988 120020515G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT BOTTLE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 EMERGENCY FLOAT BOTTLE GUAGE HAS CORROSION. 1G71 3U O H2SW 20020604000502002060400050SW 2002 6 4 HEEA078989 120020515G3212212073905001 GAUGE BELL 407 407 1182206SW FLOAT BOTTLE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0357416 53070 EMERGENCY FLOAT BOTTLE GAUGE HAS CORROSION. 1G71 3U O H2SW 20020604000592002060400059SW 2002 6 4 HEEA078990 120020515G3212206373901103 SOLENOID VALVE BELL 407 407 1182206SW FLOAT BOTTLE LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING. 1G71 3U O H2SW 20020604000602002060400060SW 2002 6 4 HEEA078991 120020515G2910407073854101 TUBE BELL 407 407 1182206SW HYD SYSTEM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 MLG TUBE PITTING UNDER SLEEVES AND FLARE IS DAMAGED. 1G71 3U O H2SW 20020604000612002060400061SW 2002 6 4 HEEA078994 120020515G5260407301108 STEP BELL 407 407 1182206SW FUSELAGE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 HEAVY CORROSION AROUND MOUNT HOLES ON AIRSTAIR STEP. 1G71 3U O H2SW 20020604000632002060400063SW 2002 6 4 HEEA078995 120020515G5260407301109 STEP BELL 407 407 1182206SW AIRSTAIR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 CORRODED BEYOND LIMITS ON AIRSTAIR STEP. SCRAPPED. 1G71 3U O H2SW 20020604000642002060400064SW 2002 6 4 HEEA078996 120020515G5260407301110 STEP BELL 407 407 1182206SW AIRSTAIR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 CORRODED BEYOND LIMITS ON AIRSTAIR STEP. SCRAPPED. 1G71 3U O H2SW 20020604000652002060400065SW 2002 6 4 HEEA078997 120020515G5260407301110 STEP BELL 407 407 1182206SW AIRSTAIR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 CORRODED BEYOND LIMITS AIRSTAIR STEP. SCRAPPED. 1G71 3U O H2SW 20020604000662002060400066SW 2002 6 4 HEEA078998 120020515G6420407310203101 MOUNT BELL 407 407 1182206SW TAIL ROTOR DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 ELASTOMERIC RUBBER DETERIORATED ON TAIL ROTOR MOUNT. 1G71 3U O H2SW 20020604000672002060400067SW 2002 6 4 HEEA078999 120020515G6420407310203101 MOUNT BELL 407 407 1182206SW TAIL ROTOR DETERIORATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 ELASTOMERIC SEPARATION AROUND CIRCUMFERENCE ON TAIL ROTOR MOUNT. 1G71 3U O H2SW 20020604000682002060400068SW 2002 6 4 HEEA079000 120020515G6420407310203101 MOUNT BELL 407 407 1182206SW TAIL ROTOR DELAMINATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 MOUNT COLLAPSED, DELAMINATED ON TAIL ROTOR. 1G71 3U O H2SW 20020604000702002060400070SW 2002 6 4 HEEA079002 120020515G6321407340302101FM CALIPER BELL 407 407 1182206SW ROTOR BRAKE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH1956 53400 REMOVED ROTOR BRAKE FOR OVERHAUL. FOUND EXCESSIVE WEAR ON HOUSING AND PAD RETAINER BOLTS. 1G71 3U O H2SW 20020604000722002060400072SW 2002 6 4 HEEA079003 120020515G6510407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03741PH 53457 COOLER BLOWER BEARING COMING APART AND MAKING NOISE. 1G71 3U O H2SW 20020604000772002060400077SW 2002 6 4 HEEA079004 120020515G6510407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03490PH 53378 COOLER BLOWER BEARING PRODUCING BLACK GREASE. 1G71 3U O H2SW 20020604000792002060400079SW 2002 6 4 HEEA079005 120020515G6510407340339101 BEARING BELL 407 407 1182206SW COOLER BLOWER WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 COOLER BLOWER HAS A WORN BEARING. 1G71 3U O H2SW 20020604000812002060400081SW 2002 6 4 HEEA079006 120020515G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 TAIL ROTRO DISC PACK IS CRACKED. 1G71 3U O H2SW 20020604000832002060400083SW 2002 6 4 HEEA079007 120020515G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 TAIL ROTOR DISC PACK HAS FRETTING CORROSION BEYOND LIMITS. 1G71 3U O H2SW 20020604000852002060400085SW 2002 6 4 HEEA079008 120020515G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020604000872002060400087SW 2002 6 4 HEEA079009 120020515G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020604000902002060400090SW 2002 6 4 HEEA079010 120020515G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 TAIL ROTOR DISC PACK CRACKED. 1G71 3U O H2SW 20020604000912002060400091SW 2002 6 4 HEEA079011 120020515G3212407350301101 FLOAT BELL 407 407 1182206SW MLG FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03612PH 53199 EMERGENCY FLOAT FAILED 6 MONTH INSPECTION. 1G71 3U O H2SW 20020604000922002060400092SW 2002 6 4 HEEA079012 120020515G3212407350302101 FLOAT BELL 407 407 1182206SW MLG FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 EMERGENCY FLOAT FAILED 6 MONTH INSPECTION. 1G71 3U O H2SW 20020604000972002060400097SW 2002 6 4 HEEA079013 120020515G2840407362005103 SWITCH BELL 407 407 1182206SW FUEL SYSTEM CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 LOW LEVEL SWITCH HAS CORROSION WHERE WIRING EXITS HOUSING. 1G71 3U O H2SW 20020604001002002060400100SW 2002 6 4 HEEA079014 120020515G2897407362013101 PRESSURE SWITCH BELL 407 407 1182206SW FUEL BOOST CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 FUEL BOOST PUMP PRESSURE SWITCH WIRES CORRODED AND BROKEN. 1G71 3U O H2SW 20020604001022002060400102SW 2002 6 4 HEEA079015 120020515G2822407362013101 PRESSURE SWITCH BELL 407 407 1182206SW FUEL BOOST FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03490PH 53378 CAUTION WOULD NOT COME ON WHEN PUMPS WERE SWITCHED OFF. REPLACE PRESSURE SWITCH. 1G71 3U O H2SW 20020604001032002060400103SW 2002 6 4 HEEA079016 120020515G2822407362013101 PRESSURE SWITCH BELL 407 407 1182206SW FUEL BOOST INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 FUEL BOOST PRESSURE SWITCH INOPERATIVE. 1G71 3U O H2SW 20020604001042002060400104SW 2002 6 4 HEEA079017 120020515G2560407370720101 RESTRAINT BELL 407 407 1182206SW COCKPIT SEATBELTFRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 RESTRAINT ASSY FRAYED AND CORRODED. 1G71 3U O H2SW 20020604001062002060400106SW 2002 6 4 HEEA079018 120020515G2560407370721101 RESTRAINT BELL 407 407 1182206SW COCKPIT SEATBELTFRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 FRAYED AND CORRODED. 1G71 3U O H2SW 20020604001082002060400108SW 2002 6 4 HEEA079019 120020515G2560407370721105 RESTRAINT BELL 407 407 1182206SW COCKPIT SEATBELTFRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 RESTRAINT ASSY FRAYED AND CORRODED. 1G71 3U O H2SW 20020604001092002060400109SW 2002 6 4 HEEA079020 120020515G6340407375001105 INDICATOR BELL 407 407 1182206SW MGT ILLUMINATED E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03742PH 53461 MGT INDICATOR ILLUMINATED IN CRUISE FLIGHT. 1G71 3U O H2SW 20020604001112002060400111SW 2002 6 4 HEEA079021 120020515G7714407375002103 INDICATOR BELL 407 407 1182206SW ENGINE NG MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03720PH 53277 NG INDICATOR WILL NOT DISPLAY RPM BUT WILL TEST. 1G71 3U O H2SW 20020604001122002060400112SW 2002 6 4 HEEA079022 120020515G7712407375003107 INDICATOR BELL 407 407 1182206SW TORQUE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03407PH 53003 TORQUE INDICATOR HAS NO INDICATION ON LINEAR OR NUMERIC DISPLAYS. 1G71 3U O H2SW 20020604001142002060400114SW 2002 6 4 HEEA079023 120020515G7933407375004101 INDICATOR BELL 407 407 1182206SW ENG OIL TEMP INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03457PH 53147 ENGINE OIL TEMP INDICAOTR RECEIVED FROM STOCK AND WOULD NOT INDICATE OIL PRESSURE. 1G71 3U O H2SW 20020604001152002060400115SW 2002 6 4 HEEA079025 120020515G7797407375012101 WIRE HARNESS BELL 407 407 1182206SW FADEC DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 WIRE HARNESS OUTER INSULATION COVER OIL SOAKED. 1G71 3U O H2SW 20020604001162002060400116SW 2002 6 4 HEEA079026 120020515G33404596 LIGHT BELL 407 407 1182206SW EXTERIOR INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03402PH 53159 EXTERIOR LIGHT INOPERATIVE. SCRAPPED LOCALLY. 1G71 3U O H2SW 20020604001172002060400117GL 2002 6 4 HEEA079027 220020515G731347101 NOZZLE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE FUEL DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 INTERMITTENT STARTING PROBLEMS. REPLACED WITH SERVICEABLE FUEL NOZZLE. 1G71 3U3 UO H2SW E1GL 20020604001192002060400119 2002 6 4 HEEA079028 420020515G34215040017901 INDICATOR BELL 407 407 1182206SW ATTITUDE PRECESSES E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03407PH 53003 ATTITUDE INDICATOR PRECESSES. REPLACED WITH SERVICEABLE UNIT. 1G71 3U O H2SW 20020604001202002060400120 2002 6 4 HEEA079029 420020515G342150400179015 INDICATOR BELL 407 407 1182206SW ATTITUDE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03407PH 53003 WILL NOT CAGE, SPINS CONTINUOUSLY. REPLACED WITH SERVICEABLE UNIT. 1G71 3U O H2SW 20020604001212002060400121GL 2002 6 4 HEEA079030 220020515G73206839 BULB BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL FADEC INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03496PH 53398 FADEC MANUAL SWITCH BULB INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020604001222002060400122GL 2002 6 4 HEEA079031 220020515G73136899001 NOZZLE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 N1, TOT, AND TORQUE OSCILLATION AFTER 20 MINUTES OF FLIGHT. REPLACED WITH SERVICEABLE UNIT. 1G71 3U3 UO H2SW E1GL 20020604001242002060400124SW 2002 6 4 HEEA079033 120020515G792070079H000D142 HOSE BELL 407 407 1182206SW FUEL SYSTEM COLLAPSED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 FUEL DISTRIBUTION HOSE COLLAPSED. 1G71 3U O H2SW 20020604001252002060400125SW 2002 6 4 HEEA079034 120020515G32128226003 FUSIBLE PLUG BELL 407 407 1182206SW EMERGENCY FLOAT LEAKING E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03492PH 53390 EMERGENCY FLOAT FUSIBLE PLUG LEAKING. 1G71 3U O H2SW 20020604001262002060400126 2002 6 4 HEEA079035 420020515G2350AMS44 CONTROLLER BELL 407 407 1182206SW DUAL AUDIO SYS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03495PH 53397 INTERMITTENT FM HOT MIKE ON PASSENGER SIDE. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020604001272002060400127SW 2002 6 4 HEEA079036 120020515G3411AN58131 PITOT TUBE BELL 407 407 1182206SW STATIC/PITOT SYSDAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CORROSION ON INSIDE AND ON BACKSIDE OF PITOT TUBE. CONNECTION TUBE IS TWISTED, PITOT TUBE HAS SMALL DENT ON EXTERIOR. 1G71 3U O H2SW 20020604001282002060400128SW 2002 6 4 HEEA079037 120020515G3340DK202 LIGHT BELL 407 407 1182206SW EXTERIOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 LIGHT PLASTIC RETAINER FOR LENS CRACKED AROUND SCREW HOLES. 1G71 3U O H2SW 20020604001302002060400130SW 2002 6 4 HEEA079038 120020515G6420J123131 MOUNT BELL 407 407 1182206SW TAIL ROTOR DEBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03447PH 53114 TAIL ROTOR RUBBER IS UNBONDING FROM MOUNT. 1G71 3U O H2SW 20020604001312002060400131SW 2002 6 4 HEEA079042 120020515G6510 BEARING BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 53147 ROUGH BEARING ON COOLER BLOWER ASSY. 1G71 3U O H2SW 20020604001322002060400132SW 2002 6 4 HEEA079044 120020515G6510 BEARING BELL 407 407 1182206SW COOLER BLOWER ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 ROUGH BEARINGS ON COOLER BLOWER ASSY. 1G71 3U O H2SW 20020604001342002060400134SW 2002 6 4 HEEA079045 120020515G3300PM212302 SWITCH BELL 407 407 1182206SW LIGHT SYSTEM BROKEN E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03490PH 53378 LIGHTING SYSTEM SWITCH BROKEN. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020604001352002060400135SW 2002 6 4 HEEA079047 120020515G2110S3008EC6 COMPRESSOR BELL 407 407 1182206SW AIR CONDITIONER LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW038595X1161 53267 AIR CONDITIONER COMPRESSOR WAS LEAKING OIL. 1G71 3U O H2SW 20020604001362002060400136SW 2002 6 4 HEEA079048 120020515G2432SM20ACD300A21 RELAY BELL 407 407 1182206SW MAIN BATTERY FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407XM 53464 BATTERY WON'T COME ON LINE. 1G71 3U O H2SW 20020604001382002060400138 2002 6 4 HEEA079049 420020515G3452066106200 TRANSCEIVER BELL 407 407 1182206SW ATC INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03724PH 53327 ATC TRANSCEIVER MODE "C" INTERMITTENT AND TWO DIGITS OFF. IN SHOP FOR REPAIR. 1G71 3U O H2SW 20020604001402002060400140SW 2002 6 4 HEEA079052 120020515G3212206050247138 COVER BELL 407 407 1182206SW FLOAT MISMARKED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03494PH 53396 RECEIVED COVER WITH P/N 206-050-247-138 FOR RIGHT HAND AFT POSITION. COVER FWD AND AFT FLAPS ARE SET UP FOR LEFT HAND. 1G71 3U O H2SW 20020604001412002060400141SW 2002 6 4 HEEA079053 120020515G3246206053184121 SKID BELL 407 407 1182206SW MLG WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 MLG SKID TUBE WORN. 1G71 3U O H2SW 20020604001432002060400143SW 2002 6 4 HEEA079054 120020515G6510206061432121 HOUSING BELL 407 407 1182206SW COOLER BLOWER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 53323 TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED. 1G71 3U O H2SW 20020604001452002060400145SW 2002 6 4 HEEA079055 120020515G7810206064203101 DUCT BELL 407 407 1182206SW EXHAUST SYS CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 EXHAUST DUCT CRACKED. 1G71 3U O H2SW 20020604001492002060400149SW 2002 6 4 HEEA079059 120020515G6720209001053001 BEARING BELL 407 407 1182206SW TAIL ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 TAIL ROTOR BEARING HAS RADIAL PLAY OF .007 INCH AND LIMIT IS .005 INCH. 1G71 3U O H2SW 20020604001512002060400151GL 2002 6 4 HEEA079060 220020515G725023001832 NOZZLE BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE BENT E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 ENGINE NOZZEL TUBE BENT. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020604001542002060400154GL 2002 6 4 HEEA079061 220020515G726123063144 FILTER ELEMENT BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE OIL CLOGGED E HEEAK NONE J WARNING INDICATION ININSP/MAINT 1 SW03742PH 53461 ENGINE OIL FILTER CLOGGED, OIL BYPASS INDICATOR POPPING. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020604001572002060400157GL 2002 6 4 HEEA079062 220020515G726123066697 FILTER BELL 407 407 1182206SW ALLSN 250C 250C30 03013GL ENGINE OIL CLOGGED E HEEAK NONE J WARNING INDICATION ININSP/MAINT 1 SW034999 53323 BYPASS BUTTON EXTENDED ON DAILY. ENGINE OIL FILTER CLOGGED. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020604001612002060400161SW 2002 6 4 HEEA079064 120020515G3211400052015103 SUPPORT BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 MLG SUPPORT HAS CORROSION AROUND BOLT HOLES. 1G71 3U O H2SW 20020604001622002060400162SW 2002 6 4 HEEA079065 120020515G6230206010421011 BUSHING 406010401117BELL 407 407 1182206SW SWASHPLATE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH A685 53228 BUFFER ON BUSHING IS WORN ON SWASHPLATE. 1G71 3U O H2SW 20020604001632002060400163SW 2002 6 4 HEEA079070 120020515G6710 BEARING BELL 407 407 1182206SW PITCH CONTROL WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MAIN ROTOR UPPER PC LINK BEARING WORN. 1G71 3U O H2SW 20020604001652002060400165SW 2002 6 4 HEEA079071 120020515G6710 BEARING BELL 407 407 1182206SW PITCH CONTROL ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH 53266 MAIN ROTOR PITCH CONTROL LINK BEARING ROUGH. 1G71 3U O H2SW 20020604001682002060400168SW 2002 6 4 HEEA079072 120020515G6710 BEARING BELL 407 407 1182206SW PITCH LINK DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03612PH 53199 CORROSION BLEEDING FROM BEARING RACE AND AROUND EXTERIOR OF PITCH LINK. 1G71 3U O H2SW 20020604001792002060400179SW 2002 6 4 HEEA079073 120020516G334001077005813 LIGHT BELL 214 214ST 1182106SW STROBE INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0359806 28140 EXTERIOR STROBE LIGHT INOPERATIVE. 2G72 4U H10SW 20020604001802002060400180 2002 6 4 HEEA079074 420020516G2312064102300 TRANSCEIVER BELL 214 214ST 1182106SW VHF SYSTEM DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW033897N 28106 INTERMITTENTLY BREAKS SQUELCH AND WEAK. PERFORMED PRELIMINARY INSPECTION. REMOVED CORROSION FROM CHASSIS. REPLACED CORRODED Q109 AND Q110 TRANSISTORS AND INSULATORS, BAD Q102, Q104 AND Q106 TRANSISTOR INSULATORS, BAD Q110 SOCKET AND BROKEN NAMEPLATE. REPLACED BURNED F101 FUSE. FOUND RECEIVER WEAK AND NO TRANSMIT. RESOLDERED RF CONNECTOR. REPAIRED. ALIGNED TRANSMITTER. BENCH CHECK GOOD. 2G72 4U H10SW 20020604001812002060400181SW 2002 6 4 HEEA079075 120020516G6710209001051001 BEARING BELL 214 214ST 1182106SW COLLECTIVE WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0359806 28140 COLLECTIVE CONTROL ASSY HAS WORN BEARINGS. 2G72 4U H10SW 20020604001822002060400182 2002 6 4 HEEA079076 420020516G2300214074305105 AMPLIFIER BELL 214 214ST 1182106SW RADIO SYSTEM WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035748M 28102 LIGHTS WOULD NOT COME ON DURING MONITOR TEST. 2G72 4U H10SW 20020604001852002060400185SW 2002 6 4 HEEA079077 120020516G77203036T52G01 WIRE HARNESS BELL 214 214ST 1182106SW ENG TEMP IND DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW038045T 28101 NR 2 ENGINE TEMPERATURE CONNECTOR ON GREEN HARNESS IS CAUSING THE ENGINE TEMPERATURE INDICATOR TO PEG OUT AT VARIOUS TIMES. 2G72 4U H10SW 20020604001862002060400186 2002 6 4 HEEA079078 420020516G344240016702513 INDICATOR BELL 214 214ST 1182106SW WX RADAR SYS INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03822H 28139 DOES NOT TURN ON. SCRAPPED. 2G72 4U H10SW 20020604001882002060400188 2002 6 4 HEEA079079 420020516G34427021450601 COMPUTER BELL 214 214ST 1182106SW COCKPIT FAILED E K NONE L NO TEST ININSP/MAINT 1 SW0359806 28140 WEATHER RADAR CENTRAL COMPUTER GOES TO FAIL MODE WHEN TURNED ON. 2G72 4U H10SW 20020604001922002060400192SW 2002 6 4 HEEA079080 120020516G6310214040849105 SEAL 214040014105BELL 214 214ST 1182106SW M/R DRIVESHAFT CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038045T A00000003 28101 FOUND BOOTS CRACKED, CORRODED AND DAMAGED ON 250 HOUR COUPLING LUBE INSPECTION. REPLACED WITH SERVICEABLE PARTS. 2G72 4U H10SW 20020604001962002060400196SW 2002 6 4 HEEA079081 120020516G6420 HUB BELL 214 214ST 1182106SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035748M 28102 FOUND 4 PITCH HORN BOLTS CORRODED, ONE GRIP BOLT CORRODED AND DAMAGED, 2 BLADE BOLTS CORRODED AND 2 FEATHERING BEARINGS WORN. (ADP) 2G72 4U H10SW 20020604001992002060400199SW 2002 6 4 HEEA079082 120020516G2840473203003 SIGNAL COND UNIT BELL 412 412 1182202SW FUEL INDICATOR FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 INDICATOR READS ZERO. REPLACE FAILED SIGNAL CONDITIONING UNIT. 1G72 4U H4SW 20020604002002002060400200 2002 6 4 HEEA079084 420020516G3417214175421101 ADC BELL 214 214ST 1182106SW COCKPIT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ADC SHOWS BOTH ENGINES ZERO POWER AT 40 PERCENT. 2G72 4U H10SW 20020604002112002060400211 2002 6 4 HEEA079085 420020516G2200214074305105 AMPLIFIER BELL 214 214ST 1182106SW ELEVATOR MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ELEVATOR AMPLIFIER DRIVES ACTUATOR WITH NO A/S SIGNAL. 2G72 4U H10SW 20020604002122002060400212 2002 6 4 HEEA079086 420020516G2200214074305105 AMPLIFIER BELL 214 214ST 1182106SW ELEVATOR MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ELEVATOR AMPLIFIER COULD NOT ALIGN AMP TO STAY ENGAGED WITH OTHER SYSTEM. 2G72 4U H10SW 20020604002132002060400213SW 2002 6 4 HEEA079087 120020516G6700214001970111 ACTUATOR BELL 214 214ST 1182106SW FLY BY WIRE SYS ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ELEVATOR FLY BY WIRE ACTUATOR MOVEMENT IS ROUGH AND RATCHETY. 2G72 4U H10SW 20020604002142002060400214 2002 6 4 HEEA079089 420020516G3451064100900 TRANSCEIVER BELL 212 212 1181420SW DME/TACAN SYS INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035736J 31140 DME/TACAN TRANSCEIVER WILL NOT TRANSMIT OR RECEIVE. REPLACED WITH SERVICEABLE UNIT. 1G71 4U H4SW 20020604002152002060400215SW 2002 6 4 HEEA079090 120020516G6320212040233001 LINE BELL 212 212 1181420SW TRANSMISSION CRACKED E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW035736D 31135 CRACKED LINE. REPLACED WITH SERVICEABLE PART. 1G71 4U H4SW 20020604002162002060400216SW 2002 6 4 HEEA079091 120020516G7714222375022111 INDICATOR BELL 230 230 1182149SW ENGINE NG MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911RC 23037 ENGINE NG INDICATOR HAS A FLUCTUATING NEEDLE. 1G72 3U NCH9SW 20020604002202002060400220 2002 6 4 HEEA079096 420020520G2200214074305105 AMPLIFIER BELL 214 214ST 1182106SW ELEVATOR WILL NOT TEST E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 ELEVATOR AMPLIFIER WILL NOT MONITOR TEST. 2G72 4U H10SW 20020604002222002060400222SW 2002 6 4 HEEA079097 120020520G7720212075067119 INDICATOR BELL 412 412 1182202SW ENGINE ITT INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ITT INDICATOR WOULD NOT INDICATE. 1G72 4U H4SW 20020604002262002060400226GL 2002 6 4 HEEA079098 220020520G7261174000101 FILTER BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE OIL LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW0330KH 51527 ENGINE OIL FILTER LEAKING FROM HOSE. 1G71 3U3 U H2SW E1GL 20020604002272002060400227SW 2002 6 4 HEEA079099 120020520G5310205030280141 STRUCTURE BELL 412 412 1182202SW WORK DECK SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03800Y 33134 NEWLY INSTALLED WORK DECK FOUND TO BE SEPARATED ON BOTTOM. THE SEPARATED AREA WAS 5 INCHES IN DIAMETER NEAR FWD CENTER OF DECK ASSY. 1G72 4U H4SW 20020604002292002060400229SW 2002 6 4 HEEA079100 120020520G2822205060606003 PUMP BELL 412 412 1182202SW FUEL BOOST INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03107X 33113 FUEL BOOST PUMP INOPERATIVE. 1G72 4U H4SW 20020604002302002060400230SW 2002 6 4 HEEA079101 120020520G6210206015001107 BLADE BELL 206 206L1 1182107SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033905B2968 45598 BLADE HAS A BULGE OVER THE SPAR AT STA. 96.25 INCHES ON THE UPPER SURFACE WHICH APPEARS TO BE EXFOLIATION. BLADE HAS EXCESSIVE CORROSION AND SEPARATION ON THE LOWER SURFACE NEAR THE TIP. 1G71 3U H2SW 20020604002332002060400233SW 2002 6 4 HEEA079102 120020521G6220 BEARING BELL 206 206L3 1182108SW PITCH LINK DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0331077 51520 RUBBER IS POOCHING OUT OF THE UPPER ELASTOMERIC BEARING. 1G71 3U H2SW 20020604002342002060400234SW 2002 6 4 HEEA079103 120020521G6220 BEARING BELL 206 206L3 1182108SW PITCH LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0330KH 51527 PITCH LINK ASSY HAS A WORN BEARING. 1G71 3U H2SW 20020604002352002060400235SW 2002 6 4 HEEA079104 120020521G6220 BEARING BELL 206 206L3 1182108SW PITCH LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW033116P 51530 PITCH LINK ASSY HAS A WORN BEARING. 1G71 3U H2SW 20020604002372002060400237SW 2002 6 4 HEEA079105 120020521G6220 BEARING BELL 206 206L3 1182108SW PITCH LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0330KH 51527 PITCH LINK ASSY HAS A WORN BEARING. 1G71 3U H2SW 20020604002382002060400238SW 2002 6 4 HEEA079106 120020521G6220 BEARING BELL 206 206L3 1182108SW PITCH LINK WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW036251X 51552 PITCH LINK ASSY HAS A WORN BEARING. 1G71 3U H2SW 20020604002392002060400239SW 2002 6 4 HEEA079107 120020521G3246206324007 SKID BELL 206 206L3 1182108SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038594X 51531 SKID TUBE HAS SEVER CORROSION IN SEVERAL AREAS. 1G71 3U H2SW 20020604002412002060400241SW 2002 6 4 HEEA079108 120020521G7720206375007101 INDICATOR BELL 206 206L3 1182108SW ENGINE TOT READS HIGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03363BH 51345 ENGINE TOT READS TEMP HIGH. 1G71 3U H2SW 20020604002422002060400242SW 2002 6 4 HEEA079110 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03800Y 33134 CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES. 1G72 4U H4SW 20020604002442002060400244SW 2002 6 4 HEEA079111 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033893L 33006 CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES. 1G72 4U H4SW 20020604002452002060400245SW 2002 6 4 HEEA079112 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03108X 33115 CROSSTUBE HAS SEVERAL AREAS OF PITTED CORROSION BETWEEN SADDLES. 1G72 4U H4SW 20020604002462002060400246SW 2002 6 4 HEEA079113 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0322347 36005 CROSSTUBE IS CORRODED BEYOND LIMITS ON TOP SIDE BETWEEN SADDLES. 1G72 4U H4SW 20020604002482002060400248SW 2002 6 4 HEEA079114 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035759N 33002 CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS. 1G72 4U H4SW 20020604002492002060400249SW 2002 6 4 HEEA079115 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0322608 33075 CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS. 1G72 4U H4SW 20020604002502002060400250SW 2002 6 4 HEEA079116 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033893P7741 33012 CROSSTUBE CORRODED BEYOND LIMITS IN SEVERAL AREAS. 1G72 4U H4SW 20020604002522002060400252SW 2002 6 4 HEEA079117 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW032258F 33073 CROSSTUBE CORRODED BEYOND LIMITS. 1G72 4U H4SW 20020604002542002060400254SW 2002 6 4 HEEA079118 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033893N1025 33010 CORROSION PITS IN ZONE 1 ON TOP SIDE OF TUBE AT A DEPTH OF .010 OF AN INCH DEEP NEAR SADDLE MOUNT. 1G72 4U H4SW 20020604002562002060400256SW 2002 6 4 HEEA079119 120020521G3213212321103 CROSSTUBE BELL 412 412 1182202SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033911L 33023 MLG CROSSTUBE HAS CORROSION IN ZONE 1 & 2 RADIAL DAMAGED AREAS TO BE BEYOND LIMITS. 1G72 4U H4SW 20020604002632002060400263SW 2002 6 4 HEEA079120 120020521G6340212040805001 SENSOR BELL 206 206B3 1181506SW XMSN TEMP MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW032275Y 3626 SENSOR CAUSING TRANSMISSION TEMP LIGHTS EVEN WITH THE TEMPS IN THE GREEN. 1G71 3U H2SW 20020604002652002060400265SW 2002 6 4 HEEA079123 120020521G2510222320823119 SEAT BELT BELL 206 206L3 1182108SW COCKPIT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0330KH 51527 SEAT BELT WORN. 1G71 3U H2SW 20020604002722002060400272SW 2002 6 4 HEEA079124 120020521G2510222320823119 SEAT BELT BELL 206 206L3 1182108SW COCKPIT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0331077 51520 SEAT BELT WORN AND FRAYED. 1G71 3U H2SW 20020604002782002060400278SW 2002 6 4 HEEA079125 120020521G2510222320823119 SEAT BELT BELL 206 206L3 1182108SW COCKPIT FRAYED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034835 51131 SEAT BELT FRAYED. 1G71 3U H2SW 20020604002832002060400283SW 2002 6 4 HEEA079127 120020521G5320 BRACKET BELL 206 206L3 1182108SW FUSELAGE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038594X 51531 MOUNT BRACKET FOR THE SHOULER HARNESS TO AIRFRAME WERE ELONGATED. 1G71 3U H2SW 20020604002882002060400288SW 2002 6 4 HEEA079128 120020522G5310412030009107 STRUCTURE BELL 412 412 1182202SW SERVICE DECK SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03107X 33113 ENGINE DECK SEPARATION. 1G72 4U H4SW 20020604002922002060400292SW 2002 6 4 HEEA079129 120020522G3212412050017135 COVER BELL 412 412 1182202SW EMERGENCY FLOAT WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03107X 33113 EMERGENCY FLOAT COVER WORN. 1G72 4U H4SW 20020604003082002060400308 2002 6 4 HEEA079130 420020522G34427007700705 INDICATOR BELL 412 412 1182202SW COCKPIT WORN E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03142PH 33150 RADAR SYS WON'T PAINT TARGETS. 1G72 4U H4SW 20020604003092002060400309 2002 6 4 HEEA079131 420020522G2350A3016W INTERPHONE BELL 412 412 1182202SW CABIN MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 INTERPHONE BOX HAS ERRATIC VOLUME CONTROL ON ALL RADIOS. 1G72 4U H4SW 20020604003102002060400310 2002 6 4 HEEA079132 420020522G2350A3016W INTERPHONE BELL 412 412 1182202SW CABIN MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0322608 33075 ADF SELECTOR SWITCH WILL NOT TURN IT'S AUDIO OFF (INTERMITTENTLY). FACEPLATE NEEDS REFURBISH. 1G72 4U H4SW 20020605000012002060500001 2002 6 5 HEEA079133 420020522G2350A3016W INTERPHONE BELL 412 412 1182202SW CABIN MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035759N 33002 INTERPHONE BOX HAS STATIC ON ALL CHANNELS. 1G72 4U H4SW 20020605000022002060500002 2002 6 5 HEEA079134 420020522G3442MI5851345V INDICATOR BELL 412 412 1182202SW WX RADAR SYS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 RADAR CAUSES STREAKS AND FALSE TARGETS IN MAP AND WEATHER MODE. 1G72 4U H4SW 20020605000032002060500003 2002 6 5 HEEA079135 420020522G3442MI5851352 INDICATOR BELL 412 412 1182202SW WX RADAR SYS INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 WEATHER RADAR SYSTEM IS INOPERATIVE. 1G72 4U H4SW 20020605000042002060500004 2002 6 5 HEEA079136 420020522G3442MI585136 INDICATOR BELL 412 412 1182202SW WX RADAR SYS INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 WEATHER RADAR SYSTEM INTERMITTENTLY GOES OFF AND ON. 1G72 4U H4SW 20020605000052002060500005 2002 6 5 HEEA079137 420020522G3442MI5852013 INDICATOR BELL 412 412 1182202SW WX RADAR SYS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03107X 33113 WEATHER RADAR SYSTEM SHOWS NOISE BAND TEST PATTERN ONLY. 1G72 4U H4SW 20020605000062002060500006 2002 6 5 HEEA079141 420020523G2300407530014101 MOUNT BELL 407 407 1182206SW ANTENNA CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03724PH3680 53327 CORROSION AT RADIO ANTENNA MOUNT. 1G71 3U O H2SW 20020605000072002060500007SW 2002 6 5 HEEA079143 120020523G3212206050247138 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 EMERGENCY FLOAT COVER IS TORN. 1G71 3U O H2SW 20020605000082002060500008SW 2002 6 5 HEEA079146 120020523G5240206064819006S ACCESS DOOR BELL 407 407 1182206SW XMSN COWLING CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03492PH 53390 RT TRANSMISSION COWL ACCESS DOOR CORRODED. SCRAPPED. 1G71 3U O H2SW 20020605000092002060500009SW 2002 6 5 HEEA079147 120020523G5320206072215101 SUPPORT BELL 407 407 1182206SW FUSELAGE BROKEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03407PH 53003 FUSELAGE SUPPORT STRUCTURE BROKEN - HAS EXCESSIVE WEAR. 1G71 3U O H2SW 20020605000102002060500010SW 2002 6 5 HEEA079150 120020523G282123066697 FILTER BELL 407 407 1182206SW FUEL SYSTEM CLOGGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 FUEL FILTER BYPASSING BUTTON POPPED. 1G71 3U O H2SW 20020605000112002060500011SW 2002 6 5 HEEA079151 120020523G5310400052007115 BEAM BELL 407 407 1182206SW FUSELAGE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 FUSELAGE BEAM HAS CORROSION UNDER BUSHING AND BEARING CAP. 1G71 3U O H2SW 20020605000122002060500012SW 2002 6 5 HEEA079152 120020523G6720406001704101 BELLCRANK BELL 407 407 1182206SW TAIL ROTOR CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 TAIL ROTOR BELLCRANK LUG IS CHAFED BEYOND LIMITS. 1G71 3U O H2SW 20020605000132002060500013SW 2002 6 5 HEEA079153 120020523G6230406010401117 SWASHPLATE BELL 407 407 1182206SW MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH636 53396 MAIN ROTOR SWASHPLATE PUSHING UP GREASE THROUGH UPPER SEAL. 1G71 3U O H2SW 20020605000142002060500014SW 2002 6 5 HEEA079154 120020523G6230 PITCH LINK BELL 407 407 1182206SW SWASHPLATE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH A6565 53159 MAIN ROTOR SWASHPLATE PITCH CONTROL LINK CORRODED. 1G71 3U O H2SW 20020605000152002060500015SW 2002 6 5 HEEA079155 120020523G6230406010426101 LINK BELL 407 407 1182206SW SWASHPLATE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 SWASHPLATE PITCH CONTROL LINK HAS SURFACE CORROSION. 1G71 3U O H2SW 20020605000162002060500016SW 2002 6 5 HEEA079161 120020523G6520 SEAL BELL 407 407 1182206SW GEARBOX LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03447PH A682 53114 TAIL ROTOR GEARBOX INPUT SEAL LEAKING. 1G71 3U O H2SW 20020605000172002060500017SW 2002 6 5 HEEA079163 120020523G6520406040453101 SEAL BELL 407 407 1182206SW GEARBOX LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03612PH 53199 TAIL ROTOR GEARBOX INPUT SEAL HAS AN OIL LEAK. 1G71 3U O H2SW 20020605000182002060500018SW 2002 6 5 HEEA079164 120020523G6220406310405101 UNIVERSAL BELL 407 407 1182206SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03721PH 53278 MAIN ROTOR HEAD UNIVERSAL BUSHING WORN. 1G71 3U O H2SW 20020605000222002060500022SW 2002 6 5 HEEA079165 120020523G6420406310411101 BOOT BELL 407 407 1182206SW TAIL ROTOR HEAD TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 TAIL ROTOR HEAD BOOT IS TORN. 1G71 3U O H2SW 20020605000242002060500024SW 2002 6 5 HEEA079166 120020523G6220 BEARING BELL 407 407 1182206SW IDLER ASSY UNSTAKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 MAIN ROTOR HEAD BEARING UNSTAKED. 1G71 3U O H2SW 20020605000252002060500025SW 2002 6 5 HEEA079167 120020523G6220407001524105 BELLCRANK BELL 407 407 1182206SW M/R HEAD UNBONDED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03501PH 53401 MAIN ROTOR HEAD BELLCRANK WEAR PAD UNBONDED. 1G71 3U O H2SW 20020605000292002060500029SW 2002 6 5 HEEA079174 120020523G5320407023800118S SUPPORT BELL 407 407 1182206SW FUSELAGE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 FUSELAGE SUPPORT STRUCTURE CRACKED. 1G71 3U O H2SW 20020605000302002060500030SW 2002 6 5 HEEA079175 120020523G3210407030112103 STRAP BELL 407 407 1182206SW MLG CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 STRAP ON MLG CHAFED. 1G71 3U O H2SW 20020605000312002060500031SW 2002 6 5 HEEA079181 120020523G3213407050202101 CROSSTUBE BELL 407 407 1182206SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03720PH 53277 CORROSION ON AFT CROSSTUBE. 1G71 3U O H2SW 20020605000322002060500032SW 2002 6 5 HEEA079182 120020523G2510407070620125 PANEL BELL 407 407 1182206SW SEAT TRIM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 RT CREW SEAT TRIM PANEL CRACKED. 1G71 3U O H2SW 20020605000332002060500033SW 2002 6 5 HEEA079183 120020523G5230407070620143 PANEL BELL 407 407 1182206SW LITTER DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 LITTER DOOR TRIM PANEL CRACKED. 1G71 3U O H2SW 20020605000342002060500034SW 2002 6 5 HEEA079184 120020523G5230407070620157 PANEL BELL 407 407 1182206SW LITTER DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 LT AFT DOOR UPPER TRIM PANEL CRACKED. 1G71 3U O H2SW 20020605000352002060500035SW 2002 6 5 HEEA079185 120020523G5230407070620158 PANEL BELL 407 407 1182206SW LITTER DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 UPPER TRIM PANEL ON RT AFT DOOR CRACKED. 1G71 3U O H2SW 20020605000362002060500036SW 2002 6 5 HEEA079186 120020523G5210407070620205 COVER BELL 407 407 1182206SW DOOR STRIKER CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 CREW DOOR STRIKER COVER CRACKED. 1G71 3U O H2SW 20020605000372002060500037SW 2002 6 5 HEEA079187 120020523G5230407070620218 PANEL BELL 407 407 1182206SW LITTER DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 LOWER TRIM PANEL ON RT AFT DOOR CRACKED. 1G71 3U O H2SW 20020605000382002060500038SW 2002 6 5 HEEA079188 120020523G3212206373901103 SOLENOID VALVE BELL 407 407 1182206SW FLOAT BOTTLE LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW0357416 207 53070 EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING. 1G71 3U O H2SW 20020605000392002060500039SW 2002 6 5 HEEA079189 120020523G3212206373901103 SOLENOID VALVE BELL 407 407 1182206SW FLOAT BOTTLE LEAKING E HEEAK NONE O OTHER ININSP/MAINT 1 SW03457PH 248 53147 EMERGENCY FLOAT BOTTLE SOLENOID VALVE LEAKING. 1G71 3U O H2SW 20020605000432002060500043SW 2002 6 5 HEEA079190 120020523G6310407310203101 MOUNT BELL 407 407 1182206SW ENGINE/XMSN SEPARATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 ENGINE/TRANSMISSION COUPLING MOUNT WEAK AND SEPARATED. 1G71 3U O H2SW 20020605000452002060500045SW 2002 6 5 HEEA079191 120020523G6510407340340101 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 TAIL ROTOR DISC PACK HAS CORROSION. 1G71 3U O H2SW 20020605000462002060500046SW 2002 6 5 HEEA079192 120020523G6510407340340103 DISC PACK BELL 407 407 1182206SW TAIL ROTOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03499PH 53400 TAIL ROTOR DISC PACK IS CRACKED. 1G71 3U O H2SW 20020605000492002060500049SW 2002 6 5 HEEA079193 120020523G2841 WIRE BELL 407 407 1182206SW SWITCH BROKEN E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03402PH 286 53159 FUEL INDICATOR SWITCH HAS A BROKEN WIRE AT DETECTOR OUTPUT. 1G71 3U O H2SW 20020605000522002060500052 2002 6 5 HEEA079194 420020524G2210214074305105 AMPLIFIER BELL 214 214ST 1182106SW AUTOFLIGHT MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03 AUTOFLIGHT AMPLIFIER MALFUNCTIONED, ELEVATOR WOULD NOT STAY ON LINE. 2G72 4U H10SW 20020605000542002060500054SW 2002 6 5 HEEA079195 120020524G2841407362013101 PRESSURE SWITCH BELL 407 407 1182206SW FUEL INDICATOR INTERMITTENT E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03404PH 53188 FUEL INDICTOR PRESSURE SWITCH WORKS INTERMITTENTLY. 1G71 3U O H2SW 20020605000552002060500055SW 2002 6 5 HEEA079196 120020524G5320407412101 PANEL BELL 407 407 1182206SW FUSELAGE TRIM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 FUSELAGE TRIM PANEL CRACKED. 1G71 3U O H2SW 20020605000562002060500056SW 2002 6 5 HEEA079197 120020524G5260407535101 STEP BELL 407 407 1182206SW AIRSTAIRS DEFORMED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 AIRSTAIR FOLDING STEP DOES NOT FIT COUNTOUR OF AIRCRAFT. 1G71 3U O H2SW 20020605000592002060500059SW 2002 6 5 HEEA079198 120020524G5340500913 BRACKET BELL 407 407 1182206SW FUSELAGE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH 53159 FUSELAGE BRACKET CLIP FOR RETAINER STAP MISSING. 1G71 3U O H2SW 20020605000602002060500060 2002 6 5 HEEA079199 420020524G34578143802240D GPS BELL 407 407 1182206SW COCKPIT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 DISPLAY COVER MISSING. PERFORMED PRELIMINARY INSPECTION AND REPLACED BAD DISPLAY LENS. REPAIRED. REALIGNED BUTTONS AND FACEPLATE. BENCH CHECK GOOD. 1G71 3U O H2SW 20020605000612002060500061SW 2002 6 5 HEEA079200 120020524G524090015102156 LATCH BELL 407 407 1182206SW ACCESS DOOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH 53399 LEFT ENGINE COWL ACCESS DOOR LATCHES WORN. 1G71 3U O H2SW 20020605000622002060500062SW 2002 6 5 HEEA079201 120020524G524090015032125 LATCH BELL 407 407 1182206SW ACCESS DOOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03498PH 53399 LEFT TRANSMISSION DECK ACCESS DOOR UPPER LATCH WORN. 1G71 3U O H2SW 20020605000642002060500064SW 2002 6 5 HEEA079203 120020524G6220MS211536 BEARING 406012129101BELL 407 407 1182206SW PITCH LINK ASSY ROUGH E HEEAK NONE O OTHER ININSP/MAINT 1 SW03404PH 53188 MAIN ROTOR PITCH LINK ASSY ROD END BEARINGS ARE ROUGH. 1G71 3U O H2SW 20020605000672002060500067SW 2002 6 5 HEEA079206 120020524G6420 SEAL BELL 407 407 1182206SW PITCH LINK ASSY LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03404PH 53188 TAIL ROTOR PITCH LINK ASSY SEALS ARE LEAKING, BOOT IS DETERIORATED. 1G71 3U O H2SW 20020605000692002060500069SW 2002 6 5 HEEA079207 120020524G6420206011728003 TRUNNION BELL 407 407 1182206SW PITCH LINK ASSY WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 TAIL ROTOR PITCH LINK ASSY TRUNNION WORN. 1G71 3U O H2SW 20020605000702002060500070SW 2002 6 5 HEEA079208 120020524G5210 STRUCTURE BELL 407 407 1182206SW CREW DOOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03402PH5631 53159 CORROSION ON INSIDE OF CREW DOOR. 1G71 3U O H2SW 20020605000872002060500087SW 2002 6 5 HEEA079211 120020524G6220206011117003 RESTRAINT BELL 206 206L3 1182108SW MAIN ROTOR HEAD STUCK E HEEAK NONE O OTHER ININSP/MAINT 1 SW0392MT 51175 FLAP RESTRAINT EAR STICKS IN STOWED POSITION. REPLACED WITH SERVICEABLE PART. 1G71 3U H2SW 20020605000922002060500092SW 2002 6 5 HEEA079212 120020524G6310206040270123 FREEWHEEL UNIT BELL 206 206L3 1182108SW MAIN ROTOR MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW0381671 51301 FREEWHEEL UNIT MAKING METAL. 1G71 3U H2SW 20020605000932002060500093SW 2002 6 5 HEEA079213 120020524G3246206324007 SKID BELL 206 206L3 1182108SW MLG CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03206FS 51506 SKID TUBE CRACKED DUE TO CORROSION EXFOLIATING FROM TUBE AT FORWARD END NEAR HOLD DOWN RING. 1G71 3U H2SW 20020605000982002060500098SW 2002 6 5 HEEA079214 120020524G2822 PLATE BELL 412 412 1182202SW VALVE LOOSE E HEEAK NONE O OTHER ININSP/MAINT 1 SW0322608 33075 PLATE LOOSE. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001012002060500101SW 2002 6 5 HEEA079215 120020524G7810 BRACKET BELL 412 412 1182202SW EJECTOR ASSY CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW036559Z A368 36019 EXHAUST EJECTOR AFT BRACKETS CRACKED. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001032002060500103SW 2002 6 5 HEEA079216 120020524G7810 BRACKET BELL 412 412 1182202SW EJECTOR ASSY CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW036559Z I3000612 36019 EXHAUST EJECTOR AFT BRACKETS CRACKED. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001092002060500109SW 2002 6 5 HEEA079219 120020524G6210412015300109 BLADE BELL 412 412 1182202SW MAIN ROTOR ERODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW036559Z 36019 MAIN ROTOR BLADE LEADING EDGE ERODED. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001112002060500111SW 2002 6 5 HEEA079220 120020524G3340A490A POWER SUPPLY BELL 206 206L3 1182108SW EXTERIOR LIGHTS FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0381671 51301 EXTERIOR LIGHTING POWER SUPPLY FAILED. REPLACED WITH SERVICEABLE PART. 1G71 3U H2SW 20020605001132002060500113 2002 6 5 HEEA079221 420020524G3442MI5851352 INDICATOR BELL 412 412 1182202SW WX RADAR SYS MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 STREAKS AND FALSE TARGETS IN WEATHER MODE AND MAP MODE. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001162002060500116 2002 6 5 HEEA079222 420020524G2300PHI001L0001201 RADIO BELL 206 206L1 1182107SW FM SYSTEM WEAK E HEEAK NONE O OTHER ININSP/MAINT 1 SW0327766 45312 FM RADIO RECEIVE WEAK ON PILOT SIDE. REPLACED WITH SERVICEABLE PART. 1G71 3U H2SW 20020605001222002060500122SW 2002 6 5 HEEA079223 120020524G6300PHI212412830 MAGNETIC SEAL BELL 412 412 1182202SW MAIN ROTOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW032148K 36001 MAIN ROTOR DRIVE MAGNETIC SEAL LEAKS. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020605001232002060500123SW 2002 6 5 HEEA079224 120020524G28221C2710 CARTRIDGE BELL 407 407 1182206SW FUEL BOOST DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03406PH 53198 BOOST PUMP CARTRIDGE IS INTERMITTENT WITH LOW PRESSURE. REPLACED WITH SERVICEABLE PART. 1G71 3U O H2SW 20020605001242002060500124SW 2002 6 5 HEEA079225 120020524G3212206050247138 COVER BELL 407 407 1182206SW EMERGENCY FLOAT TORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03494PH 53396 EMERGENCY FLOAT COVER IS TORN. 1G71 3U O H2SW 20020605001282002060500128SW 2002 6 5 HEEA079227 120020524G6710406010426101 LINK BELL 407 407 1182206SW MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03493PH 53393 CORROSION ON MAIN ROTOR DRIVE LINK. 1G71 3U O H2SW 20020605001382002060500138 2002 6 5 HEEA079235 420020524G34251113025 INDICATOR BELL 412 412 1182202SW HSI MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036559Z 36019 COPILOT OFF FLAG DOES NOT DISPLAY WHEN SLAVING. 1G72 4U H4SW 20020605001462002060500146 2002 6 5 HEEA079239 420020524G34211113034 INDICATOR BELL 412 412 1182202SW ATTITUDE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031202T 33112 ATTITUDE INDICATOR RT FLAG WON'T PULL FROM VIEW. 1G72 4U H4SW 20020605001512002060500151 2002 6 5 HEEA079242 420020524G34211113035 INDICATOR BELL 412 412 1182202SW ATTITUDE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031202T 33112 ATTITUDE INDICATOR COMPASS CARD FLUCTUATES 10 TO 14 DEGREES OFF COURSE. 1G72 4U H4SW 20020605001672002060500167EU 2002 6 5 HEEA079252 120020506G63001053172902 BUSHING BOLKMS105 BO105S 5626006EU M/R DRIVE CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 PITTED CORROSION ON BUSHING FLANGES ON MAIN ROTOR DRIVE. 1G72 3U H3EU 20020605001892002060500189EU 2002 6 5 HEEA079266 120020516G6220350A37124420 SCREW SNIAS 350 AS350B 8680801EU MAIN ROTOR CORRODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03854PH830 3248 SCREW CORRODED, COATINGS WORN THROUGH. . 1G71 3U H9EU 20020605001932002060500193 2002 6 5 HEEA079272 420020516G34578143802240D GPS SNIAS 350 AS350B 8680801EU COCKPIT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03972AE 3234 FACEPLATE SEPARATED. FOUND SET SCREWS ON KNOBS WOULD NOT COME OUT. HAD SET SCREWS DRILLED OUT. REPLACED LENS AND KNOBS. REPAIRED. CLEANED FACEPLATE AND ALL BUTTONS. BENCH CHECK GOOD. 1G71 3U H9EU 20020605001972002060500197 2002 6 5 HEEA079274 420020516G2312DMC634A ANTENNA SNIAS 350 AS350B2 8680813EU VHF SYSTEM CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW0340466 3004 VHF ANTENNA CRACKED AROUND BOLT HOLES. SCRAPPED. 1G71 3U H9EU 20020605001992002060500199EU 2002 6 5 HEEA079278 120020516G6730SC5083 SERVO SNIAS 350 AS350B2 8680813EU MAIN ROTOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW0340466 3004 MAIN ROTOR SERVO LEAKING. 1G71 3U H9EU 20020618000392002061800039NE 2002 6 18 HEEA079336 120020530G24007655000902101 RELAY SKRSKYS76 S76A 8143006NE ELECTRICAL FROZEN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911MJ 760231 SUSPECTED NOT LATCHING PROPERLY AND STUD AT POSITION 21 FROZEN IN PLACE. SCRAPPED. 1G72 3U H1NE 20020607000322002060700032SW 2002 6 7 HEEA079510 120020528G7931209070262101 INDICATOR BELL 412 412 1182202SW ENGINE OIL READS LOW E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035759N 33002 PRESSURE READS LOW. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020607001682002060700168 2002 6 7 HEEA079568 420020530G344280510800001 CONTROL BOX BELL 206 206L3 1182108SW WX RADAR INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW036748D 51106 WEATHER RADAR CONTROL BOX INOPERATIVE. SKYWATCH INTERMITTENTLY HAS DATA FAIL MESSAGE. 1G71 3U H2SW 20020610000042002061000004SW 2002 6 10 HEEA079588 120020530G6210412015300109 BLADE BELL 412 412 1182202SW MAIN ROTOR DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW032148K13953 36001 FIBERGLASS REPAIR BELOW THE TRIM TAB ON THE MAIN ROTOR BLADE HAS SOME SEPARATION ALONG THE EDGES. 1G72 4U H4SW 20020610001002002061000100SW 2002 6 10 HEEA079659 120020530G7714412075010105 INDICATOR BELL 412 412 1182202SW TRIPLE TACH READS LOW E HEEAK NONE O OTHER ININSP/MAINT 1 SW032148K 36001 COPILOT TRIPLE TACH READS 2 PERCENT LOW. 1G72 4U H4SW 20020610002762002061000276 2002 6 10 HEEA079768 420020531G34427021450601 INDICATOR BELL 214 214ST 1182106SW RADAR SYSTEM MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035748M 28102 WILL NOT PAINT TARGETS. 2G72 4U H10SW 20020618000712002061800071 2002 6 18 HEEA079786 420020530G2300071121540 CONTROL PANEL BOLKMS105 BO105S 5626006EU COCKPIT DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW036607K S841 DIGITS WEAK. REPLACED DISPLAY LENS AND PHOTOCELL. ALSO REPLACED MISSING FROM END OF KHZ SELECTOR SHAFT. REPLACED BAD 28 VOLT BACKLIGHT BULB AND TOUCHED UP FACEPLATE WITH BLACK PAINT. BENCH CHECK GOOD. 1G72 3U H3EU 20020618000842002061800084EU 2002 6 18 HEEA079797 120020530G2432RG390E BATTERY BOLKMS105 BO105S 5626006EU MAIN WEAK E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03911PF12 S718 BATTERY WEAK. 1G72 3U H3EU 20020710000592002071000059NE 2002 7 10 HEEA079891 120020611G62107615009043050 TIP CAP SKRSKYS76 S76A 8143006NE M/R BLADE ERODED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035128 760181 FIBERGLASS SKIN ERODED. INTERNAL DOUBLER UNBONDED, FIBERGLASS BETWEEN ENTER AND OUTER DOUBLER BROKEN. 1G72 3U H1NE 20020710000622002071000062NE 2002 7 10 HEEA079892 120020611G29107665009801104 MODULE SKRSKYS76 S76A 8143006NE HYD SYSTEM MALFUNCTIONED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03792CH 760193 OVERBOARD DRAIN WILL NOT PASS FLUID OR AIR. REPLACED HYDRAULIC MODULE. 1G72 3U H1NE 20020710001162002071000116GL 2002 7 10 HEEA079915 220020625G73200164348810 FUEL CONTROL SKRSKYS76 S76A 8143006NE ALLSN 250C 250C47B GL ENGINE MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034253S 760035 ENGINE NOT RESPONDING TO MOVEMENT IN ENG. TRIM MOTOR. 1G72 3U3 U H1NE E1GL 20020710001182002071000118NE 2002 7 10 HEEA079917 120020625G771423007981 PICKUP SKRSKYS76 S76A 8143006NE TRIPLE TACH FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03792CH 760193 NR 2 ENGINE N2 NEEDLES ON BOTH TRIPLE TACHS ERRATIC, THEN AT ZERO WITH ENGINE RUNNING. REPLACED WITH SERVICEABLE N2 PICKUP. 1G72 3U H1NE 20020711000122002071100012NE 2002 7 11 HEEA079922 120020625G77147645001076101 TACH GENERATOR SKRSKYS76 S76A 8143006NE N1 MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911UK 760275 WITH STARTER ENGAGED N1 READS BETWEEN 1 AND 6 PERCENT INTERMITTENTLY. REPLACED WITH SERVICEABLE PART. 1G72 3U H1NE 20020711000342002071100034NE 2002 7 11 HEEA079923 120020625G21217650007901103 BLOWER SKRSKYS76 S76C 8143008NE AIR DIST ODOR E HEEAK NONE O OTHER ININSP/MAINT 1 SW03505PH 760505 BLOWER PRODUCING A BURNING SMELL. 1G72 3U NCH1NE 20020711000362002071100036NE 2002 7 11 HEEA079924 120020625G62007665001802102 ACTUATOR SKRSKYS76 S76A 8143006NE VTA LEAKING E HEEAK NONE KL FLUID LOSS NO TEST ININSP/MAINT 1 SW03911MJ 760231 DURING LEAK CHECK AFTER INSTALLATION OF VTA ACTUATOR RECEIVED FROM STOCK FOUND ACTUATOR TO BE LEAKING. 1G72 3U H1NE 20020711000452002071100045SW 2002 7 11 HEEA079927 120020626G771232447066 CONTROL UNIT BELL 412 412 1182202SW TORQUE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031202T 33112 TORQUE SPLIT. REPLACED WITH SERVICEABLE CONTROL UNIT. 1G72 4U H4SW 20020711000722002071100072GL 2002 7 11 HEEA079937 220020603G731023071644 ECU BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03719PH2325 53266 ECU HAS A BROKEN CONNECTOR PIN. 1G71 3U3 UO H2SW E1GL 20020712000402002071200040SW 2002 7 12 HEEA080060 120020611G5210407070620213 PANEL BELL 407 407 1182206SW CREW DOOR CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03495PH 53397 RT AFT CREW DOOR TRIM PANEL CRACKED. 1G71 3U O H2SW 20020712000602002071200060SW 2002 7 12 HEEA080075 120020611G7714407375008101 INDICATOR BELL 407 407 1182206SW DUAL TACH INOPERATIVE E HEEAO OTHER L NO TEST NRNOT REPORTED 1 SW03496PH 53398 DUAL TACH INDICATOR ROTOR NEEDLE DROPPED TO ZERO. 1G71 3U O H2SW 20020715000292002071500029SW 2002 7 15 HEEA080128 120020626G7920212040232001 VALVE BELL 412 412 1182202SW ENGINE OIL LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW032149S 36002 VALVE LEAKS OIL. REPLACED WITH SERVICEABLE VALVE. 1G72 4U H4SW 20020715000702002071500070SW 2002 7 15 HEEA080149 120020626G2840473203003 SIGNAL COND UNIT BELL 412 412 1182202SW FUEL SYSTEM DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW032149S 36002 UNIT WILL NOT HOLD CALIBRATION. 1G72 4U H4SW 20020715000772002071500077SW 2002 7 15 HEEA080153 120020626G632194501031 BRAKE ASSY BELL 412 412 1182202SW MAIN ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW036559Z 36019 BRAKE ASSY PUCKS WORN. REPLACED WITH SERVICEABLE PART. 1G72 4U H4SW 20020820000172002082000017SW 2002 8 20 HEEA080525 120020729G77223030083 COMPENSATOR BELL 412 412 1182202SW ENGINE TRIM DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW032148K 36001 ADJUSTMENT PIN LOOSE IN HOUSING. 1G72 4U H4SW 20020821000072002082100007 2002 8 21 HEEA080619 420020729G3421504001790116 GYRO BELL 412 412 1182202SW COCKPIT PRECESSES E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW033893L 33006 DURING FLIGHT, INDICATOR WILL PRECESS AND DRIFT. REPAIRED. 1G72 4U H4SW 20020821000122002082100012 2002 8 21 HEEA080623 420020729G3421504001790116 GYRO BELL 412 412 1182202SW COCKPIT PRECESSES E HEEAK NONE L NO TEST ININSP/MAINT 1 SW032149S 36002 HORIZON GYRO PRECESSES TO THE RIGHT. REPAIRED. 1G72 4U H4SW 20020821000222002082100022SW 2002 8 21 HEEA080633 120020729G242151509002R CONTROL UNIT BELL 412 412 1182202SW GENERATOR MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03142PH 33150 AFTER SETTING PARALLEL VOLTAGE, UNIT DRIFTS. 1G72 4U H4SW 20020821000302002082100030GL 2002 8 21 HEEA080639 220020730G72006898761 ELBOW BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW0330KH 51527 ENGINE LINE ELBOW LEAKING. REPLACED WITH SERVICEABLE PART. 1G71 3U3 U H2SW E1GL 20020821000752002082100075 2002 8 21 HEEA080666 420020730G2350AA34200 RADIO BELL 206 206L3 1182108SW COCKPIT DAMAGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0331801 51074 WEAK RX AUDIO. LOOSE PARTS INSIDE. 1G71 3U H2SW 20020821000982002082100098SW 2002 8 21 HEEA080683 120020730G2910C4264215 SLEEVE BELL 206 206B3 1181506SW HYD SYSTEM LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03 LEAKED EXTERNALLY APPROX. 1 EA. TEASPOON UNDER PROOF PRESSURE TEST AT INNER SPOOL WITHIN 3 MINUTES. 1G71 3U H2SW 20020821001002002082100100 2002 8 21 HEEA080684 420020730G2300CI31020 ANTENNA BELL 206 206L3 1182108SW FM SYSTEM FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW036603X 51412 FM HAS LOW POWER OUT. SCRAPPED. 1G71 3U H2SW 20020822000262002082200026SW 2002 8 22 HEEA080714 120020807G2840473203003 SIGNAL COND UNIT BELL 412 412 1182202SW FUEL INDICATOR MALFUNCTIONED E HEEAO OTHER N FALSE WARNING NRNOT REPORTED 1 SW03 SIGNAL COND UNIT PRODUCING INTERMITTENT LOW FUEL LIGHT WITH FUEL IN AIRCRAFT. 1G72 4U H4SW 20021223000452002122300045 2002 12 23 HEEA082389 420021206G31309806020023 CVR CLARK 1000 1000CLARK 2230102SW COCKPIT MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 COCKPIT VOICE RECORDER CAUSES THE CVR TEST LIGHT TO STAY ON. 1Q71 3R 2A6 20021223000572002122300057 2002 12 23 HEEA082394 420021212G3452066104100 TRANSPONDER SKRSKYS76 S76A 8143006NE ATC INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031546K 760082 INTERMITTENT MODE "C" OPERATION. CLEANED CORROSION FROM UNIT. FOUND WEAK MTL AND TRANSMIT POWER. TROUBLESHOT AND REPLACED V201 CAVITY OSCILLATOR AND CATHODE ASSY, ADJUSTED FREQUENCY AND POWER TO SPECS. ALSO FOUND DYNAMIC RANGE OUT OF SPECS. ALIGNED AND ADJUSTED RECEIVER AND VIDEO BOARD SEVERAL TIMES. BENCH CHECK GOOD. 1G72 3U H1NE 20021223000592002122300059 2002 12 23 HEEA082395 420021212G3455066104701 TRANSCEIVER SKRSKYS76 S76A 8143006NE ADF WEAK E HEEAK NONE L NO TEST ININSP/MAINT 1 SW034253S 760035 WEAK RECEIVE AUDIO, WON'T POINT TO STATIONS. IN SHOP REPAIR. 1G72 3U H1NE 20021223000622002122300062 2002 12 23 HEEA082398 420021212G3455066107700 RECEIVER SKRSKYS76 S76A 8143006NE ADF FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0322342 760096 ADF RECEIVER FOUND INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND IC I306, I307 BAD. REPLACED. REPAIRED. BENCH CHECK GOOD. 1G72 3U H1NE 20021223000642002122300064NE 2002 12 23 HEEA082400 120021212G3150 WARNING LIGHT SKRSKYS76 S76A 8143006NE COCKPIT ILLUMINATED E HEEAK NONE N FALSE WARNING ININSP/MAINT 1 SW031546K 760082 BATTERY HOT LIGHT ON. IN SHOP REPAIR. 1G72 3U H1NE 20021226000192002122600019NE 2002 12 26 HEEA082429 120021212G3212297800013 BOTTLE SKRSKYS76 S76A 8143006NE EMERGENCY FLOAT DISCHARGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034253S 760035 EMERGENCY FLOAT BOTTLE DISCHARGED, REPAIRED. 1G72 3U H1NE 20021226000262002122600026 2002 12 26 HEEA082435 420021212G34424000038 CONTROL HEAD SKRSKYS76 S76A 8143006NE WX RADAR SYS INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03760PH 760078 WEATHER RADAR CONTROL HEAD IS INOPERATIVE. FOUND CORROSION ON UNIT, SWITCH R4/S1 AND VOLUME KNOB BAD. CLEANED CORROSION AND INSTALLED SWITCH AND VOLUME KNOB. REPAIRED. BENCH CHECK GOOD. 1G72 3U H1NE 20021227000022002122700002NE 2002 12 27 HEEA082443 120021212G31507001840913 TRANSCEIVER SKRSKYS76 S76A 8143006NE WARNING SYSTEM MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW031546G 760076 TRANCEIVER FLAG STAYS IN OFF POSITION. 1G72 3U H1NE 20021226000322002122600032 2002 12 26 HEEA082445 420021212G34427007700614 DISPLAY SKRSKYS76 S76A 8143006NE WX RADAR SYS MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03760PH 760078 WEATHER RADAR SCREEN INTERMITTENTLY COMPRESSES AND FLICKERS. 1G72 3U H1NE 20021227000302002122700030NE 2002 12 27 HEEA082488 120021213G6700 BEARING SKRSKYS76 S76A 8143006NE LINK ASSY RATCHETING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03911MJ 760231 LINK ASSY HAS RATCHETY BEARINGS. REPAIRED. 1G72 3U H1NE 20021227000552002122700055NE 2002 12 27 HEEA082505 120021213G77127645001078123 INDICATOR SKRSKYS76 S76A 8143006NE TORQUE FLUCTUATES E HEEAK NONE O OTHER ININSP/MAINT 1 SW0322342 760096 TORQUE INDICATOR FLUCTUATES IN FLIGHT. 1G72 3U H1NE 20021230000822002123000082SW 2002 12 30 HEEA082597 120021209G6720PHI214ST103 COUNTERWEIGHT BELL 214 214ST 1182106SW TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW0359806 28140 TAIL ROTOR COUNTERWEIGHT HAS WORN BEARINGS. REPAIRED. 2G72 4U H10SW 20021230001012002123000101EU 2002 12 30 HEEA082616 120021211G671010531821 CONTROL ROD BOLKMS105 BO105S 5626006EU TAIL ROTOR WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 TAIL ROTOR CONTROL ROD PITCH LINK HAS WORN BEARINGS. REPAIRED. REPLACED BEARINGS. 1G72 3U H3EU 20030102000062003010200006 2003 1 2 HEEA082625 420021211G3424206070274005 INDICATOR BOLKMS105 BO105S 5626006EU TURN & BANK INOPERATIVE E HEEAK NONE L NO TEST ININSP/MAINT 1 SW0381832 S828 TURN AND BANK INDICATOR INOPERATIVE. 1G72 3U H3EU 20030102000102003010200010GL 2003 1 2 HEEA082629 220021211G732023033400 FILTER BOLKMS105 BO105S 5626006EU ALLSN 250C 250C30 03013GL PC AIR CLOGGED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035031U S678 NR 1 ENGINE PC FILTER CLOGGING WITH WATER ON ENGINE WASH AND CAUSING HANG STARTS. REPLACED WITH SERVICEABLE FILTER. 1G72 3U3 U H3EU E1GL 20030102000152003010200015EU 2003 1 2 HEEA082634 120021211G243651565000R VOLT REGULATOR BOLKMS105 BO105S 5626006EU DC SYSTEM DEFECTIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW036607K S841 DC VOLTAGE REGULATOR WILL NOT ADJUST. TO BE SENT TO VENDOR FOR REPAIR. 1G72 3U H3EU 20030102000202003010200020EU 2003 1 2 HEEA082639 120021211G7931BSE206150G3 TRANSDUCER BOLKMS105 BO105S 5626006EU OIL PRESSURE FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035031U S678 NO OIL PRESSURE INDICATION. REPLACED WITH SERVICEABLE PART. 1G72 3U H3EU 20030102000242003010200024EU 2003 1 2 HEEA082643 120021211G7712DK50439 INDICATOR BOLKMS105 BO105S 5626006EU DUAL TORQUE READS LOW E HEEAK NONE L NO TEST ININSP/MAINT 1 SW035031U S678 DUAL TORQUE INDICATOR READS LOW. 1G72 3U H3EU 20030103000462003010300046GL 2003 1 3 HEEA082666 220021211G732023073525 ELBOW BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20 03013GL PC FILTER STRIPPED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035031U S678 PC FILTER SIDE STRIPPED. SCRAPPED. 1G72 3U3 U H3EU E4CE 20030103000562003010300056EU 2003 1 3 HEEA082676 120021211G2820AE705801 HOSE BOLKMS105 BO105S 5626006EU FUEL SYSTEM LEAKING E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW037170D S840 FUEL HOSE LEAKING. REPLACED WITH SERVICEABLE HOSE. 1G72 3U H3EU 20030103000572003010300057EU 2003 1 3 HEEA082677 120021211G7712DK50439 INDICATOR BOLKMS105 BO105S 5626006EU DOUBLE TORQUE MALFUNCTIONED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW037170D S840 INDICATOR SHOWING NR 1 NG TORQUE FLUCTUATIONS. 1G72 3U H3EU 20030106001482003010600148GL 2003 1 6 HEEA082799 220021216G72610292217030 LABYRINTH SEAL AEROSPAS355 AS355* EU ALLSN 250C 250C20 03013GL ENGINE CONTAMINATED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03973AE 3229 CARBON BUILD UP IN LABYRINTH SEALS CAUSING BINDING NG. 1G72 3U3 U H11EU E4CE 20030106001492003010600149GL 2003 1 6 HEEA082800 220021216G73230292928540 METERING VALVE AEROSPAS355 AS355* EU ALLSN 250C 250C20 03013GL TURBINE GOVERNORLEAKING E HEEAO OTHER K FLUID LOSS NRNOT REPORTED 1 SW03972AE326 3234 22065 FUEL LEAKING FROM CASE DRAIN OF METERING VALVE. 1G72 3U3 U H11EU E4CE 20020205000492002020500049SO 2002 2 5 HO1R15248 120020119G57116205401 SPAR PIPER PA32 PA32260 7103206SO LYC O540 O540E4B5 41532EA RT WING CORRODED B HO1RK NONE O OTHER ININSP/MAINT 1 EA217728J3679 321130 R1351240 DURING ANNUAL INSPECTION THE RIGHT WING AFT ATTACH FITTING OUTBOARD OF THE FUSELAGE AND AFT WING SPAR WERE FOUND TO EXHIBIT DISSIMILAR METAL CORROSION BETWEEN THE STEEL ATTACH FITTING AND THE REAR SPAR. THE AFT SPAR WAS CORRODED TO THE POINT WHERE A CRACK HAD DEVELOPED IN THE REAR SPAR. CRACK WAS NOT FOUND UNTIL STEEL ATTACH FITTING WAS REMOVED FOR HIDDEN DAMAGE INSPECTION. 1L71 3O3 O A3SO E295 20020313001482002031300148CE 2002 3 13 IC1D213K 120020212G532053120252 CHANNEL CESSNA340 340A 2076405CE HORIZONTAL STAB CRACKED D IC1DK NONE O OTHER ININSP/MAINT 1 EA23324WA3012 340A0608 AIRCRAFT PAN CHANNEL JUST BELOW HORIZONTAL STABILIZER AFT SPAR ON EMPENAGE STRUCTURE HAS (NR 2)-.7500 INCH CRACKS IN RADIUSED AREAS. CRACKS WERE FOUND ON ANNUAL INSPECTION PROBABLE CAUSE UNKNOWN STRESS. RECOMMENDATION: DETAILED INSPECTION AT ANNUAL INSPECTION. 1L72 3O 3A25 20020719000702002071900070EU 2002 7 19 IO5R080367 120020711G2121A206621250 FAN UROCOPEC120 EC120B 8680987EU AIR DISTRIBUTIONBROKEN H IO5RO OTHER O OTHER ININSP/MAINT 1 FS01488SH257 1181 PLASTIC FINS BROKEN, WILL NOT ADJUST RMA#RO37749 REMOVED AND REPLACED 1G72 3U NCR0001RD 20021015000242002101500024EU 2002 10 15 IO5R081096 120021003G243423081057 STARTER UROCOPEC135 EC135P1 8680990EU NR 1 FAILED H IO5RO OTHER O OTHER TXTAXI/GRND HDL 1 FS01551BA376 188 STARTER WILL NOT ROTATE INSTALLED LOANER ASSY. 1G72 3U O H88EU 20020123001352002012300135EU 2002 1 23 ISHA077549 120020116G6220704A33633156 BEARING SNIAS 350 AS350D1 8680804EU MAIN ROTOR WORN H ISHAK NONE O OTHER ININSP/MAINT 1 FS01301EX983 1358 WARRANTY CREDIT FOR WORN PART WHICH HAS A S.L.L.OF 6400.0 HRS. AND ONLY LAST 982.5 HRS. 1G71 3U H9EU 20020129000122002012900012NM 2002 1 29 IVSA077688 120020123G7600B2475 GOVERNOR ROBSINR22 R22BETA 7640110NM ENGINE DEFECTIVE H IVSAO OTHER O OTHER NRNOT REPORTED 1 FS01HP145593 1031 GOVERNOR MOTOR RUNS SLOWLY, TAKING 10-12 SECONDS TO BRING RPM UP TO FLIGHT RPM REPLACEMENT MOTOR INSTALLED, DEFECTIVE UNIT RETURNED TO ROBINSON FOR WARRANTY EXCHANGE OR REPAIR. 1G71 3O H10WE 20020419000272002041900027WP 2002 4 19 IVSA078430 120020409G6310A1902 BELT ROBSINR22 R22 7640102WP ENG TO ROTOR STRETCHED H IVSAA UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 FS017101J3 3005 BELTS WERE REPLACED DURING 100HR INSPECTION AFTER 693.3 HOURS TSI. FAN WHEEL WAS BALANCED AND RUNUP WAS NORMAL. FIRST FLIGHT OF APPROXIMATELY 2 HOURS WAS UNEVENTFUL. DURING SECOND FLIGHT PILOT REPORTED CLUTCH LIGHT FLICKERED ON AND OFF SEVERAL TIMES. ON INSPECTION AFTER PRECAUTIONARY LANDING, BELTS WERE FOUND STRETCHED TO THE POINT THAT OVER LIMIT SWITCH DEACTIVATED THE SYSTEM. SYSTEM INSPECTED WITH NO FAULTS FOUND OTHER THAN BELT STRETCH BEYOND LIMITS. NEW BELTS WERE INSTALLED AND ADJUSTED. FAN WHEEL BALANCE CHECKED. 1G71 3O H10WE 20021114000862002111400086CE 2002 11 14 JAC001RR 120021108G281041423 CELL CESSNA414 414 2075908CE FUEL STORAGE DETERIORATED B K NONE K FLUID LOSS ININSP/MAINT 1 GL13414TH2720 2720 4140400 DURING ANNUAL INSPECTION, LEFT WING OUTBOARD AUX FUEL CELL LEAKAGE NOTED. UPON INVESTIGATION, FUEL CELL FOUND TO BE SERIOUSLY DETERIORATED AROUND THE FILLER PORT OPENING. THE FUEL CELL MATERIAL AT THAT POINT HAD BECOME BRITTLE. SUGGEST THOROUGH EXAMINATION OF FUEL CELLS CONDITIONS DURING ALL SCHEDULED INSPECTIONS. 1L72 3O RTA7CE 20021114000872002111400087SO 2002 11 14 JAC002RR 120021108G7810 EXHAUST PIPE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA LT ENGINE WRONG PART B K NONE O OTHER ININSP/MAINT 1 GL135494R 48 317405410 RL324361A DURING 100 HOUR/ANNUAL INSPECTION, LT ENGINE TURBOCHARGER EXHAUST PIPE WAS NOTICED TO BE ABNORMAL, IN THAT IT WAS ASSEMBLED OF 13 WELDED SEGMENTS, WHEREAS THE CORRECT PART CONSISTS OF TWO WELDED SEGMENTS. PART WAS REPLACED WITH THE CORRECT ITEM, PART NUMBER 40310-10. NO MENTION OF INSTALLATION FOUND IN THE AIRCRAFT RECORDS. SUGGEST THAT A CAREFUL WATCH FOR BOGUS PARTS IS INCLUDED IN ALL MAINTENANCE FUNCTIONS. 1L72 3O3 O A20SO E14EA 20020523000102002052300010CE 2002 5 23 JG0201741 120020521G32425007916 BRAKE ASSY MTSBSIMU300 MU300 5780602CE MLG DISINTEGRATED B O OTHER O OTHER TXTAXI/GRND HDL 1 SW11574CF483 A079SA WHILE TAXIING AFTER LANDING FELT AIRCRAFT SHUTTER. STOPPED AIRCRAFT ON TAXIWAY AND VISUALY INSPECTED OUTSIDE OF AIRCRAFT NO DEFECTS NOTED. CONTINUED TAXI TO PARKING. MAINTENANCE REMOVED LT WHEEL AND FOUND BRAKE ASSEMBLY HAD CAME APART. 2H72 4F RTA14SW 20020327001712002032700171SW 2002 3 27 JJWA078248 120020321G5302206020123048S RIB BELL 206 206B 1181511SW HORIZONTAL STAB CRACKED H JJWAK NONE O OTHER ININSP/MAINT 1 FS01281CB10170 3303 REMOVED BOTH HORIZONTAL STABILIZERS THAT HAD BEEN LAST INSTALLED OVER 5 YEARS AGO. FOUND EXCESSIVE CORROSION IN SPAR CLAMP AREA ON RIB CLOSEST TO TAILBOOM. REQUIRES TOTAL RIBE REPLACEMENT OF $1966 RIB. INSPECTED OTHER RIB ALSO HAD CORROSION & PIECE MISSING SO REPLACED 206-020-123-047S RIB ON THAT SIDE ALSO. THIS IS SECOND REPORT IN LESS THAN YEAR ON SAME PARTS. SUGGEST BELL HELICOPTER INSERT A 3 YEAR INSPECTION IN MAINTENANCE MANUAL, ESPECIALLY WHEN AIRCRAFT IN CORROSIVE ENVIRONMENT LIKE THE STATE OF FLORIDA. 1G71 3U H2SW 20020719001482002071900148SO 2002 7 19 JK001 220020527G8550 OIL SYSTEM CONT O360 IO360D 17025SO MCAULY2A34C 2A34C203 GL ENGINE LOW G A UNSCHED LANDING RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 GL032442 DURING CRUISE FLIGHT OIL PRESSURE WAS NOTED TO BE LOW AND FLUCTUATING, ALONG WITH SEVERE VIBRATION. THIS WAS FOLLOWED BY A COMPLETE LOSS OF OIL PRESSURE AND SUBSEQUENT LOSS OF POWER. THE ENGINE EXPERIENCED INTERNAL FAILURE FOR UNKNOWN REASONS RESULTING IN THREE LARGE HOLES IN THE ENGINE CASE. 3 O E1CE 5 CP3EA 20021025000112002102500011WP 2002 10 25 JV2R200200001 220021024G726130726361 LINE PIPER PA23 PA23 7102302SO GARRTTTFE731TFE7313R1D 01518WP LEFT ENGINE CHAFED B JV2RK NONE K FLUID LOSS ININSP/MAINT 1 CE037SE 6830 231127 P83169 REPORTED OIL LEAK, REMOVED COWLING TO INSPECT FOR OIL LEAK, REMOVED CLAMP AND INSPECTED TO FIND THE CLAMP HAD CHAFED THE LINE WHICH CAUSED AN OIL LEAK. THE TEFLON ON THE CLAMP WAS WORN CAUSING METAL TO METAL CONTACT. INSPECTING THE LINE AT THE CHAFED AREA AND USING THUMB NAIL, A HOLE WAS CREATED. 1L72 3O4 F 1A10 E6WE 20021114000892002111400089WP 2002 11 14 JV2R200200003 220021106G726130726361 LINE RKWELLNA265 NA26565 7630107CE GARRTTTFE731TFE7313R1D 01518WP NR 1 ENGINE NICKED B JV2RK NONE O OTHER ININSP/MAINT 1 CE03750CC7625 46537 P83175 WHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN IT CAUSE BY THE CLAMPS THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT. REPACED LINE AND CLAMPS. 2L72 4J4 F A2WE E6WE 20021114000902002111400090WP 2002 11 14 JV2R200200004 220021106G726130726361 LINE RKWELLNA265 NA26565 7630107CE GARRTTTFE731TFE7313R1D 01518WP NR 2 ENGINE NICKED B JV2RK NONE O OTHER ININSP/MAINT 1 CE03750CC7603 46537 P83176 WHEN COMPLYING WITH CAMP CARDS, A VISUAL INSPECTION OF THE ENGINE WAS PERFORMED AND FOUND THE OIL LINE HAD NICKS IN THE LINE CAUSE BY THE CLAMPS, THAT HAD THE TEFLON WORN CAUSING METAL TO METAL CONTACT. REPLACED LINE AND CLAMPS. 2L72 4J4 F A2WE E6WE 20020422000382002042200038EU 2002 4 22 KBMA112001 120020108G26120301037070 HARNESS SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1B 6OO30NE FIRE DETECTION SEPARATED E KBMAK NONE O OTHER ININSP/MAINT 1 WP19 502 4173 FERRILS UNBONDED/SEPARATED. REPLACED WITH NEW HARNESS. 1G71 3U3 U H9EU E19EU 20020814000162002081400016CE 2002 8 14 L2232 120020805G571257222062 RIB CESSNA441 441 2076020CE RT CENTER WING CRACKED B LK0RK NONE O OTHER ININSP/MAINT 1 SO15666HC7255 4410292 DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (LCWS 26.85") HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45") AND EXTENDING APPROXIMATELY 1" AFT OF THE SPAR. AFTER REMOVAL FO THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. CESSNA CURRENTLY DOES NOT HAVE ANY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE, THIS AREA SHOULD BE CLOSELY INSPECTED DURING ROUTINE INSPECTIONS. 1L72 3T RTA28CE 20020814000172002081400017CE 2002 8 14 L2240 120020805G571257222061 RIB CESSNA441 441 2076020CE LT CENTER WING CRACKED B LK0RK NONE O OTHER ININSP/MAINT 1 SO15666HC7255 4410292 DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIBCAP P/N: 5722206-1 (LCWS 26.85 INCH) HAD A CRACK ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45 INCH) AND EXTENDING APPROXIMATELY 1INCH AFT OF THE SPAR. AFTER REMOVAL FO THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYPE CRACK. 1L72 3T RTA28CE 20021030002382002103000238NE 2002 10 30 MDR00402 220021009G72301711M20P08 SEAL GE GE90 GE9090B NE 1ST STAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SW99 20177 900207 FPI INDICATIONS FOUND IN STAGE 1 BLADE RETAINER ARM AT EACH BLADE LOCATION. ITEM TO BE RETURNED TO MFG FOR DETAILED ANALYSIS. PART WOULD HAVE BEEN REDUNDANT TO SB 72455. 4 F E00049EN 20030205000292003020500029CE 2003 2 5 MEA200301 120021227G56101013840227 WINDSHIELD BEECH B300 B300 1159232CE PWA PT6 PT6A60A 52043NE HARTZLHCB4M HCB4MP3 GL COCKPIT FAILED C A UNSCHED LANDING O OTHER CRCRUISE 1 GL23593MA614 FL68 A/C WAS ENROUTE AT FL260, WINDSHIELD ANTI-ICE WAS SELECTED ON AND WAS ON FOUR 1 1/2 HOURS WHEN A LOUD CRACK WAS HEARD AND THE PILOTS WINDSHIELD SHATTERED THE INNER PANE INTO PEA SIZED PIECES. CREW FOLLOWED AIRCRAFT ABNORMAL PROCEDURES AND DESCENDED BELOW 25,000 FEET AND KEEP CABIN PSI BETWEEN 2 AND 4.6. OAT AT TIME WAS -35C. AIRCRAFT WAS FLOWN BACK TO HOME BASE. 2L72 4T4 TRTA24CE E4EA 6 CP56GL 20020328000092002032800009CE 2002 3 28 N421DG030102 120020321G3230 HYDRAULIC SYSTEM CESSNA421 421C 2076016CE MLG CONTAMINATED G L ABORTED APPROACH G MULTIPLE FAILURE LDLANDING 1 NM11421DG 421C0456 EXTENDED THE MLG ON APPROACH AND ONLY THE LT LOCKED INTO PLACE. NOTIFIED TOWER OF THIS CONDITION AND MANEUVERED WHILE WORKING ON THE PROBLEM. INITIATED THE APPROACH AGAIN AND EXECUTED EMERGENCY PROCEDURES, ONLY LT MAIN WAS LOCKED, THE LANDING WAS INITIATED AND THE A/C TOUCHED DOWN WITH LT DOWN AND LOCKED, THE RT WAS PARTIALLY EXTENDED BUT NOT LOCKED, THE NOSE GEAR WAS EXTENDED BUT IT WAS NOT LOCKED. NLG STAYED EXTENDED ON ROLL OUT AND THE RT WING, AILERON, FLAP, AND PROP SUSTAINED DAMAGE. HYD MLG SYS WAS INSPECTED. FLUID WAS EXAMINED, AND A SMALL AMOUNT OF WATER WAS FOUND. IN SHOP AT 60 DEG F THE MLG FUNCTIONED NORMALLY. IT APPEARS THAT MOISTURE IN THE HYD SYS FROZE AND PREVENTED FUNCTION OF THE MLG. 1L72 3O A7CE 20020716002002002071600200CE 2002 7 16 ODAR0184 120020207G3710442CW12 PUMP BEECH 58 58 1152740CE CONT O520 IO520* 17032SO VACUUM SYS FAILED B ODARO OTHER O OTHER NRNOT REPORTED 1 EA21707PW TH1106 PILOT EXPERIENCED A DUAL VACUUM PUMP FAILURE IN VFR CONDITIONS. 1L72 3O3 O 3A16 E5CE 20020515001842002051500184CE 2002 5 15 OG5R092N 120020508G2810715371 FUEL TANK BBAVIA8 8KCAB 2110612CE LYC O360 AEIO360H1A 41514EA HARTZLHCC2Y HCC2YR4 GL FUSELAGE CRACKED B K NONE K FLUID LOSS ININSP/MAINT 1 GL21 390 L2592851A AU10095B DURING ANNUAL INSPECTION A FUEL LEAK WAS NOTED ON THE BOTTOM OF THE LEFT WING BENEATH THE FUEL TANK. UPON MORE DETAILED INSPECTION THE INTERNAL BAFFLING OF THE FUEL TANK WAS FOUND TO BE SEPERATED AND THE TANK TO BE LEAKING FROM ONE OF THE BAFFLE ATTACH WELDS. RESEARCH OF THIS AIRCRAFTS HISTORY REVEALED THAT THIS HAS HAPPENED 3 TIMES PRIOR. THE ORIGINAL TANK WAS REPLACED AT 1728.1 TOTAL TIME, THE NEXT 3 LASTED 396.0, 647.6 AND 390.0 CONCURRENTLY. WE FEEL THAT THE DESIGN OF THE TANK CONTRBUTES TO ITS FAILURES. THE INTERNAL BAFFLE IS WELDED IN THE TANK DIRECTLY UNDER THE CENTER MOUNTING STRAP FOR THE TANK CAUSING A PRELOAD UPON INSTALLATION. DURING USE FOR ACROBATIC FLIGHT THE TANKS CANNOT BE FILLED DUE TO WEIGHT 1H71 3O3 O A21CE 1E10 5 CP920 20030106000402003010600040SO 2003 1 6 P49R490N 220021221G7320AN737TW26 CLAMP CONT CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO BALANCE TUBE BROKEN B O OTHER B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 NE054898N 18267445 PILOT REPORT REPORTED SMOKE FROM THE COWLING DURING AN ATTEMPTED ENGINE START DURING COLD WEATHER. FOUND FIRE STARTED AT CLAMP SUPPORT FOR THE ENGINE INDUCTION SYSTEM BALANCE TUBE. CLAMP HAD BROKEN AND TUBE HAD CHAFED THROUGH DUE TO LOOSE AND BROKEN CLAMP. RAW FUEL LEAK OUT DURING START ATTEMPT AND WAS IGNITED THOUGH PARTIAL IGNITION. THIS IS THE SECOND BROKEN BALANCE TUBE CLAMP IN ONE MONTH ON THE 182 SERIES AIRCRAFT WITH REPLACEMENT OF THE BALANCE TUBE REQUIRED. SUGGEST CAREFUL VISUAL INSPECTION ANYTIME THE LOWER COWLING IS REMOVED AND USE PROPER TORQUE ON THE CLAMP WHEN INSTALLING. 1H71 3O3 ONT3A13 E273 20030611000102003061100010CE 2003 6 11 PF212LW 120021029G561010138402521 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A11 52043NE COCKPIT FAILED P O OTHER O OTHER CLCLIMB 1 CE07212LW BB1420 INNER PANE OF PILOTS WINDSHIELD SHATTERED WHILE CLIMBING THROUGH 28000 FEET. 1L72 4T3 T A24CE E4EA 20020419000302002041900030GL 2002 4 19 R377W 120020418G2720AN37A BOLT CIRRUSSR SR22 2130001GL RUDDER PEDLE SHEARED B D RETURN TO BLOCK F FLT CONT AFFECTED TXTAXI/GRND HDL 1 CE03225CD 0031 PILOT NOTICED RUDDER PEDALS STIFF DURING TAXI. PILOT FELT RUDDER PEDALS GIVE WAY. DURING INSPECTION, FOUND CO-PILOT'S RUDDER PEDAL TORQUE TUBE INBOARD AFT MOUNTING BRACKET BOLT PN AN3-7A SHEARED. FOUND CO-PILOT'S INBOARD MOUNTING BRACKET BENT PN 11478-001 AND BUSHING PN 11504-001 DAMAGED. BOLT APPEARS TO HAVE BEEN OVERTORQUED WHICH WEAKENED ITS SHEAR STRENGTH. REPLACED BRACKET, BUSHING AND ALL HARDWARE. SENT DAMAGE PARTS TO CIRRUS FOR ANALYSIS. 1L71 3O NTA00009CH 20020904000842002090400084GL 2002 9 4 R895W25 120020830G5330 PLATE CIRRUSSR SR22 2130001GL CONT O550 IO550N 17042SO FUSELAGE DELAMINATED B K NONE O OTHER ININSP/MAINT 1 CE03214BB 0085 685824 DURING ANNUAL INSPECTION, FOUND LOWER FORWARD FUSELAGE EXHAUST HEAT PLATE DELAMINATED. FURTHER INSPECTION REVEALED HOT SPOT UNDERNEATH CO-PILOT'S RUDDER PEDAL INSPECTION PANEL ABOVE THE EXHAUST AREA OUTLET. ALSO FOUND VISIBLE LIGHT SHOWING THROUGH THE COMPOSITE STRUCTURE AT THE FIREWALL AND FUSELAGE BELLY. INVESTIGATED AIRCRAFT N225CD, SN: 0031 AND FOUND SAME HOT SPOT CREATED BY THE SHORT EXHAUST SYSTEM. SUSPECT THE EXHAUST TAILPIPE IS TOO SHORT FOR EXHAUST GASES TO CLEAR THE COMPOSITE FUSELAGE LOWER STRUCTURE. 1L71 3O3 ONTA00009CHE3SO 20020411000912002041100091WP 2002 4 11 RFTO 120020410G2742AJH7150501 JACKSCREW DOUG DC10 DC1010 3022110WP ELEVATOR WORN H K NONE O OTHER ININSP/MAINT 1 WP23910SF69567 JACKSCREW REMOVED FROM A DC10-10,N910SF, THIS PART TO OUR KNOWLEDGE HAS 69567 HOURS, 25480 LANDINGS AND WAS INSTALLED IN PRODUCTION 1971. WE SENT THE UNIT IN FOR INSPECTION AND OVERHAUL AS NECESSARY TO THE PART MANUFACTURE AS THERE IS NOT A CURRENT INSPECTION/OVERHAUL PERIOD CALLED OUT IN THE MPD FOR THE DC10. THE TEARDOWN REPORT INDICATED CONCENTRICITY MEASUREMENT AT MIDDLE SECTION IS .010 INCH AND THE MAX. IS .004 INCH. THE BUSHING HOLE DIAMENTIONS FOR THE SCREW WERE 1.7510/1.7518 THE MAX. LIMIT IS 1.7510. THE JACKSCREW BEARING HAS EXCESSIVE PLAY WITH THE LOWER TEFLON SEAL MISSING. 2L73 4F A22WE 20020814000222002081400022EU 2002 8 14 RX8R2002001 120020719G2435150SG122Q STARTER GEN SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE ENGINE FAILED B RX8RA UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 SO154043L 362 3015 9318 DURING FLIGHT AT 2500 FT. ONE SET OF BRUSHES IN THE STARTER GENERATOR FAILED. THE GENERATOR WAS STILL PUTTING OUT 28 VDC THROUGH THE REMAINING BRUSHES SO THE GENERATOR WARNING LIGHT DID NOT ILLUMINATE. THE GENERATOR WAS NOT PUTTING OUT ENOUGH CURRENT IN ITS DAMAGED STATE TO KEEP THE AIRCRAFT BATTERY CHARGED. THE AIRCRAFT BATTERY SLOWLY LOST VOLTAGE TILL ALL AIRCRAFT ELECTRICAL POWER FAILED WITHOUT WARNING. 1G71 3U3 U H9EU E19EU 20020904000892002090400089NE 2002 9 4 S3898 220020819G7250311818101 RIVET BEECH MU300 400A 1155402CE PWA JT15 JT15D5 52112NE HP TURBINE ERODED C K NONE O OTHER ININSP/MAINT 1 SW11457CW2505 RK57 HIGH PRESSSURE TURBINE BLADE RETAINING RIVETS AND COLLARS APPEAR TO BE SUFFERING EROSION CAUSING RIVET TAILS TO FALL BELOW THE .050 INCH PROTRUSION AS OUTLINED IN THE MFG SB. IN ITS CURRENT CONDITION ALL 71 EA. RIVETS (PN 311588901) COLLARS (PN 311683801) ARE BEING REPLACED WITH NEW. 2H72 4F4 FRTA16SW E25EA 20020719001512002071900151SO 2002 7 19 S5248 120020612G5740 FITTING PIPER PA32 PA32R300 7103213SO RT WING CORRODED B K NONE O OTHER ININSP/MAINT 1 GL03882TM1852 32R7780273 RIGHT AFT WING ATTACMENT FITTING CORRODED,INSPECTED IAW PSB977 CORROSION MORE THAN SURFACE DEEP PITS 1L71 3O A3SO 20021121000052002112100005EU 2002 11 21 S5656 120021120G2510TYPE3431 SEAT BELT SOCATATBM TBM700 8682000EU COCKPIT FAILED B K NONE W INADEQUATE Q C ININSP/MAINT 1 GL11700PP 59 REF. SAIB NO.CE-02-44 DATED SEPTEMBER 4, 2002 PREBUY ON AIRCRAFT CHECK, ALL CABIN AND COCKPIT SEAT BELTS COULD BE PULLED APART WITH A SLIGHT PULL OR TUG. WOULD NOT STAY ENGAGED RECOMMEND REPLACEMENT OF ALL BELTS WITH NEWER STYLE 1L71 3T RTA60EU 20020814000232002081400023NE 2002 8 14 SQM212002 320020813G6110 PROPELLER LKHEED382 382G 526414USO ALLSN 501D 501D22A 03006GL HAMSTD54H 54H60117 NE NR 4 ENGINE LEAKING B EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 SW99401LC N401LC 550348 230992 APPROXIATELY 3.5 HRS INTO THE FLIGHT AT 0515 Z (ENROUTE TO OKO), PILOT ENCOUNTERED PROPELLER LOW OIL LIGHT. VISUAL INSPECTION CONFIRMED FLUID LEAKED AT NR 4 PROPELLER HOUSING. THE NR 4 ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO PLA. DURING THE DEFECT SIMULATION CHECK, HYDRAULIC FLUID WAS FOUND LEAKING FROM THE PROPELLER SHAFT HOUSING WHILE THE PROPELLER WAS SELECTED TO FEATHER POSITION. 2H74 4T4 T A1SO E282 6 CP906 20020314000262002031400026NM 2002 3 14 SROM200200001 120020204G53156545834109 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP310304865 23465 CORROSION ON FLOORBEAM BS 294.5, LBL12, WL208 CUT OUT AND REPLACED CORRODED SECTION OF FLOORBEAM PER SRM 53-10-2 & 53-10-9. 2L72 4F RTA16WE 20020314000282002031400028NM 2002 3 14 SROM200200002 120020202G53156545810502 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP310304865 23465 CORROSION ON FLOOR BEAM B.S.312 LBL 12 TP RBL 12 WL 208. REMOVED CORROSION, FOUND OUT OF LIMITS PER SRM 53-10-1 FIG. 1. FABRICATED REPAIR PARTS, COMPLETED REPAIR TO B.S. 312 FLOOR BEAM PER SRM 53-10-9 FIG. 5. 2L72 4F RTA16WE 20020314000302002031400030NM 2002 3 14 SROM200200003 120020127G53306545775 SKIN BOEING737 737205 1384456NM FUSELAGE GOUGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP310301304 23465 GOUGE ON FUSELAGE SKIN AT B.S. 791. 6 INCHES BELOW STR. 23 RIGHT. BLENDED GAUGE .028 REMAINING OUT OF LIMITS. REPAIRED IAW SRM 53-30-3 FIG. 46. 2L72 4F RTA16WE 20020314000322002031400032NM 2002 3 14 SROM200200004 120020216G53306545774 SKIN BOEING737 737205 1384456NM FUSELAGE DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309281480 23466 DURING C CHECK INSPECTION FOUND FUSELAGE SKIN HAS SEVERAL DENTS FROM B.S. 847 TO 872 BETWEEN STR. 19R AND 20R. REMOVED DAMAGE 11 INCHES X 7 INCHES AT STA. 864 TO 874. FABRICATED REPAIR DOUBLE & FILLER, ALODINED & PRIMED AND INSTALLED PARTS PER SRM 53-30-2 FG 6 PG 11-12A AND SRM 51-10-02. 2L72 4F RTA16WE 20020314000332002031400033NM 2002 3 14 SROM200200005 120020216G53306545774 SKIN BOEING737 737205 1384456NM FUSELAGE DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309281480 23466 DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 910, 2 INCHES BELOW STRINGER 22R. REPAIRED DENT IN FUSELAGE SKIN AT B.S. 910 2" BELOW STRINGER I.A.W. SRM 53-30-03 PAGE 97. 2L72 4F RTA16WE 20020314000342002031400034NM 2002 3 14 SROM200200006 120020216G53306545774 SKIN BOEING737 737205 1384456NM FUSELAGE DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309281480 23466 DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 898, 2 INCHES ABOVE STRINGER 24R. DENT FOUND TO BE OUT OF LIMITS. REMOVED DAMAGE IN A 4X8 INCH AREA. FABRICATED DOUBLER AND FILLER AND INSTALLED PER SRM 53-30-03 FIG. 6. 2L72 4F RTA16WE 20020314000372002031400037NM 2002 3 14 SROM200200007 120020218G5315654681025 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE DAMAGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309284838 23466 DURING C CHECK INSPECTION FOUND AT BS 967 RBL 29 W.L. 208 FASTNER HOLE IN FLOOR BEAM ELONGATED. CUT OUT FWD. FLANGE OF BS 967 UPPER FLOORBEAM CHORD AT RBL 29 AND RBL 43 IN A 1.2 X 3 INCH AREA. FABRICATED REPAIR ANGLES AND FILLERS AND INSTALLED REPAIR PER SRM 53-10-09 FIG. 7. 2L72 4F RTA16WE 20020314000382002031400038NM 2002 3 14 SROM200200008 120020219G53156545815108 FLOORBEAM BOEING737 737205 1384456NM FUSELAGE CORRODED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309284838 23466 DURING C CHECK INSPECTION FOUND CORROSION ON FLOORBEAM STA 344 LBL 2 TO RBL 10 WL 208. REPAIRED PER SRM 53-10-9 FIG. 6. 2L72 4F RTA16WE 20020314000402002031400040NM 2002 3 14 SROM200200009 120020220G53116546525 FRAME BOEING737 737205 1384456NM FUSELAGE DAMAGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309284838 23466 DURING C CHECK INSPECTION FOUND FRAME SHEAR TIE BS 380 BETWEEN STR 20 RT & STR 21 RT TO HAVE ELONGATED HOLES. REMOVED DAMAGE SECTION OF FRAME SHEAR TIE, FABRICATED NEW SECTION & INSTALLED I.A.W. SRM 53-10-4 FIG. 8. 2L72 4F RTA16WE 20020314000422002031400042NM 2002 3 14 SROM200200010 120020216G52306547952161 BEAM BOEING737 737205 1384456NM CARGO DOOR CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309281480 23466 DURING C CHECK INSPECTION FOUND AFT CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B T-CHORD VERTICAL FLANGE CRACKED AT FWD STOP-PIN FITTING BETWEEN FIRST & SECOND FASTNER. REMOVED AFT CARGO DOOR TRANSVERSE BEM & INSTALLED REPLACEMENT BEAM. 2L72 4F RTA16WE 20020314000432002031400043NM 2002 3 14 SROM200200011 120020227G5230654692124 BEAM BOEING737 737205 1384456NM CARGO DOOR CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309561480 23466 DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR NR 1 TRANSVERSE BEAM FROM BOTTOM O/B TEE CHORD CRACKED ON VERTICAL FLANGE AT AFT STOP PIN FITTING BETWEEN FASTNESRS. REPAIRED TEE CHORD PER ASA EM 5230-01097 STEP 6 C OF SECTION 2. 2L72 4F RTA16WE 20020314000442002031400044NM 2002 3 14 SROM200200012 120020227G53106549921116 DOOR FRAME BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309561480 23466 DURING C CHECK INSPECTION FOUND FORWARD CARGO DOOR FORWARD LOWER FRAME CRACKED AT NR 4 FWD STOP FITTING.(COUNTING FROM TOP TO BOTTOM) REMOVED AND REPLACED FRAME PER ASA EM 5230-01097. 2L72 4F RTA16WE 20020314000462002031400046NM 2002 3 14 SROM200200013 120020216G53306545768238 SKIN BOEING737 737205 1384456NM FUSELAGE DENTED C SROMK NONE O OTHER ININSP/MAINT 1 AL03733PA309281480 23466 DURING C CHECK INSPECTION FOUND DENT IN FUSELAGE SKIN AT B.S. 404 1 INCH ABOVE STRINGER 19R. TRIMMED OUT DAMAGE, INSTALLED REPAIR PER ER 02-0215 ASA EA 5330-01572 2L72 4F RTA16WE 20020328000132002032800013NM 2002 3 28 SROM200200014 120020326G3350 BULB BOEING737 737205 1384456NM CABIN BURNED OUT C SROMK NONE L NO TEST NRNOT REPORTED 1 AL03733PA 6 23466 OVERHEAD BIN EMERGENCY LIGHTS ROW 9 (RT) AND LAST 3 LIGHTS ON LT SIDE OUT. RELAMPED AND ALL OPS NORMAL 2L72 4F RTA16WE 20020424000522002042400052NM 2002 4 24 SROM200200015 120020422G33506013211 BATTERY PACK BOEING737 737205 1384456NM CABIN DISCHARGED C SROMK NONE L NO TEST ININSP/MAINT 1 AL03733PA 6 23466 AFT LT BULLNOSE EMERGENCY LIGHTS INOPERATIVE. REPLACED AFT OVERHEAD EMERGENCY LIGHTS BATTERY PACK. ALL OPS NORMAL. REF. 33-51-151 2L72 4F RTA16WE 20020719001542002071900154NM 2002 7 19 SROM200200016 120020628G335058209 BATTERY PACK BOEING737 737205 1384456NM CABIN DISCHARGED C SROMK NONE L NO TEST ININSP/MAINT 1 AL03733PA 6 23466 L2 EMERGENCY EXIT SIGN LIGHT DIM. REPLACED BOTH AFT EXIT SIGNS AND BATTERY PACK AT L2 DOOR. OPS CHECKED NORMAL. 2L72 4F RTA16WE 20020814000242002081400024NM 2002 8 14 SROM200200017 120020804G33506013211 BATTERY PACK BOEING737 737205 1384456NM CABIN DISCHARGED C SROMK NONE L NO TEST ININSP/MAINT 1 AL03736BP 3 23465 "R1 EMERGENCY DOOR (OVERHEAD) STAYS LIT FOR ONLY 20 SEC." REPLACED BATTTERY PACK. CHECKED GOOD REF MM 33-51-01. 2L72 4F RTA16WE 20030106000412003010600041NM 2003 1 6 SROM200200022 120021217G532069429494 BRACKET BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP322851255 23465 DURING C CHECK INSPECTION FOUND THRESHOLD BRACKET CRACKED BS 807, RBL 22 IN AFT CARGO. REMOVED DAMAGED BRACKET AND INSTALLED NEW PER SRM 51-30-2. MAJOR REPAIR. 2L72 4F RTA16WE 20030106000422003010600042NM 2003 1 6 SROM200200023 120021213G531069353509 STANCHION BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP322851255 23465 DURING C CHECK INSPECTION FOUND FWD CARGO BAY STANCHON CRACKED. REPLACED STANCHON PER SRM 51-30-2. 51-10-3, MINOR REPAIR. 2L72 4F RTA16WE 20030106000432003010600043NM 2003 1 6 SROM200200024 120021213G53206546533503 BRACKET BOEING737 737205 1384456NM FUSELAGE CRACKED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP322851255 23465 DURING C CHECK INSPECTION FOUND CRACKED BRACKET IN FWD CARGO COMPARTMENT BAY. REPLACED BRACKET PER SRM 51-30-2, 51-10-3. MINOR REPAIR. 2L72 4F RTA16WE 20030106000442003010600044NM 2003 1 6 SROM200200025 120021216G521065458001215 SKIN BOEING737 737205 1384456NM PAX DOOR WORN C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP32285 23465 DURING C CHECK REPLACED SMALL OUTER SKIN PANEL FWD OF L-1 DOOR BETWEEN HINGES THAT HAD A PREVIOUS REPAIR OF A HOLE IN THE SKIN WITH A EXTERNAL DOUBLER. REMOVED AND REPLACED PER SRM 51-30-2, 51-20-1. MAJOR REPAIR. 2L72 4F RTA16WE 20030106000452003010600045NM 2003 1 6 SROM200200026 120021217G57206573771 GUSSET BOEING737 737205 1384456NM WING GOUGED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP322851255 23465 DURING C CHECK INSPECTION FOUND NUMBER ONE O/B FIXED FAIRING UPPER AFT GUSSET GOUGED. REMOVED, FABRICATED AND INSTALLED GUSSET PER SRM 54-10-2 & 51-30-2. MINOR REPAIR. 2L72 4F RTA16WE 20030106000472003010600047NM 2003 1 6 SROM200200028 120021215G575365464312 SKIN BOEING737 737205 1384456NM RT TE FLAPS CHAFED C SROMK NONE O OTHER ININSP/MAINT 1 AL03736BP322851255 23465 RT OUTBOARD FORE FLAP CHAFED INBOARD END 4 INCHES FROM INBOARD END ON LEADING EDGE. REPLACED CHAFFED SKIN PER SRM 57-50-1 & 51-30-2. MINOR REPAIR. 2L72 4F RTA16WE 20020130000732002013000073SO 2002 1 30 U23R624Y 120020108G5320 BRACKET PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360RB 17025CE MCAULY3AF32C3AF32C505 GL LT ENGINE BROKEN B K NONE G MULTIPLE FAILURE ININSP/MAINT 1 EA0735GK 178 36 3449174 322317 992855 UPON ANNUAL INSPECTION OF THE AIRCONDITIONING COMPRESSOR, IT WAS NOTED TO MOVE AROUND BY PRESSING ON THE AIRCONDITIONING BELT FURTHER INSPECTION REVEALED THE FORWARD AIRCONDITIONING BRACKET TO BE BROKEN. DURING REMOVAL OF THE BRAKET IT WAS ALSO FOUND TO BE BROKEN AT THE LOWER FORWARD INBOARD ATTACH POINT ALSO. THERE WAS A TOTAL OF TWO BRAKES FOUND OF THIS ITEM ONE HIDDEN AND ONE NEEDING A MIRROR TO LOCATE. 1L72 3O3 O A7SO E9CE 5 CP22EA 20020814000322002081400032CE 2002 8 14 UVVR200200001 120020805G49401666731 GASKET RKWELLNA265 NA26565 7630107CE APU START FAILED B A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CE0565AK 46535 "AFT FUSELAGE HOT" LIGHT CAME ON IN FLIGHT. CREW MADE LANDING AT SUS. AVMATS TROUBLESHOT PROBLEM, FOUND APU START BYPASS VALVE GASKET BLOWN - CAUSING HOT BLEED AIR TO TRIP THERMAL SWITCH, ILLUMATING WARNING LIGHT. REMOVED AND REPLACED GASKET WITH NEW GASKET. 2L72 4J A2WE 20020205000582002020500058NE 2002 2 5 WRLA200201 220020201G7230 BLADE DOUG DC10 DC1030 3023501WP GE CF6 CF650C2 30018NE COMPRESSOR VIBRATION A WRLAA UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 SO11526MD 46998 517515 NR 1 ENGINE VIBRATION 80-95, ALL OTHER INDICATIONS NORMAL. EVENT OCCURRED AT THE TOP OF THE CLIMB SEGMENT WHEN THE FLIGHT AS THE CREW WAS LEVELING THE AIRCRAFT. THE CAPTAIN ELECTED TO RETURN TO MIA. LUBED FAN BLADES, PERFORMED MAX POWER RUN AT 80-95 PERCENT TRANSITION, NO VIBRATION NOTED. THE ENGINE WAS RUN AT ALL POWER SETTING FROM IDLE TO TAKEOFF POWER WITH NO VIBRATION NOTED ON THE NUMBER ONE ENGINE. 2L73 4F4 F A22WE E23EA 20021015000382002101500038 2002 10 15 YHLR200200001 420021010G34972055612 CONNECTOR AMRGENAA5 AA5B 3960105SO GPS SYSTEM ARCED B O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SO17854PD AA5B0854 AIRCRAFT OWNER STATED THAT UNIT QUIT WORKING IN FLIGHT. REMOVED GPSCOMM FROM TRAY AND FOUND THAT PINS 21 & 25 HAD ARCED. FOUND THAT GPSCOMM WAS NOT SEATED PROPERLY IN TRAY AT TIME OF ORIGINAL INSTALLATION BY GULF COAST AVIONICS. REPLACED CONNECTOR & DAMAGED PINS 21 & 25. THIS COULD HAVE BEEN PREVENTED IF THE ORIGINAL INSTALLER (GULF COAST AVIONICS) HAD VERIFIED THAT THE UNIT WAS SEATED PROPERLY & CORRECTLY IN THE TRAY. 1L71 3O A16EA 20020920000722002092000072SW 2002 9 20 YT2R01050763 120020808G6230206010443001 BEARING BELL 206 206L3 1182108SW SWASHPLATE ROUGH C YT2RK NONE O OTHER ININSP/MAINT 1 WP01206MB 51321 SWASHPLATE BEARING SERIAL NUMBER F02-09999 IS ROUGH AND HAS A CATCH TO IT WHEN INSTALLED. CAUSED HIGH IPS. 1G71 3U H2SW 20021010001122002101000112SW 2002 10 10 YT2R631356 120020816G6320407375001105 INDICATOR BELL 407 407 1182206SW MGT FAILED B YT2RK NONE O OTHER ININSP/MAINT 1 WP01407KA592 53121 INDICATOR HAS FAILED (FALSE EXCEEDANCES THAT CANNOT BE CLEARED). WHEN LAPTOP IS CONNECTED GET AN ERROR SAYING THAT IP ADDRESS IN NOT CORRECT. 1G71 3U O H2SW 20021010001132002101000113SW 2002 10 10 YT2R631357 120020816G7714407375002103 INDICATOR BELL 407 407 1182206SW NG FAILED B YT2RK NONE O OTHER ININSP/MAINT 1 WP01407KA592 53121 REPLACED GAUGE, INDICATOR HAS FAILED (FALSE EXCEEDANCES) THAT CANNOT BE CLEARED. WHEN LAPTOP IS CONNECTED GET AN ERROR SAYING THAT IP ADDRESS IS NOT CORRECT. 1G71 3U O H2SW 20021115000132002111500013SW 2002 11 15 YT2R631367 120021023G28407G547 SWITCH BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUEL BOOST INOPERATIVE B YT2RK NONE O OTHER ININSP/MAINT 1 WP01 FUEL BOOST SWITCH INOPERATIVE UPON INSTALLATION. 1G71 3U3 U H2SW E4CE 20021115000142002111500014SW 2002 11 15 YT2R631369 120021023G28407G547 SWITCH BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUEL BOOST INOPERATIVE B YT2RK NONE O OTHER ININSP/MAINT 1 WP01 FUEL BOOST SWITCH INOPERATIVE UPON INSTALLATION. 1G71 3U3 U H2SW E4CE 20020124000302002012400030EA 2002 1 24 YTRR077529 220020102G73223028325 LINE 3028325 BELL 212 212 1181420SW PWA PT6 PT6B36 52043EA P3 FILTER CRACKED H YTRAK NONE O OTHER ININSP/MAINT 1 FS01293CA 1 33005 CPPS62245 P3 FILTER LINE ON NR 1 ENGINE CRACKED, REPLACED P3 FILTER LINE ASSEMBLY WITH NEW SERVICEABLE ASSEMBLY. 1G71 4U4 U H4SW E4EA 20020328000292002032800029SW 2002 3 28 YTRR077999 120020315G6230204011404125 BUSHING BELL 212 212 1181420SW SWASHPLATE WORN H YTRAK NONE O OTHER ININSP/MAINT 1 FS01250MH438 30519 SWASHPLATE SUPPORT BUSHINGS AT GIMBAL RING MOUNT HAD ELONGATED BOLT HOLE. COMPONENT HAD BEEN IN SERVICE FOR APPROXIMATELY HALF OF ITS LIFE. 1G71 4U H4SW 20020328000302002032800030SW 2002 3 28 YTRR078000 120020315G7331206364601101 TRANSMITTER BELL 206 206L3 1182108SW FUEL SYSTEM MISOVERHAULED H YTRAK NONE W INADEQUATE Q C ININSP/MAINT 1 FS01104RT 51364 UPPER FUEL PROBE WAS OVERHAULED. THE UNIT FAILED 7 DAYS AFTER INSTALLATION. 1G71 3U H2SW 20020419000312002041900031SW 2002 4 19 YTRR078431 120020410G73342060751865 METER BELL 206 206L1 1182107SW ALLSN 250C 250C28 03013GL FUEL PRESSURE MISREPAIRED H YTRAK NONE O OTHER ININSP/MAINT 1 FS015750Y 45517 FUEL PRESSURE / LOADMETER WAS OVERHAULED. THE FUEL PRESSURE SIDE FAILED AFTER 1.0 HRS IN SERVICE. THE UNIT WAS RETURNED FOR WARRANTY REPAIR. 1G71 3U3 U H2SW E1GL 20020419000322002041900032SW 2002 4 19 YTRR078432 120020410G6520206011728001 TRUNNION BELL 206 206L4 1182110SW T/R GEARBOX WORN H YTRAK NONE O OTHER ININSP/MAINT 1 FS01207RT464 52207 TRUNNION WAS FOUND WORN BEYOND LIMITS DURING A 100 HR A/F INSPECTION. 1G71 3U NCH2SW 20020423000532002042300053NE 2002 4 23 YTRR078434 220020416G7532 DIAPHRAGM BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE BLEED VALVE RUPTURED H YTRAK NONE O OTHER ININSP/MAINT 1 FS01250MH 30519 BLEED VALVE LEAKING DUE TO RUPTURED DIAPHRAM. 1G71 4U4 U H4SW E22EA 20020423000542002042300054 2002 4 23 YTRR078435 420020416G345713824120234 RECEIVER BELL 206 206L3 1182108SW GPS FAILED H YTRAO OTHER O OTHER NRNOT REPORTED 1 FS01473RT 51473 GPS UNIT REPAIRED. IT REMAINED SERVICEABLE FOR 4 MONTHS FROM THE DATE OF INSTALL THE FAILED AGAIN. 1G71 3U H2SW 20020827000662002082700066GL 2002 8 27 YTRR080718 220020819G7261357950111452 SHAFT BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL WORN WORN B YTRAK NONE O OTHER ININSP/MAINT 1 FS01207RT555 52207 OIL PUMP SPLINES WORN EXCESSIVELY. 1G71 3U3 UNCH2SW E1GL 20020827000672002082700067GL 2002 8 27 YTRR080719 220020819G7261357950111452 SHAFT BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL OIL PUMP WORN B YTRAK NONE O OTHER ININSP/MAINT 1 FS01207RT1343 52207 OIL PUMP SPLINES WORN EXCESSIVELY. 1G71 3U3 UNCH2SW E1GL 20020827000682002082700068GL 2002 8 27 YTRR080720 220020819G7261357950111452 SHAFT BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL OIL PUMP WORN H YTRAK NONE O OTHER ININSP/MAINT 1 FS01520RL1100 52052 OIL PUMP SPLINES WORN EXCESSIVELY. 1G71 3U3 UNCH2SW E1GL 20021217001262002121700126SW 2002 12 17 YTRR081614 120021211G5302206033426001 SUPPORT BELL 206 206L3 1182108SW T/R GEARBOX CRACKED H YTRAK NONE O OTHER ININSP/MAINT 1 FS01405RL4290 51405 CASTING CRACKED AT AFT LEFT T/R GEARBOX MOUNTING HOLE. 1G71 3U H2SW